Inventors list

Assignees list

Classification tree browser

Top 100 Inventors

Top 100 Assignees


WITH DIVERSELY ORIENTED INLET OR ADDITIONAL INLET FOR DIVERSE FLUID (E.G., HEATING, COOLING OR MIXED WORKING FLUID, ETC.)

Subclass of:

415 - Rotary kinetic fluid motors or pumps

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
415116000WITH DIVERSELY ORIENTED INLET OR ADDITIONAL INLET FOR DIVERSE FLUID (E.G., HEATING, COOLING OR MIXED WORKING FLUID, ETC.)89
20080206042METHODS AND SYSTEM FOR RECUPERATED CIRCUMFERENTIAL COOLING OF INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES - A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface.08-28-2008
20080232954VACUUM SYSTEM FOR CONVEYING A HIGH AMOUNT OF SUPPLEMENTAL LIQUID - A pump apparatus for conveying a gas-liquid mixture comprises a first pump (09-25-2008
20130084162Gas Turbine - A gas turbine is provided that can suppress an increase in the supplied amount of cooling air in clearance adjustment through casing cooling.04-04-2013
20100068035APPARATUS AND METHOD FOR COOLING A TURBINE - A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine.03-18-2010
20130089408TURBINE BLADE TIP CLEARANCE CONTROL - An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising.04-11-2013
20090304495DEVICE FOR SUPPLYING VENTILATION AIR TO THE LOW PRESSURE BLADES OF A GAS TURBINE ENGINE - The present invention relates to a device for supplying ventilation air to a turbine rotor of a gas turbine engine comprising a first and a second turbine disk (12-10-2009
20130058760AXIAL COMPRESSOR WITH AN INJECTION DEVICE FOR INJECTING A FLUID - An axial compressor is disclosed for compressing air, such as for a gas turbine. The axial compressor can include a rotor, having a multiplicity of rotor blades, and rotor casing. The casing and rotor can form an annular gas passage. Outside the gas passage an annular and concentric bleed air chamber, can include at least one bleed air slot in functional communication with the gas passage. At least one injection device having at least one nozzle which can inject the fluid into the gas passage via the bleed air slot.03-07-2013
20090035125IMPINGEMENT COOLED STRUCTURE - An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.02-05-2009
20130064647GAS TURBINE - A gas turbine configured to prevent eccentricity of a rotor (03-14-2013
20090232637Cooling Air Manifold Splash Plates and Gas Turbines Engine Systems Involving Such Splash Plates - Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plates includes: a base having an aperture; and an air deflector supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially.09-17-2009
20110293402GAS TURBINE - A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.12-01-2011
20090238678COLD AIR BUFFER SUPPLY TUBE - A cold air buffer supply tube for a gas turbine engine includes a tube body having a first tube end and a second tube end. A fitting is secured to the first tube end, and a metering cap is secured to the tube second end. The metering cap includes a cap body having a peripheral wall with a plurality of holes to direct flow from an air supply into a bearing compartment for the gas turbine engine.09-24-2009
20110268556PLASMA ACTUATOR CONTROLLED FILM COOLING - A film cooling apparatus with a cooling hole (11-03-2011
20100028132WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared 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. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e., wind): a primary air stream which rotates, and transfers energy to, the impeller while passing through the turbine; and a high energy bypass flow or “secondary” air stream which is entrained into the ejector, where the secondary air stream mixes with, and transfers energy to, the primary air stream. 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. 02-04-2010
20090226300Passage obstruction for improved inlet coolant filling - A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage.09-10-2009
20130216356APPARATUS FOR EXTRACTING ENERGY FROM A FLUID FLOW - An apparatus for extracting energy from a fluid flow including a secondary fluid channel, a fluid driveable generator unit and a primary fluid channel. The primary fluid channel comprises a fluid intake in fluid communication with a throat. The throat is configured to increase the flow velocity and reduce the pressure of the primary fluid flowing through the primary fluid channel and includes at least one plenum in the interior of the throat configured to further reduce the pressure of the primary fluid flowing through the primary fluid channel. The plenum includes at least one perforation through its exterior surface in fluid communication with the secondary fluid channel. As such, the flow of primary fluid through the primary fluid channel draws the secondary fluid into the primary fluid channel through the secondary fluid channel and the perforation and thereby into driving engagement with the generator.08-22-2013
20100111673TURBINE WITH INTERRUPTED PURGE FLOW - A blade attachment apparatus for a turbine is provided and includes a member, which rotates about an axis of the turbine, including fore and aft disk posts that retain corresponding fore and aft turbine blades, respectively, fore and aft of a turbine nozzle and a central portion proximate the turbine nozzle and an attachment retained between the fore and aft disk posts and the fore and aft turbine blades and coupled to the central portion, such that a portion of the attachment interrupts a purge flow through the turbine.05-06-2010
20090285671VORTEX COOLED TURBINE BLADE OUTER AIR SEAL FOR A TURBINE ENGINE - A cooling system for a turbine blade outer air seal that is positioned in close proximity to a tip of a rotatable turbine airfoil to seal the gap between the tip of the turbine blade and the blade ring carrier. The turbine blade outer air seal may be formed from a housing including a cooling fluid collection chamber and one or more vortex cooling channels in fluid communication with the cooling fluid collection chamber via one or more vortex channel feed holes. In one embodiment, a plurality of vortex cooling channels may extend from proximate to an upstream edge of an outer sealing plate of the outer air seal to a downstream edge of the outer sealing plate. During use, cooling fluids pass through the vortex channel feed holes and into the vortex cooling channels, in which vortices may be created.11-19-2009
20100034641STEAM TURBINE AND STEAM TURBINE PLANT SYSTEM - A steam turbine 02-11-2010
20080310950Flow cavity arrangement - It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred.12-18-2008
20090053040APPARATUS AND METHOD FOR PRESSURIZED INLET EVAPORATIVE COOLING OF GAS TURBINE ENGINES - An apparatus for cooling air for an intake to a gas turbine, is provided and includes a pressurized water piping and nozzle apparatus for producing a water spray in an airflow to the intake; and evaporative media for receiving the spray and causing a pressurizing of the air in the airflow.02-26-2009
20090053041GAS TURBINE ENGINE CASE FOR CLEARANCE CONTROL - A gas turbine engine includes an active clearance control (ACC) system within the engine casing. The case includes a wall structure with a cast-in cooling configuration through Refractory Metal Core technology which is tailored to address traditional hot spots and improve discrete control of case growth.02-26-2009
20090097964WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared 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. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e., wind): a primary air stream which rotates, and transfers energy to, the impeller while passing through the turbine; and a high energy bypass flow or “secondary” air stream which is entrained into the ejector, where the secondary air stream mixes with, and transfers energy to, the primary air stream. 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.04-16-2009
20090097963Vane and a Vane assembly for a gas turbine engine - A fan outlet guide vane for a gas turbine engine comprises a generally radially-extending internal structural member and at least one surface member securable in use to the internal structural member so as to define an aerofoil. The gas turbine engine includes an annular first structure and an annular second structure, the second structure being radially outward of the first structure so as to define a duct between them, and in use the internal structural member of the vane is secured between the first structure and the second structure. In a preferred embodiment, the surface member or surface members are secured only to the internal structural member, and not to the first or second structures.04-16-2009
20090003990FLANGE WITH AXIALLY EXTENDING HOLES FOR GAS TURBINE ENGINE CLEARANCE CONTROL - A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.01-01-2009
20090208325LARGE FILLET AIRFOIL WITH FANNED COOLING HOLE ARRAY - A turbine airfoil has a fillet connecting the nominal portion of the airfoil into an end wall. Cooling holes are formed over a greater circumferential extent in the fillet than they are through the nominal portion of the airfoil.08-20-2009
20090252597VALVE SYSTEM FOR A GAS TURBINE ENGINE - A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher pressure plenum into a lower pressure flowpath.10-08-2009
20090263235Damper10-22-2009
20100003123INLET AIR HEATING SYSTEM FOR A GAS TURBINE ENGINE - A gas turbine engine has an inlet for delivering air into a compressor section. The compressor section is connected to feed air into a combustion section, wherein the air mixes with fuel and combusts. The combustion section is connected to turbine rotors such that products of combustion can pass over the turbine rotors to drive the turbine rotors. An exhaust communicates with the turbine sections to receive the products of combustion. A bleed tap communicates the exhaust to the inlet. A control controls the amount of exhaust gasses tapped into the inlet to achieve desired operating conditions.01-07-2010
20100021283SYSTEM AND METHOD FOR PROVIDING SUPERCRITICAL COOLING STEAM INTO A WHEELSPACE OF A TURBINE - A system for cooling a high pressure section of a turbomachine includes a conduit configured to carry cooling steam from a boiler to a space upstream of a first stage nozzle of the turobmachine. The conduit extends through a housing of the turbomachine and a nozzle diaphragm of the first stage nozzle. The system further includes a control valve in the conduit configured to regulate the flow of cooling steam. A turbomachine includes a housing; a turbine shaft rotatably supported in the housing; and a plurality of turbine stages located along the turbine shaft and contained within the housing. Each turbine stage includes a diaphragm attached to the housing. The diaphragm comprises a plurality of nozzles. A hole is provided in the diaphragm upstream of a first stage of the plurality of stages for the introduction of cooling steam. A method of cooling a high pressure section of a turbomachine includes introducing cooling steam into the turbomachine through the at least one hole.01-28-2010
20100215476GAS TURBINE COMBUSTION SYSTEM COOLING ARRANGEMENT - Cooling is provided for a gas turbine combustion system that includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface. A source of cooling gas is in fluid communication with the exterior surface of the first member. An open space, in which is located a hula seal, is located between the interior surface of the first member and the second member. At least one opening in the wall of the first member provides a passageway for the cooling gas from the exterior surface of the first member to the open space. The passageway has a directional axis along which the cooling gas flows and is discharged into the open space. The directional axis is substantially oriented in a direction other than a direction towards the central area of the first member.08-26-2010
20100239413APPARATUS FOR TURBINE ENGINE COOLING AIR MANAGEMENT - An exemplary embodiment of the invention is directed to a turbine engine having a first, rotatable turbine rotor assembly, a second, stationary nozzle assembly disposed adjacent thereto and a wheel space which is defined between the first, rotatable turbine rotor assembly and the second, stationary nozzle assembly. The wheel space is operable to receive cooling air therein and includes a sealing feature located on the first rotatable turbine rotor assembly that extends axially into the wheel space to terminate adjacent to a sealing land positioned on the second, stationary nozzle assembly. The sealing feature and the sealing land operate to control the release of cooling air from within the wheel space and the sealing land is constructed of shape memory alloy.09-23-2010
20080292450BLOWER APPARATUS - Blower apparatus has: an air duct having suction and supply openings; a blower fan for creating a flow of air in the duct; and an electrostatic atomizer. The atomizer includes a hollow body exposed to the air in the duct. The body is provided therein with an electrostatic atomization chamber, and has a barrier, an inlet and an outlet. The barrier is put in the duct so that a part of the air flowing in the duct collides with the front of the barrier and thereby pressure-increased air is obtained. The inlet is located at the front side of the barrier so that the pressure-increased air can enter the chamber through the inlet. The outlet is located at the rear side of the barrier so that all the pressure-increased air higher than that of the air flowing in the duct, from the chamber can flow out into the duct.11-27-2008
20090035124Hot-Gas-Ducting Housing Element, Protective Shaft Jacket and Gas Turbine System - Disclosed is a hot-gas-conducting housing element for a hot-gas-conducting housing of a gas turbine system encompassing a compressor, a turbine, and a turbine rotor. The hot gas-conducting housing element is embodied so as to surround a protective shaft jacket placed around the turbine rotor and conduct a hot gas to the turbine. The hot gas-conducting housing element comprises: —at least one hot gas inlet; —an opening facing the turbine; —a section for conducting the hot gas from the at least one hot gas inlet to the opening facing the turbine, said conducting section being provided with an inner housing hub which is configured so as to surround the protective surface facing the protective shaft jacket. Said rib extends in the circumferential direction, protrudes from the circumferential surface, and is disposed in the zone of the circumferential surface bordering the opening that faces the turbine. The rib and/or the inner housing hub is/are fitted with cooling fluid ducts.02-05-2009
20100221099APPARATUS, METHODS, AND/OR SYSTEMS RELATING TO THE DELIVERY OF A FLUID THROUGH A PASSAGEWAY - A method of constructing an industrial machine such that, in operation, a supply of a fluid coolant through a hollow passageway is delivered at a reduced temperature, the method including the steps of: a) identifying at least a section of the hollow passageway that transports or is meant to transport the fluid coolant through a space that resides at a temperature that is significantly higher than a desired temperature of the fluid coolant; and b) through at least a majority of the identified section of the hollow passageway that transports the fluid coolant through the space that resides at the temperature that is significantly higher than the desired temperature of the fluid coolant, constructing the hollow passageway such that the outer surface of the hollow passageway has an emissivity coefficient less than about 0.1.09-02-2010
20100150700BYPASS AIR SCOOP FOR GAS TURBINE ENGINE - A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine.06-17-2010
20100054915AIRFOIL INSERT - An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.03-04-2010
20120201655RADIO COMMUNICATION SYSTEM, TRANSMITTING APPARATUS, RECEIVING APPARATUS, RECEIVING METHOD AND TRANSMITTING METHOD - The invention relates to a turbine casing (08-09-2012
20090324388GAS TURBINE AND COOLING AIR SUPPLY STRUCTURE THEREOF - The present invention includes an introducing passage that is provided within a turbine stationary blade fixed within a turbine casing and that communicates an interior of the turbine casing with an exterior thereof; a nozzle that is provided in an inner circumference of the turbine stationary blade in a manner that the nozzle communicates with the introducing passage and that includes an outlet facing the opening of the rotor cavity and a swirler at the outlet; and a pressurizing passage that communicates a cooling passage with a rotor cavity. In this arrangement, the outlet of the nozzle and the connecting opening of the pressurizing passage are arranged so that distances of the outlet and of the connecting opening from the central axis line in the radial direction of the rotor are the same distance r.12-31-2009
20120201654TURBINE ENGINE COMPRESSOR HAVING AIR INJECTIONS - A turbine engine compressor, including a first housing for supporting injectors, a second housing arranged around the first housing while forming with the first housing an annular space therewith, and a plurality of air injectors each mounted in recesses. Each air injector includes at least one inner air injection channel which leads, on one side, into an outflow jet of the gas stream and, on the other side, into the space formed between the recesses, and, at an upstream end, an upstream rim having an inner surface radially bearing against an upstream rim of the corresponding recess of the first housing and an outer surface radially bearing against an inner surface of the second housing. A mechanism clamping the upstream rim of the air injectors between the housings enables the air injectors to be held in position in the recesses of the first housing.08-09-2012
20100111674System and Method for Reducing Bucket Tip Losses - A system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface.05-06-2010
20090257862WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of prior wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: a turbine shroud with a flared 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. Unlike gas turbine mixers and ejectors which also mix with hot core exhaust gases, Applicants' preferred apparatus mixes only two air streams (i.e., wind): a primary air stream which rotates, and transfers energy to, the impeller while passing through the turbine; and a high energy bypass flow or “secondary” air stream which is entrained into the ejector, where the secondary air stream mixes with, and transfers energy to, the primary air stream. 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. 10-15-2009
20090010751ANGLED ON-BOARD INJECTOR - A secondary flow system provides a compact injector cooling structure for turbine blades which includes an Angled On-board Injector (AOBI) that locates a metering throat at an inward angle relative to an engine centerline. The AOBI positions the metering throat at the inward angle relative to an engine centerline to communicate cooling airflow to an angled annular section of a turbine rotor disk coverplate.01-08-2009
20110305557WIND TURBINE - A wind turbine has a spindle, a first fan device and a second fan device. The first fan device is rotatably mounted around the spindle and has a first pivot hole and at least two first blades. The first pivot hole is formed through a center of the first fan device and is mounted around the spindle. The at least two first blades are radially mounted on and protrude from an external surface of the first fan device. The second fan device is rotatably mounted around the spindle, abuts with the first fan device and has a second pivot hole and at least two second blades. The second pivot hole is formed through a center of the second fan device and is mounted around the spindle. The at least two second blades are mounted on and protrude from an external surface of the second fan device.12-15-2011
20120045313FLOW DEVICE COMPRISING A CAVITY COOLING SYSTEM - A flow device having a cooling-air injection system for injecting cooling air into cavities (02-23-2012
20100129201HYDRAULIC MACHINE INCLUDING MEANS FOR INJECTING A FLOW DRAWN FROM A MAIN FLOW - The invention relates to a machine through which a main flow (E) of water passes, including a turbine wheel (05-27-2010
20130142623COMPRESSOR HOUSING AND TWO-STAGE TURBOCHARGER THEREOF - A compressor housing surrounds an impeller of a compressor, compressing and discharging air suctioned from the impeller, the compressor may include a body having an impeller seating portion where the impeller is installed at the center of the body, an air inflow hole being in communication with the impeller seating portion formed at one side of the body, an air outflow hole formed at the other side of the body, and a scroll-shaped air path being in communication with the air inflow hole to the air outflow hole while surrounding the impeller seating portion, and a cooling chamber provided in the body, which has a cooling water path through which cooling water cooling air that flows on the air path flows and a plurality of exits being in communication with the cooling water path.06-06-2013
20120207585Centrifugal Compressor - A centrifugal compressor is provided. The centrifugal compressor includes a housing and a rotatable assembly mounted for rotation about an axis within the housing. The rotatable assembly includes an impeller forming part of a compressor stage and a motor rotor forming an armature of a motor for driving the rotating assembly about the axis. A first air intake is located at a first end of the apparatus, the first air intake providing an air source for the compressor stage and a second air intake is located at a second end of the apparatus, the second air intake providing an air source for at least two air cooling passageways.08-16-2012
20120163957DEVICE FOR SUPPORTING A TURBINE RING, TURBINE HAVING SUCH A DEVICE, AND TURBINE ENGINE HAVING SUCH A TURBINE - A device for supporting a ring of a gas turbine, the ring configured to surround mobile blades of the turbine which are driven by a gas stream flowing upstream to downstream. The device includes at least one upstream hook facing upstream, to be housed in an upstream groove of the ring, opened toward the downstream direction, and at least one downstream hook facing downstream, to be housed in a downstream groove of the ring, opened toward the upstream direction. The hooks are protected and clearances at apexes of the blades are more easily controlled. The device further includes, upstream from the upstream hook, a mechanism injecting cooling gas to cool the upstream hook and/or includes, downstream from the downstream hook, a mechanism injecting a cooling gas to cool the downstream hook.06-28-2012
20100247291GAS TURBINE ENGINE ARTICLE HAVING COLUMNAR MICROSTRUCTURE - A gas turbine engine article includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases, and an outer side. A gaspath layer is bonded to the inner side of the substrate and includes a metallic alloy having a columnar microstructure.09-30-2010
20120321442TURBOMOLECULAR PUMP DEVICE - A turbomolecular pump device includes: a turbomolecular pump main body; a power unit that drives the turbomolecular pump main body; and a water cooling unit that is provided between the turbomolecular pump main body and the power unit, wherein components provided in a casing of the power unit are classified into an intensive cooling required component that requires intensive cooling, a moderate cooling required component that requires moderate cooling, and a no cooling required component that requires substantially no cooling, the intensive cooling required component is mounted on a first high-conductivity substrate contacting to the water cooling unit, the moderate cooling required component is mounted on a second high heat-conductive substrate contacting to an inner surface of the casing, and the no cooling required component is mounted on a substrate arranged in a space between the first high heat-conductive substrate and the second high heat-conductive substrate.12-20-2012
20120177481GAS TURBINE - This gas turbine includes a turbine cooling structure of cooling a turbine by using cooling air and a filter that reduces dust in the cooling air on an upstream side of the turbine. Furthermore, the gas turbine includes a supply pipe for supplying the cooling air to the filter, a branch pipe that is branched from the supply pipe on an upstream of the filter, and a unit that calculates or estimates a circulation amount of dust in the cooling air. In this gas turbine, at a time of start-up of a turbine, the supply pipe is closed and the branch pipe is opened, and when the circulation amount of dust in the cooling air becomes equal to or less than a predetermined threshold, the supply pipe is opened and the branch pipe is closed.07-12-2012
20120257959STEAM TURBINE IN A THREE-SHELLED DESIGN - A turbomachine including a rotor and an inner interior housing an outer interior housing and an exterior housing, wherein the turbomachine has a first flow and a second flow arranged opposite the first flow for a high-pressure blading or medium-pressure blading, wherein the inner interior housing is made of a higher quality material tan the outer interior housing and solely accommodates the high-pressure and medium-pressure inflow regions including the balance piston is provided.10-11-2012
20090252598Gas turbine inlet temperature suppression during under frequency events and related method - A method is provided for augmenting power output in a gas turbine electrical power-generating plant including a multistage compressor, a combustor and a multistage turbine component, during events when grid frequency drops below a predetermined target frequency. The method is carried out by a) providing a supply of liquified air arranged to permit selective addition of liquified air to an ambient air inlet to the compressor; and b) flowing controlled amounts of the liquified air into the ambient air inlet during such events.10-08-2009
20110038711STEAM TURBINE AND SYSTEM FOR START-UP - A steam turbine and a start-up system for a steam turbine are disclosed comprising: a plurality of stages, a steam path through the plurality of stages, an inlet port for introducing steam to a first stage, an exhaust port at a last stage for allowing exhaust to exit the steam turbine, an admission port for allowing steam to enter the steam path at a location downstream from the inlet port, and a ventilator port for allowing steam to exit the steam path, the ventilator port located upstream of the admission port to create a reverse flow of steam towards the ventilator port from the admission port.02-17-2011
20120269615BLADE MEMBER AND ROTARY MACHINE - The airfoil member of the present invention is provided with an airfoil body, an end wall which is installed at an end part of the airfoil body in a blade span direction and extends so as to intersect in the blade span direction, a fillet portion which smoothly connects the end part of the airfoil body with the end wall, and a cooling channel which allows a cooling medium to circulate inside the airfoil body and the end wall and in which two main channels extending along the blade span direction are connected so as to bend in a folding manner at a return channel formed on the end wall side. The return channel is formed so as to run along the fillet portion on a cross section intersecting with a center line of a profile of the airfoil body and also formed in such a manner that the width thereof in the profile thickness direction is greater than the width of the main channel in the profile thickness direction.10-25-2012
20120328414Gas Turbine For Aeronautic Engines - In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.12-27-2012
20090067988Mixer for cooling and sealing air system for turbomachinery - A system for mixing flows from a compressor is provided. The system comprises an ejector that combines a first flow and a second flow, from the compressor, into a third flow. A bypass flow is connected between the first flow and the third flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the respective pressures and temperatures of the bypass flow and the third flow.03-12-2009
20130170955EXHAUST PUMP - Provided is an exhaust pump that comprises connecting opening portions that can be deburred easily and that are suitable for enhancing gas evacuation performance. A rotor (a cylindrical rotating member) of an exhaust pump comprises a plate body that has a ring-like projection on a reverse side outer peripheral section of the rotor, and a cylindrical body that is fitted into an outer periphery of the ring-like projection. Connecting opening portions of the exhaust pump comprise holes that are formed by notching an outer peripheral section of the plate body and an outer peripheral section of the ring-like projection, and a portion (specifically, a hole) of the holes that opens in the form of a horizontal hole is covered by an outer-peripheral upper end portion of the cylindrical body.07-04-2013
20130170956DISABLING CIRCUIT IN STEAM TURBINES FOR SHUTTING OFF SATURATED STEAM - A cooling option for a steam turbine is provided, wherein the steam turbine includes a high-pressure zone and a medium-pressure zone, wherein the saturated steam streaming out of the high-pressure zone is discharged via a saturated steam conduit to a first pressure chamber in a second flow channel of the medium-pressure zone and thus the possibility of the saturated steam causing damage by corrosion and erosion in the high-pressure zone is prevented.07-04-2013
20130177398SYSTEM FOR PRESSURING THE BEARING CHAMBERS OF TURBINE ENGINES MACHINES USING AIR TAKEN FROM THE INTAKE DUCT - A system for pressurizing at least one chamber for lubricating bearings of a turbine engine, including a circuit for supplying the chamber with pressurized air, and a circuit for recovering oil mist formed in the chamber and for returning the mist to an oil tank of the turbine engine. The supply circuit supplies the chamber with air taken upstream from the low-pressure compressor.07-11-2013
20120251296AROMATIC NEBULIZING DIFFUSER - An aromatic nebulizing diffuser includes a base panel, a holder defining therein an oscillation chamber, a power switch, an electric fan, a fluid container, an ultrasonic oscillator, a fluid intake control device set in between the oscillation chamber and the fluid container, a dip tube in communication between the oscillation chamber and the fluid container and changeable between an open status and a close status to control the fluid intake control device in closing/opening the passage between the oscillation chamber and the fluid container, an outer housing, an air passage in air communication between the oscillation chamber and the cover for the passing of currents of air caused by the electric fan, an exhaust passage for guiding a generated fine mist of aromatic fluid droplets out of the oscillation chamber into the atmosphere.10-04-2012
20130129480COMPRESSION APPARATUS - Provided is a compression apparatus for cooling multiple devices using a single fan with a small amount of electric power. An upper limit temperature, a first gain applied in a case in which a suction adjustment valve is opened, and a second gain applied in a case in which the suction adjustment valve is closed are set in advance for each of multiple temperature detectors provided at different locations of the compression apparatus; and, for each of the multiple temperature detectors, a difference between a detected value and the upper limit temperature is calculated, and a rotation speed of the fan is determined based on the smallest value in the differences, and the first gain or the second gain set for the temperature detector having the smallest difference.05-23-2013
20130149107GAS TURBINE OUTER CASE ACTIVE AMBIENT COOLING INCLUDING AIR EXHAUST INTO A SUB-AMBIENT REGION OF EXHAUST FLOW - A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end.06-13-2013
20120282080COOLING APPARATUS, GAS TURBINE SYSTEM USING COOLING APPARATUS, HEAT PUMP SYSTEM USING COOLING SYSTEM, COOLING METHOD, AND METHOD FOR OPERATING COOLING APPARATUS - The amount of water to be injected in an intercooler is controlled to cool the compressed gas to the saturation temperature. It is difficult to adjust the amount of the water to be injected, however, since the temperature of the compressed gas at an intercooler outlet is actually higher than the saturation temperature. An intercooling system is configured so as to cool a gas to the saturation temperature without controlling the amount of water injection and thereby maintain the reliability of the compressor while improving the cooling efficiency. The intercooling system is located between a plurality of compression stages of a gas compressor to cool the gas that has been in the compressor. A desired amount of liquid is sprinkled to cool the compressed gas while restraining inflow of the liquid into the compression stages.11-08-2012
20130183140FAN SHROUD WITH COOLING PASSAGE - A fan shroud includes a cylindrical body which is made of a heat conducting material and which enclose an annular passage. The shroud also has a flange projecting radially outwardly from the body. The body forms a wall interposed in the passage. An inlet port and an outlet port communicate with the passage on opposite sides of the wall. Inlet and outlet supply lines are connected to the inlet and outlet ports.07-18-2013
20100202873Ceramic Matrix Composite Turbine Engine - In one embodiment a transition section for a turbine engine is provided that includes one or more components constructed of a ceramic matrix composite. The transition section may fluidly connect a high-pressure turbine and a low-pressure turbine within the gas turbine engine. The transition section may include a transition duct and a variable area turbine nozzle. One or both of the transition duct and the variable area turbine nozzle may be constructed of the ceramic matrix composite.08-12-2010
20130243575COOLING PEDESTAL ARRAY - A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.09-19-2013
20130121810INTER-BLADE SEALING FOR A TURBINE OR COMPRESSOR WHEEL OF A TURBINE ENGINE - An inter-blade sealing for a turbine or compressor wheel of a turbine engine includes inserts engaged in longitudinal cavities in side edges of platforms of blades and bearing, in operation, against facing side edges of platforms of adjacent blades. Each insert has a cylindrical elongate shape and includes in its outer cylindrical surface at least one annular groove for passing platform cooling air.05-16-2013
20130121809REFRIGERANT COMPRESSOR - A refrigerant compressor comprises an electric element; a compression element; and a sealed container; wherein the compression element includes: a crankpin; a piston pin; and a connecting rod having a large hole portion into which the crankpin is inserted, a small hole portion in which the piston pin is rotatably disposed, and a coupling rod portion; wherein an oil guide hole is provided in the coupling rod portion of the connecting rod such that the large hole portion and the small hole portion are communicated with each other via the oil guide hole; a circular first groove is provided on an outer peripheral surface of the piston pin such that the first groove communicates with the oil guide hole; and a second groove extending in a center axis direction of the piston pin is provided in a first region of the small hole portion of the connecting rod.05-16-2013
20130243576GAS TURBINE - A gas turbine includes a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft, and a channel provided in the blade ring 09-19-2013
20130189080ROTARY COMPRESSOR - A refrigerant being low in both ODP and GWP and containing at least hydrofluoroolefin having a double bond of carbon is used. By providing a first compression-chamber oil feed path for feeding refrigerating machine oil to a compression chamber 07-25-2013
20130195619EXHAUST TURBOCHARGER OF AN INTERNAL COMBUSTION ENGINE - The invention relates to an exhaust turbocharger (08-01-2013
20130195620EXHAUST TURBOCHARGER - The invention relates to an exhaust turbocharger (08-01-2013
20100178158TURBINE WASH PORT FOR A GAS TURBINE ENGINE - An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.07-15-2010
20130209232MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS - A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed.08-15-2013
20130209233COOLING HOLE WITH ENHANCED FLOW ATTACHMENT - A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.08-15-2013
20130209234MULTIPLE DIFFUSING COOLING HOLE - A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge.08-15-2013
20130209235GAS TURBINE ENGINE COMPONENT WITH CUSPED, LOBED COOLING HOLE - A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp on the transition, and a first longitudinal ridge extending along the diffusing section between the transition and the outlet. The first longitudinal ridge divides the diffusing section into first and second lobes.08-15-2013
20130209236GAS TURBINE ENGINE COMPONENT WITH COMPOUND CUSP COOLING CONFIGURATION - A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition.08-15-2013
20130209238SET OF ROTOR DISKS FOR A TURBINE ENGINE - A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk.08-15-2013
20130209237OIL SUPPLY APPARATUS - In an oil supply apparatus, a valve body includes first and second radially protruding lands, and a small-diameter portion continuously connecting the first and second lands and having a diameter smaller than at least the outer diameter of the first and second lands. Rotational speeds of a rotor are set as first, second and third rotational ranges in the ascending order. In the first rotational range, work oil from a second discharge port is fed to a first oil passage via the small diameter portion. In the second rotational range, work oil from the second discharge port is fed to a return oil passage via the small diameter portion. In the third rotational range after the second oil passage is blocked relative to the return oil passage by the second land, work oil from the second discharge port is fed to the first oil passage.08-15-2013
20100129200PELTON HYDRAULIC MACHINE INCLUDING MEANS FOR INJECTING A FLOW DRAWN FROM A MAIN FLOW - The invention relates to a Pelton machine through which a main flow (E) of water passes, including at least one Pelton turbine (05-27-2010
20090155053Turbine cooling flow modulation - Cooling air flow in a gas turbine engine, for example to a first turbine rotary stage is modulated in accordance with a predetermined cooling schedule by means of a fluidic valve arrangement disposed in the interior of the engine. Since fluidic valves have no moving parts they are more reliable than conventional mechanical and electrically operated valves and able to withstand better the environment in the interior of a gas turbine engine. The fluidic valves are operated remotely by a relatively small control flow that may be governed by an electrically operated valve mounted externally and under the control of a predetermined cooling schedule.06-18-2009
20130272850COMPONENTS WITH MICROCHANNEL COOLING - A component includes a substrate having outer and inner surfaces, where the inner surface defines at least one hollow, interior space. The outer surface defines pressure side and suction side walls, which are joined together at leading and trailing edges of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface. The coating comprises at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge. A method of forming cooling channels in the vicinity of the trailing edge is also provided.10-17-2013
415117000 Diverse fluids to motor 4
20100034642DEVICE FOR ENHANCING EFFICIENCY OF AN ENERGY EXTRACTION SYSTEM - A device is provided. The device is configured to introduce a pressurized flow along a Coanda profile and to entrain additional fluid flow to create a high velocity fluid flow; wherein the high velocity fluid flow is directed to an end use system through a flow path in flow communication with the device.02-11-2010
20110129333METHOD OF OPERATING TURBOCHARGED PISTON ENGINE - Invention relates to method of operating turbocharged piston engine including the steps of running the engine during a period, shutting down the engine, and restarting the engine. After a first time interval from shutting down the engine, and while a turbine and compressor parts of the turbocharger are rotating, a cleaning agent is introduced into the stream of gas flowing in a flow channel upstream the turbine part during a second time interval prior to restarting the engine.06-02-2011
20130094939IN-PIPE HYDRO TURBINE WITH AIR BUBBLE - An in-pipe turbine with the use of an air bubble in a new and unique configuration with electronic controls can improve the efficiency of in-pipe hydroelectric turbines.04-18-2013
20130209239COOLING DEVICE FOR ELECTRIC MOTOR - The invention relates to a device for cooling of electric motor (08-15-2013

Patent applications in class WITH DIVERSELY ORIENTED INLET OR ADDITIONAL INLET FOR DIVERSE FLUID (E.G., HEATING, COOLING OR MIXED WORKING FLUID, ETC.)

Patent applications in all subclasses WITH DIVERSELY ORIENTED INLET OR ADDITIONAL INLET FOR DIVERSE FLUID (E.G., HEATING, COOLING OR MIXED WORKING FLUID, ETC.)