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415 - Rotary kinetic fluid motors or pumps

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DocumentTitleDate
20090304494Counter-vortex paired film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall for providing film cooling to the exterior face of the wall, and a second film cooling passage extending through the wall adjacent to the first film cooling passage for providing film cooling to the exterior face of the wall. The first film passage includes a first vortex-generating structure for inducing a vortex in a first rotational direction in a cooling fluid passing therethrough, and the second film passage includes a second vortex-generating structure for inducing a vortex in a second rotational direction in a cooling fluid passing therethrough. The first and second rotational directions are substantially opposite one another.12-10-2009
20090196731METHOD AND APPARATUS FOR STARTING SUPERSONIC COMPRESSORS - A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated.08-06-2009
20090196730Gas turbine with a compressor with self-healing abradable coating - A gas turbine with a compressor includes at least one row of blades, with the blades having a free end each, with a self-healing abradable coating being provided adjacent to the free end of the blades on an annular casing area and/or an annular drum area.08-06-2009
20090297330Blade clearance arrangement - Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap adjustment systems have been relatively course. By provision of a winding through which a specific electrical current is passed in order to create electro-magnetic force for displacement of an armature associated with a seal forming part of the casing it is possible to adjust the gap between that seal and a tip part of a rotating blade assembly. Normally a blade gap monitoring technique is used in association with specific operational requirements with respect to the gap by the control in order to determine the electrical current presented to the winding. As a fail-safe measure a permanent magnet or bias or some other form can be provided to ensure displacement to a fail-safe position with an adequate blade gap clearance for continued operation should there be power failure or an excess electrical current presented to the winding.12-03-2009
20100061836Process for producing a turbine blade or vane with an oxide on a metallic layer, use of such a turbine blade or vane, a turbine and a method for operating a turbine - A process for producing a component of a gas turbine having a substrate with a metallic layer is provided. The metallic layer is a MCrAlX layer which is treated at temperatures elevated above the operating temperature, by at least 50° C., so that the oxidation and corrosion behavior are improved. In particular a MCrAlX of the type, NiCoCrAlX is used.03-11-2010
20100143092Power-Generating Turbine in a Rotor-Stator Arrangement - A rotor blade for a horizontal axis wind turbine is provided. The rotor blade includes a fixing section for fixing the rotor blade to a rotary shaft of a rotor of the horizontal axis wind turbine. Furthermore, the rotor blade includes a geometrically adjusted section with a root end. The rotor blade extends from the fixing section to the root end. A section of the root end of the geometrically adjusted section and a section of a guide panel of a stator of the horizontal axis wind turbine closest to the root end are substantially coplanar.06-10-2010
20110194926Submersible Pump for Operation In Sandy Environments, Diffuser Assembly, And Related Methods - Submersible pumps, diffuser assemblies, and related methods for pumping a fluid having a substantial sand content, are provided. A diffuser assembly for a submersible pump can include anti-swirl ribs forming sand dams positioned on an upper surface of the diffuser bowl floor at an acute angle to guide trapped between the bottom shroud of an impeller and the diffuser bowl to the inner surface of the diffuser bowl outer wall and back into the production fluid stream. The diffuser assembly can also include sand jump ramps each separately positioned adjacent the outer peripheral surface of one of the sand dams and positioned adjacent a separate portion of the inner surface of the diffuser bowl outer wall to further enhance deflection of sand back into the production fluid stream.08-11-2011
20090196732Turbomachine, in Particular a Gas Turbine - The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The aim of said invention is to develop a device and a method for the turbo-machine making it possible to reduce the size of a radial split of the turbo-machine in order to obtain greater degree of efficiency. The inventive turbo-machine comprises a rotor rotationally mounted in the case of the turbo-machine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbo-machine rotor by heating fluid flowing there-through are also disclosed.08-06-2009
20080279675OPERATION OF AN AIRCRAFT ENGINE AFTER EMERGENCY SHUTDOWN - A method of emergency operation of an aircraft turbofan engine during an aircraft flight is provided. The engine includes a fan shaft with a fan, and an electric motor/generator mounted for rotation therewith. The method includes shutting down the engine while allowing the engine to windmill, operating the electric motor/generator to rotate the shaft at a determined windmilling speed which is desired for the fan shaft, and operating the engine at the desired windmilling speed for substantially a remainder of the aircraft flight.11-13-2008
20090317229INTEGRATED ACTUATOR MODULE FOR GAS TURBINE ENGINE - An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.12-24-2009
20100074725METHOD FOR CONTROLLING A TURPOCOMPRESSOR - Method for controlling a turbocompressor, whereby a compressed air line (03-25-2010
20130034425METHOD FOR ADAPTING THE AIR FLOW OF A TURBINE ENGINE HAVING A CENTRIFUGAL COMPRESSOR AND DIFFUSER FOR IMPLEMENTING SAME - A method for maintaining efficiency and duty of a turbine engine compressor to reduce specific consumption, while guaranteeing a high enough pumping margin with partial load. The method adapts airflow to a variable demand for flow or mechanical or electric power in a centrifugal compressor of a turbine engine. The method includes diffusing the airflow through a first annular blade ring having variable pitch blades, radially bordered by a second annular blade ring having a same number of fixed pitch blades with an equivalent extension, guiding the radial extension diffusion by coupling the blades of the two blade rings. According to the method, each blade of the first blade ring is spun off-axis.02-07-2013
20130034424TIP CLEARANCE CONTROL DEVICE - A tip clearance control device adapted to control the clearance of a rotating aerofoil structure with a surrounding casing portion, and a method of controlling the tip clearance of a rotating aerofoil structure with a surrounding casing portion. The device includes a member operatively connected to the casing portion; the member having at least a first configuration in which the casing portion is at a first radial position and a second configuration in which the casing portion is at a second radial position, wherein the configuration of the member is controlled by magnetic flux in a magnetic circuit which includes at least one ferromagnetic element including ferromagnetic material, where the configuration of the member is responsive to the temperature of the ferromagnetic element.02-07-2013
20130034423SYSTEM AND METHOD FOR PASSIVELY CONTROLLING CLEARANCE IN A GAS TURBINE ENGINE - A system for passively controlling clearance in a turbine engine comprises a static assembly arranged circumferentially about an engine rotor assembly and defining a gap between a tip end of the rotor assembly and an adjacent inner surface of the static assembly. The static assembly includes a gap control member that defines the inner surface, is exposed to the engine working fluid, and comprises a shape memory material selected and preconditioned to deform in a pre-selected manner in response to a temperature of the engine working fluid. Alternatively, airfoil blades of the rotor assembly include a gap control member. A method for passively controlling clearance in a turbine engine comprises assembling the engine so as to define an initial set of build clearances, operating the engine to observe running clearances, configuring a gap control member comprising a shape memory material and re-assembling the engine with the gap control member.02-07-2013
20130028707METHOD FOR INJECTING WATER INTO A MULTISTAGE AXIAL COMPRESSOR OF A GAS TURBINE - A method is disclosed for injecting water into a multistage axial compressor of a gas turbine. With low equipment cost, a significant power enhancement can be achieved, even under changing boundary conditions, by water being injected at a plurality of points along the axial compressor, and by the injected water mass flow being controlled at the individual injection points in accordance with ambient conditions and operating parameters of the gas turbine in such a way that an evened-out loading in the individual stages of the axial compressor can be created.01-31-2013
20130028706METHOD AND APPARATUS FOR ADJUSTING IMPELLER/RING CLEARANCE IN A PUMP - In a pump arrangement, each adjusting screw has first and second end portions, a third intermediate raised portion, and a fourth portion to allow each adjusting screw to be rotated clockwise/counterclockwise. Each first end portion passes through a suction liner aperture so left-handed threads couple to a respective left-handed seal ring aperture. Each second portion passes through a suction half casing aperture so the fourth portion can be accessed to allow clockwise/counterclockwise rotation of each adjusting screw. Each adjusting screw rotates clockwise and moves until the third portion pushes against the suction half casing, so the screw stops moving and the seal ring moves away from the suction liner as the screw is rotated clockwise, or rotates counterclockwise and moves until the third portion pushes against the suction liner, so the screw stops moving and the seal ring moves towards the suction liner as the screw is rotated counterclockwise.01-31-2013
20120183385METHOD FOR PREVENTING SURGE IN A DYNAMIC COMPRESSOR USING ADAPTIVE PREVENTER CONTROL SYSTEM AND ADAPTIVE SAFETY MARGIN - A method of preventing surge in a dynamic compressor is disclosed. The method includes providing an anti-surge valve having an adjustable opening for increasing the flow through a dynamic compressor. The next step is sensing process conditions in the dynamic control to determine a compressor load variable. A control system estimates a process disturbance model using the compressor load variable. The control system then adjusts a safety margin using a rate limited response and initiates a closed loop response using process feedback based on the process disturbance model. The control system adjusts the opening of the anti-surge valve according to the safety margin and closed loop response.07-19-2012
20120183386COOLED GAS TURBINE ENGINE MEMBER - A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer.07-19-2012
20090185894Turbine Casing - The turbine casing as described herein may include a first section flange, a second section flange, the first section flange and the second section flange meeting at a joint, and a heat sink positioned about the joint.07-23-2009
20130039736Variable Stator Vane Control System - The present application provides a variable stator vane control system. The variable stator vane control system may include a variable stator vane positioned by an actuator and a trimmer motor, a resolver to determine a position of the variable stator vane, and a controller in communication with the resolver, the actuator, and the trimmer motor to prevent over travel of the variable stator vane.02-14-2013
20130039737METHOD FOR CONTROLLING A COMPRESSOR - A method for controlling a compressor that includes a compressor element, whereby during a transition from full load or partial load to zero load, a process A is followed that involves: (1) reducing the inlet pressure; and (2) reducing the speed and/or the drive torque. During a transition from zero load to part load or full load, a process B is followed that involves: (3) increasing of the speed or drive; and (4) increasing the inlet pressure.02-14-2013
20130039735VARIABLE VANE ACTUATION SYSTEM AND METHOD - A variable vane actuation system and method is disclosed herein. The variable vane actuation system includes a first ring member disposed for pivoting movement about a centerline axis. The first ring member is operably connected with at least one vane such that the at least one vane pivots in response to the pivoting movement of the first ring member. The variable vane actuation system also includes a first pin engaged with the first ring member. The variable vane actuation system also includes a ring moving device operably engaged with the first pin to move the first ring member about the centerline axis. The ring moving device includes at least one plate having a first slot and an actuator operable to move the at least one plate. The first pin is received in the first slot and is a cam follower to a cam defined at least in part by a surface of the first slot.02-14-2013
20100111667RING FAN AND SHROUD AIR GUIDE SYSTEM - A ring fan and shroud guide system which includes a rotating fan member with a conical outer ring and a cylindrical shroud member overlapping at least a portion of the outer ring. A plurality of guide vanes are provided in the shroud which minimize the tangential velocity component of the air flow entering the tip-gap region and provide improved air flow through the system. The guide vanes can have a curved configuration.05-06-2010
20130136575METHOD FOR MONITORING THE CLEARANCE OF A KINEMATIC LINK BETWEEN A CONTROL MEMBER AND A RECEIVING MEMBER - The method consists, based on an operating parameter of the turbojet engine, in:05-30-2013
20100104415RISERLESS TRANSFER PUMP AND MIXER/PRE-MELTER FOR MOLTEN METAL APPLICATIONS - A pump for processing molten metal having an enlarged tubular body which houses a centrifugal pump at its bottom end. The bottom end has a parabolic shape which receives the ejected molten metal from the impeller and forms a vortex within the tubular body. The pump is controlled to cause the vortex to climb up the inner wall of the body up to and out of an outlet formed in the upper end of the body. A radial vane impeller is formed in the back plate of the impeller. When the impeller is rotated, solid particles introduced into the body are accelerated radially by the back plate impeller into the vortex.04-29-2010
20090155042MULTI FUNCTIONAL PUMP FOR PUMPING MOLTEN METAL - The present invention features a multi-functional pump for pumping molten metal, which includes a base that is submerged in molten metal having at least two impeller chambers. The base includes one or more inlet openings and one or more outlet openings. Each outlet opening leads from one of the impeller chambers. The invention enables the impeller to be moved to a position to rotate in either impeller chamber or while straddling impeller chambers. This enables the pump to have the versatility to operate in a circulation mode; a transfer mode; two or more circulation modes; two or more transfer modes; and a combination of transfer and circulation modes. The impeller chambers can be stacked over each other and the impeller can be moved vertically in and between impeller chambers. Inventive vaned or barrel type impellers can be used to facilitate pumping while straddling impeller chambers, in view of an elongated bearing member on the impeller that maintains position relative to a bearing ring attached to the base or an inlet protector sleeve. The multifunctional pump of the invention enables infinite adjustment of the impeller using a programmable logic controller that results in positioning of the impeller at any of various locations in the base to achieve any desired output. The inventive pump is ideally suited for use in die casting and scrap submergence applications. Also featured is a method of operating the multifunctional pump of the present invention.06-18-2009
20100040453APPARATUS AND METHOD FOR CONTROLLING A COMPRESSOR - A compressor comprises a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the compressor further comprising at least one plasma actuator for suppressing rotating stall inception of the compressor, the at least one plasma actuator being mounted adjacent to the blade tips.02-18-2010
20130045077PNEUMATIC COMPOSITE HAVING MASS BALANCING - The invention relates to a blower device for delivering at least one medium, comprising a blower having a housing with an inlet and an outlet, a nozzle, which is fluidically connected and arranged on the housing such that at least one medium can flow there through, wherein the nozzle is designed to effect a negative pressure on the at least one medium at least in some sections, at least one sensor, wherein the sensor is arranged in the effective region of the nozzle and designed to measure at least parameters of the at least one medium which are required to determine the mass of the at least one medium.02-21-2013
20130045076COMPRESSOR CONTROL METHOD AND SYSTEM - A compressor control method includes providing variable aerodynamic sizing of fluid flow through a compressor at multiple operating points of the compressor. A head is determined for an operating point, based on a process input at that operating point. Further, for that operating point, a control pressure number is determined as a function aerodynamic flow sizing at that operating point. The control pressure number is determined a function of the head divided by the square of a tip speed of the impeller of the compressor. An operating speed setpoint is determined based on the determined head and control pressure number.02-21-2013
20130045078BEARING ASSEMBLY FOR A VERTICAL TURBINE PUMP - A bearing assembly for supporting a drive shaft of a pump is structured with a cylindrical body having an internal cavity filled with a lubricant, a sealing element arrangement positioned at one or both ends of the cylindrical body and a pressure equalization element that functions to equalize the pressure differential that exists between an area within the cylindrical body and outside of the cylindrical body to improve the operating life of the sealing arrangement and the bearing assembly.02-21-2013
20130084160Turbine Shroud Impingement System with Bellows - The present application provides a turbine shroud impingement system. The turbine shroud impingement system may include a turbine shroud segment, an impingement box positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows positioned about the feed tube.04-04-2013
20090116951METHOD AND APPARATUS FOR FAN SHAFT BEARING LUBRICATION - A lubrication system for a bearing assembly includes a fan shaft with a plurality of conduits, a first bearing rotatably supporting the fan shaft, and a second bearing rotatably supporting the fan shaft where the second bearing is axially spaced from the first bearing. The plurality of conduits includes at least a first conduit aligned with the first bearing and a second conduit aligned with the second bearing. A spray bar includes a plurality of supply orifices that direct lubricating fluid to the first and second bearings via at least the first and second conduits.05-07-2009
20100068029WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas.03-18-2010
20130028705GAS TURBINE ENGINE ACTIVE CLEARANCE CONTROL - An active clearance control system utilizes a working fluid stream to control radial thermal growth and thereby a clearance between turbine blades and a corresponding shroud of a gas turbine engine. Conduits disposed about a turbine case and proximate to pads defined within the turbine case include a flow surface parallel to the pads. The pads are an area of increased thickness in the turbine case that receives impingement flow from the conduits. Grooves within the pads further increase impingement cooling flow effectiveness. The increased thickness of the pads provides the thermal mass desired to effect thermal expansion and contraction responsive to the cooling airflow.01-31-2013
20130028704BLADE OUTER AIR SEAL WITH PASSAGE JOINED CAVITIES - A blade outer air seal assembly includes a body that defines a first cavity separated from a second cavity by a circumferential rib. The circumferential rib includes at least one passage which provides communication between the first cavity and the second cavity.01-31-2013
20130089407EXTERNALLY THREADED JOURNAL HOUSING - A journal housing including a series of housing threads defined on an outer radial surface. The series of housing threads may be adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing. A shoulder may extend radially-outward from the outer radial surface, and the shoulder may be disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener.04-11-2013
20130089406TURBINE OUTLET FROZEN GAS CAPTURE APPARATUS AND METHOD - A turbine outlet frozen gas capture apparatus is provided and includes an enclosure divided into first and second chambers, the first chamber being receptive of turbine outlet exhaust including frozen gas, a wheel disposed and configured to be rotatable such that frozen gas received in the first chamber is captured and transported into the second chamber and a heater disposed within the second chamber and configured to vaporize the frozen gas transported therein to thereby produce vaporized gas.04-11-2013
20130051976FLOW CONTROL MODULE FOR A TURBOMACHINE - A flow control module for a turbomachine includes an inlet extending to an outlet through a flow passage having at least one side wall. A flow control member is arranged within the flow control module. The flow control member is secured to the at least one side wall between the inlet and the outlet. The flow control member is selectively passively activated to extend into the flow passage to block cooling fluid passing through the flow control module.02-28-2013
20130051977ADJUSTABLE VANE DIFFUSER INSERT FOR ELECTRICAL SUBMERSIBLE PUMP - A pump having an insert between an impeller and diffuser, where the insert includes an annulus that is in communication with fluid flow passages in the impeller and diffuser. The passages and annulus define a fluid flow path through the pump. Vanes are provided in the annulus that can pivot and vary the cross sectional area of the fluid flow path. Regulating the fluid flow path area alters the flow rate where the pump operates at its maximum efficiency. Thus by monitoring flow through the pump, the vanes can be adjusted so the flow rate of maximum efficiency corresponds to the actual flow rate.02-28-2013
20130051972BLADE OUTER AIR SEAL WITH MULTI IMPINGEMENT PLATE ASSEMBLY - A multi impingement plate assembly for a Blade Outer Air Seal (BOAS) includes a first impingement plate which defines a multiple of first impingement plate holes and a second impingement plate attached to the first impingement plate. The second impingement plate includes a platform section spaced away from the multiple of first impingement plate holes to define a plate cavity.02-28-2013
20130051974GAS TURBINE ENGINES AND METHODS FOR COOLING COMPONENTS THEREOF WITH MID-IMPELLER BLEED COOLING AIR - Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.02-28-2013
20130051975AIR TURBINE STARTER AND METHOD FOR VENTING WITHOUT LOSS OF OIL - A clutch assembly includes a shaft, vent plug and oil guide sleeve. The shaft includes an internal cavity, first passages for allowing oil to lubricate clutch components, and second passages for allowing excess oil to drain from the internal cavity. The vent plug has a radial passage in communication with the internal cavity for venting the cavity with an external source of air. The oil guide sleeve directs oil into the internal cavity. A method for lubricating and venting an air turbine starter includes delivering lubricating oil to an internal cavity of a clutch via an oil guide sleeve. The oil guide sleeve prevents oil from exiting the cavity through excess oil drainage passages before it lubricates the clutch components. The method also includes draining excess oil from the cavity through excess oil drainage passages so that excess oil does not substantially impede air flow through a vent plug passage.02-28-2013
20130051973COMPRESSOR DIFFUSER PLATE - A diffuser plate for a centrifugal compressor includes an inner edge disposed at an inner diameter about a central axis; an outer edge disposed at an outer diameter, the outer edge displaced an axial distance from the inner edge; a deformable section that includes a substantially S-shaped cross-section, the deformable section disposed between the inner edge and the outer edge; and a spring constant for forced axial displacement of the outer edge with respect to the inner edge, the spring constant characterized, at least in part, by the deformable section. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.02-28-2013
20090304492Blower systems and methods having multiple outlets - A blower system comprising a housing and a fan assembly. The housing defines a housing chamber, at least one inlet opening, a primary outlet opening, and a secondary outlet opening. The fan assembly is mounted within the housing chamber. Operation of the fan assembly draws air into the housing chamber through the at least one inlet opening and forces air out of the housing chamber through at least one of the primary outlet opening and the secondary outlet opening.12-10-2009
20110002769CENTRIFUGAL PUMP FOR DE-WATERING - A method of de-watering during intermittent dry running periods with a self-priming centrifugal pump is presented. Centrifugal pumps, as opposed to diaphragm pumps, are advantageous because they are less expensive and can provide greater capacity. The shaft seals are sensitive, however, to frictional heating when water flow is interrupted. In some situations, this fractional heating may desiccate self-priming. The inventive concept provides a continuous stream of pressurized water moving through the pump to cool the seal and sustain priming capability without substantially impairing the ability of the pump to resume wet operation.01-06-2011
20120219399ELECTRIC DEVICE - An electric device has a casing with an air-inlet and an air-outlet, a main unit disposed inside the casing, a first temperature sensor for detecting the temperature inside the casing, a second temperature sensor for detecting the temperature outside the casing, an electric fan, and a control unit. The control unit rotates the electric fan at the time of the low-temperature startup such that the temperature detected by the first temperature sensor is lower than a preset first threshold value, while the temperature detected by the second temperature sensor is higher than the temperature detected by the first temperature sensor.08-30-2012
20120219398METHOD OF DETECTING AND CONTROLLING STALL IN AN AXIAL FAN - A method of detecting stall in an axial fan through acoustical measurements in air the air flow, includes measuring the sound emanating from the flow adjacent the fan, preparing a visual representation of the sound, comparing the visual representation with a library of fixed visual representations derived from a plurality of tests representative of the performance of the fan under a range of operating parameters, selecting the fixed visual representation most closely matching the visual representation of the said sound, and deriving a control signal from the selected fixed visual representation. The visual representations are formed by a symmetrised dot pattern (SDP) technique.08-30-2012
20130071227BLADE OUTER AIR SEAL ASSEMBLY LEADING EDGE CORE CONFIGURATION - An example blade outer air seal assembly may consist of a blade outer air seal containing channels that communicate cooling air through at least some of the blade outer air seal. The blade outer air seal has at least one circumferentially extending barrier separating the leading channel into a forward portion and an aft portion. Cooling air outlets from the leading channel are exclusively coupled to the aft portion.03-21-2013
20130071228STATIONARY CO-AXIAL MULTI-ROTOR WIND TURBINE SUPPORTED BY CONTINUOUS CENTRAL DRIVESHAFT - Co-axial, multi-rotor wind turbines, producing more power than a single rotor of the same diameter, are made even more powerful by increasing driveshaft length and supporting the driveshaft from more than one point. Sacrificing the ability to aim, for the extra length to support additional rotors, results in a more powerful co-axial multi-rotor turbine, especially useful for areas with a predominantly unidirectional wind resource. Ideally the turbine is placed at an offset angle α (alpha) from the wind direction, which, in combination with proper spacing between rotors, allows fresh wind to reach each rotor, so that all rotors contribute toward rotation of the driveshaft. Placing the driveshaft under tension can raise critical speeds and reduce the number of intermediate supports required. This places the Earth or underlying substrate in compression, making it effectively part of the structure of the turbine, saving cost. Cross-axis and reversible blades may also be incorporated.03-21-2013
20130071226METHODS AND SYSTEMS FOR USE IN CHECKING THE POLARITY OF MULTI-COIL SERVOS - A method and system for configuring a valve in a turbine. The method includes transmitting a first signal from a servo to a first coil of an actuator to cause the valve to move to a first position, determining a first magnitude of the valve, and transmitting a second signal from the servo to a second coil of the actuator to cause the valve to move to second position. The method also includes determining a second magnitude of the valve, and comparing the first magnitude to the second magnitude to determine the polarity of wiring coupled between the servo and the actuator.03-21-2013
20130058756FLOW DISCOURAGER INTEGRATED TURBINE INTER-STAGE U-RING - A gas turbine having rotor discs (03-07-2013
20130058757PRIMING VALVE SYSTEM FOR PRE-PRIMING CENTRIFUGAL PUMP INTAKES - A priming valve for priming a centrifugal pump includes a valve assembly separating an inlet chamber from an outlet chamber. The inlet chamber is fluidly coupled to an intake for the centrifugal pump and the outlet chamber is fluidly coupled to a priming pump. A control valve is provided to operate the valve assembly in order to fluidly connect the inlet chamber with the outlet chamber. While the valve assembly fluidly connects the inlet chamber with the outlet chamber, the priming pump can operate to replace air in the intake and the centrifugal pump with water.03-07-2013
20130183136START SYSTEM FOR GAS TURBINE ENGINES - A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.07-18-2013
20130183135METHOD AND APPARATUS FOR TURBO-MACHINE NOISE SUPPRESSION - A turbo-machine inlet includes a gas passage having a non-gradual bend prior to an impeller assembly. The non-gradual bend causes a localized shockwave in fluid flowing through the gas passage.07-18-2013
20110014028COMPRESSOR COOLING FOR TURBINE ENGINES - Systems, apparatuses and methods (“utilities”) for use in “internally” cooling the compressor of a gas turbine engine so as to approximate isothermal compression and thereby increase the power and/or efficiency of the engine. In one arrangement, a “cooling jacket” or heat exchanger having coolant circulating or passing therethrough may be mounted around an outer surface of the compressor to absorb heat or thermal energy generated from the compressor. In another arrangement, the stator blades of the compressor may include passages through which a coolant may be circulated or passed to absorb heat from air passing through the compressor.01-20-2011
20110064560AXIAL TURBINE AND METHOD FOR DISCHARGING A FLOW FROM AN AXIAL TURBINE - An axial turbine (03-17-2011
20110064559METHOD AND APPARATUS FOR CONTROLLING TONAL NOISE FROM SUBSONIC FANS - A method and apparatus for reducing a selected tonal noise generated by a fan operating in a non-uniform flow by locating at least one obstruction in the non-uniform flow such that the at least one obstruction generates a noise that is out of phase with the selected tonal noise. The noise generated by the at least one obstruction interferes with the selected tonal noise, thus reducing the selected tonal noise. It is also contemplated to use additional obstructions to reduce other tonal noises generated by the fan.03-17-2011
20090290971SEAL MONITORING AND CONTROL SYSTEM - A seal monitoring and control system for a gas lubricated non-contacting seal includes various sensors providing signals to a programmable logic control system. The control system is disposed to determine a presence of an anomalous operating condition of the seal, for example, based on phase, relative position of rotor to stator or other signals in combination provided by the various sensors to provide an output signal, which in one embodiment performs at least one mitigating process to correct the anomalous operating condition by adjusting at least one operating parameter of the seal.11-26-2009
20130064644VARIABLE PARTIAL WIND WALL - A wind power system including a wind turbine affixed to a support tower, and a wind deflector deployable relative to a direction of air flow and configured to control the movement of at least a portion of air flow passing through rotor blades of the wind turbine to reduce wind loads on the components of the wind turbine while maintaining the air flow in an operating power production range.03-14-2013
20130064642Tank Dampening Device - A compressor assembly having a compressed gas tank having a tank dampening device in the form of a vibration absorption member. The vibration absorption member can provide a pressure to a portion of the compressed gas tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which exerts a force upon the compressed gas tank. A means for controlling the sound level of a compressed gas tank by using a means for absorbing vibration from the compressed gas tank which exerts a pressure on a portion of the compressed gas tank.03-14-2013
20130064641Air Ducting Shroud For Cooling An Air Compressor Pump And Motor - A compressor assembly having an air ducting shroud that can direct a cooling air stream from a fan to components of the compressor assembly, such as a pump assembly. The pump assembly can have at least a pump, a motor and a fan. The compressor can be cooled by providing cooling air to a cylinder head of the pump without the cooling air experiencing choking or substantial cooling flow interference from a cooling of the motor.03-14-2013
20130064643Tank Dampening Device - A compressor assembly that has a compressed air tank having a vibration absorption member. The vibration absorption member can exert a pressure on a portion of the compressed air tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which applies a force against the compressed gas tank. Controlling the sound level of the compressed gas tank is accomplished by absorbing vibration from the compressed gas tank by which exerting a pressure on a portion of the compressed gas tank.03-14-2013
20130064640PERFORATED HYDROCRATIC GENERATOR - A hydrocratic device comprises an inner pipe defining a mixing area, an outer pipe, and an annular chamber between the inner and outer pipes. A feed inlet supplies the annular chamber, and a plurality of perforations are formed in the wall of the inner pipe.03-14-2013
20130064639GAS TURBINE ENGINES WITH IMPROVED TRAILING EDGE COOLING ARRANGEMENTS - An airfoil is provided for a gas turbine engine. The airfoil includes a pressure side wall; a suction side wall; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity. The cooling arrangement includes a first land extending to a first downstream end aft of the pressure side trailing edge, a second land extending to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot, a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, a first pin positioned upstream and indexed to the first passageway, and a second pin positioned upstream and indexed to the second passageway.03-14-2013
20130064638Boundary Layer Blowing Using Steam Seal Leakage Flow - A steam turbine includes a final turbine stage, a flow diffuser receiving a main flow from the final turbine stage, a diverging wall in the axial or radial flow diffuser that extends from a diffuser inlet to a diffuser exit, and a centerbody in the axial or radial flow diffuser. An opening is provided in the diverging wall and an opening is provided in the centerbody for fluidically actuating the main flow. The openings are located downstream from the diffuser inlet and upstream from a point where boundary layer separation would occur along the walls in a diffuser without the openings. A plurality of openings are provided in the diverging wall, and an end packing seal is positioned adjacent an end portion of the final turbine stage. An annular manifold collects fluid from leakage flow from the end packing seal and distributes the leakage flow to the openings.03-14-2013
20090245997METHOD AND DEVICE TO AVOID TURBO INSTABILITY IN A GAS TURBINE ENGINE10-01-2009
20090035121Fluid Flow Modulation and Measurement - In fluid flow measurement applications, apparatus and associated systems, computer program products, and methods may include a positive displacement fluid flow meter having an actuator to control fluid flow through the meter, and further having two or more rotating members with substantially parallel axes that rotate in response to the actuator and to fluid flow through the meter. In various implementations, the actuator may promote and/or retard a fluid flow being measured through the meter. In some examples, the fluid flow meter may operate as a pump to controllably increase a line pressure, controllably regulate a fluid flow rate by opposing rotation of the rotating members, substantially stop a fluid flow, and/or reverse a base fluid flow direction. In an illustrative example, the meter may operate to accurately monitor and control fluid flow (e.g., fluid pressure, velocity, and/or volume) before, during, and/or after a line break.02-05-2009
20130164115BLEED AIR AND HOT SECTION COMPONENT COOLING AIR SYSTEM AND METHOD - Combined bleed air and hot section component cooling air systems for gas turbine engines and methods of operating combined bleed air and hot section component cooling air systems are disclosed. An example system may include a high-pressure bleed air line receiving high-pressure bleed air; a precooler receiving at least some of the high-pressure bleed air and discharging cooled high-pressure bleed air; a pressure regulator receiving at least some of the cooled high-pressure bleed air and discharging pressure-regulated cooled bleed air to a pneumatic systems supply line; and/or a hot section component cooling air line connected upstream of the first pressure regulator and configured to convey at least some of the cooled high-pressure bleed air to a hot section component for use as hot section component cooling air.06-27-2013
20120114459Axial compressor and associated operating method - An axial compressor for compressing a flow medium is provided and includes compressor stator blades, which fastened on a stator blade carrier, and compressor rotor blades, which are fastened on a compressor disk of a compressor shaft, wherein two consecutive compressor disks enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space. A cooling medium feed duct leads through a stator blade carrier and a compressor stator blade, and is arranged upstream of the last compressor disk, which cooling medium feed duct, at the tip end of the compressor stator blade facing the compressor shaft, via a discharge opening arranged there, opens into the hollow space, wherein this hollow space, via a cooling medium transfer passage which is led through the subsequent compressor disks, is connected to the rear hollow space.05-10-2012
20120114458SHROUD LEAKAGE COVER - A method and system for improving performance of a compressor section of a gas turbine by diverting leakage air flowing from high pressure downstream of a stator vane assembly to low pressure upstream of the stator vane assembly from disrupting design flow patterns at a leading edge of stator vanes. A cover is provided at a forward face of an inner shroud assembly to prevent the leakage air from impinging on the leading edge. The cover may be provided at an outlet channel of a flow diverter mounted on the forward face of the inner shroud assembly.05-10-2012
20100086393TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind/Water Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind/water turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass fluid flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas.04-08-2010
20130164114ADJUSTABLE CORE TURBOCHARGER - A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands.06-27-2013
20100329835AIRFOIL WITH HYBRID DRILLED AND CUTBACK TRAILING EDGE - An apparatus for a gas turbine engine includes an airfoil, a metering opening for metering a cooling fluid, a cutback slot configured to deliver the cooling fluid from the metering opening, and a cooling hole. The airfoil defines a trailing edge, opposite first and second faces, and a mean camber line. The cutback slot is defined along the first face of the airfoil adjacent to the trailing edge and offset from the mean camber line of the airfoil. The cooling hole has an outlet that is located at the trailing edge and substantially aligned with the mean camber line of the airfoil. The cooling hole delivers a portion of the cooling fluid from the metering opening.12-30-2010
20100247284AIRFLOW INFLUENCING AIRFOIL FEATURE ARRAY - An example gas turbine engine airfoil includes an airfoil wall establishing a cavity that extends axially from an airfoil leading edge portion to an airfoil trailing edge portion and extends radially from an airfoil inner end to an airfoil outer end. The cavity is configured to receive a baffle that is spaced from the airfoil leading edge portion such that an impingement cooling area is established between the airfoil leading edge portion and the baffle when the baffle is received within the cavity. An array of nonuniformly distributed features is disposed on the airfoil wall within the impingement cooling area. The features are configured to influence airflow within the impingement cooling area.09-30-2010
20090317228APPARATUS AND METHOD FOR CONTROLLING A BLADE TIP CLEARANCE FOR A COMPRESSOR - An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.12-24-2009
20100247288FLUID ELASTOMERIC DAMPER ASSEMBLY INCLUDING INTERNAL PUMPING MECHANISM AND VOLUME COMPENSATOR - Rotary wing system with a rotating blade rotating about a rotation axis. The system includes a fluid damper with a damper fluid for controlling a troublesome motion. The fluid damper has an inboard end and an outboard end, the damper inboard end attached to a first rotary wing system inboard member proximate the rotation axis and the outboard end attached to a second rotary wing system outboard member distal from the rotation axis. The fluid damper contains a damper fluid volume in at least a first working chamber which is worked by a relative motion between said first rotary wing system inboard member and said second rotary wing system outboard member to control the troublesome motion. The damper includes a volume compensator channel in fluid communication with the damper fluid, the volume compensator channel including a centrifugal force mass member movable along a volume compensating length of the volume compensating channel, wherein a rotation about the rotation axis forces the centrifugal force mass member towards an outboard end of the volume compensating channel and pushes damper fluid from the volume compensator channel towards the at least first working chamber.09-30-2010
20100329839Screw Shaft Turbine Compressor and System - Disclosed herein are screw shaft turbine compressors having (i) a compressor section, (ii) a turbine section, (iii) a combustion section coupling to the compressor section and the turbine section, and (iv) a grooved shaft. The grooved shaft can include one or more grooves for providing fuel from the compressor section to the combustion section and for allowing exhaust to leave the combustion section and exit the turbine section. A method for generating different speed to torque ratios on the shaft and a system for generating torque on the shaft are further disclosed.12-30-2010
20110280705WATER PUMP AND WATER PUMP SYSTEM AND METHOD - This disclosure relates a water pump, a system for cooling internal combustion engine components including a water pump, and a method for operating an internal combustion engine including a water pump. The water pump, system and method provide protection of the pump impeller during dry pump operation, such as when a watercraft engine is started while the watercraft is out of water, by dispensing fluid from a reservoir to the pump's impeller chamber. The fluid enters the chamber via a controllable flow path and interacts with the impeller and chamber walls to cool and lubricate the impeller.11-17-2011
20110280706Helico-axial pump, a rotor for a helico-axial pump, method for the hydrodynamic journalling of a rotor of a helico-axial pump, as well as a hybrid pump with a rotor for a helico-axial pump - The invention relates to a helico-axial pump (11-17-2011
20110135443System and method for collecting, augmenting and converting wind power - A system, apparatus, and method for collecting and concentrating an airstream for converting into mechanical or electrical energy, includes an elongated housing structure, including an airstream inlet chamber, a central chamber, and an airstream outlet chamber, and an ancillary airstream injector sub-system.06-09-2011
20120189427GAS TURBINE ENGINE FLOW PATH MEMBER - A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.07-26-2012
20120189426BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT - An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member. An example blade outer air seal assembly includes a blade outer air seal assembly having an inwardly facing surface. A blade path portion of the inwardly facing surface is axially aligned with a tip of a rotating blade. A peripheral portion of the inwardly facing surface is located axially in front of the blade path portion, axially behind the blade path portion, or both. The blade outer air seal assembly establishes cooling paths that terminate at a plurality of apertures established within the inwardly facing surface. The plurality of apertures are locate exclusively within the blade path portion.07-26-2012
20120189425SYSTEM AND METHOD FOR REDUCING CORROSION IN A COMPRESSOR - A system for reducing corrosion in a compressor includes a compressor blade having a corrosion potential. A sensor connected to the compressor blade generates a signal reflective of the corrosion potential. A power supply connected to the compressor blade at an electrical connection produces an electrical potential at the electrical connection. An electrolyte coats at least a portion of the sensor and the electrical connection. A method for reducing corrosion in a compressor includes sensing a corrosion potential of a compressor blade and generating a signal reflective of the corrosion potential. The method further includes generating an electrical potential at an electrical connection on the compressor blade and flowing an electrolyte over at least a portion of the compressor blade and the electrical connection.07-26-2012
20110142593METHOD AND SYSTEM FOR VALIDATING WIND TURBINE - A method of validating a wind turbine including a rotor includes intentionally inducing a loading imbalance to the rotor. The method also includes measuring the loading imbalance induced to the rotor, transmitting a signal representative of the measured loading imbalance to a calibration module, and at least one of detecting an error and calibrating at least one component of the wind turbine based on the signal.06-16-2011
20100008755METHOD OF EXTENDING TUBING LIFE OF A PERISTALTIC PUMP - A method is provided for extending useful life of tubing of a peristaltic pump. The method can comprise switching inlet and discharge hoses between respective inlet and outlet ends of the tubing of the peristaltic pump, and reversing a direction of rotation of a rotor of the peristaltic pump. In implementations of methods disclosed herein, the useful life of the tubing of a peristaltic pump can be approximately doubled.01-14-2010
20120099960SYSTEM AND METHOD FOR COOLING A NOZZLE - A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. The nozzle further includes apertures through at least one of the center body or shroud, a plenum in fluid communication with the apertures, and a louvers proximate to the apertures and connected to at least one of the center body or shroud. A method for cooling a nozzle includes flowing a cooling medium through a plenum inside a center body of the nozzle and flowing the cooling medium through apertures in the center body. The method further includes redirecting the cooling medium with louvers to flow the cooling medium across a surface of the center body.04-26-2012
20110286831PARTITIONING OF TURBOMACHINE FAULTS - An example method of partitioning turbomachine faults includes using a modeling computer to model a system, to establish a modeled gas path parameter, and to establish a modeled subsystem parameter. The method then determines a gas path condition representing a difference between an actual gas path parameter and the modeled gas path parameter. The method also determines a subsystem condition representing a difference between an actual subsystem parameter and the modeled subsystem parameter. The method diagnoses a sensor failure based on the gas path condition and the subsystem condition.11-24-2011
20130216352EJECTOR AND METHOD - In an aspect of the invention there is provided fluid pump apparatus comprising a plurality of ejectors, the apparatus having at least one motive fluid inlet arranged to supply motive fluid to the apparatus, at least one suction fluid inlet arranged to supply suction fluid to the apparatus and a common discharge outlet from which motive fluid and suction fluid that have passed through the ejectors may be expelled from the apparatus, each ejector having a respective injector portion and a respective diffuser portion, the injector portion being arranged to inject motive fluid from at least one said at least one motive fluid inlet into the diffuser portion thereby to draw suction fluid into the diffuser portion from at least one said at least one suction fluid inlet, the diffuser portion having a Venturi portion, each ejector having a respective flow stabilisation portion downstream of the Venturi portion thereof, the flow stabilisation portion being arranged to stabilise a flow of motive fluid and suction fluid therethrough before the respective flows of fluid through each ejector meet downstream of the ejectors, wherein the flow stabilisation portion comprises a flow stabilisation conduit of substantially constant diameter and a length substantially equal to at least the diameter thereof.08-22-2013
20110293400INSTALLATION FOR CONVERTING HYDRAULIC ENERGY, AND A METHOD OF CONTROLLING SUCH AN INSTALLATION - The invention relates to a unit comprising a hydraulic turbine (12-01-2011
20110293399 HYDROELECTRIC TURBINE WITH PASSIVE BRAKING - This present invention relates to a hydroelectric turbine having a stator and a rotor within the stator on at least one set of bearings, the turbine having a brake which becomes operational following a predetermined level of bearing wear in order to avoid damage to the turbine.12-01-2011
20090136334Bearing and Shaft Wheel Assembly Balancing Techniques and Equipment for Turbochargers - An exemplary clamp for clamping a bearing cartridge and shaft subassembly of a turbocharger includes an upper portion, a lower portion where the upper portion and the lower portion form a bore having a bore diameter sized to clamp a bearing cartridge and a fluid passage defined in part by the upper portion, the lower portion or the upper portion and the lower portion where the fluid passage includes an opening to the bore. Various other exemplary devices, systems, methods, etc., are also disclosed.05-28-2009
20090297331TURBOMACHINE CASING INCLUDING A DEVICE FOR PREVENTING INSTABILITY DURING CONTACT BETWEEN THE CASING AND THE ROTOR - The invention relates to a cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel, the casing including a device for preventing instability during contact between the casing and the bladed wheel. In characteristic manner, said device comprises a succession of elements disposed around the circumference of the casing, and presenting between two adjacent elements, different stiffnesses, the number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan.12-03-2009
20110299972IMPELLER BACKFACE SHROUD FOR USE WITH A GAS TURBINE ENGINE - An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.12-08-2011
20110299971GEAR ARRANGEMENT - An example gear arrangement includes a gearbox shaft and a journal shaft. The journal shaft establishes an opening that receives an end portion of the gearbox shaft. The gearbox shaft is configured to rotate the journal shaft. The journal shaft is configured to selectively rotatably couple with another shaft. The journal shaft is allowed to align to the bearing surface while the gearbox shaft allows for misalignment between the accessory and gearbox drive.12-08-2011
20100034634ACOUSTIC VISCOUS DAMPER FOR CENTRIFUGAL GAS COMPRESSOR - An acoustic viscous damper for a compressor including a porous liner located within the discharge duct, the porous liner having a plurality of holes for passage of a purge working fluid therethrough into the discharge duct.02-11-2010
20100028128COMPONENT WITH DIAGONALLY EXTENDING RECESSES IN THE SURFACE AND PROCESS FOR OPERATING A TURBINE - The invention is related to a component of a turbine machine with diagonally extending recesses in the surface of the component. Thermally stressed components of a turbine machine can be protected against excessive heat input by active cooling or by applying thermal insulation layers. The invention increases the effect by providing diagonally extending slots in the surface of the component.02-04-2010
20120189424MATEFACE COOLING FEATHER SEAL ASSEMBLY - A feather seal assembly includes a seal having a directional passage to direct an airflow generally non-perpendicular to the seal.07-26-2012
20130022442SYSTEM AND METHOD FOR OPERATING A TURBINE - A system for operating a turbine includes a rotating component and a non-rotating component separated from the rotating component by a clearance. A first actuator is connected to the non-rotating component, and the first actuator comprises a shape-memory alloy. A method for operating a turbine includes sensing a parameter reflective of a clearance between a non-rotating component and a rotating component and generating a parameter signal reflective of the clearance. The method further includes generating a control signal to at least one actuator based on the parameter signal and moving at least a portion of the non-rotating component relative to the rotating component to change the clearance.01-24-2013
20130022445System for Reducing Compressor Oil Consumption - An air induction system for a power source including a first compressor and a second compressor is disclosed. The air induction system includes an air feed passageway that directs compressed air from the second compressor to an area between a compressor wheel and a center housing in the first compressor to reduce oil consumption in the first compressor.01-24-2013
20090162186Method and apparatus for vibration-based automatic condition monitoring of a wind turbine - Method and apparatus for vibration-based automatic condition monitoring of a wind turbine, comprising the steps of: determining a set of vibration measurement values of the wind turbine; calculating a frequency spectrum of the set of vibration measurement values; calculating a cepstrum of the frequency spectrum; selecting at least one quefrency in the cepstrum, and detecting an alarm condition based upon an amplitude of the cepstrum at the selected quefrency, and a wind turbine therefor.06-25-2009
20100178155STEAM TURBINE AND COOLING METHOD THEREOF - A steam turbine includes a casing, a rotor arranged inside the casing so as to extend in an axial direction of the casing, a rotor disk integrally formed with the rotor, a rotor-side implanting portion formed in the rotor disk, a plurality of moving blades arranged on the rotor disk in a circumferential direction of the rotor, and a moving blade-side implanting portion formed in the moving blade, in which the moving blade-side implanting portions of the moving blades are engaged with the rotor-side implanting portions, respectively. A cooling medium flows through a gap formed at least on a blade portion side of the moving blade among gaps formed between the moving blade-side implanting portions and the rotor-side implanting portions.07-15-2010
20100111666Method for fan control according to the position of a device and device implementing the procedure - The present invention relates to a control method for the operation of a fan equipping an electronic device. A determination step detects the vertical or horizontal position of the electronic device. The fan is not started up during the powering up of the device while the device is in a vertical position. The flow of air produced by the “fireplace” effect in the device in a vertical position suffices to ensure correct ventilation. According to an improvement the device has a sensor measuring the internal temperature of the device, whatever the position of the device, the fan being started up from a determined temperature. The present invention relates also to a device implementing the method.05-06-2010
20100196137CLOSED-LOOP CONTROL FOR A GAS TURBINE WITH ACTIVELY STABILIZED COMPRESSOR - A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor.08-05-2010
20090097959Optimization method for power generation systems - Apparatus for controlling the power output efficiency of a power generation system based on an operator input. A processor is coupled to the input means and (i) receives the generated operator command, (ii) receives a plurality of detected ambient air conditions, (iii) receives a plurality of detected engine. performance parameters, (iv) determines first and second engine control commands based on the received pilot thrust command, the detected ambient environmental conditions, and the engine performance parameters, and (v) outputs control commands to optimize the efficiency of the power generation system.04-16-2009
20100266382WIND TURBINE WITH BOUNDARY LAYER CONTROL - The invention relates to a wind turbine comprising a rotor with a hub and turbine blades, and further comprising a boundary layer control system for the turbine blades. A plurality of pressure chambers is located in the blade distributed over the length of the blade. Each pressure chamber is in communication with the outside of the blade through one or more corresponding openings in the outer surface of the turbine blade. Furthermore a suction channel and a blow channel extend inside the blade for supplying an underpressure and an overpressure respectively to the pressure chamber, each pressure chamber being connected to at least one of said channels through an air passage in which an actively operable valve is located. The valve is connected to a control unit for selectively bringing the pressure chamber into communication with or close it off from said channel(s) so as to blow air out of the pressure chamber or suck air into the pressure chamber through the corresponding opening(s) in the blade surface.10-21-2010
20100284781MITIGATING MECHANICAL VIBRATIONS CAUSED BY A FAN IN A COMPUTER SYSTEM - One embodiment provides a system that mitigates vibrations caused by cooling fans in a computer system. More specifically, the system includes a cooling fan mechanically coupled to the chassis of the computer system, wherein vibrations generated by the cooling fan are coupled to the chassis. The system also includes an actuation mechanism that creates a relative displacement between the cooling fan and the chassis when a control signal is applied to the actuation mechanism. The system additionally includes a detection mechanism which detects the relative displacement and generates a feedback signal which represents the relative displacement. The system further includes a control signal generation mechanism which converts the feedback signal into the control signal, which is subsequently applied to the actuation mechanism. When the control signal is applied to the actuation mechanism, the relative displacement between the cooling fan and the chassis vibrationally decouples the cooling fan from the chassis.11-11-2010
20100329836METHOD OF OPERATING A HEATED GUIDE VANE ASSEMBLY - A method of operating a heated guide vane assembly for turbomachinery, the heated guide vane assembly including a plurality of guide vanes each having two major surfaces joined about their periphery by edges and an associated electric heater element secured to at least one major surface of the guide vanes. The method includes the steps of energizing heater elements on at least one of the guide vanes, de-energizing heater elements on at least one of the guide vanes, and energizing heater elements on at least one of the guide vanes which was not energized in the first energizing step.12-30-2010
20110200423VACUUM PUMP - A differentially pumped vacuum system including apparatus having at least first and second chambers; and a vacuum pump for differentially pumping fluid from the chambers to generate a first pressure above 0.1 mbar in the first chamber and a second pressure lower than the first pressure in the second chamber, the pump having at least first and second pump inlets each for receiving fluid from a respective pressure chamber and a plurality of pumping stages positioned relative to the inlets so that fluid received from the first chamber passes through fewer pumping stages than fluid from the second chamber, the inlets being attached to the apparatus such that at least 99% of the fluid mass pumped from the apparatus passes through at least one of the pumping stages of the pump.08-18-2011
20130216351MAGNETICALLY-COUPLED DAMPER FOR TURBOMACHINERY - A system, method, and apparatus for damping vibration in a rotor supported by primary bearings are provided. The system includes a magnetic coupling configured to magnetically engage a rotor supported by one or more primary bearings, and a piston coupled to the magnetic coupling. The system also includes a damper engaging the piston and configured to damp the rotor, wherein the damper is substantially non-load bearing.08-22-2013
20120107089Fluid Flow Control System Having a Moving Fluid Expander Providing Flow Control and Conversion of Fluid Energy into Other Useful Energy Forms - A fluid flow control system for controlling flow of a primary fluid to a downstream flow-inducing device includes a moving fluid expander with variable expansion ratio and variable speed arranged to receive the flow of the primary fluid and to expand the primary fluid, resulting in a reduction in temperature of the primary fluid. The system further includes an optional heat exchanger arranged to receive the reduced-temperature primary fluid as well as a higher-temperature secondary fluid and to cause varying degrees of heat exchange between the primary and secondary fluids such that the secondary fluid is cooled by the primary fluid. The primary fluid is discharged from the heat exchanger and is supplied to the flow-inducing device.05-03-2012
20120107087METHOD FOR VARYING THE GEOMETRY OF A MID-TURBINE FRAME - A method for varying the geometry of a mid-turbine frame includes detecting a strain in a mid-turbine frame with a piezoelectric material; applying a deformation voltage to the piezoelectric material as a function of the detected strain; deforming the piezoelectric material to actuate an actuation plate; and repositioning an engine casing through the actuation of the actuation plate.05-03-2012
20120107086MOTOR ASSISTED FINE PITCH STARTUP RAM AIR TURBINE - A startup assistance apparatus for a fine pitch Ram Air Turbine (RAT) is provided and includes a generator to provide motive power to the RAT when operating in a first mode and to generate electricity from RAT operation when operating in a second mode and a control unit, including a speed sensing unit configured to sense an operating condition of the generator and a controller operably coupled to the generator and configured to control the generator to operate in the first or the second mode based on the sensed operating condition.05-03-2012
20120107085Housing and Mass Airflow Rate Control System for a Wind Turbine - The present invention provides control for airflow to a wind turbine that allows a wind turbine to operate cost effectively and efficiently in a wide range of speeds and a variety of ambient conditions. A system has a housing, a wind turbine assembly located within an interior space of the housing, and at least one moveable shutter or deflector. The wind turbine assembly includes a shaft, a plurality of air foils or turbine blades, and a plurality of spars supporting the plurality of air foils or turbine blades rotatably around the shaft. At least one movable shutter or deflector is coupled to the housing and adjustably positioned relative to the open sides of the housing to be able to move between different positions to partially or fully cover each open side depending upon the wind speed of the ambient wind.05-03-2012
20110200421Exhaust Diffuser - An exhaust diffuser including an outer flow guide surface and an inner flow guide surface defining an inlet, a first collection chute having an outlet in fluid communication with the inlet, the first collection chute operative to diffuse a flow of a fluid, a second collection chute having an outlet in fluid communication with the inlet, the second collection chute operative to diffuse the flow of the fluid, and the outer flow guide surface and the inner flow guide surface are operative to guide and direct the flow of the fluid to the first collection chute and the second collection chute.08-18-2011
20110200424COUNTER-ROTATING GEARBOX FOR TIP TURBINE ENGINE - A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.08-18-2011
20090202337METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.08-13-2009
20080206039TIP CLEARANCE CONTROL SYSTEM - The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal P08-28-2008
20100129193SYSTEM AND METHOD FOR EXTRACTING POWER FROM FLUID USING A TESLA-TYPE BLADELESS TURBINE - Smooth, preferably variable-sweep fluid collection device surfaces disposed into opposition with wind, river, surf, ocean or tidal currents generate enhanced velocity fluid flows at length driven into onboard work-extracting disc turbines at advantageous angles of attack. Keyed to shafts turning freely through optionally extendable volutes, disc turbines comprising a dense population of smooth, axially fixed or adjustably spaced discs conducting preferably laminar flow between adjacent elements develop significant torque through boundary layer adhesion and viscous shear-stress between fluid layers. Exhaust of disc turbine throughput into divergent channels drafting into external currents of initially higher than ambient velocity and lower pressure may reduce turbine discharge backpressure, rapidly clear system throughput, and allow normally disadvantageous drag to be utilized to develop greater work generation. Gainfully turning with, instead of at odds to natural or anthropogenic currents provided, disc turbines utilized as disclosed may provide unprecedented renewable energy from fluids in motion.05-27-2010
20090280002Method and system for determining gas turbine tip clearance - A system for sensing at least one physical characteristic associated with an engine including a turbine having a plurality of blades turning inside a casing, the system including: a pressure sensor coupled substantially adjacent to the casing and including at least one output; a port in the turbine casing for communicating a pressure indicative of a clearance between the blades and casing to the pressure sensor; a cooling cavity substantially surrounding the pressure sensor; and, an inlet for receiving fluid from the engine and feeding the fluid to the cooling cavity to cool the pressure sensor; wherein, the pressure sensor output is indicative of the clearance between the blades and casing.11-12-2009
20110200422MULTI-LOBE SEMI-FLOATING JOURNAL BEARING - An exemplary turbocharger assembly includes a housing with a through bore having a central axis extending between a compressor end and a turbine end of the housing and a bearing, configured for receipt by the through bore, where the bearing includes an inner journal configured to rotatably support a turbocharger shaft and where the inner journal includes a central axis, an axial length, a lubricant opening, an axially confined lubricant well, a lubricant ramp, and a lubricant channel that spans the axial length of the inner journal. Various other exemplary devices, systems, methods, etc., are also disclosed.08-18-2011
20090129913Computer Room Environmental Conditioning Unit with Translatable Blowers - A conditioning unit can allow the blower to be easily translated from a first operable position in the conditioning unit to a second operable position external to the conditioning unit. The translation of the blower does not require the disconnection of the blower and, accordingly, does not require that the blower be disconnected and reconnected to the control system. Such capability can facilitate the installation of the conditioning unit into a variety of applications and allows the purchaser to customize the blower location based on the desired performance. The ability to customize the installation of the conditioning unit without requiring disconnection and reconnection of the blower can reduce the cost and expense associated with the installation into differing applications.05-21-2009
20100284783Diffuser of natural aromas for refrigerated environments - A diffuser of natural aromas for refrigerated environments includes a dome designed to build up aromas, and houses a cartridge containing coffee as a natural base product, which is covered by a waterproofed mesh to protect the substance from moisture. The dome is coupled to a base that hosts an isolated battery compartment. Windows cut in the base are covered with a dehumidifying net allowing refrigerated and dried air to penetrate the base's inner surface. An electronic fan connected to the battery compartment is mounted on an overhang inside the base to convey air from the refrigerated environment through and outside the dome, creating an airflow cycle. A method of providing a way to neutralize unpleasant odors within refrigerated environments by diffusing natural aromas and a method of providing beneficial effects to a subject when natural aromas are inhaled may be implemented using the above described diffuser.11-11-2010
20120294703DIFFUSER DIVIDER - A diffuser divider shaped as disc with a central axis, a leading edge disposed at an inner radius about the central axis, a trailing edge disposed at an outer radius about the central axis, an upper surface disposed between the leading edge and the trailing edge, a lower surface disposed between the leading edge and the trailing edge and one or more mounting features configured to mount the disc in a diffuser section configured to receive air compressed by two compressor wheel faces and to direct the compressed air to a volute. Such a divider can define throats in a diffuser section of a compressor assembly. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.11-22-2012
20100278629Vertical Multi-Phased Wind Turbine System - A rotational axis multi-phased wind turbine power generating system is disclosed. A differential pressure is created by utilizing the prevailing wind, and air from the prevailing wind is directed into air blades for the creation of power. Optimally, the air blades directly utilize the prevailing wind in combination with the created differential pressure to create power. An adjustable air scoop, adjustable exit drag curtain or barrier, orienting systems, and air flow directing dampers are disclosed.11-04-2010
20100135765PUMPS - A pump assembly and components therefor including an impeller which has flow inducer elements on an inner surface of a front shroud thereof, a flow directing device or strainer having passageways for delivering material to the impeller and at least one flow circulating passageway and a pump casing having an intake section with flow distribution vanes in the region of a feed opening adjacent the intake section.06-03-2010
20080232950METHOD FOR DETECTING ROTATING STALL IN A COMPRESSOR - A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall.09-25-2008
20100129192COMPRESSION METHOD AND MEANS - The invention is a compression method having characteristics of smooth compression and internal cooling of the gas. Embodiments of the invention employ a cylindrical chamber and an orbiting rotor to create a moving duct or chamber whose walls converge, relative to a static gas packet drawn into the moving duct, at a ‘pinch point’. Preferably the closing speed of the walls is subsonic and the speed of the pinch point is supersonic. This enables high pressure to co-exist, at the narrowing end of the duct, with low pressure elsewhere in the duct, because of the pressure information barrier produced by the supersonic advance of the pinch point. The invention also discloses means for adjusting the running clearance between the cylinder and the rotor, and means for counterbalancing the rotor.05-27-2010
20090317230TURBINE SYSTEM FOR UTILIZING THE ENERGY OF OCEANIC WAVES - A turbine system for the utilization of the energy of oceanic waves includes: a chamber that is provided with an opening at its lower end and at its upper end respectively; a duct that is open at both ends for guiding a stream of air, the lower end of the chamber being designated to be submerged in ocean water, and the opening of the upper end being connected with one of the ends of the duct; an energy unit that is mounted coaxial to such and surrounded by the duct; and a device for cleaning the rotor blades of deposits or for preventing the formation of deposits on the rotor blades.12-24-2009
20110008149BLOOD PUMP BEARINGS WITH SEPARATED CONTACT SURFACES - Rotary hydrodynamic blood pumps have been used to treat over a thousand patients. The Jarvik 2000 has supported a patient for seven years and uses blood immersed bearings washed by high flow to avoid excessive thrombus formation. This permits the pump to be very simple and small. Nonetheless, the present Jarvik 2000 bearings and all other mechanical blood immersed bearings of the prior art have a supporting structure that predisposes to thrombus adjacent to the bearings. The present invention provides a bearing structure that eliminates this predilection site for thrombus formation, and may provide indefinite thrombus free operation. The rotor of the preferred embodiment includes a tapered hub fabricated of wear resistant material supported by three posts at each end of the rotor, upon which the rotor rotates. Blood washes the unobstructed spaces between the posts to prevent the accumulation of a torus of thrombus that could enlarge excessively.01-13-2011
20080279676Turbine Anti-Rotating Stall Schedule - A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window.11-13-2008
20100135766KINETIC HYDROPOWER GENERATION SYSTEM AND INTAKE THEREFORE - A kinetic hydropower generation system has a turbine and a generator coupled to the turbine. An underwater intake nozzle assembly is fluidly coupled to the turbine. For one embodiment, an underwater tower nozzle may be fluidly coupled between the turbine and the underwater intake nozzle assembly. The underwater intake nozzle assembly may include a collector and a converging nozzle.06-03-2010
20120195736Plasma Actuation Systems to Produce Swirling Flows - The present application provides a plasma actuation system for a turbo-machinery device. The plasma actuation system may include an end wall, a number of end wall actuators positioned about the end wall, and a blade positioned adjacent to the end wall. The end wall actuators are oriented to produce a swirling flow between the end wall and the blade.08-02-2012
20100143090COOLING SYSTEM AND METHOD FOR A TURBOMACHINE - An embodiment of the present invention provides a cooling system for a flame detection system of a turbomachine. An embodiment of the present invention may provide a control system for the operation of the cooling system. The control system may be configured to automatically and/or continuously monitor the cooling system to determine whether the position of the at least one valve should be changed.06-10-2010
20090180858Method to Prevent Brinelling Wear of Slot and Pin Assembly - A method to prevent brinelling wear of a slot and pin assembly of an adjustable inlet guide vane mechanism includes: providing a compressor having the adjustable inlet guide vane mechanism including a control ring with a plurality of tapered slots positioned around a circumference of the control ring; providing a plurality of tapered pin/lever arm assemblies each comprising a tapered pin having a tapered body with a first threaded end and a second end, a lever arm extending perpendicularly from the second end of the tapered body of the tapered pin and a vane coupled to an end of the lever arm; positioning the tapered pin of the tapered pin/lever arm assembly within each of the plurality of tapered slots such that the first threaded end of the tapered body of the tapered pin extends through the tapered slot; positioning a washer and spring over the first threaded end of the tapered pin of each of the tapered pin/lever arm assemblies; and securing the tapered pin of each of the tapered pin/lever arm assemblies within each of the tapered slots by coupling a nut to the first threaded end of the tapered pin of each of the tapered pin/lever arm assemblies. The tapered body of the tapered pin of each of the tapered pin/lever arm assemblies and each of the plurality of tapered slots are shaped to ensure contact between the tapered body of the tapered pin and the tapered slot thereby preventing brinelling wear.07-16-2009
20120070267Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor - There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.03-22-2012
20120070266TURBO-MACHINE TEMPERATURE CONTROL - A method, system, and computer program for turbo-machine temperature control is presented. The method includes: receiving an exhaust temperature (T03-22-2012
20090053035APPARATUS AND METHOD FOR REDUCING ECCENTRICITY AND OUT-OF-ROUNDNESS IN TURBINES - A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided.02-26-2009
20110142592SUPERSONIC COMPRESSOR ROTOR - The present invention provides a supersonic compressor comprising a supersonic compressor rotor comprising a clockable rotor disk allowing restriction or opening of portions of a fluid flow channel of the rotor in order to enhance performance of the rotor during different operational stages, for example rotor start-up or steady state. The supersonic compressor rotor comprises a first rotor disk, a second rotor disk and a third rotor disk which share a common axis of rotation. The first and second rotor disks are rotatably coupled, and the third rotor disk is disposed between them. The third rotor disk is independently rotatable relative to said first and second disks, and comprises a raised surface structure for restricting or opening a portion of the flow channel defined by the rotor disks and at least two vanes. The flow channel comprises a supersonic compression ramp and encompasses the raised surface structure.06-16-2011
20100028127TURBINE ENGINE LUBRICATION METHOD AND SYSTEM - A method and a system for lubricating a turbomachine including an oil tank, an oil feed pump, an oil/air separator, and at least two enclosures closed by air flow rate seals, each including a low outlet and housing shaft-supporting rolling bearings. The method injects oil from the tank into the enclosures by the pump to lubricate the bearings, introduces compressed air at a low flow rate into the enclosures via the seals to pressurize the enclosures, recuperates all of the air and the oil introduced into the enclosures via their low outlet, uses gravity and the pressurization of the enclosures to convey the oil/air mixture as recovered in this way to the oil/air separator, separates the oil and the air of the mixture by the oil/air separator, returns the oil to the tank, and exhausts the air to outside the turbomachine.02-04-2010
20110229303Method for operating a multistage compressor - A method for operating a multistage compressor is provided. The method includes monitoring the pump limit, wherein at least a first measurement parameter measured during operation is compared to a reference parameter. The reference parameter is characteristic of reaching the surge limit or a specific distance of the operating point from the surge limit. A multistage compressor is also provided. In order to enlarge the operating range without risking safety, it is proposed that each stage to be monitored individually for the onset of the surge.09-22-2011
20110229300APPARATUS AND METHOD FOR INDIVIDUAL PITCH CONTROL IN WIND TURBINES - In a method for blade load reduction control of a rotor of a wind turbine, the rotor includes a plurality of blades, and a pitch angle of each blade is controllable by an actuator. The method includes measuring mechanical load parameters on the rotor, providing control for a collective pitch blade setting based on a rotor speed; providing individual pitch control including transforming the mechanical load parameters from a rotational reference frame to a mechanical load on the rotor in a fixed reference frame; determining from the mechanical load two multi-blade pitches; correcting the multi-blade pitches to corrected multi-blade pitches using actuator limitations; inversely transforming the corrected multi-blade pitches to an individual pitch deviation for each blade in the rotational reference frame; adding up for each blade, the individual pitch deviation to the collective pitch to form an individual pitch; and setting each blade to the respective individual pitch.09-22-2011
20110223003OIL COOLED RUNNER - An oil cooled runner, for a rotary seal between an engine case and a shaft rotationally mounted to the case, includes an annular runner ring having a platform with a radially outer seal engagement surface and a radially inner surface, and an oil distributor having a radially inner portion in communication with a source of liquid lubricant and an outer lubricant casting cone with a rim disposed radially inwardly from the inner surface of the platform.09-15-2011
20090220329ROTOR AND NOZZLE ASSEMBLY FOR A RADIAL TURBINE AND METHOD OF OPERATION - A rotor for a radial flow turbine has an impulse chamber (09-03-2009
20120141252Wind Turbine - A wind driven turbine device is disclosed that includes a housing having an air inlet and an air outlet, a turbine rotor having a plurality of radially distributed turbine rotor blades mounted in the housing for rotation in direct response to atmospheric wind to thereby generate rotary power, a baffle arrangement is also provided for directing wind through the housing from the air inlet to contact the turbine rotor blades from a plurality of angles as internal driving wind.06-07-2012
20120141249FLUID FLOW CONTROL PROVIDING INCREASED ENERGY EXTRACTION - Systems and methods configured to control ambient fluid flow for increased energy extraction using a turbine are disclosed. In various examples, a system can include a convergent nozzle configured to receive and accelerate an ambient flow of fluid and a turbine including one or more rotor blades. The convergent nozzle can include a configuration having a ratio of a nozzle inlet area to a nozzle outlet area between about 1.5:1 to about 10:1, inclusive. An interior nozzle surface can include one or more contours aligned with a direction of the ambient flow of fluid. The convergent nozzle can include apertures in a region near a nozzle outlet. The apertures can be selectively controlled to draw additional fluid flow into the accelerated flow to avoid excessive stress on turbine components. The rotor blades can have a length equal to or slightly greater than a radius of the nozzle outlet.06-07-2012
20100003121VARIABLE AREA FAN NOZZLE FOR ACCOMMODATING A FOREIGN OBJECT STRIKE EVENT - A gas turbine engine system includes a fan (01-07-2010
20120141253TURBOMACHINE - A turbomachine is disclosed. The turbomachine includes a housing and a guide blade ring. An outer shroud of the guide blade ring is divided into segments by joints, where the outer shroud is fastened to the housing by a first fastening element for absorbing axial force and a second fastening element independent of the first fastening element for absorbing circumferential force. The first fastening element and the second fastening elements enable play in a radial direction for the segments of the outer shroud.06-07-2012
20100183424Electrodynamic Control of Blade Clearance Leakage Loss in Turbomachinery Applications - Electrodynamic control of fluid leakage loss is provided. Embodiments utilize electrohydrodynamic (EHD) principles to control and/or reduce leakage flow in turbomachinery. Electrodes can be used to provide a flow actuation mechanism inside the clearance gap for generating discharge. The electrodes can be positioned to have geometric asymmetry. Embodiments provide the electrodes on a turbine blade. The blade can have a DC power that can function as a square pulsed DC wave with the duty cycle equal to the blade passing frequency and the stator can be grounded. In an embodiment, the stator can have the actuator of the electrode-insulator assembly attached to the inside. In one embodiment, the actuators can be arranged just on the stator or casing. The phase and power supply to individual electrodes can be adapted as needed. In one embodiment, the phase can be lagged for accurate control of leakage flow. The control of the power supply to the electrodes can involve a closed control loop that monitors tip gap size.07-22-2010
20100183423Injecting Processing Fluid While Writing Data - An apparatus and associated method is provided for injecting a processing fluid in a device that operably rotates a disc stack. A fluid injector has a nozzle defining an outlet sized to longitudinally span the disc stack to operably direct the processing fluid toward the disc stack. The nozzle also has a flow rate feature that operably directs a first flow rate of the processing fluid from the nozzle into a space adjacent a storage surface of a first disc of the disc stack and that directs a substantially different second flow rate of the processing fluid from the nozzle into another space adjacent a storage surface of a second disc of the disc stack.07-22-2010
20090047116System and method for loads reduction in a horizontal-axis wind turbine using upwind information - A system and method provide a proactive mechanism to control pitching of the blades of a wind turbine to compensate for rotor imbalance during normal operation by pitching the blades individually or asymmetrically, based on turbulent wind gust measurements in front of the rotor, determined before it reaches the rotor blades.02-19-2009
20100260591Spanwise split variable guide vane and related method - Accordingly, in one aspect, the invention relates to a variable guide vane for an axial flow compressor comprising: a first radially outer vane section; and a second radially inner vane section; the first and second vane sections angularly adjustable relative to each other about a longitudinal radial axis of the vane.10-14-2010
20100260592GUIDED WIND KITE FOR INCREASED WIND TURBINE POWER OUTPUT - A wind turbine system includes a kite positioned upstream to a turbine to direct wind to the turbine, thereby increasing revolutions per minutes and power output of the turbine.10-14-2010
20100260593FLUID TURBINE DEVICES AND METHODS RELATED TO FLUID TURBINE DEVICES - Fluid turbine devices and methods related to fluid turbine devices are disclosed herein. One example method includes deflecting a first portion of a fluid flow from a return path of at least a portion of a vertical blade assembly, while permitting a second portion of the fluid flow to enter a drive path of the vertical blade assembly. One example fluid turbine device includes a vertical blade assembly having multiple blades and a shroud rotatable relative to the vertical blade assembly. The shroud includes a leading edge portion for deflecting a first portion of a fluid flow from entering a return path of at least a portion of the vertical blade assembly and a portion defining multiple openings configured to permit fluid from within a compartment defined by the vertical blade assembly to exhaust out of the return path.10-14-2010
20110129328PLASMA SENSORS AND RELATED METHODS - Plasma sensors, systems and related methods are described. An example method for predicting an event includes providing a carrier signal across two electrodes and forming a plasma between the two electrodes. The example method also includes measuring a modulated signal from the plasma, manipulating the modulated signal to produce a value and comparing the value to a threshold. Finally, the example method includes determining the likelihood of the event based on the comparison.06-02-2011
20090297332Wind Diverter - Apparatuses and methods are provided for a wind diverter at least partially encircling a wind turbine support column to direct the wind from an area around a wind turbine to the rotor blades of the wind turbine. The wind diverter may also reduce turbulence and increases the laminar flow of the airstream delivered to the rotor blades. Additionally, the wind diverter increases both the volume of air and the velocity of the airstream reaching the rotor so as to increase the rotor speed. Increasing the rotor speed increases the energy available to the wind turbine. Energy increases as the cube of the rotor speed and the increased energy produces an increase in the power generated by the wind turbine. The wind diverter also allows a wind turbine to begin producing energy at lower initial wind speeds due to the concentration of air.12-03-2009
20100178154Method And System For Controlling A Turbocompressor Group - A method for controlling at least two turbocompressors (07-15-2010
20100178153Turbine Having Compact Inflow Housing Thanks to Internal Control Valves - A turbine having an inflow housing is provided. The turbine includes an inlet for an inflowing working fluid, wherein the inlet can be closed by a quick closing valve, a plurality of control valves and at least two nozzle groups. The flow of the working fluid is controllable by the inlet into the nozzle groups via the control valves. Furthermore, the inlet can be connected via an inlet line to the first nozzle group, wherein the inlet line is guided through the primary control valve such that the flow of the working fluid along the inlet line can be controlled using the primary control valve. The secondary control valve connects the first nozzle group to the second nozzle group such that the flow of the working fluid from the first nozzle group into the second nozzle group may be controlled using the secondary control valve.07-15-2010
20110110758GAS TURBINE COMPRESSOR AND METHOD OF OPERATION - The present application provides a compressor for a gas turbine. The compressor may include a number of rotor wheels positioned about a compressor aft section having a low alloy material, a number of inlet guide vanes positioned about a compressor inlet section, and a wet compression system positioned about the compressor inlet section.05-12-2011
20100254797ENDWALL WITH LEADING-EDGE HUMP - An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped area forward the airfoil leading edge portion.10-07-2010
20100239409Method of Using and Reconstructing a Film-Cooling Augmentation Device for a Turbine Airfoil - A method of using a film-cooling insert for a turbine airfoil is disclosed. The method includes forming an airfoil sidewall having a film-cooling hole that extends between an airfoil cooling circuit and an airfoil surface. The method also includes forming a film-cooling insert and disposing the film-cooling insert in the film-cooling hole. A method of reconstructing a film-cooling insert for a turbine airfoil is also disclosed. The method includes removing a remnant of a film-cooling insert from a film-cooling hole of a turbine airfoil. The method also includes disposing a second film-cooling insert in the film-cooling hole.09-23-2010
20110058928CENTRIFUGAL PUMP WITH THRUST BALANCE HOLES IN DIFFUSER - A centrifugal pump has alternating impellers and diffusers. One or more vent holes extend through one or more vanes of one or more diffusers. In an upthrust condition, high pressure production fluid from an upper impeller is able to pass through the one or more vent holes, and thereby exert force on the preceding impeller. The force exerted on the preceding impeller offsets the upthrust force acting against the preceding impeller.03-10-2011
20100239410COMPRESSOR - A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between said passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.09-23-2010
20100143091VACUUM GENERATOR SEAL - A vacuum generator seal can comprise an upstream annular cavity adjacent to the upstream side of the bearing, a downstream annular cavity adjacent to the downstream side of the bearing, and at least one drain slot positioned on the upstream side of the bearing housing. The vacuum generator seal can include a retainer that at least partially defines the upstream annular cavity. The retainer may be in contact with the bearing housing and may have a tight clearance with the impeller hub. The retainer along with a supply of grease packed within the annular cavities can seal the bearing; and the drain slot can direct water and waste away from the bearing and towards the scroll.06-10-2010
20120141248ACTIVE FAN FLUTTER CONTROL - A flutter control system for a turbomachine fan includes a plurality of fan case sensors located at a fan case of the turbomachine and configured to sense passing of blade tips of a fan of the turbomachine. A controller is operably connected to the plurality of fan case sensors. A variable fan area nozzle actuator is operably connected to the controller, such that the variable fan area nozzle actuator urges a change in fan nozzle area in response to data from the plurality of fan case sensors indicating flutter or near flutter conditions. A method of flutter control for a turbomachine fan includes sensing a blade tip passing of a plurality of fan blades. Data from a plurality of fan case sensors is compared to a threshold and a fan exit area is changed based on the comparison to dampen flutter of the plurality of fan blades.06-07-2012
20120141251METHOD AND DEVICE FOR PREDICTING THE INSTABILITY OF AN AXIAL COMPRESSOR - The present invention relates to a method and device for predicting the instability of an axial compressor, which is applicable to the aerospace and industrial field, specifically to the field of one- or multi-stage axial compressors. The invention relates to a method and a device for predicting the instability of an axial compressor which allows protecting said compressor from the instabilities of devices of this type. The present invention could be used in all those products requiring the use of said compressors, such as aircraft engines, turbofans, turboshafts, or turboprops in the aerospace field, gas turbines in the energy field, air conditioning systems in the civil field, and gas compression systems in the chemical or oil industry.06-07-2012
20120141250WIND TURBINE SHROUD - A shroud for a wind turbine and a method for modifying performance of a wind turbine are disclosed. The wind turbine includes a rotor mounted to a nacelle, the rotor including a plurality of rotor blades and defining an outer diameter. The shroud is positioned downstream of the rotor in an air flow direction, and has an inner diameter of less than the outer diameter of the rotor.06-07-2012
20110129326FUEL PUMP WITH DUAL OUTLET PUMP - An outlet plate of an impeller pump is provided, the outlet plate having an outlet port disposed in the outlet plate, the outlet port being defined by a first outlet port and a second outlet port each extending through the outlet plate; a separator wall located in the outlet port, the separator wall separating an inlet of the first outlet port from an inlet of the second outlet port; and a groove located only on a first surface of the outlet plate, the groove having a first distal end and a second distal end, the first distal end terminating at the first outlet port, wherein the separator separates the groove from the second outlet port.06-02-2011
20110236178BRANCHED AIRFOIL CORE COOLING ARRANGEMENT - An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.09-29-2011
20110027062SYSTEM AND METHOD FOR IMPROVED WIND CAPTURE - A system for improved fluid capture comprises a first vertical turbine. A first radial vane support module comprises a first vertical pole and a second vertical pole and is disposed adjacent to the first vertical turbine. The first radial vane support module comprises a first radial vane storage module coupled to the first vertical support pole and the second vertical support pole and the first radial vane storage module comprises a first motor and a first radial vane. The first radial vane comprises a first retractable panel. The first motor couples to the first radial vane and is configured to extend and retract the first radial vane. A first radial vane control module couples to the first motor and is configured to control the operation of the first motor. In one embodiment, a saucer vane module couples to the first vertical turbine.02-03-2011
20110027061Method For Braking A Rotor Of A Turbine Engine And A Turning Gear For Driving The Rotor Of A Turbine Engine - The invention relates to a method for braking a rotor of a turbine engine, comprising a turning gear, with a drive supplied from an energy source, having an input shaft to which the rotor may be coupled, whereby, during a cooling phase for the turbine, the rotor may be driven by the drive using the coupled input shaft. According to the invention, a method for braking a rotor of a turbine engine can be achieved, in which the rotation of a rotor, caused by the airflow through the turbine, is slowed until the rotor stops, whereby after the end of the cooling phase, the drive drives the rotor in the reverse sense by means of the input shaft in order to brake the same.02-03-2011
20100221095STEAM TURBINE AND METHOD FOR EXTRACTING MOISTURE FROM A STEAM TURBINE - A steam turbine is disclosed which includes a casing containing a plurality of expansion stages, each including stator and rotor airfoils. Downstream of the stator airfoils of one or more expansion stages, the casing includes a slot arranged to receive moisture that concentrates on an end wall of the stator airfoils and discharge it to the outside. Each end wall has a side portion facing the slot having a variable radial obstruction in a tangential direction, in order to define with the slot a passage through which the moisture may pass that is smaller or closed at the suction side and larger at the pressure side of the stator blades, to at least partially prevent the dry steam from entering the slot at the suction side of the blade.09-02-2010
20100221096COMPUTER SYSTEM AND PROGRAM PRODUCT FOR CONTROLLING VIBRATIONS - The computer programmable system and program product include first program instructions for actively driving a first imbalance mass concentration rotor and a second imbalance mass concentration rotor at a vibration canceling rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a rotating net force vector to inhibit periodic vibrations. The program product includes second program instructions to opposingly orient the first imbalance mass concentration relative to the second imbalance mass concentration during a starting stopping rotation speed less than the vibration canceling rotation frequency. The system includes a fault mode control protocol for controlling a rotation of the rotors during a sensed failure of the rotating assembly vibration control system.09-02-2010
20090110536Blade outer air seal with improved thermomechanical fatigue life - A blade outer air seal for a gas turbine has an abradable coating with a substantially uniform thickness during service use. Prior to being placed in service, the abradable coating has a central portion with a greater thickness than leading and trailing portions. When placed in service, the blade outer air seal is positioned so that the central portion of the abradable coating with the greater thickness is located in a blade rub path of the turbine blades. As a result of abrasion in the blade rub path, the thickness of the central portion of the abradable coating is reduced so that it becomes substantially similar to the thickness of the leading and trailing portions.04-30-2009
20110110759METHOD AND SYSTEM FOR REDUCING THE IMPACT ON THE PERFORMANCE OF A TURBOMACHINE OPERATING AN EXTRACTION SYSTEM - A method and system for increasing the efficiency of a turbomachine having an extraction system is provided. The extraction system may have multiple extraction ports from which the working fluid of the turbomachine is extracted to meet extraction load requirements of an independent process. The method and system may enable a control system to optimally determine the which extraction ports to draw the working fluid from for meeting the extraction load requirement. The optimal location may be determined by utilizing the data on the load requirement, where the extraction load requirement may be operationally distinct from the turbomachine load.05-12-2011
20130129472WIND TURBINE - Wind turbine systems and methods are provided. The wind turbine system includes a plurality of coaxial, counter-rotating turbine assemblies. First and second shroud assemblies define a generally spherical volume containing the first and second turbine assemblies. The first and second shroud assemblies each include a shroud member that can selectively shield or expose portions of the respective turbine assemblies to the wind by changing the rotational position of the shroud members about the system axis. The turbine assemblies are interconnected to a generator for the production of electrical power.05-23-2013
20100296912Active Rotor Alignment Control System And Method - A rotating machine, such as a gas turbine, includes an active rotor alignment clearance control system wherein a plurality of actuators are circumferentially spaced around at least one rotor shaft bearing. The actuators are configured to eccentrically displace the bearing, and thus the rotor shaft, relative to stationary outer casing structure. A plurality of sensors are circumferentially spaced around a component of the casing structure, such as an inner shroud, and measure a parameter indicative of an eccentricity, such as blade tip clearance between the rotor blades and the structure, as the rotor rotates within the structure. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the rotor by moving the shaft bearing to compensate for eccentricities detected between the rotor and casing structure.11-25-2010
20100296911Active Casing Alignment Control System And Method - A gas turbine with an active clearance control system includes a plurality of actuators circumferentially spaced between an inner shroud and an outer casing. The actuators are configured to eccentrically displace the shroud relative to the outer casing. A plurality of sensors circumferentially spaced around the shroud detect a parameter that is indicative of an eccentricity between the rotor and shroud as the rotor rotates within the shroud. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the shroud to compensate for eccentricities detected between the rotor and shroud.11-25-2010
20100303606TURBOMACHINE COMPRESSOR WHEEL MEMBER - A turbomachine includes a rotor assembly including a wheel member. The wheel member includes a first portion that extends to a second portion through an intermediate portion. The intermediate portion partially defines a first wheel space and a second wheel space. The wheel member further includes a rotor inertia belt member arranged at the second portion. The rotor inertia belt member includes an extraction air cavity. The extraction air cavity includes an inlet, a first plurality of extraction air passages each including an inlet section and an outlet section, the outlet section leading into the first wheel space, and a second plurality of extraction air passages each including an inlet portion and an outlet portion, the outlet portion leading into the second wheel space.12-02-2010
20130136574INTAKE ASSEMBLIES FOR WIND-ENERGY CONVERSION SYSTEMS AND METHODS - An intake assembly for a wind-energy conversion system has a substantially vertical converging nozzle, an object extending into the nozzle, and a converging flow passage between the object and the nozzle. For some embodiments, the object may be another nozzle. There may be vanes in one or both nozzles in further embodiments. The object may be configured to move in yet other embodiments.05-30-2013
20100303604SYSTEM AND METHOD TO REDUCE ACOUSTIC SIGNATURE USING PROFILED STAGE DESIGN - To reduce noise and thereby increase turbine efficiency, the end walls and airfoils of a turbine are designed to reduce or eliminate radial pressure gradients on rotor blades and their incipient secondary flow vortices which may noisily excite downstream blade and vane rows. Instead of generating inefficient noise, the fluid energy may be properly directed into the shaft as efficient work.12-02-2010
20100303607Turbine Exhaust Diffuser Flow Path with Region of Reduced Total Flow Area - An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub that has an upstream end and a downstream end. The outer boundary has a region in which the outer boundary extends radially inward toward the hub. The region can begin at a point that is substantially aligned with the downstream end of the hub or, alternatively, at a point that is proximately upstream of the downstream end of the hub. The region directs at least a portion of an exhaust flow in the diffuser toward the hub. As a result, the exhaust diffuser system and method can achieve the performance of a long hub system while enjoying the costs of a short hub system.12-02-2010
20100310353ROTOR CASING TREATMENT WITH RECESSED BAFFLES - A compressor rotor casing treatment comprises a plurality of axially spaced-apart circumferential grooves defined in the inner surface of the compressor casing adjacent the tips of the compressor rotor blades. A plurality of circumferentially spaced-apart recessed baffles projects from a bottom surface of each groove to a distance less than a full height of the groove.12-09-2010
20110150626METHOD AND SYSTEM FOR DETECTING A CRACK ON A TURBOMACHINE BLADE - Embodiments of the present invention may provide real-time monitoring of a compressor section to determine the possibility of a crack forming on a rotating blade. The present invention does not require the shutdown of the machine. The present invention may be configured to automatically raise an alarm if the acoustic signature of the compressor changes in way that may be consistent with the cracking of a blade.06-23-2011
20110110760METHOD AND SYSTEM FOR INCREASING AN EFFICIENCY OF A PRESSURIZED MACHINE - A method and system for regulating the pressure of steam in a Steam Seal Header (SSH) for a pressurized machine is provided. In the SSH, the pressure of steam may be regulated according to the operating status of the pressurized machine. The variable pressure SSH system may maintain a pressure packing of the pressurized machine within an optimized pressure range.05-12-2011
20090035122CENTRIFUGAL COMPRESSOR, IMPELLER AND OPERATING METHOD OF THE SAME - A centrifugal compressor is equipped with an impeller having a blade angle distribution that makes it possible to achieve a relatively wide operating range. The blade angle of a shroud side facing a circular plate of a blade is termed a first angle and a blade angle of a hub side disposed at the circular plate is a second angle. The shroud side is formed in a curved shape having an angle distribution from a front area in a shaft direction toward a centrifugal direction in which the first angle is the local maximum point before a substantially middle portion and the local minimum point after the substantially middle point. The hub side is formed in a curved shape having an angle distribution from the front area in the shaft direction toward the centrifugal direction in which the second angle is the maximum local point before the substantially middle portion.02-05-2009
20110116906AIRFOIL COMPONENT WEAR INDICATOR - An example airfoil assembly includes an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side. The assembly further includes a first protective sheath, an indicator sheath, and a second protective sheath. The first protective sheath has an outer side and an inner side that forms a cavity for receiving at least a portion of the airfoil body. The inner side being bonded to the leading edge of the airfoil body. A portion of the indicator sheath is positioned forward the first sheath relative to the leading edge of the airfoil. A portion of the second protective sheath is positioned forward the indicator sheath relative to the leading edge of the airfoil.05-19-2011
20110243709NON-INTEGRAL PLATFORM AND DAMPER FOR AN AIRFOIL - A section of a gas turbine engine includes a damper which extends from a disk between a first blade and a second blade to provide a dissipating vibratory motion energy in the form of friction heating.10-06-2011
20110243708METHODS, SYSTEMS AND APPARATUS RELATING TO TIP CLEARANCE CALCULATIONS IN TURBINE ENGINES - A method of calculating the tip clearance during operation of a combustion turbine engine that includes the steps of: measuring a cold tip clearance and a cold shell-to-shell distance; while the combustion turbine engine is operating, measuring an operating parameter and measuring a shell-to-shell distance with a proximity sensor; calculating the tip clearance based on the cold tip clearance measurement and the operating parameter measurement; calculating the shell-to-shell distance based on the cold shell-to-shell distance measurement and the operating parameter measurement; comparing the shell-to-shell distance measurement of the proximity sensor with the shell-to-shell distance calculation; and calibrating the calculated tip clearance calculation based on the comparison.10-06-2011
20110129327BALL BEARING AND PUMP FOR CRYOGENIC USE - A ball bearing for a cryogenic application including an inner ring and an outer ring positioned around the inner ring. The inner ring and the outer ring define a raceway therebetween. The ball bearing includes a plurality of rolling balls disposed in the raceway and a slug separator positioned between and slidingly engaging each of adjacent pairs the rolling balls. The slug separator defines an exterior surface thereon, which has a recess extending at least partially into the slug separator. The recess is configured to flow cryogenic fluid therethrough.06-02-2011
20110250049Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower - Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.10-13-2011
20110250048Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower - Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.10-13-2011
20110250046TURBOFAN ENGINE PERFORMANCE RECOVERY SYSTEM AND METHOD - Methods and apparatus are provided for improving engine performance in a turbofan gas turbine engine following foreign object ingestion in turbofan gas turbine engines that include an intake fan that includes a plurality of fan blades, and that is disposed within and surrounded by a fan case. The occurrence of a foreign object ingestion by the turbofan gas turbine engine is detected and, upon detecting that a foreign object has been ingested, air is bled from a region proximate the blades of the intake fan through a slot in the fan case.10-13-2011
20110085887HIGH TEMPERATURE RADIALLY FED AXIAL STEAM TURBINE - The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.04-14-2011
20110085886SYSTEM AND METHOD FOR COOLING STEAM TURBINE ROTORS - A steam turbine includes a rotor having a plurality of early stages and a stator portion surrounding a portion of the rotor and arranged such that a leakage region exists between the stator portion and the rotor and having a cooling steam channel that passes cooling steam from one portion of the stator portion to the leakage region. The turbine also includes at least one cooling steam transmission channel axially displaced about the rotor that receives the cooling steam from the leakage region and provides it to at least a portion of the early stages.04-14-2011
20100178152Compressor Clearance Control System Using Turbine Exhaust - The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine.07-15-2010
20110176907MULTI-PIECE TURBOCHARGER BEARING - An exemplary multi-piece bearing for a turbocharger includes a cylindrical piece that has a coefficient of thermal expansion, opposing ends and an outer surface and an inner surface that extend between the opposing ends where the outer surface includes one or more lubricant openings; an end piece that has a different coefficient of thermal expansion and a face where the face includes one or more lubricant openings; and lubricant passages formed by the cylindrical piece and the end piece for passage of lubricant between the one or more lubricant openings of the outer surface of the cylindrical piece and the one or more lubricant openings of the face of the end piece. As described herein, such an exemplary multi-piece bearing can, upon selection of coefficients of thermal expansion, help maintain axial clearances between various components during operation of a turbocharger. Other exemplary bearings, arrangements and methods are also disclosed.07-21-2011
20100054909VARIABLE TURBO SUPERCHARGER AND METHOD OF DRIVING THE SOME - A hydraulic servo drive device for driving a swing mechanism of a variable geometry turbocharger includes a servo piston connected to a driveshaft of the swing mechanism and a pilot spool that is accommodated in a center hole of the servo piston and slides by pilot pressure. A first hydraulic chamber to and from which pressure oil flows are provided in a housing. The servo piston separately includes a pressure port for introducing pressure oil from an outside, a first piston port for intercommunicating the center hole and the first hydraulic chamber, a second piston port for intercommunicating the center hole and the second hydraulic chamber, and a return port for exiting pressure oil.03-04-2010
20110150627METHOD OF OPERATING A FAN SYSTEM - A method of operating a fan system is described comprising the steps of pressurizing an airflow in a forward fan stage to generate a pressurized flow, directing a first portion of the pressurized airflow towards a tip-fan of an aft fan stage, and directing a second portion of the pressurized airflow towards a circumferential row of air-turbine blades of the aft fan stage to drive the aft fan stage.06-23-2011
20110176908Method and apparatus for efficiently generating and extracting power from an air flow to do useful work - This invention relates to a clean, efficient, substantially isentropic method and apparatus for transforming the internal energy of a mass flow of a fluid, such as air, into increased flow kinetic energy and then efficiently transferring this additional kinetic energy to a power take-off means for doing useful work. The acceleration of the air flow is accomplished by passing the air flow through a set of converging nozzles which generate thrust; the nozzle thrust is then transformed into torque which turns a rotor which is coupled to a power take-off means. The method and apparatus can be made to be self-sustaining.07-21-2011
20110081226METHOD FOR OPERATING A WIND TURBINE - The present disclosure relates to a method for operating a wind turbine with the steps: detection of the values of predetermined operating parameters by means of suitable sensors, detection of at least one predetermined initial condition, comparison of the detected values to stored values of the operating parameters. The disclosure further relates to a wind turbine for implementing the method. Therefore, the object of the present disclosure is, to be able to adapt the operation of a wind turbine to changes using a method of the type named above, such that when the detected parameter values deviate from the stored parameter values, as a function of the initial condition, either the stored parameter values are adapted to the detected parameter values or the operation of the wind turbine is influenced as a function of the detected parameter values. In this way, the disclosure is based on the knowledge that, from a pragmatic view, the formation of ice on a rotor blade is also a (temporary, meteorologically-related) change to the rotor blade shape. From this it follows that the formation of ice on the rotor blades always leads to a change of the aerodynamic profile and thus to a negative effect of the output of the wind turbine. However, deviations from this shape and thus deviations in the magnitude of the generated output also result just from manufacturing-dependent deviations of the rotor blades from the predetermined optimum shape and from gradual soiling of the rotor blades during operation.04-07-2011
20090087299FOIL GAS BEARING SUPPORTED HIGH TEMPERATURE CENTRIFUGAL BLOWER AND METHOD FOR COOLING THEREOF - This invention provides a blower design capable of high temperature operation due to use of a self-sustaining cooling scheme through a sealed motor housing in which a cooling circuit can be created, and the use of a thermal barrier across which a temperature gradient may be formed. The thermal barrier may be formed by a thermal choke plate assembly positioned between a hot side and a cold side of the blower to dissipate heat conducted from the hot side. Alternatively, the thermal barrier may be formed by an internal fan ring provided with the blower's rotating assembly to dissipate heat conducted from the blower's impeller. The thermal choke plate assembly and the fan ring may further be used in combination to block heat transfer by all modes between a hot side and a cold side of the blower.04-02-2009
20110070064System and Method for Accommodating Changing Resource Conditions for a Steam Turbine - A system and method for configuring a steam turbine to accommodate changing resource conditions, such as may be encountered with geothermal wells. A plurality of sets of nozzle/blade assemblies are provided for installation in a diaphragm structure and on a rotor, respectively. As the condition of steam provided to the turbine changes, a different set of nozzle/blade assemblies may be installed to maintain a preferred thermodynamic efficiency for the turbine.03-24-2011
20110076131METHOD FOR DETECTING ROTATING STALL IN A COMPRESSOR - A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall.03-31-2011
20110070065Wind energy device with increased wind speed feature - Wind energy device is composed of an enlarged main shroud structure with flare feature to capture more on-coming wind energy, and with wind flow swirling vane feature to force the captured wind flow to rotate. A multiple stage coaxial counter rotating fan system with duct feature is attached to the main shroud to boost the wind flow energy captured by the main shroud to increase the air power passing through the fan system. The coaxial counter rotating fan's rotating direction is opposite to the captured wind flow rotating one forced by the wind flow swirling vanes for higher fan efficiency. A multiple blade supply windmill with shroud feature is mounted to the coaxial counter rotating fan system to capture and convert on-coming wind energy and supply the power to drive the coaxial counter rotating fan system to achieve inputting more energy into the wind flow captured by the main shroud through the fan system. A multiple blade main windmill at the coaxial counter rotating fan system's outlet place will capture and convert the boosted air power into mechanical energy to drive an electrical generator at the front of the device through a drive shaft passing through the coaxial counter rotating fan system. Multiple stage coaxial counter rotating fan system is an efficient approach to increase air flow energy passing through the system. The boosted air power through the coaxial counter rotating fan system will significantly increase the wind kinetic energy capacity that will well offset the cost for the components added, then generate low cost wind powered electricity.03-24-2011
20110070063Pressure Regulation Circuit for Turbine Generators - A pressure regulation circuit delivers pressurized fluid into a generator. The circuit includes pressure regulator structure and a primary valve. The pressure regulator structure outputs pressurized fluid at a predetermined output pressure that is greater than a desired operating pressure of the generator and less than a predetermined upper alarm pressure. The primary valve is downstream from the pressure regulator structure and is selectively opened and closed by a controller based on the pressure within the generator. The controller opens the primary valve to allow the pressurized fluid outputted from the pressure regulator structure to flow into the generator upon the pressure within the generator being at or below a predetermined lower limit. The controller closes the primary valve to prevent the pressurized fluid outputted from the pressure regulator structure from flowing into the generator upon the pressure within the generator being at or above a predetermined upper limit.03-24-2011
20110070066FLUID TURBINE DEVICES AND METHODS RELATED TO FLUID TURBINE DEVICES - Fluid turbine devices and methods related to fluid turbine devices are disclosed herein. One example method includes deflecting a first portion of a fluid flow from a return path of a vertical blade assembly, while permitting a second portion of the fluid flow to enter a drive path of the vertical blade assembly. Another example method related to a fluid flow device includes orienting a shroud relative to a fluid flow to deflect a first portion of a fluid flow from a return path of a vertical blade assembly and to permit a second portion of the fluid flow to enter a drive path of the vertical blade assembly and activating a generator, based on an operating characteristic of the fluid turbine device, to regulate a rotational speed of the vertical blade assembly.03-24-2011
20110150628FLUID ENERGY MACHINE - A fluid energy machine is provided. The fluid energy machine includes a housing having a motor, an impeller, at least two radial bearings, and a shaft which extends along a shaft longitudinal axis and which supports the impeller and a rotor of the motor wherein the shaft is mounted in the radial bearings. The motor includes a stator which at least partially surrounds the rotor in the region of the motor. A gap which extends in the circumferential direction along the shaft longitudinal axis is formed between the rotor and stator and between the rotor and the radial bearings, which gap is at least partially filled with fluid. The motor is embodied as a bearing and is connected to a controller which activates the motor so that forces acting radially with respect to a shaft longitudinal axis can be exerted in addition to torques for driving the fluid energy machine.06-23-2011
20120201651CONTROL UNIT AND A METHOD FOR CONTROLLING BLADE TIP CLEARANCE - A method and system for controlling clearance between the tips of blades of a turbine rotor in a gas turbine airplane engine and a turbine ring of a casing surrounding the blades. A valve is controlled to act on a flow rate and/or a temperature of air directed against the casing. The valve is of the on/off type for switching between an open state and a closed state in a determined reaction time, the valve control module including a corrector for determining a first binary control signal that can take a first value corresponding to an open state and a second value corresponding to a closed state of the valve. The corrector includes a time-delay module for determining a binary control signal, with the duration between two successive changes of state in the control signal being not less than the reaction time of the valve.08-09-2012
20120201650PASSIVE COOLING SYSTEM FOR A TURBOMACHINE - A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket.08-09-2012
20100310354TANDEM SEAL ARRANGEMENT WITH REVERSE FLOW SECONDARY SEAL - A process fluid communication system includes a fluid source in communication with a process seal and a gearbox seal to communicate a pumping medium into a turbomachinery housing and a gearbox housing through the process seal and the gearbox seal.12-09-2010
20100310355MOVING VERTICAL AXIS TURBINE FOIL - A new movable foil for accelerating the fluid hitting the blades of a vertical axis turbine is presented.12-09-2010
20100303605REMOVAL OF MOISTURE FROM PROCESS GAS - Embodiments of the disclosure may provide an exemplary method for operating a compressor system, wherein the method may include cooling a process gas containing water vapor to a first temperature. The water vapor may form a condensate at the first temperature, and cooling the process gas may produce residual heat. At least a portion of the condensate is removed from the process gas, wherein any portion of the condensate that is not removed is a remaining condensate. The remaining condensate may be heated to a second temperature with the residual heat, wherein the remaining condensate in the process gas evaporates at the second temperature.12-02-2010
20100296910THERMAL SYSTEM FOR A WORKING MEMBER OF A POWER PLANT - A working member for a power plant is disclosed herein. The working member includes a body defining at least one working surface of the working member. The at least one working surface is operable to contact a working fluid. The body also includes at least one inner surface opposite the at least one working surface. The working member also includes an interior chamber defined within at least part of the body proximate to the at least one working surface. The working member also includes at least one inlet to the interior chamber. The working member also includes at least one outlet from the interior chamber. The working member also includes a quantity of open-cell foam positioned in the interior chamber between the inlet and the outlet. The quantity of open-cell foam fills less than all of the interior chamber such that at least one empty space is defined in the interior chamber between the at least one inner surface and the quantity of open-cell foam.11-25-2010
20100278628Turbine with variable number of nozzles - A gas turbine generally exhibits a substantial deterioration in efficiency against fluctuation of gas flow rate. A variable nozzle turbine is a solution for this disadvantage; however, it has also another disadvantage of low efficiency under partial load conditions and a large number of heat-resistant moving components. A variable nozzle number turbine according to this invention overcomes these disadvantages. The turbine includes nozzles for injecting gas to rotor blades. The nozzles include inlet ports circumferentially arranged so as to be grouped into a group and an opening and closing valve disposed thereover so as to be commonly functioned therefore. This arrangement realizes a gas turbine with no deterioration of efficiency against fluctuation of gas inflow rate by only one heat-resistant moving component additionally installed. The variable nozzle number turbine according to this invention also realizes a turbine compressor with no surge limit when used as a regenerator. These turbines further realizes a small-sized gas turbine with improved fuel economy under partial load conditions and a turbocharger for regenerating electric power as well as improving efficiency of a displacement engine used therewith. It is to be noted that the inventor is ready for grant of working license.11-04-2010
20120034064CONTOURED AXIAL-RADIAL EXHAUST DIFFUSER - In accordance with one embodiment, a system includes a gas turbine diffuser. The gas turbine diffuser includes an axial diffuser section including a first duct portion having an axial flow path along a centerline of the gas turbine diffuser. The gas turbine diffuser also includes an axial-radial diffuser section coupled to the axial diffuser section, wherein the axial-radial diffuser section includes a second duct portion having a curved flow path along the centerline from the axial flow path to a radial flow path and the axial-radial diffuser section excludes any turning vane in the second duct portion.02-09-2012
20090317227AIRFOIL EMBODYING MIXED LOADING CONVENTIONS - A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications.12-24-2009
20090238675AIRFOIL THERMAL MANAGEMENT WITH MICROCIRCUIT COOLING - A turbine engine component, such as a turbine engine blade, has an airfoil portion with a pressure side wall and a suction side wall, a plurality of ribs extending between the pressure side wall and the suction side wall, and a plurality of supply cavities located between the ribs. The component further has an arrangement for cooling the airfoil portion. The cooling arrangement comprises a first cooling circuit embedded within the suction side wall for convectively cooling the suction side wall, a second cooling circuit embedded within the pressure side wall for cooling the pressure side wall, and a third passageway for increasing a temperature of at least one of the ribs by conduction.09-24-2009
20090185893Radial inner diameter metering plate - A nozzle assembly for directing cooling fluid in a vane comprising a hollow airfoil containing at least two cooling chambers. The chambers are separated by a generally radial rib. A metering plate mount is attached to the rib. A metering plate, having at least one aperture for tuning the cooling fluid flow within the airfoil, is adjacent the metering plate mount.07-23-2009
20110255951Axial Thrust Balanced Impeller For Use With A Downhole Electrical Submersible Pump - An electrical submersible pumping system having a pump, a motor, a shaft connecting the pump and motor. Coaxially stacked rotating impellers and stationary diffusers are coaxially housed within the pump. Radial ports are formed in a hub of the diffusers that direct fluid pressurized by an impeller to a cavity formed on the shroud of the impeller. Axial ports are formed in the shrouds of the impellers that direct fluid from the cavity to a fluid flow passage within the impeller. Strategic placement and sizing of the radial and axial ports balances thrust forces exerted onto the impeller.10-20-2011
20110164957Method and Apparatus for Double Flow Turbine First Stage Cooling - A cooling path is defined through a double-flow steam turbine. The steam turbine includes a generator end and a turbine end and a double-flow tub diaphragm disposed axially between the generator end and the turbine end. A first stage of the steam turbine includes a plurality of first stage nozzles and a plurality of first stage buckets, and a steam path is defined from an inlet region, through the turbine end, to a steam outlet. The cooling path includes cooling holes in the tub diaphragm and root radial seals permitting steam flow beneath the tub diaphragm and around the first stage nozzles and back into the steam path before the first stage buckets.07-07-2011
20110164958Centrifugal reverse flow disk turbine and method to obtain rotational power thereby - A centrifugal reverse flow disk turbine for power generation, comprising; a) a turbine shaft; b) a disk rotor disposed on said turbine shaft; c) a housing, having said turbine shaft and said disk rotor, bearings, seal devices, and at least one jet nozzle means; d) a plurality of radially engraved channel for transporting working fluid from entering ports, placed axially near said turbine shaft; e) a plurality of said channels having two curvatures; first curvature has a small radius, and concaved pertinent to rotational direction of said rotor, starting from the entering port to middle of its flow path, and the second curvature has a large radius, convexed pertinent to rotational direction of said rotor, positioned near the peripheral of said rotor; a plurality of a buket attached at every flow channel, directing against nozzle disposed on said housing, thereby deriving impinging counter supersonic flow.07-07-2011
20110255952COMPRESSOR GAS FLOW DEFLECTOR AND COMPRESSOR INCORPORATING THE SAME - A turbocharger compressor includes a compressor housing having a housing wall that includes a shroud that defines a central air channel and a compressor inlet in fluid communication with the central channel and an inlet duct. It also includes a compressor wheel configured to draw air into the compressor inlet from the inlet duct and create a main airflow in the central air channel axially toward a compressor outlet. The compressor also includes a bypass channel that extends between an opening in the main channel located between the compressor inlet and compressor outlet proximate the compressor blades and the compressor inlet. The compressor also includes a deflector that includes a deflector surface that is configured to direct a bypass airflow in the bypass channel, and flowing in a direction from the main channel toward the compressor inlet, into the compressor inlet axially and radially inwardly toward the compressor wheel.10-20-2011
20110020105NACELLE FLOW ASSEMBLY - A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume.01-27-2011
20110020106Blade containment structure - The fan duct of a ducted fan gas turbine engine has a fan case lined with a honeycomb structure that acts to absorb the energy of a separated part of a blade. A layer of composite material lining honeycomb structure delaminates/breaks when a separated blade part passes through a further, inner honeycomb liner and hits it. The resulting free end of composite liner wraps round the striking end of the blade part, thus blunting the cutting action of the blade part and spreading the generated forces to the extent that the blade part is de-energised sufficiently to prevent it penetrating the fan case.01-27-2011
20110027063SYSTEM AND METHOD FOR ONLINE MONITORING OF CORROSION OF GAS TURBINE COMPONENTS - A system and method capable of performing online corrosion monitoring of a component installed in a gas turbine. A sensing device is located so that electrodes thereof are exposed to an operating environment within the gas turbine section containing the component. The electrodes are formed of a material so that the component and electrodes similarly respond to corrosive agents within the gas turbine section. The electrodes are electrically insulated from each other and each electrode is operable as an anodic electrode or a cathodic electrode, depending on the extent of corrosion thereat, so that each electrode has an electrical potential value, voltages exist across the electrodes, electric currents flow between the electrodes, and the electrical potential/current values correspond to corrosion behaviors at the anodic electrodes. During gas turbine operation, output signals are obtained from the sensing device and indications are provided as to when certain maintenance operations should be performed on the gas turbine.02-03-2011
20110027065AXIAL COMPRESSOR VANE - A gas turbine engine axial compressor vane is disclosed having an aperture capable of flowing a relatively high pressure working fluid to change a direction of a flow vector downstream of the vane. The relatively high pressure working fluid can originate from a compressor discharge. The vane may have any number of apertures.02-03-2011
20110027066METHOD OF CONTROLLING TURBINE EQUIPMENT AND TURBINE EQUIPMENT - To provide a method of controlling a turbine equipment and a turbine equipment capable of carrying out a starting operation of controlling a load applied to a speed reducing portion while complying with a restriction imposed on an apparatus provided at a turbine equipment. The invention is characterized in including a temperature elevating step (S02-03-2011
20110027064SYSTEM AND METHOD FOR MODIFYING ROTOR THRUST - A gas turbine includes a compressor, a turbine downstream of the compressor having stators, and a rotor connecting the compressor to the turbine. The rotor includes rotor cavities. A supply plenum containing a process by-product gas and a control valve is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities. A process for operating a gas turbine having a compressor and a turbine includes connecting the compressor to the turbine by a rotor, creating cavities in the rotor, and injecting a process by-product gas into at least one of the cavities. The process further includes regulating the flow of the process by-product gas into at least one of the cavities according to a pre-programmed parameter.02-03-2011
20100284782STEAM TURBINE, SYSTEM, AND METHOD OF OPERATION - Embodiments of the invention relate generally to steam turbines, steam turbine systems, and methods for their operation and, more particularly, to high-pressure-intermediate-pressure (HPIP) steam turbine configurations having pressure drop-limited seals and exhibiting reduced mid-packing and/or end-packing leakage. One embodiment of the invention provides a combined high-pressure-intermediate-pressure (HPIP) steam turbine comprising: a high-pressure section; an intermediate-pressure section sharing a common rotor with the high-pressure section; at least one packing ring disposed along a length of the rotor and between the high-pressure section and the intermediate-pressure section; and at least one conduit having a first end disposed adjacent a packing ring and a second end disposed adjacent a steampath stage of the high-pressure section.11-11-2010
20100284780Method of Operating a Compressor - A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.11-11-2010
20110255953Turbo machine and method to reduce vibration in turbo machines - A turbo machine (10-20-2011
20100329837SYSTEM AND METHOD FOR ALIGNING TURBINE COMPONENTS - Embodiments include a system having a turbine support key having a set of key segments selectively stackable together in a plurality of combinations to adjust a thickness between turbine supports based solely on a selection of the key segments from the set.12-30-2010
20100329838AERODYNAMIC PERFORMANCE ENHANCEMENTS USING DISCHARGE PLASMA ACTUATORS - The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing.12-30-2010
20110135441Compressor Performance Adjustment System - A compressor performance adjustment system includes a compressor chassis defining an inlet passageway, a diffuser passageway coupled to the inlet passageway, and a return passageway extending from the diffuser passageway. At least one inlet vane is located in the inlet passageway. At least one diffuser vane is located in the diffuser passageway. At least one return vane is moveably coupled to the compressor chassis and located in the return passageway. The return vanes may be adjusted without disassembling the compressor chassis in order to adjust the flow incident on compressor components and adjust the performance of a compressor.06-09-2011
20110135442SYSTEM, DEVICE, AND METHOD FOR ACOUSTIC AND VISUAL MONITORING OF A WIND TURBINE - A method for monitoring a wind turbine. A monitoring signal, including an audio signal and/or an image signal, is received from a monitoring device. Operating data are calculated based on the received monitoring signal. An operating condition and/or a deviation is determined by comparing the operating data to baseline data.06-09-2011
20110052368METHOD AND A SYSTEM FOR ADJUSTING ALARM LEVEL OF A COMPONENT IN A WIND TURBINE - A method and a system for adjusting alarm level of a component in a wind turbine is provided. The method comprises defining an alarm level corresponding to an operational parameter of the component in the wind turbine, monitoring the operational parameter of the component, determining whether the operational parameter exceeds the alarm level, thereby triggering an alarm. In the case when the alarm is triggered, the method further comprises inspecting the component to determine whether the alarm level corresponds to a predetermined remaining useful lifetime of the component, and adjusting the alarm level based on the inspection of the component.03-03-2011
20110052367SEALING AND COOLING AT THE JOINT BETWEEN SHROUD SEGMENTS - A gas turbine engine shroud includes a plurality of shroud segments disposed circumferentially one adjacent to another to form a full, circumferentially segmented ring about the rotor. The radial seal between each pair of adjacent shroud segments is positioned on the back side of the shroud platform. Cooling underneath the radial seals may be done by conduction heath transfer through the platform of the shroud segments.03-03-2011
20110085885VARIABLE VANE ACTUATION SYSTEM - A variable vane actuation system is disclosed herein. The variable vane actuation system includes a first vane having a first vane axis. The variable vane actuation system also includes an actuator operably engaged with the first vane to selectively pivot the first vane about the first vane axis. The variable vane actuation system also includes a ring member operably connected with the first vane. The ring member is disposed for pivoting movement about a centerline axis transverse to the first vane axis. The variable vane actuation system also includes a second vane having a second vane axis spaced from the first vane axis about the centerline axis. The second vane is operably connected with the ring member. Forces moving the second vane are generated by the actuator and transmitted first through the first vane and then through the ring member before being applied to the second vane.04-14-2011
20100322755USE OF NON-UNIFORM NOZZLE VANE SPACING TO REDUCE ACOUSTIC SIGNATURE - A stator for a turbomachine. The stator includes a plurality of nozzle vanes, with the distance between each of the plurality of nozzle vanes varying circumferentially around the stator in a repeating pattern configured to distribute a vibration energy over a plurality of side band vibration frequencies around a nominal passing frequency in a rotor.12-23-2010
20090087298COMPRESSOR AND HEAT PUMP SYSTEM - A centrifugal turbocompressor including an open-type impeller and a casing compresses a gaseous body that condenses into a liquid. The compressor suppresses erosion due to accumulation of a liquid on a casing surface in the compressor. Such accumulation is possible during the starting time of the compressor, if the gaseous body that has come into contact with the casing condenses on the surface of the casing and changes into liquid droplets, centrifugal force may cause the droplets to accumulate on the surface of the casing positioned outside an impeller, and thus to grow into coarser and larger droplets or a liquid film. If the blade tips of the impeller rotating at high speed scrape the droplets or the film upward, erosion of the blade tips is liable to result.04-02-2009
20110097188STRUCTURE AND METHOD FOR IMPROVING FILM COOLING USING SHALLOW TRENCH WITH HOLES ORIENTED ALONG LENGTH OF TRENCH - A turbine airfoil includes a plurality of shallow trenches. Each trench includes a plurality of film holes disposed within and located along the lengthwise direction of the trench and angled through an airfoil substrate in the lengthwise direction of the trench.04-28-2011
20120121375VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD - A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.05-17-2012
20110188990BENKATINA HYDROELECTRIC TURBINE: ALTERATIONS OF IN-PIPE TURBINES - New in-pipe hydroelectric turbine devices, systems, and methods offer the potential for less costly and greater energy output in many applications.08-04-2011
20110188989EXHAUST EDUCTOR SYSTEM WITH A RECIRCULATION BAFFLE - An exhaust eductor system includes a primary exhaust nozzle configured to transport an active flow stream; and a mixing duct at least partially surrounding the primary exhaust nozzle and configured to transport a passive flow stream that is entrained by mixing with the active flow stream from the primary exhaust nozzle. The mixing duct has an interior, and a baffle on the interior of the mixing duct is configured to prevent the mixed flow streams from exiting the mixing duct.08-04-2011
20110188988PLAIN BEARING FOR A WIND TURBINE BLADE AND METHOD OF OPERATING A WIND TURBINE HAVING SUCH A PLAIN BEARING - A plain bearing assembly for mounting a blade to a hub of a wind turbine includes an outer member mountable to one of the blade or hub, and an inner member mountable to the other of the blade or hub and movable relative to the outer member. The plain bearing further includes fluid cavities associated with one of the outer or inner member and arranged to confront the other of the outer or inner member. The fluid cavities are coupled to a pressure source for establishing a pressurized fluid film between the inner and outer members. A method includes monitoring at least one parameter of the fluid film, comparing the at least one parameter to a threshold criteria, and altering a dynamic state of the wind turbine and/or altering the state of the blade bearing assembly if the threshold criteria is exceeded.08-04-2011
20110188987REGULATABLE COOLANT PUMP AND METHOD FOR ITS REGULATION - A regulatable coolant pump and a method for regulation of this regulatable coolant pump for internal combustion engines, which is driven by way of a pulley actives a valve slide using an electromagnetically activated piston pump equipped with a return spring in the form of a pressure spring. The pump implements a “pump feed” using many small “partial lifts.” A “leakage volume stream” that flows opposite to the “pumped volume stream” is superimposed on the “pumped volume stream” via the arrangement of circular apertures both in the inlet valve membrane of the working piston and in the outlet valve membrane so that the valve slide can be moved in defined manner and in a very robust and reliable manner, with low drive power via the defined superimposition of these two volume streams.08-04-2011
20110188986System and method for improving wind turbine efficiency by adjusting blade pitch in response to localized wind speed - A wind turbine for generating electrical power, the turbine having a rotor assembly comprising a hub, a rim and a plurality of blade members extending between the hub and rim, and at least two anemometers mounted at stationary locations relative to the rotor assembly or on the rotor assembly itself, wherein the pitch of individual blade members is adjustable in response to differences in wind speed detected by the anemometers as the rotor assembly rotates.08-04-2011
20100028126APPARATUS AND METHOD FOR CONTROLLING A ROTARY MACHINE USING PRESSURIZED GAS - An apparatus and method for controlling rotating bladed machinery by using a source of pressurized gas is disclosed. The source of pressurized gas, such as air, imparts braking torque on a turbomachinery component through the use of one or more impinging orifices or jets. The orientation of the jets is such that the transfer of momentum from the pressurized gas results in a force substantially opposite the direction of rotation of the turbomachinery component. This transfer of momentum from the pressurized gas allows for a controlling torque to be applied to the turbomachinery component without the need of mechanical and/or electrical devices applying torque to the rotating shaft.02-04-2010
20110217155COOLING GAS TURBINE COMPONENTS WITH SEAL SLOT CHANNELS - A segment of a component for use in a gas turbine includes a leading edge; a trailing edge; a pair of opposed lateral sides between the leading and trailing edges; and a seal slot provided in each lateral side. The seal slot includes a surface having a channel extending in an axial direction defined from the leading edge to the trailing edge, at least one inlet to the channel, and at least one outlet from the channel. The at least one outlet is spaced downstream from the at least one inlet in the axial direction. The segment may be an inner shroud segment or a nozzle segment.09-08-2011
20090304493Axially oriented shingle face seal for turbine rotor and related method - An axial seal arrangement is provided between a rotor and a stator. The rotor is provided with a first disk having a substantially flat sealing face surface. The stator is provided with a second annular disk surrounding the rotor, supporting proximate ends of a plurality of axially extending, flexible, compliant seal elements arranged in an annular array of plural, circumferentially-overlapping radial layers to thereby provide a tortuous path for radially outward leakage flow.12-10-2009
20110305556METHODS AND SYSTEMS FOR VARIABLE GEOMETRY INLETS NOZZLES FOR USE IN TURBOEXPANDERS - A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.12-15-2011
20110305554LIGHT WEIGHT VANELESS COMPRESSOR CONTAINMENT DESIGN - A vaneless compressor containment design has an inner bolt circle with more than three fasteners situated in the vaneless space to cut up tri-hub pieces to smaller pieces prior to reaching an outer bolt circle and its associated flange. This containment design may allow a thinner radial wall thickness for the outermost flange as compared to the conventional design. The thinner radial wall thickness may reduce the weight of the compressor. This weight reduction may be achieved with little or no increase in the compressor space envelope.12-15-2011
20100189542TURBINE ARRANGEMENT AND METHOD OF COOLING A SHROUD LOCATED AT THE TIP OF A TURBINE BLADE - A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurised combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud.07-29-2010
20120148382METHOD AND APPARATUS FOR THE MODEL-BASED MONITORING OF A TURBOMACHINE - The method for the model-based monitoring of a turbomachine by means of a monitoring unit which receives relevant process parameters of the turbomachine, carries out calculations on the basis of these parameters and, as a result, determines one or more state values, by means of which the state of the turbomachine can be assessed, the calculations of the state values being carried out on the basis of one or more physical models of at least one subsystem of the turbomachine, wherein the at least one subsystem is an axial bearing of the turbomachine, and the one or more state values are selected from the axial thrust force, the axial bearing load and the axial shaft attitude.06-14-2012
20100135767Variable and Centrifugal Flywheel and Centrifugal Clutch - A flywheel is attached to a shaft of a turbine. As the shaft rotates, the flywheel swings outwards away from the shaft and regulates the angular velocity of the rotating shaft. In an embodiment, there are multiple flywheels attached to the shaft. In another embodiment there is a first flywheel that controls a second flywheel.06-03-2010
20090081019Systems and Methods for Controlling the Stability of a Water Brake Dynamometer - A system for stabilizing a water brake including at least two rotor disks, a chamber of the water brake for containing water positioned between the at least two rotor disks, a pressure measuring device for measuring a partial pressure in the chamber, and an air injection device for injecting air into the chamber to increase the partial pressure in the chamber.03-26-2009
20120039702 COMPRESSOR - A compressor has a housing defining a gas inlet flow path and a gas outlet and a rotatable impeller wheel between the gas inlet flow path and the gas outlet. The housing has an inner wall defining a surface located in close proximity to radially outer edges of impeller wheel vanes that sweep across said surface as the impeller wheel rotates. At least one opening is provided in the inner wall at the surface. A port is provided in the compressor housing in gas communication with the at least one opening and for diverting gas in a direction away from the gas inlet flow path during relatively low gas flow rate conditions. A gas displacement device such as a pump is disposed outside of the gas inlet flow path and connected to said port, the pump being operable to remove gas selectively through the at least opening and the port in a direction away from said gas inlet flow path.02-16-2012
20100034635Predictive Model Based Control System for Heavy Duty Gas Turbines - A system for controlling the clearance between a turbine blade and the turbine casing that includes an impingement cooling manifold attached to a turbine casing, a temperature sensing device for determining the temperature of the turbine casing, a blower, a control system logic for determining the setting temperature of the casing, and a controller for controlling the blower, wherein the blower forces air onto the impingement cooling manifold to cool the casing towards the setting temperature and control the clearance.02-11-2010
20120039701Closed Cycle Brayton Cycle System and Method - Method and unit for generating energy with improved efficiency. A Brayton cycle unit includes a multistage compressor configured to compress a flowing medium; a first heat exchanger fluidly connected to the multistage compressor and configured to transfer heat from a working medium passing the first heat exchanger to the compressed flowing medium; an expander fluidly connected to the first heat exchanger and configured to expand the heated compressed flowing medium for producing a rotation of a shaft of the expander; and a second heat exchanger fluidly connected between the expander and the compressor and configured to remove heat from the expanded flowing medium. A path of the flowing medium through the unit is closed. At least one inter-cooler mechanism between first and second stages of the multistage compressor is configured to cool the flowing medium to a predetermined temperature.02-16-2012
20130142618STEAM TURBINE ARRANGEMENT OF A THREE CASING SUPERCRITICAL STEAM TURBINE - A steam turbine arrangement is provided and includes a first steam turbine with a first steam outlet, wherein the first steam turbine exhibiting a first sealing leakage, a second steam turbine exhibiting a second sealing leakage, and a third steam turbine with a cooling steam inlet, a functional device and a cooling arrangement. The cooling arrangement is coupled to the cooling steam inlet. The cooling arrangement is adapted for guiding a cooling steam to the functional device for cooling purposes. A steam pipe is coupled to the first steam turbine and to the second steam turbine such that a first steam being provided by the first sealing leakage and a second steam being provided by the second sealing leakage is gathered to a cooling steam in the steam pipe. The steam pipe is coupled to the cooling steam inlet such that the cooling steam is injectable to the cooling arrangement.06-06-2013
20080199300MEANS TO REDUCE SECONDARY FLOW IN A CENTRIFUGAL PUMP - A technique improves the pumping performance of a centrifugal pump in a cost-effective manner. The centrifugal pump comprises a pumping component having one or more vanes defining fluid flow paths. A passage is formed through at least one vane such that an end of the passage is exposed to a low energy flow, i.e. secondary flow, region. Each passage enables the flow of a small amount of fluid from the low energy region to an opposite side of the vane to reduce the secondary flow effects and improve pumping efficiency.08-21-2008
20120063885FLUID CHANNELING DEVICE FOR BACK-TO-BACK COMPRESSORS - A fluid channeling device including a channeling body, an axial transfer channel, and a radial outlet channel. The channeling body includes first and second annular body sections spaced axially apart and a tubular body section extending between the first and second body sections. The axial transfer channel is defined axially through the channeling body, and is configured to fluidly couple a first compression assembly with a second compression assembly. The radial outlet channel is defined radially through the channeling body and is configured to fluidly couple the second compression assembly with an outlet.03-15-2012
20120063882Internally-cooled centrifugal compressor with cooling jacket formed in the diaphragm - An internally-cooled centrifugal compressor (03-15-2012
20120063881ABRADABLE BUCKET SHROUD - The present application provides an abradable bucket shroud for use with a bucket tip so as to limit a leakage flow therethrough and reduce heat loads thereon. The abradable bucket shroud may include a base and a number of ridges positioned thereon. The ridges may be made from an abradable material. The ridges may form a pattern. The ridges may have a number of curves with at least a first curve and a second curve and with the second curve having a reverse camber shape.03-15-2012
20120063883METHODS AND DEVICES FOR LOW SPEED LOW TORQUE TESTING OF A ROTOR IN A TURBOMACHINERY - Methods and devices for performing a low torque low speed test to determine whether a rotor of a turbomachinery is free to rotate are provided. A method includes automatically applying a torque to the rotor, the torque gradually increasing up to a predetermined torque value. The method further includes monitoring the speed of the rotor while the torque is gradually increased. The method also includes outputting an indication that the rotor is free to rotate after the speed of the rotor becomes positive, or outputting an indication that the rotor is locked when the speed of the rotor remains zero and the applied torque has reached the predetermined torque value.03-15-2012
20120063880ROTOR ASSEMBLY - A rotor assembly is disclosed herein. The rotor assembly includes a hub disposed for rotation about an axis of rotation. The rotor assembly also includes at least one blade fixed with the hub for concurrent rotation with the hub. The at least one blade extends along a height axis radially outward from the hub with a root portion proximate to the hub at a first end of the height axis and an airfoil portion extending radially inward from a second end of the height axis opposite the first end. The rotor assembly also includes a sheath extending at least partially around the root portion. The sheath is pivotally engaged with the at least one blade to pivot about the height axis and allowed to weathervane to reduce noise.03-15-2012
20120177476TURBOCHARGER OPERATING SYSTEM AND METHOD FOR AN INTERNAL COMBUSTION ENGINE - A method of operating a turbocharger apparatus on an internal combustion engine, having a first oil circuit and a second oil circuit, includes steps of sensing a plurality of engine operating parameters via a plurality of sensors associated with the internal combustion engine; providing oil to the engine from the first oil circuit at a first pressure level; controlling operation of the second oil circuit for said engine via an electronic control unit, based on the sensed engine operating parameters; and applying a variable hydraulic preload to said first and second bearing assemblies via the operation of the second oil circuit, wherein oil from the second oil circuit is provided at a second pressure level which is different from the first pressure level. A system usable for carrying out such method is also described.07-12-2012
20110318161APPARATUS, SYSTEM AND METHOD FOR A WIND TURBINE - A wind turbine apparatus having a plurality of blades, a shaft connecting the blades and a housing for the blades. The housing is configured to provide an operational angle of over approximately 90 degrees. A wind turbine system having at least one wind turbine apparatus with a housing having a top enclosure and a bottom enclosure. The wind turbine system also includes a post pivotally connected to the at least one wind turbine apparatus and an electrical generator operatively connected to the at least one wind turbine apparatus. A method of wind tunneling wind to a wind turbine apparatus, which includes routing wind towards withdrawing blades of a wind turbine apparatus via a top enclosure; and routing wind towards arising blades of a wind turbine apparatus via angled slots provided in a bottom enclosure.12-29-2011
20110318160TURBOEXPANDER AND METHOD FOR USING MOVEABLE INLET GUIDE VANES AT COMPRESSOR INLET - A turboexpander-compressor system includes an expander configured to expand an incoming gas, a first set of moveable inlet guide vanes configured to control a pressure of the incoming gas, a compressor configured to compress a gas received from the expander, a shaft configured to support and rotate an expander impeller and a compressor impeller, a second set of moveable inlet guide vanes attached to the compressor and configured to control a pressure of the gas input into the compressor, and a controller configured to acquire information about a rotating speed of the shaft, a pressure and a temperature of the incoming gas, a pressure and a temperature of the gas output from the expander, and to control the second set of moveable inlet guide vanes to maximize a ratio between the rotating speed of the shaft and a drop of an enthalpy across the expander, in off-design conditions.12-29-2011
20090324381AIR BEARING TURBO COOLING AIR FLOW REGULATING DEVICE - A cooling air flow regulating device for controlling the flow of cooling air to an air bearing may comprise a housing with a piston and a spring disposed within. When the pressure of the cooling air is high, the piston is forced out of the path of the cooling air and into an open position. As the pressure of the cooling air decreases, the spring forces the piston back into the path of the cooling air, effectively blocking the flow of cooling air to the air bearing. The cooling air flow regulating device of the present invention may be useful for controlling the cooling of air bearings in turbochargers of turbocharged engine, where at low engine speed, cooling air is not required for air bearings. Methods for using the cooling air flow regulating device of the present invention are also provided.12-31-2009
20120045312VANE CARRIER ASSEMBLY - A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.02-23-2012
20100202869HUBLESS WINDMILL - Systems, apparatus and methods for generating power from fluid motion, such as wind are provided. The apparatus is a wing-shaped airfoil with cup-shaped indentations that allow the airfoil to harness wind energy throughout a wide range of wind speeds and from different wind directions. The indentations harness wind energy at low wind speeds while the wing-shape generates a lifting force at high wind speeds to harness wind energy. The system comprises one or more of the devices configured in a hollow, generally cylindrical, shape and connected to a ring frame. The system rotates about an axis running through the center of the ring frame. The rotational motion of the system generates electrical power via a generator. The method is a method for generating electrical power from the rotational motion of the system.08-12-2010
20120014778Sealing Device for Steam Turbines and Method for Controlling Sealing Device - Subject: To provide a sealing structure, and control method therefor, which improve sealing performance between a rotating region and a fixed region, prevent fins from being damaged, and prevent increases in the amount of steam leakage from any clearances newly formed by further abrasion of an abradable material.01-19-2012
20120014777METHOD FOR CONTROLLING A REGULATED-ROTATION-SPEED LOW-PRESSURE CENTRIFUGAL FAN - Method for controlling an automatic stall-prevention of a rotation-speed-regulated centrifugal fan. What is essential in the invention is that the control automatics is controlled by means of the automation system of the process, in which control automatics stalling is detected from a function of the electric current, voltage and frequency going to the motor of the centrifugal fan.01-19-2012
20120014776Method and apparatus for enhancing compressor performance - The present invention provides a non-axisymmetric flow member disposed in a duct of a gas turbine engine. The flow member narrows the area aft of a vane to reduce the cross sectional area through which a wake from the vane traverses.01-19-2012
20120057958CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor (03-08-2012
20120301272VORTEX REDUCER - The present disclosure relates to a vortex reducer (11-29-2012
20120301271SUPERSONIC COMPRESSOR ROTOR AND METHOD OF COMPRESSING A FLUID - A supersonic compressor rotor. The supersonic compressor rotor includes a substantially cylindrical disk body that includes an upstream surface, a downstream surface, and a radially outer surface that extends generally axially between the upstream surface and the downstream surface. The disk body defines a centerline axis. A plurality of vanes are coupled to the radially outer surface. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends generally axially between an inlet opening and an outlet opening. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is selectively positionable at a first position, at a second position, and at any position therebetween.11-29-2012
20120301270SUPERSONIC COMPRESSOR STARTUP SUPPORT SYSTEM - A supersonic compressor includes a fluid inlet, fluid outlet, and a fluid conduit extending therebetween with a supersonic compressor rotor disposed therein. The supersonic compressor rotor includes a first endwall and a plurality of vanes coupled thereto. Each pair of the vanes defines a fluid flow channel. The fluid flow channel defines a flow channel inlet opening and a flow channel outlet opening and includes a throat portion. The supersonic compressor rotor also includes a second endwall and at least one axially translatable fluid control device positioned adjacent to the rotor. The axially translatable fluid control device is configured to obstruct the throat portion and includes at least one axially translatable protrusion insertable into at least a portion of the throat portion.11-29-2012
20120301269CLEARANCE CONTROL WITH CERAMIC MATRIX COMPOSITE ROTOR ASSEMBLY FOR A GAS TURBINE ENGINE - A gas turbine engine includes a CMC static structure and a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure.11-29-2012
20120301268Supersonic Cooling With Pulsed Inlet and Bypass Loop - A supersonic cooling system operates by pumping liquid without the need of a condenser. An inlet of the system may be pulsed to reduce energy required of a pump and to increase the cooling power of the system. The supersonic cooling system utilizes a compression wave in the generation of the cooling effect. The formation of the compression wave may be assisted by a resonance chamber. An evaporator of the cooling system operates in the critical flow regime.11-29-2012
20120301267CONDUCTING UNIT, AND CONDUCTING METHODS - The invention relates to a delivering unit for gas, comprising a compressor (11-29-2012
20120107088DEVICE AND METHOD FOR POSITIONING VARIABLE-GEOMETRY EQUIPMENT FOR A TURBOMACHINE, USING A RELATIVE-MEASUREMENT JACK - A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop.05-03-2012
20120063884CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor (03-15-2012
20120063879ENERGY EFFICIENT IPS BLOWER ASSEMBLY - According to the invention a method and apparatus relating to a blower that is used in an environment of particle contaminated air, as with a helicopter engine, is disclosed. The blower has a power input, a fan, a power output attaching to the fan, and a clutch disposed between the power input and the power output whereby the power input may be selectively coupled to the power output to move the fan to vent the particle contaminated air. The clutch, which may be electrically, mechanically or hydraulically engaged, is activated by a user, a particle or altitude sensor, or by a full authority digital electronic controller (“FADEC”).03-15-2012
20120156005BUFFER AIR FOR A LABYRINTH SEAL - A method of providing buffer air to a labyrinth seal includes operating a multi-stage compressor system having an earlier stage and a later stage such that the air pressure at the later stage is higher than the air pressure at the earlier stage. The method may further include selectively directing compressed air from one of the earlier stage or the later stage to the seal based on a parameter indicative of air pressure within the compressor system.06-21-2012
20120156004METHOD FOR SHUTTING DOWN A TURBOMACHINE - A method for increasing the operational flexibility of a turbomachine during a shutdown phase is provided. The turbomachine may include a first section, a second section, and a rotor disposed within the first section and the second section. The method may determine an allowable range of a physical parameter associated with the first section and/or the second section. The method may modulate a first valve and/or a second valve to allow steam flow into the first section and the second section respectively, wherein the modulation is based on the allowable range of the physical parameter. In addition, the physical parameter allows the method to independently apportion steam flow between the first section and the second section of the turbomachine, during the shutdown phase.06-21-2012
20110091310THERMOMECHANICAL PART CONSTITUTING A BODY OF REVOLUTION ABOUT A LONGITUDINAL AXIS AND INCLUDING AT LEAST ONE ABRADABLE RING FOR A SEALING LABYRINTH - The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly.04-21-2011
20120207583CASE WITH BALLISTIC LINER - A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.08-16-2012
20110103931GAS TURBINE COMPRESSOR - A gas turbine compressor is disclosed. The compressor includes a compressor housing, guide vanes, rotor blades, and valve-controlled blow-in openings for stabilizing the compressor flow by air that is blown in. The air flow is detected by pressure sensors and the valves are controlled as a function thereof.05-05-2011
20110103930Valve Sequencing System and Method for Controlling Turbomachine Acoustic Signature - A system and method for controlling the acoustic signature of a turbomachine having a plurality of valves wherein an operating load is identified and an arc of admission across a plurality of nozzles is associated therewith. A valve sequencing scheme is selected and implemented to activate the arc of admission for a particular operating load so as to minimize valve noise by adjusting valves simultaneously rather than consecutively.05-05-2011
20130170942Multiple Fan Blade Angles in a Single Crossflow Fan - A fan may be provided. The fan may comprise a first plurality of vanes and a second plurality of vanes. The first plurality of vanes may be arranged substantially parallel to an axis of rotation and positioned along a first arc substantially centered on the axis of rotation. Vanes in the first plurality of vanes may be being positioned at a first angle relative to the first arc. The second plurality of vanes may be arranged substantially parallel to the axis of rotation and positioned along a second arc substantially centered on the axis of rotation. Vanes in the second plurality of vanes may be positioned at a second angle relative to the second arc. The first angle may be different than the second angle.07-04-2013
20100092275HOUSEHOLD APPLIANCE INCLUDING A FAN SPEED CONTROLLER - A household appliance including a fan speed controller, and a method of controlling fan speed of a household appliance, are provided. The system includes a fan speed controller that cut a voltage to the fan motor, measures an electromotive force (EMF) of the fan motor at a predetermined time after the cutting of the voltage to the fan motor, and compares the measured electromotive force (EMF) to a table.04-15-2010
20120121377GAS TURBINE ARRANGEMENT AND METHOD FOR OPERATING A GAS TURBINE ARRANGEMENT - A gas turbine arrangement and a method of operating are provided. The turbine includes an annulus, axially delimited between a rotor unit, and at least one stationary component. Cooling medium outlet openings, lead into the annulus, from the stationary component. The cooling medium flows into cooling medium inlet openings, in the rotor unit in a flow direction, which propagates through the annulus. At least one inner cavity, radially to the annulus, is delimited by the rotor unit and by the stationary component. The inner cavity is pressurized with a purging gas, and is fluidically connected to the annulus. The stationary component and the rotor unit include a constriction by which the inner cavity is separated from the radially outer annulus and via which the inner cavity is fluidically connected to the radially outer annulus. Flow guides, fastened on the stationary component on one side, project into the constriction.05-17-2012
20120121376METHOD OF CONTROLLING A COMPRESSOR AND APPARATUS THEREFOR - The present invention relates to a method of controlling a compressor and an apparatus therefor, the method, comprising at least the steps of: (a) providing a compressor feed stream (05-17-2012
20120121378OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine and a compressor hub driven by the first shaft. The compressor hub is within a compressor section of the gas turbine engine. An epicyclic gear train is driven by the first shaft. A common attachment point secures the first shaft and the compressor hub to the second shaft.05-17-2012
20120121373Cranking Pad Interlock - A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing.05-17-2012
20120121374Rotor Coupling Guard - The present application provides a rotor coupling guard for use with removing a flow of air about a rotor coupling of a turbo-machine. The rotor coupling guard may include an inner cover with a number of apertures surrounding the rotor coupling and an outer cover surrounding the inner cover. Rotation of the rotor coupling forces the flow of air through the apertures in the inner cover and away from the rotor coupling.05-17-2012
20120163955SYSTEM AND METHOD TO ELIMINATE A HARD RUB AND OPTIMIZE A PURGE FLOW IN A GAS TURBINE - A system and method to eliminate hard rub and optimize a purge flow in a gas turbine is provided. The gas turbine includes a stator configured to guide a flow of an incoming gas. The gas turbine also includes a rotor configured to expand the incoming gas and extract kinetic energy from the incoming gas. The gas turbine further includes a purge flow bled from a compressor and configured to reduce a temperature of a wheel space by limiting ingestion of the incoming gas. The gas turbine also includes an angel wing disposed between the rotor and the stator and configured to act as a sealing surface between the rotor and the stator. The gas turbine further includes a fan blade disposed on a surface of the angel wing at an axial position and configured to generate a recirculation zone of the purge flow, wherein the recirculation zone is reduces a volume of successive purge flows entering the wheel space.06-28-2012
20100247285Systems and Methods for Providing Compressor Extraction Cooling - Embodiments of methods and apparatus for providing compressor extraction cooling are provided. According to one example embodiment, a method for providing compressor extraction cooling in a gas turbine comprising a compressor and a turbine section can be provided. The method can include providing a cooling medium. The method can include extracting air from a compressor associated with a gas turbine. The method can also include introducing the cooling medium to the compressor extraction air, wherein the compressor extraction air is cooled by the cooling medium prior to or during introduction to the turbine section.09-30-2010
20100247287NOZZLE ADJUSTING MECHANISM AND METHOD - Method and nozzle adjustment mechanism for adjusting a flow of a fluid. The nozzle adjustment mechanism includes a fixed ring; at least a vane connected to the fixed ring by a pivot pin and configured to rotate with the pivot pin; an adjusting ring rotatably connected to the fixed ring and configured to rotate around a longitudinal axis of the nozzle adjustment mechanism; and a connection mechanism connecting the at least a vane to the adjusting ring and configured to move the at least a vane when the adjusting ring is rotated, the connection mechanism including a lever component and a link component connected to each other. The lever component is connected to the at least a vane and the link component is connected to the adjusting ring.09-30-2010
20100247282SYSTEMS, METHODS, AND APPARATUS FOR PASSIVE PURGE FLOW CONTROL IN A TURBINE - Systems, methods and apparatus for passive purge flow control in a turbine are provided. Various embodiments of the invention include providing a path for air to flow to a bore of a rotor with a plurality of stacked wheels. The air flow path includes at least one inlet hole on a rotor structure and a plurality of holes in at least some of the stacked wheels. The method further involves control of air flow to the at least one inlet hole based at least in part on axial deflection between the rotor and an associated stator during the gas turbine operation. Additionally, a portion of the air flowing into the inlet hole is directed through the plurality of holes in the at least some of the stacked wheels to purge the rotor.09-30-2010
20100247283METHOD AND APPARATUS FOR CLEARANCE CONTROL - A system, in certain embodiments, includes a magnetic actuator configured to adjust a radial clearance between a housing and rotary blades via translational movement along a rotational axis. The system includes a controller configured to engage the magnetic actuator to adjust the radial clearance in response to feedback.09-30-2010
20100247286FEEDING FILM COOLING HOLES FROM SEAL SLOTS - A cooling arrangement for a first stage nozzle of a turbine includes a slot formed in a forward face of the first stage nozzle, the slot opening in a direction facing a combustor transition piece and adapted to receive a flange portion of a seal extending between the first stage nozzle and the transition piece. The slot has a closed end formed with at least one cooling cavity provided with at least one cooling passageway extending between the cavity and an external surface of the first stage nozzle.09-30-2010
20120171010REMOVABLE STEAM INLET ASSEMBLY FOR STEAM TURBINE - A removable steam inlet assembly and lifting fixture for a steam turbine are provided to facilitate lifting of the upper exhaust hood of the steam turbine. The removable steam inlet assembly is detached from the steam inlet of the turbine inner casing for the lift and mounted to the upper exhaust hood with a lifting fixture. Detaching and removal of the steam inlet assembly substantially lowers the clearance height for the lift, allowing lower turbine building height with significant cost savings.07-05-2012
20120128463SYSTEM AND METHOD FOR MANAGING THERMAL ISSUES IN ONE OR MORE INDUSTRIAL PROCESSES - The present invention generally relates to a system that enables one to both: (i) address various thermal management issues (e.g., inlet air cooling) in gas turbines, gas turbine engines, industrial process equipment and/or internal combustion engines; and (ii) yield a supercritical fluid-based heat engine. In one embodiment, the present invention utilizes at least one working fluid selected from ammonia, carbon dioxide, nitrogen, or other suitable working fluid medium. In another embodiment, the present invention utilizes carbon dioxide or ammonia as a working fluid to achieve a system that enables one to address inlet cooling issues in a gas turbine, internal combustion engine or other industrial application while also yielding a supercritical fluid based heat engine as a second cycle using the waste heat from the gas turbine and/or internal combustion engine to create a combined power cycle.05-24-2012
20100172738Method of Matching Thermal Response Rates Between A Stator and a Rotor and Fluidic Thermal Switch for Use Therewith - A turbine power generation system with thermal response rate matching provided by one or more fluidic thermal switches and a method for mitigating restart pinch during a hot restart. The turbine power generating system includes a stator and a rotor situated within the casing of the stator. Auxiliary heat is provided to the stator casing during shutdown operations from a heat source via one or more fluidic thermal switch which are configured to provide localized heating to portions of the stator casing subject to restart pinch. The fluidic thermal switch includes two solid, thermal conductors having fluid contacting elements spatially separated within an insulated vessel. A highly conductive and capacitive fluid is provided to the insulated vessel when localized heating is needed.07-08-2010
20120076636Controlled Angular Acceleration for Air Moving Devices - Various methods related to air moving devices in electronic systems are disclosed. Various electronic systems including controlled air moving devices are also disclosed. Thus, in one method of controlling an air moving device in an electronic system, the air moving device is operable to accelerate between rotational speeds at a maximum angular acceleration. The method includes limiting an angular acceleration of the air moving device to a first acceleration limit less than the maximum angular acceleration when changing the air moving device from a first rotational speed to a second rotational speed.03-29-2012
20120076634Turbine Blade Tip Shroud for Use with a Tip Clearance Control System - The present application provides a tip clearance control system for reducing an airflow through a turbo machine. The tip clearance control system may include a casing shroud and a tip shroud positioned within the casing shroud. The tip shroud may include a first step at a leading edge and a second step adjacent to the first step. The casing shroud and the tip shroud may define a first cavity therebetween downstream of the second step.03-29-2012
20120315125TURBINE BLADES WITH MIXED BLADE LOADING - An unevenly loaded turbine blade is disclosed including a first region configured for extracting power from a fluid flow and a second region configured for adding power to the fluid flow. The power extracted from the fluid flow is typically greater than the power added to the fluid flow resulting in a net power extracted for the blades. The addition of power to the fluid flow advantageously results in localized injections of high velocity fluid flow which provide distributed mixing of wake and tip vortices along the length of the blade.12-13-2012
20120237332FLUID-COOLING DEVICE FOR A TURBINE ENGINE PROPULSIVE UNIT - The invention relates to a fluid cooling device (09-20-2012
20120251292METHOD AND ARRANGEMENT FOR ESTIMATING FLOW RATE OF PUMP - A method and arrangement for determining the flow rate (Q) produced by a pump, when the pump is controlled with a frequency converter, which produces estimates for rotational speed and torque of the pump, and the characteristic curves of the pump are known. The method includes determining the shape of a QH curve of the pump, dividing the QH curve into two or more regions depending on the shape of the QH curve, determining on which region of the QH curve the pump is operating, and determining the flow rate (Q) of the pump using the determined operating region of the characteristic curve.10-04-2012
20090060706BALL BEARING AND PUMP FOR CRYOGENIC USE - A ball bearing for use in cryogenic applications has an inner ring and an outer ring that define a raceway between them, and there is a set of rolling balls in the raceway with slug ball separators between adjacent rolling balls. The bearing may be used in a pump for cryogenic fluids such as LNG, LOX, LH2, etc.03-05-2009
20090060705Sanitary Air Jet Device - A sanitary air jet device [03-05-2009
20090060704ACTIVE FLOW CONTROL FOR NACELLE INLET - The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition.03-05-2009
20120263572TURBINE FOR CONVERTING ENERGY AND METHOD FOR OPERATING THE SAME - A turbine and a method for converting energy are provided, wherein an angular position of an exit of a cooling duct in the casing depends on angular positions of a downstream edge 10-18-2012
20120257954METHOD FOR COOLING TURBINE STATORS AND COOLING SYSTEM FOR IMPLEMENTING SAID METHOD - A method and system for cooling turbine engine turbines, the system includes: at least one pair of parts to be cooled, the pair including a stator upstream from the rotor valve, and a sealing ring mounting a downstream movable blade rotor that is adjacent to the stator; a turbine casing; and an outlet path. The system further includes: at least one opening in the casing facing at least one part to be cooled; and an air circuit producing a forced convection in connection with the parts and at least one downstream outlet in the path so as to draw in and transport an ambient air flow.10-11-2012
20120230810SHROUNDED WIND TURBINE CONFIGURATION WITH NOZZLE AUGMENTED DIFFUSER - Disclosed are a system, a method and an apparatus of diffuser nozzle augmented wind turbine. In one embodiment, a method includes attaching a nozzle with a streamlined opening to a diffuser to direct an air flow into a wind turbine. In addition, the method includes increasing a wind speed approaching a set of turbine blades within a shrouded wind turbine configuration. The method also includes recirculating the air within the shroud configuration to increase an output power generated through the wind turbine. The system is composed of diffuser and nozzle integrated and non-integrated with and without a flange. In one embodiment, a method includes increasing a pressure differential of a wind turbine.09-13-2012
20110002772CONTROL DEVICE AND METHOD FOR AN AERODYNAMIC BRAKE OF A WIND ENERGY CONVERTER - A wear-free, self-contained control device for an aerodynamic emergency brake of a wind energy converter is presented that comprises multiple components in order to provide a most effective means to control the rotation of a vertical axis wind turbine by a brake, which is able to activate itself without external actuation in malfunction situations and is able to shut down the vertical axis wind turbine. Therefore, a mass element is utilised to store mechanical energy which in turn is used to deploy an aerodynamic braking operation. It also represents a means to control and limit the amount of torque, as absorbed by the turbine in high-wind conditions, and thus provides the ability to harvest electrical/mechanical energy, beyond the normal operational wind speeds of turbines.01-06-2011
20110002771ROTOR BLADE OVER-TIP LEAKAGE CONTROL - A system is provided for controlling rotor blade over-tip leakage of a working fluid in rotating machine. The system has a circumferential row of rotor blades, and a circumferential row of seal segments for sealing with the radially outer tips of the rotor blades to reduce over-tip leakage of the working fluid. The seal segments have an inboard abradable layer which is adapted to be abraded by the blade tips to form a wear track for the blade tips. The system further has one or more tip wearing bodies which are adapted to wear down the blade tips. The thickness of the abradable layer and the cold build radial positions of the blade tips, seal segments and tip wearing bodies are arranged such that, during running-in of the machine, a wear track having a uniform radius is formed in the abradable layer by the blade tips, and the tip wearing bodies also wear down the blade tips to provide a uniform blade tip radius.01-06-2011
20110002770COMPRESSOR - A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises inner and outer tubular walls extending away from the impeller wheel in an upstream direction and defining between them gas flow passage. A bleed passage between the gas flow passage and the impeller wheel is selectively opened and closed by movement of a sliding sleeve in a helical direction.01-06-2011
20120263571VARIABLE VANE FOR GAS TURBINE ENGINE - A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button.10-18-2012
20090067978VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes a ring of turbine nozzle segments each having paired turbine vanes. Turbine throat area is modulated by rotating each rotational turbine vanes about an axis of rotation which is located such that rotation changes the turbine throat area concurrently between one rotational stator vane and two adjacent fixed turbine vanes. Each paired turbine vane doublet includes at least one rotational turbine vane between two fixed turbine vanes.03-12-2009
20120269612TURBINE INLET CASING WITH INTEGRAL BEARING HOUSING - The present application provides a compressor inlet casing. The compressor inlet casing may include an inner bellmouth and a bearing housing. The bearing housing may include an integrally cast first half connected to the inner bellmouth and a cavity positioned between the inner bellmouth and the integrally cast first half of the bearing housing.10-25-2012
20110229302WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas.09-22-2011
20110236181VERTICAL AXIS WIND TURBINE - A vertical axis wind turbine comprises upper and lower rotor blades and upper and lower bearing assemblies. Horizontal members connect the upper rotor blades to the upper bearing assembly and the lower blades connect the upper rotor blades to the lower bearing assembly. The upper rotor blades can be arranged vertically or non-vertically. In non-vertical arrangements, the upper rotor blades can be twisted or swept back in a straight manner. The turbine can be self-supporting with a need for a continuous vertical axis connecting the bearing assemblies. Sweeping jet actuators are incorporated into the rotor blades to deliver oscillating air jets to surfaces of the rotor blades to delay occurrence of dynamic stall. Conduits in the blades can deliver pressurized flow of air to the actuators. The turbine can be supported by a structure that can exerts only horizontal and/or lifting forces on the rotor blade assembly to reduce the load on the lower bearing.09-29-2011
20110236179SEAL CLEARANCE CONTROL ON NON-COWLED GAS TURBINE ENGINES - A method for controlling turbine blade tip seal clearance on a non-cowled gas turbine engine includes the step of directing a flow of relatively hot, pressurized air in contact with an exterior surface of the engine core casing circumscribing the turbine. The flow of relatively hot, pressurized air may be selectively directed in contact with the exterior surface of the engine core casing circumscribing the turbine when it is desired to expand the turbine shroud radially outward, such as during transient operation of the gas turbine engine.09-29-2011
20110236177Steam Seal System - The present application provides a variable steam seal system for use with a steam turbine. The variable steam seal system may include a seal steam header, a first pressure section, a first pressure seal positioned about the first pressure section, and a flow path through the first pressure seal and extending to the seal steam header. The first pressure seal may include a moveable seal packing ring for varying the flow path through the first pressure seal to the seal steam header.09-29-2011
20080247860Hydroelectric power plant and method of generating power - A hydroelectric power plant includes a fluid intake, a fluid exhaust, a fluid engine located in a fluid path between the fluid intake and the fluid exhaust, and a fluid accelerating device located adjacent to the fluid exhaust. The fluid accelerating device is configured to accelerate fluid past the fluid exhaust and is approximately shaped as a portion of a cone.10-09-2008
20110158788A SECTIONAL BLADE - The invention provides a sectional blade for a wind turbine. The blade comprises at least a first blade portion and a second blade portion extending in opposite directions from a joint. The first blade portion and the second blade portion are structurally connected by at least one spar bridge extending into both blade portions to facilitate joining of said blade portions.06-30-2011
20100232929COOLING ARRANGEMENT FOR A TURBINE ENGINE COMPONENT - An example turbine component cooling arrangement includes a film plate having a plurality of film channels extending from film channel entrances on a first side of the film plate to corresponding film channel exits on an opposing second side of the film plate. The arrangement also includes an impingement plate establishing a plurality of impingement channels. The impingement plate is spaced a distance from the film plate. The plurality of impingement channels are configured to direct a fluid across the distance to contact the film plate between adjacent ones of the film channel entrances. In one example, the distance from the film plate to the impingement plate is between two and four times more than diameter of one of the impingement channels.09-16-2010
20100232928METHOD OF OPTIMIZING A DUCTED ANTI-TORQUE ROTOR OF A ROTORCRAFT, IN PARTICULAR A HELICOPTER, TO MINIMIZE ACOUSTIC ANNOYANCE, AND A DUCTED ANTI-TORQUE ROTOR OBTAINED THEREBY - The present invention relates to a method of minimizing the noise emitted by a ducted rail rotor anti-torque device at a frequency FE and perceived at a frequency FP, in which method the diameter D, the number of blades b, and the tangential speed U of the rotor are determined so that the perceived frequency FP is less than or equal to the bottom limit frequency FL of a predetermined one-third frequency octave centered on a frequency FC.09-16-2010
20110250050SINGLE FAN TRAY IN A MIDPLANE ARCHITECTURE - A chassis may include a front section that contains a first electronic circuit board oriented in a first plane, a rear section that contains a second electronic circuit board oriented in a second plane, where the first plane and the second plane are substantially orthogonal, a midplane dividing the front and the rear sections, and a fan tray assembly including a plurality of fans to cool both the first electronic circuit board of the front section and the second electronic circuit board of the rear section.10-13-2011
20110250047Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower - Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.10-13-2011
20120321439Eddy Current Damper and Method - An apparatus for supporting a shaft of a turbomachine. The apparatus may include a magnetic bearing to support the shaft during a normal operation of the turbomachine, and an auxiliary bearing to support the shaft during a drop event. The apparatus may also include a disk coupled to the shaft and comprising a substantially non-ferrous, conductive material, and a magnetic assembly disposed proximal the disk, the magnetic assembly configured to magnetically engage the disk to damp vibrations during the drop event, to apply a circumferential braking force on the disk during the drop event, or both.12-20-2012
20120321438 COMPRESSOR UNIT AND A METHOD TO PROCESS A WORKING FLUID - A compressor unit for processing a working fluid comprising a compressor inside a housing to compress the working fluid wherein a collection chamber is fluidly coupled with a working fluid inlet of said housing.12-20-2012
20120321437TURBINE SEAL SYSTEM - A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage including a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage including a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal extending axially between the first and second turbine stages. The interstage seal is configured to be installed or removed while the first and second wheels remain in place in the respective first and second turbine stages.12-20-2012
20120328410SURGE ESTIMATOR - A method of correcting surge control parameters that includes providing a dynamic compressor having a compressor, driver, surge valve, and control system. The control system establishes surge control parameters such as surge detection lines, surge limit lines, and then detects the onset of a surge in the dynamic compressor. When the surge is detected the control system measures variables of the dynamic compressor such as fluid pressure, fluid speed, power, speed and valve position and based on these variables the control system automatically corrects the surge control parameters based on these variables at the time of the onset of the surge is detected. Advisory information is provided by control system to user for corrective actions to prevent surge.12-27-2012
20120282078BEARING ASSEMBLY WITH DAMPING FEATURES - A turbocharger bearing assembly can include a compressor side bearing; a turbine side bearing; and a spacer configured to axially space the compressor side bearing and the turbine side bearing where the spacer includes lubricant passages to direct lubricant to spacer-bearing interfaces and where the spacer optionally includes a spring disposed in a central through bore to load the bearings. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.11-08-2012
20120328409SYSTEMS AND METHODS FOR COOLING HIGH PRESSURE AND INTERMEDIATE PRESSURE SECTIONS OF A STEAM TURBINE - The present application provides a section cooling system for a steam turbine to limit a leakage flow therethrough. The section cooling system may include a first pressure flow extraction from a first section to a shaft packing location between the first section and a second section and a rotor aperture extending towards the first section. The first pressure flow extraction diverts the leakage flow from the first section into the rotor aperture so as to limit the leakage flow to the second section.12-27-2012
20120328411MULTI-STAGE TURBOCHARGER SYSTEM WITH EXHAUST CONTROL VALVE - A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.12-27-2012
20120288357VERTICAL MULTI-PHASED WIND TURBINE SYSTEM - A rotational axis multi-phased wind turbine power generating system is disclosed. A differential pressure is created by utilizing the prevailing wind, and air from the prevailing wind is directed into air blades for the creation of power. Optimally, the air blades directly utilize the prevailing wind in combination with the created differential pressure to create power. An adjustable air scoop, adjustable exit drag curtain or barrier, orienting systems, and air flow directing dampers are disclosed.11-15-2012
20100202871Gearbox For A Wind Turbine, A Method Of Converting Wind Energy And Use Of A Gearbox - A gearbox for a wind turbine. The gearbox includes at least one first epicyclical gear stage, at least one second gear stage, and a torque transferring shaft including a shaft part and a connection part, wherein the torque transferring shaft is adapted for connecting a first gear of the first epicyclical gear stage with a second gear of the second gear stage and wherein the torque transferring shaft is connected to the second gear stage via the connection part to form a torque-transferring connection area between the connection part and the second gear stage and wherein the outer diameter of the shaft part of the torque transferring shaft is smaller than an inner diameter of the connection area between said torque transferring shaft and said second gear stage.08-12-2010
20100202870METHOD AND APPARATUS FOR LUBRICATING A THRUST BEARING FOR A ROTATING MACHINE USING PUMPAGE - A fluid machine and method of operating the same includes a pump portion having a pump impeller chamber, a pump inlet and a pump outlet and a turbine portion having a turbine impeller chamber, a turbine inlet and a turbine outlet. A shaft extends between the pump impeller chamber and the turbine impeller chamber. The shaft has a shaft passage therethrough. A turbine impeller is coupled to the impeller end of the shaft disposed within the impeller chamber. The turbine impeller has vanes at least one of which comprises a vane passage therethrough. A thrust bearing is in fluid communication with said vane passage.08-12-2010
20100068028REDUCED TIP CLEARANCE LOSSES IN AXIAL FLOW FANS - An axial fan assembly including a casing wall with a forward facing step formed therein and a fan rotor with blade tips, each having an aft facing step which radially overlaps the casing step so as to reduce the clearance backflow loss in the assembly. A vane is attached to the suction side of each of the blade tips with the vane having an aft facing step which radially overlaps the casing forward facing step to promote further reduction of clearance backflow. Variations on the invention include the option of an additional inlet bellmouth piece that further restricts the clearance flow and wedges integral to the casing step to improved flow stability.03-18-2010
20130017057BLADE OUTER AIR SEAL ASSEMBLYAANM Lagueux; KenAACI BerlinAAST CTAACO USAAGP Lagueux; Ken Berlin CT US - An example blade outer air seal assembly includes a blade outer air seal that is biased toward a second part. The blade outer air seal and the second part move together radially during operation. Radial inward movement of the blade outer air seal is limited exclusively by the second part during operation.01-17-2013
20130017059HOLE FOR ROTATING COMPONENT COOLING SYSTEMAANM Wu; Charles C.AACI GlastonburyAAST CTAACO USAAGP Wu; Charles C. Glastonbury CT USAANM McCusker; Kevin N.AACI West HartfordAAST CTAACO USAAGP McCusker; Kevin N. West Hartford CT USAANM Turner; Mark S.AACI HartfordAAST CTAACO USAAGP Turner; Mark S. Hartford CT US - A rotor for a gas turbine engine comprises an annular body and a plurality of holes. The annular body is configured to rotate in a circumferential direction about an axis extending through a center of the annular body. The annular body comprises an outer diameter surface and an inner diameter surface. The plurality of holes extends through the annular body. Each of the holes comprises an elongate profile in the circumferential direction, and a side wall extending between the outer diameter surface and the inner diameter surface. The side wall is slanted in the circumferential direction.01-17-2013
20130017060TIP CLEARANCE CONTROL FOR TURBINE BLADESAANM BOSWELL; John H.AACI DerbyAACO GBAAGP BOSWELL; John H. Derby GBAANM TIBBOTT; IanAACI LichfieldAACO GBAAGP TIBBOTT; Ian Lichfield GB - An arrangement for heating and cooling a turbine casing of a gas turbine engine, the arrangement comprising an inboard duct, adjacent to an inboard surface of the turbine casing, an outboard facing wall of the inboard duct having a plurality of impingement holes opening towards the inboard surface of the casing, through which temperature control fluid can pass from within the inboard duct to impinge upon the inboard surface of the turbine casing.01-17-2013
20130017061TURBOCHARGER VANE01-17-2013
20130017058BLADE OUTER AIR SEAL HAVING PARTIAL COATINGAANM Joe; Christopher R.AACI WethersfieldAAST CTAACO USAAGP Joe; Christopher R. Wethersfield CT USAANM Lutjen; Paul M.AACI KennebunkportAAST MIAACO USAAGP Lutjen; Paul M. Kennebunkport MI USAANM Mongillo, JR.; Dominic J.AACI West HartfordAAST CTAACO USAAGP Mongillo, JR.; Dominic J. West Hartford CT US - A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating.01-17-2013
20110158787WIND TURBINE - Wind turbine systems and methods are provided. The wind turbine system includes a plurality of coaxial, counter-rotating turbine assemblies. First and second shroud assemblies define a generally spherical volume containing the first and second turbine assemblies. The first and second shroud assemblies each include a shroud member that can selectively shield or expose portions of the respective turbine assemblies to the wind by changing the rotational position of the shroud members about the system axis. The turbine assemblies are interconnected to a generator for the production of electrical power.06-30-2011
20110158786METHOD FOR OPERATING STEAM TURBINE WITH TRANSIENT ELEVATED BACK PRESSURE - A method and control system for implementing a transient exhaust pressure protection logic to avoid a turbine exhaust vacuum trip due to a short duration turbine exhaust pressure transient caused by a large reduction in turbine flow coupled with a transient increase in exhaust pressure, which specifically occurs during full load rejections. When full load rejection conditions are sensed by power load unbalance and confirmed by secondary means, normal alarm settings and trip settings for turbine exhaust pressure are blocked for a delay period while transient operating limits are in place.06-30-2011
20130022443FAN MOTOR COOLING - An example fan assembly impeller moves air along a secondary flow path when driven by a motor. The motor also drives a fan rotor to move air along a primary flow path of the fan assembly. Air moving along the primary flow path moves in a first direction. Air moving along the secondary flow path moves in a second direction opposite the first direction. An example fan shroud communicates air used to cool a motor into a primary flow path of a fan assembly. The shroud communicates the air into the primary flow path so that the flow of air is at least partially aligned with air moving through the primary flow path of the fan assembly.01-24-2013
20130022444LOW PRESSURE TURBINE EXHAUST DIFFUSER WITH TURBULATORS - A turbine exhaust diffuser for use adjacent a last stage row of buckets fixed to a turbine rotor includes an annular inner diffuser ring and an annular outer diffuser ring defining a flow path for steam exiting a last stage row of buckets in a first substantially axial direction at a diffuser inlet, and turning substantially ninety degrees to a diffuser outlet. The outer diffuser ring has a curved steam guide surface extending between the diffuser inlet and the diffuser outlet including a first portion extending away from the diffuser inlet and a second portion extending to said diffuser outlet, the second portion shaped to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in a second opposite axial direction. The second portion is also provided with a plurality of turbulators to minimize flow separation along the steam guide surface.01-24-2013
20130022446FLUIDIC DAMPENING FILM SUPPLY METHOD FOR A GUIDING BEARING OF A TURBINE ENGINE SHAFT - A fluidic dampening film supply method for a guiding bearing of a turbine engine shaft, said turbine engine being known to vibrate according to at least one given vibratory mode, said turbine engine being adapted to enter in resonance at a given resonance speed (w01-24-2013
20130022447CENTRIFUGAL PUMP FOR DE-WATERING - A method of de-watering during intermittent dry running periods with a self-priming centrifugal pump is presented. Centrifugal pumps, as opposed to diaphragm pumps, are advantageous because they are less expensive and can provide greater capacity. The shaft seals are sensitive, however, to frictional heating when water flow is interrupted. In some situations, this fractional heating may desiccate self-priming. The inventive concept provides a continuous stream of pressurized water moving through the pump to cool the seal and sustain priming capability without substantially impairing the ability of the pump to resume wet operation.01-24-2013
20130170943HYBRID BEARING TURBOMACHINE - A turbomachine includes a housing and a rotatable shaft, where at least a portion of the rotatable shaft is located in the housing. The turbomachine also includes a magnetic thrust bearing that axially positions the rotatable shaft and a radial bearing that centers the rotatable shaft. The turbomachine includes a flexure including a first portion secured to the housing and a second portion axially moveable relative to the first portion. The second portion of the flexure is connected to the radial bearing, and the second portion moves axially to eliminate thrust loads on the radial bearing and allow the magnetic thrust bearing to carry axial loads.07-04-2013
20130170948TURBOCHARGER BYPASS SYSTEM - A turbocharger bypass system and method for minimizing the occurrence of oil seepage from the bearing housing into the compressor housing as a result of a pressure differential across the bearing housing and the compressor housing. A bypass system with a pressure dependent check valve is connected to the inlet air passage of a turbocharged engine. When the pressure in the inlet air passage drops to below atmosphere or a predetermined level of depression, the check valve opens to allow a flow of atmospheric air into the inlet air passage, thus minimizing or eliminating the pressure differential generated as a result of a vacuum in the inlet air passage during motoring conditions, or when an exhaust valve downstream of the turbocharger is closed, such as during engine braking. The bypass system is applicable to both single stage and dual stage turbocharged internal combustion engines.07-04-2013
20120243970ARRANGEMENT AND METHOD FOR CLOSED FLOW COOLING OF A GAS TURBINE ENGINE COMPONENT - An arrangement for cooling a gas turbine engine component includes a gas turbine engine component provided with at least one cooling channel through which a cooling medium is intended to flow during operation of the arrangement, a feeding system configured to supply cooling medium to the cooling channel, a cooling channel inlet, and a cooling channel outlet. The feeding system is arranged in flow communication with both the inlet and the outlet of the cooling channel such as to form a closed flow system. A gas turbine engine provided with such a component and a method for cooling such a component are also provided.09-27-2012
20080232949Turbomachine Having an Axially Displaceable Rotor - The invention relates to a compressor, which is axially flowed through, for a gas turbine having an axially displaceable rotor. An annular flow channel, which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface and an inner delimiting surface on the rotor. A stationary ring comprised of guide profiles and at least one ring comprised of moving profiles attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade is located opposite an axial section of one of both delimiting surfaces while forming a radial gap. The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor. To this end, the invention provides that the size of the radial gap between the end of each moving or guide blade and the opposite axial section of the delimiting surface is constant at least over the path of displacement of the rotor, and the radial gap extends parallel to the rotation axis of the rotor.09-25-2008
20080226439Blade variation in dependence of the degree of throttling on fluid-flow machine - A method for the variation of at least one blade row of a fluid-flow machine, in which, in dependence of the actual operating point, in addition to an aerodynamic speed, at least one further quantity pertinent to the position of the operating point in the family of characteristics of the fluid-flow machine is employed for control.09-18-2008
20130170950VARIABLE SHAPE INLET SECTION FOR A NACELLE ASSEMBLY OF A GAS TURBINE ENGINE - A method of improving the aerodynamic performance of an inlet section of a nacelle assembly of a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, (a) sensing an operability condition, (b) adjusting a leading edge of the inlet section in response to the step (a), and (c) adjusting a thickness of the inlet section in response to the step (a).07-04-2013
20130170951LEAD ANGLE VALUE SETTING METHOD, MOTOR DRIVING CONTROL CIRCUIT, AND BRUSHLESS MOTOR - A method for setting a lead-angle value of a motor drive control circuit is disclosed. The motor drive control circuit energizes and drives the windings of a motor with an energizing timing based on a stored lead-angle value. The method includes the steps of: rotating a rotor at a given rpm (step S07-04-2013
20130170945FURNACE AIR HANDLER BLOWER WITH ENLARGED BACKWARD CURVED IMPELLER AND ASSOCIATED METHOD OF USE - A blower having a blower housing having a cutoff and a top portion with an air outlet opening, a fan within the blower housing, the fan being adapted for rotation about a fan axis and having an outer diameter with a distance between the outer diameter of the fan and the top portion of the air outlet opening extending along a vertical line between the fan axis and the air outlet opening being less than seventy-five percent of the distance between the outer diameter of the fan and the cutoff of the blower housing extending along a line between the fan axis and the cutoff, and a motor having a stator and a rotor, the rotor being rotatably coupled to the stator for rotation about the fan axis, the rotor and fan being coupled such that the fan rotates with the rotor.07-04-2013
20130170946RISERLESS TRANSFER PUMP AND MIXER/PRE-MELTER FOR MOLTEN METAL APPLICATIONS - A pump for processing molten metal having an enlarged tubular body which houses a centrifugal pump at its bottom end. The bottom end has a concave curved shape whose shape is a function of the particular type of vortex to be created for the application at hand. This curved portion of the body receives the ejected molten metal from the impeller and forms an uplifting axial vortex within the tubular section of the body. The pump is designed to cooperate synergistically with said body such that the uplifting axial vortex to climb up the inner wall of the body up to and out of an outlet formed in the upper end of the body. A radial vane impeller is formed in the back plate of the impeller. When the impeller is rotated, solid particles introduced into the body are accelerated radially by the back plate impeller into the vortex.07-04-2013
20130170944TURBINE ASSEMBLY AND METHOD FOR REDUCING FLUID FLOW BETWEEN TURBINE COMPONENTS - According to one aspect of the invention, a turbine assembly includes a first bucket with a first slashface and a second bucket including a recess formed in a second slashface of the second bucket, wherein the second slashface is adjacent to the first slashface when the first bucket is positioned adjacent to the second bucket. The turbine assembly also includes a pin configured to be placed in the recess, wherein the pin is magnetically urged toward the first slashface to reduce fluid flow between the first and second buckets.07-04-2013
20110274533FLUID TURBINE WITH MOVEABLE FLUID CONTROL MEMBER - A shrouded fluid turbine includes an impeller for generating power from a fluid stream and a shroud surrounding the impeller. The impeller and/or the shroud have a moveable member for controlling power generation in the fluid turbine. The shroud has a plurality of mixing lobes on a trailing edge thereof, the trailing edge having a circular crenellated shape. The power generation is controlled by reducing loads and/or controlling impeller speed. Various moveable components are described for the stator vanes and the rotor blades.11-10-2011
20130177387INTERSEGMENT SPRING "T" SEAL - A spring seal includes a split body portion with a first leg and a second leg that extend away from a plane and a projection portion which extends from the split body portion within the plane.07-11-2013
20130177388STARTUP METHOD FOR LARGE STEAM TURBINES - A method of controlling a steam turbine, having a controller controlling at least the position of a steam inlet valve located in a steam conduit between a steam generator and the turbine to control mass flow into the turbine, includes selecting, before beginning startup, a predefined set of startup sequences of setpoints based on a turbine status at the beginning of startup and/or a startup mode chosen by the operator, the set of startup sequences of setpoints includes parameters controlled and not controlled by the controller; using the controller to control the parameters controlled by the controller so as to progress the turbine from setpoint to setpoint in accordance with predefined set of startup sequences until reaching a release point; and at the release point, delaying moving to the next setpoint until actual setpoint values agree with predefined release point setpoint values for parameters not controlled by the controller.07-11-2013
20130177393Hybrid Compressor System and Methods - An apparatus (07-11-2013
20130177383DEVICE AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A device for sealing a gas path in a turbine includes a first shroud segment and a slot in a surface of the first shroud segment. A barrier extends inside the slot, and a bypass channel in the slot provides fluid communication between the barrier and the slot to the gas path in the turbine. A method for sealing a gas path in a turbine includes placing a barrier between a first slot in a first shroud segment and a second slot in a second shroud segment and flowing a fluid between the barrier and the first slot to the gas path in the turbine, wherein the fluid flows through a first bypass channel in the first slot.07-11-2013
20130177384TURBINE NOZZLE COMPARTMENTALIZED COOLING SYSTEM - The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.07-11-2013
20130177385GAS TURBINE ENGINE FORWARD BEARING COMPARTMENT ARCHITECTURE - A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.07-11-2013
20130177386TURBINE ASSEMBLY AND METHOD FOR CONTROLLING A TEMPERATURE OF AN ASSEMBLY - According to one aspect of the invention, a turbine assembly includes a first component, a second component circumferentially adjacent to the first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to abut a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first side surface, a second slot formed longitudinally in the second side surface, wherein the first and second slots are configured to receive a sealing member, and a first groove formed in a hot side surface of the first slot, the first groove extending axially from a leading edge to a trailing edge of the first component.07-11-2013
20130177389TURBOMACHINE COMPONENT TEMPERATURE CONTROL - Apparatus and methods for expanding a process fluid are disclosed. The apparatus includes a casing having an inlet and an outlet, and a component carrier disposed in the casing. The component carrier and the casing defining a cavity therebetween, and the component carrier at least partially defines a process flowpath fluidly communicating with the inlet and the outlet of the casing. The apparatus also includes a rotor disposed at least partially in the component carrier, with the rotor at least partially defining a first expansion stage intersecting the process flowpath. The apparatus also includes a bleed port extending from the process flowpath at a first point of the process flowpath to the cavity, to provide a thermal buffer fluid to the cavity.07-11-2013
20130177390TURBINE ENGINE SHAFT - A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet.07-11-2013
20130177391ELECTROSTATIC CONTROL OF AIR FLOW TO THE INLET OPENING OF AN AXIAL FAN - A method of modifying the airflow to the inlet of an axial fan comprises operating an axial fan to move air longitudinally through an air inlet opening of the axial fan, and, during operation of the axial fan, applying an electrical potential between an emitter and a collector to cause ionic air movement radially outwardly away from a central axis of the axial fan, wherein the radially outward air movement is caused upstream of the axial fan before the air reaches the air inlet opening.07-11-2013
20130177392Aircraft Airflow Modulation System and Method - The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.07-11-2013
20130170947ROTOR BEHAVIOUR DETERMINATION - A method of resolving vibration behaviour of a rotor assembly having a plurality of rotor blades. The method including generating a computational model of the rotor by discretization of the rotor geometry and assigning parameter values representative of a plurality of physical characteristics of the rotor. An artificial parameter feature is applied to each rotor blade such that the parameter values for the artificial parameter feature substantially depart from the physical characteristics of the rotor. A vibration response is calculated for the rotor or blade thereof for the applied artificial parameter features and compared to a predetermined vibration response so as to determine a value of the artificial parameter feature which results in a calculated vibration response that substantially matches the predetermined vibration response.07-04-2013
20130170949WIND TURBINES AND METHODS FOR CAPTURING WIND ENERGY - Wind turbines and energy capturing assemblies for capturing fluid energy are provided. The wind turbines includes a plurality of helical air foil blades mounted for rotation about an axis, and a cylindrical airfoil mounted along the axis and shaped to direct a flow of fluid, such as, air or water, toward the plurality of helical airfoil blades. Incorporating photovoltaic devices within the turbines can enhance the energy capturing capacity of some turbines. The energy capturing assemblies include a plurality of airfoil blades mounted for rotation about an axis, a structure having an outer surface shaped to direct a flow of fluid toward the plurality of airfoil blades; and an electrical generator operatively connected to the plurality of airfoil blades. The structure may be a building, a residence, a tower, a tank, or a vessel. Methods and devices for capturing fluid energy are also included.07-04-2013
20080219831Pipe flow-driven power generator - A pipe flow-driven power generator includes a vane wheel pivotally mounted in a water chamber in a water pipe and rotatable by a flow of water running through the water pipe, a dynamo pivotally mounted on the outside of the water chamber and coupled to the vane wheel through a transmission gear set for generating electricity upon running of water through the water pipe, and a storage battery for storing electricity generated by the dynamo.09-11-2008
20120251291STATOR-ROTOR ASSEMBLIES WITH FEATURES FOR ENHANCED CONTAINMENT OF GAS FLOW, AND RELATED PROCESSES - A stator-rotor assembly is described, including at least one interface region and a gap between a surface of the stator and a surface of the rotor. The stator is a nozzle or vane that includes circumferential endwalls. Each endwall includes at least one leading edge and one trailing edge, relative to a hot gas flow path. A trailing edge of at least one of the endwalls includes a pattern of cavities that are capable of impeding the entry of hot gas into a wheelspace region that adjoins the gap between the stator and the rotor. The cavities can also be formed on various sections of the rotor. The stator-rotor assembly can be incorporated into various turbomachines, such as gas turbine engines. Related processes are also described.10-04-2012
20120251290ASPIRATING FACE SEAL, AND A RELATED METHOD THEREOF - An aspirating face seal includes a primary seal, a secondary seal, and a biasing device. The primary seal includes a first seal component and a second seal component. The first seal component is configured to be coupled to a rotor and rotatable with the rotor. The secondary seal includes a plurality of flexible elements and configured to be disposed between the second seal component and a stator housing. A biasing device is coupled to the second seal component such that the second seal component is biased along an axial direction away from the first seal component during a non-operating condition.10-04-2012
20110268554SYSTEMS, METHODS, AND APPARATUS FOR CONTROLLING TURBINE GUIDE VANE POSITIONS - Certain embodiments of the invention may include systems, methods, and apparatus for controlling turbine guide vane positions. According to an example embodiment of the invention, a method is provided for controlling at least one turbine guide vane. The method includes receiving a reference signal associated with the at least one turbine guide vane, measuring an actuator position and an angular position associated with the at least one turbine guide vane, generating a deadband signal based at least in part on the angular position, and manipulating the at least one turbine guide vane based at least in part on the deadband signal and the reference signal.11-03-2011
20130094937GAS TURBINE ENGINE OIL BUFFERING - A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment.04-18-2013
20130094938TURBOMACHINE - A turbomachine comprising a housing defining a bearing cavity and a turbine chamber separated by a first wall, a heat shield disposed between the first wall and the turbine wheel, a heat shield cavity defined between the first wall and the heat shield. The shaft extends through a passage defined in part by a first aperture in the wall and a second aperture in the heat shield. A first seal is provided between the shaft and the first aperture. The housing defines a first gas channel communicating with the heat shield cavity for connection to a pressure source for raising pressure within the heat shield cavity. A second channel is provided between the heat shield cavity and the passage, the second channel opening to the passage on the opposite side of the first seal to the bearing assembly. A second seal is provided between the shaft and the second aperture.04-18-2013
20130115043ROTATIONAL POSITIONING SYSTEM IN A WIND TURBINE - A rotational positioning system in a wind turbine is provided that comprises a driven part (101), a plurality of positioning drives (102) coupled to the driven part (101), a plurality of sensors (111) each arranged to sense a load parameter indicative of the load of the respective positioning drive (102), and a load controller (112, 113, 114, 115) connected to the plurality of sensors (111). The load controller (112, 113, 114, 115) is arranged to determine a load of a respective positioning drive (102) based on the sensed load parameter, to compare said load with an expected load value, and to output a signal (115) indicative of a failure of the respective positioning drive (102) in response to the load being smaller than the expected load value.05-09-2013
20130115042DYNAMIC THRUST BALANCING FOR CENTRIFUGAL COMPRESSORS - Systems and methods for dynamically balancing axial loads in centrifugal compressors to reduce residual axial loads on the bearings used therein are described. A sensor or probe detects a parameter associated with the axial load acting on the bearing. Based on the detected parameter, the pressure in a balance chamber is controlled to adjust the compensating axial force generated by a balance drum.05-09-2013
20130115044EXHAUST GAS DIFFUSER FOR A GAS TURBINE AND A METHOD FOR OPERATING A GAS TURBINE THAT COMPRISES SUCH AN EXHAUST GAS DIFFUSER - An exhaust gas diffuser for a gas turbine is provided. The diffuser has an annular outer wall for guiding the diffuser flow and in which an annular guiding element is arranged concentrically to the outer wall and influences the diffuser flow. The guiding element has a surface which is radially directed inwards and has a circumferential contour that is convex in the longitudinal section to form a displacement element. The guiding element is axially displaceable between two positions so that the guiding element, when in a first position, allows a flow between the guiding element and outer wall and, when in a second position, largely prohibits a flow between the guiding element and outer wall. The aerodynamic effect of the diffuser is improved and simultaneously optimal adapted for a plurality of operational gas turbine states.05-09-2013
20130101388COMPRESSION DEVICE AND METHOD FOR COOLING A COMPRESSION MEDIUM - The invention concerns a compression device fitted with a drive unit; 04-25-2013
20130101387SYSTEM AND METHOD FOR INTEGRATING SECTIONS OF A TURBINE - A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average.04-25-2013
20130101389HEAT-DISSIPATING SYSTEM AND CONTROL METHOD THEREOF - The invention provides a heat-dissipating system and a control method thereof. The heat-dissipating system has a plurality of fans and is configured for adjusting rotation-speeds of the fans. The control method includes following steps: obtaining a plurality of rotation-speed values of the fans; computing out a rotation-speed reference value according to the rotation-speed values; when the rotation-speed reference value is greater than a first threshold value, decreasing the rotation-speeds of the fans through a corresponding fan control signal; when the rotation-speed reference value is less than a second threshold value, increasing the rotation-speeds of the fans through the corresponding fan control signal.04-25-2013
20130101386DUAL-FLOW STEAM TURBINE WITH STEAM COOLING - A dual flow steam turbine includes coolant passageways which extract coolant steam from the main steam flow paths at locations downstream from the inlet. The coolant passageways conduct the coolant steam through portions of the dual flow steam turbine which are subjected to a high temperature flow. In some cases, the passageways conduct the coolant steam through first stage nozzle boxes and an inlet assembly of the dual flow steam turbine. In some cases, the inlet assembly of the steam turbine includes an annular diaphragm, and a coolant passageway passes through the annular diaphragm to help cool the annular diaphragm.04-25-2013
20130101390METHOD FOR CONTROLLING A COMPRESSOR ELEMENT OF A SCREW COMPRESSOR - Method for controlling a compressor element of a screw compressor, where the compressor element has a housing with two meshing helical rotors supported in the housing in the axial direction using at least one axial bearing. The method has a process A and/or a process B, where process A has a first step of switching on a first magnet during start-up of the compressor element, such that the magnet exerts a force on the rotor that is directed from an outlet side to an inlet side, and of switching off this first magnet during nominal operation of the compressor element; and where process B has a first step of keeping a second magnet switched off during start-up of the compressor element, and switching on this second magnet during nominal operation of the compressor element, such that this second magnet exerts a force that is directed from the inlet side to the outlet side.04-25-2013
20130101385VARIABLE VANE ASSEMBLY FOR A GAS TURBINE ENGINE HAVING AN INCREMENTALLY ROTATABLE BUSHING - A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions.04-25-2013
20130121806EXHAUST DIFFUSER FOR A GAS TURBINE, AND METHOD THEREOF - An exhaust diffuser assembly is provided, particularly for a stationary gas turbine. The exhaust diffuser assembly includes a longitudinal axis, a diffuser inlet for receiving a turbine mainflow gas, a diffuser outlet, and a diverging diffuser wall having an adjustable geometry and forming a conduit for flow of the gas therethrough from the diffuser inlet to the diffuser outlet. The diffuser wall has a divergence angle ‘α’ with respect to the longitudinal axis. The diffuser assembly also has a diffuser geometry control device for controlling a recovery of pressure from the gas between the diffuser inlet and the diffuser outlet by adjusting the divergence angle ‘α’ of the diffuser wall to cause a resultant flow field of the gas that is attached to the diffuser wall.05-16-2013
20130129476ROTARY MACHINE FOR COMPRESSION AND DECOMPRESSION - A rotary machine for compression and decompression, comprising a disc-shaped rotor having a first rotation axis at right angles to the plane of the rotor and situated in a plane of orientation and a disc-shaped swing element having a second rotation axis. In the orientation plane, the second rotation axis makes an angle with the first rotation axis. Furthermore, a spherical housing is present surrounding the rotor and the swing element and in combination forming four (de-)compression chambers. A connecting body positions the rotor and the swing element in the housing. The rotary machine furthermore comprises a power drive and a mechanical connection delivering power to or taking off power from the rotary machine. In addition, the rotary machine is suitable for the seamless integration of generator components for generating or using electricity.05-23-2013
20130129475Method for operating a pump - A method for operating a switchable pump, which is situated in a motor vehicle and configured to provide a setpoint pressure for a medium, the pump being activated in trailing-throttle operation of the motor vehicle.05-23-2013
20130129474WIND POWER PLANT FOUNDATION AND WIND POWER PLANT - There is provided a wind power installation foundation having a reinforcement comprising a plurality of steel bars and radial steel bars and a lower pylon segment having a plurality of holes in the wall of the pylon segment for receiving the bars or radial bars. In addition there is provided a concrete body which covers the reinforcement and the lower portion of the pylon segment. The foundation has a plurality of holders for holding the bars or radial bars of the reinforcement. The holder has an upper bracket for fixing to the pylon segment and a lower foot for receiving the bars or radial bars of the reinforcement. The length of the holder is adapted to be variable.05-23-2013
20130129477METHOD FOR OPERATING A COMPRESSOR - A method for operating a compressor including providing suction pressure measurement, final pressure measurement, throughput measurement is provided. Using a first control characteristic map a target value for a pump surge limiter is determined from one or two of the measurements, and the pump surge limiter compares the target value to the throughput measurement, wherein the pump surge limiter opens a bypass valve when the measured value falls below or exceeds the target value, such that the final pressure is lowered or the flow through the compressor is increased. In the event of failure of a measurement, a further measurement of another physical variable of the compression process, together with a measured variable that did not fail or a modification of the measured variable, is an input variable for a substitute control characteristic map, form which a substitute target value is determined.05-23-2013
20130129473AVOIDANCE OF TORSIONAL EXCITATIONS IN CONVERTER-CONTROLLED COMPRESSOR RUNS - A machine has a rotor and includes a converter-controlled drive and a working machine, wherein the drive and the working machine are connected such that a torque is transmitted. A frequency converter is electrically connected to the drive. The frequency converter is embodied such that in a Campbell diagram intersection points are based on the natural torsional frequency of the rotor and V-shaped symmetrical straight lines of the inter-harmonic exciter frequency for output frequencies. The output frequencies are grouped into a plurality of concentration ranges based upon a rotational speed of the machine, wherein each concentration range comprises output frequencies which are close to one another and which respectively have a common output point on the abscissa of the Campbell diagram. Each concentration range defines a blocking range, wherein the machine has an operating rotational speed range which lies outside the blocking ranges.05-23-2013
20130129471Method and System for Reducing Seal Gas Consumption and Settle-Out Pressure Reduction in High-Pressure Compression Systems - A compressor is disclosed having a shaft seal assembly and system that allows a high-pressure compressor to settle-out at a lower pressure level during shutdown. The seal assembly may be disposed about a portion of the shaft and define a blow-down seal chamber, the seal assembly including one or more gas seals in fluid communication with the blow-down seal chamber. A blow-down line is communicably coupled to the blow-down seal chamber to reference the blow-down seal chamber to a low pressure reference, such as a separate centrifugal compressor, or the like. Referencing the blow-down seal chamber to the low pressure reference reduces the required sealing pressure of the one or more gas seals. A valve may be disposed in the blow-down line and configured to regulate a flow of process gas leakage through the blow-down line.05-23-2013
20130129470Systems and Methods for Adjusting Clearances in Turbines - Embodiments of the invention can provide systems and methods for adjusting clearances in a turbine. According to one embodiment of the invention, there is disclosed a turbine system. The system may include one or more turbine blades; a turbine casing encompassing the one or more turbine blades; and a thermoelectric element disposed at least partially about the turbine casing, wherein the thermoelectric element expands or contracts the turbine casing by heating or cooling at least a portion of the turbine casing, thereby adjusting a clearance between the one or more turbine blades and the turbine casing.05-23-2013
20130142616Pumping Device - A pump is disclosed, with a casing comprising a substantially circular body having at least two radial inlets, at least one peripheral outlet and a transversal aperture. The casing further comprises a substantially circular impeller mounted within the body for rotation about the aperture. The impeller has a substantially uninterrupted sinusoidal profile. A pumping system and a method of pumping are also disclosed, which use the pump configuration.06-06-2013
20130142617METHOD AND EQUIPMENT FOR DETECTING ROTATING STALL AND COMPRESSOR - A method for detecting rotating stall in a compressor is disclosed herein. The method comprises measuring radial vibration of the rotor relative to the stator and generating a vibration measurement signal, calculating a frequency spectrum of the vibration measurement signal, identifying a plurality of frequency bandwidths of the frequency spectrum, neglecting one first frequency bandwidth of the plurality of frequency bandwidths if the rotation frequency of the rotor falls within the first frequency bandwidth, neglecting at least one second frequency bandwidth of the plurality of frequency bandwidths if the rotation frequency of the rotor falls below the second frequency bandwidth, determining the maximum magnitude of the spectrum in each of the non-neglected frequency bandwidths, and comparing each determined maximum magnitude and a predetermined value. Rotating stall is considered occurring if at least one of the comparisons shows that the corresponding determined maximum magnitude is greater than the predetermined value.06-06-2013
20130142615Blower Housing - A blower housing has a discharge direction, an axis of rotation, a polar axis that intersects the axis of rotation and is substantially perpendicular to the discharge direction, an angular sweep of increasing fluid flow area, and an axial contraction located at an angularly greater value than the angular sweep.06-06-2013
20130156542ENERGY-ABSORBING FAN CASE FOR A GAS TURBINE ENGINE - A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis and a plurality of helical ribs adjacent to the fan blade containment section.06-20-2013
20130156540STEAM SEAL HEADER, METHOD OF USING A STEAM SEAL HEADER AND STEAM TURBINE SYSTEM INCORPORATING A STEAM SEAL HEADER - A steam turbine system for use in a power plant includes a steam seal header that collects steam from seals of a high pressure steam turbine and an intermediate pressure steam turbine. The collected steam is provided to seals of a low pressure steam turbine to ensure the seals provide an effective seal for the low pressure steam turbine. Steam from the low pressure steam turbine is also collected in the steam seal header and it is mixed with the steam collected from the high and intermediate pressure seals. The mixed steam is then provided to drive the low pressure steam turbine.06-20-2013
20130156543SINGLE SYSTEM WITH INTEGRATED COMPRESSOR AND PUMP AND METHOD - Method and system for compressing a fluid in a gas phase and for pumping the fluid in a dense phase. The system includes a compressor part having an impeller; a compressor part inlet that receives the fluid in the gas phase; a compressor part outlet that provides the fluid in the gas phase; a temperature changing device that changes a phase of the fluid; a pump part having an impeller; a pump part inlet that receives the fluid in the dense phase from the compressor part outlet; a pump part outlet that outputs the fluid in the dense phase from the system; a single bull gear configured to rotate around an axial axis with a predetermined speed; plural pinions contacting the single gear bull and configured to rotate with predetermined speeds, and a pump shaft configured to rotate the at least one impeller of the pump part.06-20-2013
20130156541ACTIVE TURBINE TIP CLEARANCE CONTROL SYSTEM - An active tip clearance control (ATCC) system of a gas turbine engine includes an ejector to selectively drive an air flow passing through the ATCC system. A high pressure air flow as a motive flow of the ejector is controlled by a valve according to engine operation requirements.06-20-2013
20110211940SYSTEM AND METHOD FOR INSPECTION OF STATOR VANES - Embodiments of the invention include an inspection system to inspect internal components of a compressor of a gas turbine engine. The inspection system includes an image recording assembly having one or more image recording devices, light sources, storage devices, and power supplies. The image recording assembly may be inserted into a compressor without removal of the compressor housing or disassembly of the compressor. The image recording assembly may be removably coupled to a rotary component of the compressor, e.g., a rotor blade, and used to record images of stationary components, e.g., stator vanes, of the compressor. The images may be inspected to identify wear and/or defects in the stationary components, e.g., stator vanes09-01-2011
20110229301ACTIVE TIP CLEARANCE CONTROL FOR SHROUDED GAS TURBINE BLADES AND RELATED METHOD - A turbine bucket tip clearance control system includes a rotor assembly having a rotor supporting a plurality of axially spaced wheels, each wheel mounting an annular row of buckets, the annular row of buckets on at least one of the plurality of axially-spaced wheels having a radially outer tip shroud provided with at least one seal tooth. A stator assembly includes a radially inwardly facing, axially-stepped surface, formed with radially inner and outer seal surfaces connected by a shoulder. The stator assembly and rotor assembly are moveable axially relative to each other, enabling selective positioning of the at least one seal tooth radially opposite one of the radially inner and outer seal surfaces to thereby selectively alter a clearance gap between the at least one seal tooth and the radially inward facing axially-stepped surface.09-22-2011
20130136576WIND TURBINE AIR FLOW GUIDE DEVICE - The invention extends to an air flow device for wind turbines which includes a number of flow paths which assist in the movement of air through the air flow device which assists in increasing the efficiency and power output of the wind turbine. The air flow device includes flow passages alongside a central channel which houses the wind turbine.05-30-2013
20110236180GAS DRIVEN ROTATION MOTOR, A TOOL PROVIDED WITH A GAS DRIVEN ROTATION MOTOR AND A METHOD FOR REGULATING SPEED OF A GAS DRIVEN ROTATION MOTOR - A gas driven motor includes a housing, a gas driven rotating member including a rotor and a rotor shaft carrying the rotor and journalled in a first bearing and a second bearing supported in the housing, and a speed governor for controlling a pressure gas inlet flow in response to the rotation speed of the rotating member. The first bearing includes a set of rolling elements, an outer race arranged in the housing and an inner race arranged on a shaft portion of the rotating member, the set of rolling elements being in contact with the races on which the rolling elements roll. The motor further includes a coupling device arranged to couple the speed governor to the rolling elements of the first bearing, thereby transferring the rotary motion from the rolling elements to the speed governor.09-29-2011
20130149101REDUCED LEAKAGE BALANCE PISTON SEAL - Balance piston assembly, apparatus, and methods are provided. The assembly includes a balance piston coupled to a rotatable shaft and configured to rotate therewith, the balance piston including a first shelf and a second shelf, the first and second shelves being axially-overlapping and radially-offset. The assembly also includes a seal including a first sealing surface configured to seal with the first shelf and a second sealing surface configured to seal with the second shelf.06-13-2013
20130149102TURNING GEAR FOR GAS TURBINE ARRANGEMENTS - An apparatus for driving a load is provided. The apparatus comprises a multiple-shaft gas turbine comprising a high pressure compressor and a high pressure turbine drivingly connected to one another by a first gas turbine shaft and a low pressure compressor and a power turbine drivingly connected to one another by a second gas turbine shaft extending coaxial with the first gas turbine shaft, the high pressure compressor and the high pressure turbine. The apparatus also comprises a load coupling drivingly connecting the power turbine to the load and a dual-speed turning gear with an output shaft drivingly engageable to and disengageable from the load, the dual-speed turning gear comprising a low speed turning motor and a high speed turning motor, wherein the low speed turning motor and the high speed turning motor are configured to selectively drive the load.06-13-2013
20130149098FAN BLADE TIP CLEARANCE CONTROL VIA Z-BANDS - An engine has a blade, a casing surrounding the blade, an seal ring, and a passive system for connecting the seal ring to the casing and for accommodating thermal expansion of the seal ring relative to the casing so as to maintain blade tip clearance control. The passive system may include at least one, metallic Z-band extending between the casing and the seal ring.06-13-2013
20130149099GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE TO REDUCE FAN INSTABILITY - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area to reduce a fan instability.06-13-2013
20130149100GAS TURBINE ENGINE - A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.06-13-2013
20120275899AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS - The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.11-01-2012
20120275898Blade Clearance Control Using High-CTE and Low-CTE Ring Members - An engine has a blade stage and a circumferential array of blade outer air seal segments. A support ring carries the blade outer air seal segments. The support ring has a low-CTE member and a high-CTE member intervening between the blade outer air seal segments and the low-CTE member.11-01-2012
20120087775Turbine Bucket Shroud Tail - The present application provides an axial flow turbine. The axial flow turbine may include a stator casing and a turbine bucket positioned about the stator casing. A tip shroud may be positioned on the turbine bucket. A shroud tail may be attached to the tip shroud at a downstream end of the tip shroud.04-12-2012
20100316484MECHANICAL JOINT FOR A GAS TURBINE ENGINE - A mechanical joint for a gas turbine engine includes:(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together.12-16-2010
20130195613APPARATUS AND METHOD FOR CONTROLLING A COMPRESSOR - An apparatus and method for controlling a compressor are provided. An input voltage of a commercial power source, a motor voltage of a compressor motor, and a motor current of the compressor motor are detected, based on which voltage values of a capacitor and voltage values of a triac may be calculated. Thus, an additional operational amplifier or a sensor to measure a capacitor voltage is not required, reducing costs.08-01-2013
20130156544Compressor Surge Detection - A compressor (06-20-2013
20120282079REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR - In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.11-08-2012
20130183137CENTRIFUGAL PUMP WITH SECONDARY IMPELLER AND DUAL OUTLETS - A fluid pump includes a primary impeller and a secondary impeller disposed on a common drive shaft within a pump housing. The pump housing including a respective diffuser or volute therein for each of the primary impeller and the secondary impeller. A fluid passage is formed within the housing connecting a discharge of the primary impeller to an intake of the secondary impeller. Each of the primary and secondary impellers has a respective outlet port.07-18-2013
20130121803COMPRESSOR HAVING PURGE CIRCUIT AND METHOD OF PURGING - A compressor having a purge circuit. In one embodiment, the compressor includes: a rotor having a plurality of stages, each of the plurality of stages including a set of radially extending rotor wheels; a working fluid supply path for providing working fluid to each of the plurality of stages for compression by each set of radially extending rotor wheels; a purge circuit for diverting a first portion of the working fluid from an upstream portion of the working fluid supply path to at least one downstream stage of the plurality of stages; and a substantially axial bypass path bypassing the at least one downstream stage, the substantially axial bypass path for diverting a second portion of the working fluid around the at least one downstream stage.05-16-2013
20130121805HYDRAULIC POWER SPLIT ENGINE WITH ENHANCED TORQUE ASSIST - A power split transmission includes a rotatable input shaft, a rotatable output shaft, and a planetary gear assembly connected between the input shaft and the output shaft. The transmission also includes a first hydraulic unit operable as a pump or a motor, the first hydraulic unit being coupled to the output shaft via the planetary gear assembly; a second hydraulic unit operable as a pump or a motor, the second hydraulic unit being coupled to the output shaft independently of the planetary gear assembly; and a braking mechanism coupled to the input shaft that is selectively engageable to retard rotation of the input shaft in at least one direction. The braking mechanism enables the power split transmission to use both the first hydraulic unit and the second hydraulic unit to provide enhanced torque at the output shaft without damaging a prime mover coupled to the input shaft.05-16-2013
20130121804Fluid Movement System and Method for Determining Impeller Blade Angles for Use Therewith - A fluid movement system that includes an impeller having a blade with a leading edge blade tip angle determined as a function of an increase in mass flow rate due to reinjection of flow from a flow stability device located proximate to the leading edge tip of the blade. In an exemplary method, the leading edge blade tip angle can be determined based on selecting a blade incidence level based on a mass flow gain versus flow coefficient curve. Blade leading edge tip angles determined in accordance with a method of the present invention are typically greater than blade leading edge tip angles determined using traditional methods. The greater blade leading edge tip angles can lead to more robust blades designs.05-16-2013
20110305555Isentropic method and apparatus for greatly increasing and extracting the power from wind and moving air - This invention employs the isentropic acceleration of a basic air flow, supplied by the wind, through a converging/diverging De Laval Nozzle, to thereby enormously increase the air flow speed and power at the nozzle throat section and to simultaneously lower the pressure there to approximately one-half of ambient pressure. This low throat pressure is then used as a ‘vacuum’ source to activate a high speed isentropic flow of air through a power take-off means consisting of a flow rotor which converts the energy of the accelerating linear air flow through it into rotational energy suitable for take-off to do useful external work at very low cost. The invention can also be mounted on a moving vehicle so that the relative air flow past the vehicle supplies the air flow to produce the high power output at very low cost.12-15-2011
20110311348MULTI-INLET VACUUM PUMP - A multi-inlet vacuum pump includes a first pump device (12-22-2011
20110311347Flash Steam Turbine - A flash steam powered flywheel turbine is provided comprising a stator housing with an internal channel for the flash and expansion of steam, the channel having a plurality of jet orifices to direct jets of expanding steam toward a rotary flywheel which is fixed to a rotational shaft within the stator housing. The rotary flywheel. is fitted with a plurality of inlet jet passages generally extending radially inwardly from the peripheral surface of the flywheel and oriented such that the force of expanding and impinging steam causes the flywheel to rotate about its central axis. Each inlet jet passage merges into one or more outlet jet passages oriented generally laterally such that the force of discharging steam causes further rotation in reaction to the discharging steam. The discharging steam is directed against steps or depressions formed on the inner lateral walls of the stator housing to add a jet-propulsion effect. in a clean and renewable manner, rotational energy and power will be generated, and the flywheel turbine and rotational shaft can be used to drive an electricity generator or as a prime mover.12-22-2011
20130189073RETROFITTABLE INTERSTAGE ANGLED SEAL - A rotary turbomachine includes a rotor mounting at least one disk having an outer surface and at least one bucket extending radially from said outer surface. A stationary stator component is located adjacent the disk, and a seal plate extends from a portion of the stationary stator component. An angel wing seal extends from the bucket, thereby defining a clearance gap between the seal plate and the angel wing seal. An abradable seal element is disposed on the seal plate, and the abradable seal element and the seal plate are canted at an acute angle relative to a center axis of the rotor extending radially outwardly in a direction toward the angel wing seal.07-25-2013
20130189071OIL PURGE SYSTEM FOR A MID TURBINE FRAME - An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF.07-25-2013
20130189072SPRING SYSTEM TO REDUCE TURBOCHARGER WASTEGATE RATTLE NOISE - A turbocharger for a motor vehicle. The turbocharger includes a compressor mechanically coupled to a turbine. The wastegate of the turbine includes a valve head matched to a valve seat. The valve head is retained at one end of an actuator arm. A resilient spacer is arranged between the valve head and the actuator arm. The resilient spacer is configured to forcibly separate the valve head from the actuator arm when the valve head is unseated.07-25-2013
20130189074MULTIPLE-CAPACITY CENTRIFUGAL COMPRESSOR AND CONTROL METHOD THEREOF - The present disclosure relates to a multiple-capacity centrifugal compressor, which includes a plurality of capacity-control mechanisms. Each of the capacity-control mechanisms includes an inlet guide vane and an outlet diffuser, so that the multiple-capacity centrifugal compressor provides a flexible control strategy. In addition, the present disclosure further provides a method for controlling the multiple-capacity centrifugal compressor that effectively adjusts and controls the capacity-control mechanisms by coarsely adjusting the inlet guide vanes and combined with subsequently adjusting the outlet diffusers.07-25-2013
20130189075APPARATUS AND METHOD FOR CONTROLLING COMPRESSOR - There is disclosed herein a compressor control apparatus, and a compressor control method. According to the present disclosure, the compressor may be operated in an operation mode in which commercial power applied to the compressor does not pass through an alternating current capacitor when the load is in an overload state, thereby preventing the loss of a drive and effectively reducing the copper and core loss of the compressor. Furthermore, according to the present disclosure, the entire power consumption may be reduced due to the loss reduction of a drive, thereby improving the energy efficiency, and reducing the harmonic components for generating the same stroke even when an alternating current (AC) capacitor is provided therein.07-25-2013
20090324382Torque-based sensor and control method for varying gas-liquid fractions of fluids for turbomachines - A torque-based sensor and control method for detecting varying gas-liquid fractions of a fluid entering a turbomachine that operates a fluid of varying liquid phases and compositions and using information about the actual gas-liquid fraction to set a control algorithm so that it can change the torque and therefore the rotation speed of the turbomachine to operate at safer conditions or conditions with higher efficiency or higher power output.12-31-2009
20120020768COOLED CONSTRUCTIONAL ELEMENT FOR A GAS TURBINE - A cooled constructional element for a gas turbine includes a wall having a front and a rear side. The front side is configured to be thermally loaded during operation of the turbine, and the rear side has a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element. A device is configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement.01-26-2012
20120027569ROTATING MACHINE WITH SHAFT SEALING ARRANGEMENT - A rotating machine comprising such as an axial power turbine or a turbocharger has a housing with a bearing cavity and a chamber separated by a first wall. A shaft is rotatable about an axis in the bearing cavity, extends through an opening in the first wall and is mounted for rotation on a bearing assembly provided in the bearing cavity. An oil sealing arrangement including an oil diffuser device is arranged on the shaft for displacing oil away from the shaft as it rotates. This restricts the flow of oil to the opening. The oil diffuser device defines a diffuser passage between the bearing assembly and the first wall, the passage extending outwardly of the axis.02-02-2012
20120027568LOW-PRESSURE STEAM TURBINE AND METHOD FOR OPERATING THEREOF - The disclosure relates to a multi-stage low-pressure steam turbine and a method for operating thereof. The steam turbine includes a last stage in which the leading edge of each vane of the last stage is skewed so as to form a W shaped K-distribution across the span of the vanes. This shape allows for efficient last stage operation at low last stage exit velocities. The disclosure includes a method for operating such a steam turbine at a last stage exit velocity between 125 m/s and 150 m/s.02-02-2012
20120027567MECHANICALLY-COUPLED TURBOMACHINERY CONFIGURATIONS AND COOLING METHODS FOR HERMETICALLY-SEALED HIGH-TEMPERATURE OPERATION - The present invention provides a hermetically sealed turbomachine, such as a motor-driven blower and a turbine driven generator, capable of reliable high-temperature operation, especially for large sized turbomachines. The hot blower, compressor or turbine end of the turbomachine is separated from the cooler electric motor, generator or alternator end of the turbomachine by a compliant mechanical coupling and a thermal choke assembly, providing reliable high-temperature operation. The turbomachine housing is also hermetically sealed, providing control over the process gas within the machine housing, and permitting an internal cooling method within the turbomachine, whereby a small amount of process gas itself is used within the turbomachine for providing cooling of the rotating shafts, the axial fan, radial fan, or turbine impeller, the bearings and the electric motor, generator or alternator disposed within the turbomachine housing. The cooling method can be aided by a heat exchanger operatively communicating with the turbomachine.02-02-2012
20120027566METHOD AND SYSTEM FOR OPERATING A WIND TURBINE - A method, system and computer program product for operating a wind turbine is disclosed. For operating the wind turbine a set of operational data points are sensed via a sensing module. The set of operational data points may include bending stress values. Based on the bending stress values, a load scenario indicator value may be computed. Further, based on the set of operational data points a loading threshold value may be obtained. At least one operating parameter of the wind turbine is changed if the load scenario indicator value exceeds the loading threshold.02-02-2012
20120027565SYSTEM AND METHOD FOR CONTROLLING LEAK STEAM TO STEAM SEAL HEADER FOR IMPROVING STEAM TURBINE PERFORMANCE - A turbine system is provided wherein during self-sealing operating conditions, excess leakoff steam is restricted from being dumped to a steam seal header and is diverted into the working steam flow path, hence increasing net output and efficiency for the turbine system. A related method is also provided.02-02-2012
20120027564Method for the pressure regulation of a barrier fluid and a pumping device for a method of this kind - A method for the pressure regulation of a barrier fluid in a pumping device (02-02-2012
20130195603TURBOMACHINE FAN CLUTCH - An exemplary turbomachine clutch assembly includes a clutch that moves from a first position to a second position in response to rotation of a turbomachine fan at a speed greater than a threshold speed. The clutch permits rotation of the turbomachine fan in a first direction whether the clutch is in the first position or the second position. The clutch limits rotation of the turbomachine fan in an opposite, second direction when the clutch is in the first position.08-01-2013
20130195615DRIVE SHAFT SYSTEM - A drive shaft system (08-01-2013
20130195604TURBOMACHINE GEARED ARCHITECTURE SUPPORT ASSEMBLY - An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion. The less compliant portion includes a stop that limits axial movement of a geared architecture within a turbomachine08-01-2013
20130195605Fan Case Rub System, Components, and Their Manufacture - A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.08-01-2013
20130195606INLET DESIGN FOR A PUMP ASSEMBLY - One embodiment includes an air pump assembly (08-01-2013
20130195607INLET DESIGN FOR A PUMP ASSEMBLY - One embodiment includes an air pump assembly (08-01-2013
20130195608DROPLET CATCHER FOR CENTRIFUGAL COMPRESSOR - A liquid droplet catching device installed in a compressor impeller, the device includes an aperture disposed on a surface of the impeller and configured to receive the liquid droplet, and a channel disposed beneath and in fluid communication with the aperture, wherein in the channel is configured to direct the liquid droplet away from the aperture and out of the compressor impeller.08-01-2013
20130195609MID-SPAN GAS BEARING - A centrifugal compressor includes a rotor assembly with a shaft and a plurality of impellers, bearings located at ends of the shaft and configured to support the rotor assembly, a sealing mechanism disposed between the rotor assembly and the bearings, and a gas bearing disposed between the plurality of impellers for supporting the shaft and receiving a working gas from an impeller downstream from a location of the gas bearing.08-01-2013
20130195610NOISE-REDUCED TURBOMACHINE - Turbomachine with an annular main flow duct (08-01-2013
20130195611Unknown - A method for vibration damping of at least one blade of a turbomachine, wherein initially at least one damping element is arranged on the blade such that it can move in the axial direction, employs a damping element having a larger permeability constant than the blade (μ08-01-2013
20130195612APPARATUS AND METHOD FOR CONTROLLING A COMPRRESSOR - An apparatus and method for controlling a compressor are provided. A motor current flowing in a compressor may be calculated from voltage values of a capacitor without using a sensor, and as a motor current value is calculated by changing voltage values of the capacitor according to voltage values of a drive and performing a definite integral thereon, the motor current value may be resistant to noise, and the compressor may be more stably controlled.08-01-2013
20130195614TURBOCHARGER CONTROL - A method of controlling a variable geometry turbocharger is provided. A predefined desired boost pressure of a turbocharger is obtained from a memory. A predefined desired mass flow rate in an intake manifold of an engine is obtained from the memory. A theoretical amount of power required by the turbocharger to generate the desired boost pressure and the desired mass flow rate is calculated. An actual mass flow rate in the intake manifold is determined. An actual amount of power required by the turbocharger to generate the desired boost pressure and the actual mass flow rate is calculated. At least one adjustable vane of the turbine of the turbocharger is adjusted to allow the theoretical amount of power required of the turbocharger to generally equal the actual amount of power by adjusting the boost pressure.08-01-2013
20130195616WAVE-DRIVEN BLOWER AND ELECTRIC MOTOR/GENERATOR - The present invention provides a wave-driven blower and a wave-driven generator. Embodiments can accelerate fluid flows with waves requiring with no or minimal moving parts. The waves driving the flow can be surface-thermal waves on the walls of the device. The velocity of the surface-thermal wave entrains the fluid near the surface and imparts a velocity to the fluid. Other types of waves can generate fluid flow. These other waves can be produced by variations in chemical composition, ionic concentration, chemical potential, total pressure, partial pressure and surface texture. Operating as a generator, the device extracts energy from a flowing fluid to amplify wave motions. The wave motions in turn generate electrical power or some other form of useable power08-01-2013
20130202403LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE - A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.08-08-2013
20130202405SELF-LUBRICATED COATING AND METHOD - Coating and method for providing a self-lubricated coating on a substrate. The method includes spraying with an inert gas at least a layer of liquid metal on the substrate; adding a compound to the liquid metal while being sprayed on the substrate; forming a porous layer on the substrate that includes the metal and the compound, where the porous layer has plural pores; heating the porous layer to open the pores; flooding the open pores with a greasing substance such that part of the greasing substance is stored in one or more pores; and cooling the porous layer to close the pores and trap the greasing substance inside the pores.08-08-2013
20130202406GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM - A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.08-08-2013
20130202407Oscillating Hydrofoil, Turbine, Propulsive System and Method for Transmitting Energy - System and method for converting kinetic energy from a fluid flow into mechanical energy, the method comprising the steps of: a) providing a turbine including first and second hydrofoils, each of the hydrofoils being able to move lin-early in a heaving motion, and being able to oscillate about a spanwise axis in a pitching motion, said heaving and pitching motions being quasi-si-nusoidal, b) coupling the heaving motions of the first and second hydrofoils to the pitching motions of the second and first hydrofoils respectively, with the pitch-heave motion phase being substantially equal to the inter-hydrofoil phase, the heaving motion of one of the hydrofoils thereby driving the pitching motion of the other hydrofoil; and c) transforming the heaving motions of the hydrofoils into a rotational movement of a rotatable shaft, with linear-to-rotary transmission means.08-08-2013
20130202404METHODS AND APPARATUS FOR DEPLOYABLE SWIRL VANES - An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream.08-08-2013
20130202402ARTICULATING SLIDER TRACK - A variable fan nozzle assembly includes a cowl member mounted on a slider track. The slider track may be articulated relative to a support member to slightly modify the position of the cowl member to vary the fan nozzle exit area. At least one 4-bar linkage may be utilized to allow articulation of the slider track responsive to an actuator. A method for varying a fan nozzle exit area includes mounting a first slider track in articulatable relationship with a support member; mounting a first cowl member in slidable relationship with a first slider track such that a fan nozzle is at least partially defined by a surface of the first cowl member; varying the operational position of the first cowl member by articulating the first slider track without sliding the first cowl member with respect to the first slider track to vary the fan nozzle exit area.08-08-2013
20130202401Method and Device for variable motion and applications using Interchangeable Heads - A machine for automating manual labor has a motor portion, transmission portion, and a head portion which may all be interchanged with alternates for different applications. The machine is driven by an electric motor that can perform different motions and actions, one at a time or simultaneously, depending on the transmission and head portions. Two such motions are rotary and linear reciprocating motion. Applications include cleaning surfaces, cleaning vessels, mixer, blender, chopper, slicer, shredder, vibrator, massager, semi and fully automatic milk cream maker.08-08-2013
20120076635NACELLE WITH POROUS SURFACES - A fan nacelle for a gas turbine engine includes a leading edge region with a flow path between an intake region in a nacelle outer surface and an exhaust region in a nacelle inner surface to locally modify a flow around the leading edge region during a predefined off-design condition.03-29-2012
20120093628FLUID PUMP CHANGEABLE IN DIAMETER, IN PARTICULAR FOR MEDICAL APPLICATION - The invention relates to a fluid pump device, in particular for the medical application, with a compressible pump housing (04-19-2012
20120093627METHOD FOR SITE SPECIFIC ENERGY CAPTURE OPTIMIZATION THROUGH MODULAR ROTOR BLADE TIP EXTENSION - A power generating system wherein a turbine (04-19-2012
20130209216TURBOMACHINE INCLUDING FLOW IMPROVEMENT SYSTEM - A turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members and a second plurality of airfoil members. A second stage is arranged within the housing relative to the first stage. The second stage includes a third plurality of airfoil members and a fourth plurality of airfoil members. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members. The predetermined clocking is configured and disposed to improve flow characteristics along the flow path.08-15-2013
20130209217PLATFORM SEGMENT FOR SUPPORTING A NOZZLE GUIDE VANE FOR A GAS TURBINE AND NOZZLE GUIDE VANE ARRANGEMENT FOR A GAS TURBINE - A platform segment for supporting a nozzle guide vane for a gas turbine is provided. The platform segment includes a gas passage surface arranged to be in contact with a streaming gas exhausted from a combustor, wherein the streaming gas streams along the gas passage surface in a streaming direction, a cooling surface, opposite to and thermally connected to the gas passage surface and arranged to be in contact with a cooling fluid, a wall protruding from the cooling surface and extending at least partially in the streaming direction, wherein the wall is arranged circumferentially between positions, at which adjacent guide vanes are to be provided, such that cooling fluid is channeled by the wall for cooling a downstream portion of the cooling surface, and a further wall protruding from the cooling surface and extending at least partially in the streaming direction.08-15-2013
20130209218TURBOMACHINE - A method for obtaining an estimate for a process quantity of a turbomachine comprises measuring (08-15-2013
20130209219FULL-FLOW WASTEWATER SEWER SYSTEMS - A wastewater sewage system is disclosed. The sewage system includes a flow control valve that controls the flow of wastewater through the sewage system such that the sewage pipes in the sewage system are substantially full.08-15-2013
20130209220NOISE REDUCTION CONTROL FOR WIND TURBINES - A method of controlling noise emission from a wind turbine with a rotor blade includes providing wind shear data comprising wind shear values as a function of height over ground, determining an expected noise emission based on the wind shear data and controlling the wind turbine to reduce noise emission from the wind turbine in accordance with the expected noise emission.08-15-2013
20130209221ROTARY DAMPING MECHANISM WITH PIVOTAL VANES - A damping mechanism that includes a housing having fluid disposed therein and an inner circumferential surface, an axle shaft that is rotatable with respect to the housing, and a first vane having a distal end and being pivotally associated with the axle shaft. When the axle shaft rotates in a first direction, the first vane pivots to a deployed position, and when the axle shaft rotates in a second direction, the first vane pivots to a stowed position. A first clearance is defined between the distal end of the first vane and the inner circumferential surface of the housing when the first vane is in the deployed position, and a second clearance is defined between the distal end of the first vane and the inner circumferential surface of the housing when the first vane is in the stowed position. The second clearance is greater than the first clearance.08-15-2013

Patent applications in class METHOD OF OPERATION