| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415191000 | Vanes | 78 |
| 20080232957 | WIND 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, single and multi-stage ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of wind turbines, so that its operating efficiency routinely exceeds the Betz limit. 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. | 09-25-2008 |
| 20090110549 | GAS TURBINES HAVING FLEXIBLE CHORDAL HINGE SEALS - Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring. | 04-30-2009 |
| 20090123275 | Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting - Vibration induced compressor vane failure from tip leakage vortex bursting is eliminated or minimized. By securing the vane at opposite ends to inner and outer stationary casings, tip leakage is entirely avoided hence avoiding the mechanism for inducing vibration. By contouring the inner surface of the flow path to converge the flow in a downstream direction with a cantilevered compressor vane having a vane tip spaced from the inner casing surface, airflow lift off is precluded or minimized maintaining the flow attached to the flowpath surfaces with consequent avoidance of tip vortex induced vibration. | 05-14-2009 |
| 20100119361 | TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind/Water 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 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. | 05-13-2010 |
| 20090035129 | Vane air-cooling system for automatic transmission torque converter - A cooling system is provided for automatic transmission torque converter assemblies having a housing shell and flex plate. The cooling system includes a housing cover having opposing exterior and interior surfaces that define a wall portion and a preferably circular base portion. The base portion is configured to attach to the flex plate, preferably by one or more stud members, to be rotated thereby. The wall portion extends from a periphery of the base portion and is configured to attach to the housing shell. The cooling system also includes a plurality of vane members positioned along the outer periphery of the base portion. The vane members are configured to increase convective dissipation of heat from the torque converter assembly to surrounding ambient air by increasing the heat transfer coefficient and surface area. Optimally, the vanes have a turbine fin configuration, but may alternatively have curved fin or a straight-fin configuration. | 02-05-2009 |
| 20130034433 | INTER-TURBINE DUCTS WITH GUIDE VANES - A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct. | 02-07-2013 |
| 20100104432 | ARRANGEMENT FOR A GAS TURBINE ENGINE - An inlet guide vane arrangement for a gas turbine is provided. The arrangement includes a plurality of guide vane duct elements, the guide vane duct elements include a suction side wall and a pressure side wall, both walls facing each other, and are designed to be adjoinable to another of the guide vane duct elements, such that the pressure side wall of one guide vane duct element cooperates with the suction side wall of the adjacent guide vane duct element thereby forming a guide vane. The guide vane duct element includes features to accept a key element adapted to be arranged between the pressure side wall and the adjacent suction side wall, when two guide vane duct elements are adjoining to one another, and to attach together both adjoining guide vane duct elements. | 04-29-2010 |
| 20090155061 | SECTORIZED NOZZLE FOR A TURBOMACHINE - A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector. | 06-18-2009 |
| 20100040460 | Platforms with Curved Side Edges and Gas Turbine Engine Systems Involving Such Platforms - Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform. | 02-18-2010 |
| 20100003130 | Windmill device - A wind power engine including a stator having stator blades and a rotor having rotor blades. The rotor is positioned inside the hollow area of the stator and is rotationally movable with respect to the stator about an axis of rotation. The stator blades are positioned in such a way that an air flow coming from the outside of the stator is oriented towards the rotor and the rotor blades. The oriented airflow allows the rotor blades to drive the rotor about the axis of rotation. At least certain rotor blades have a concave-shaped profile on one of their faces. | 01-07-2010 |
| 20130058771 | SPRING-TENSIONED STATOR RESTRAINING STRAP - A vane assembly of a gas turbine engine includes a plurality of circumferentially spaced vanes extending radially between an outer case and an inner case. A spring-tensioned stator restraining strap is provided around the outer case and surrounding outer ends of the respective vanes. The outer ends of the vanes are received in corresponding openings defined in the outer case and project radially outwardly from the outer case. The spring-tensioned strap compresses the respective vanes radially and inwardly in position. | 03-07-2013 |
| 20130094950 | COMPRESSOR UNIT - A compressor unit includes a motor and a compressor in a casing of a gastight form. The casing houses the motor and the compressor. The motor includes a rotor surrounded by a stator which has an encapsulation formed on the inner diameter as a separating can, so that a medium being handled does not damage the stator. The separating can includes a polymer matrix which is reinforced using a plurality of fibers. The polymer matrix is at least partly a ceramic fiber reinforced polymer matrix. The plurality of fibers are formed as continuous filaments. The continuous filaments include the length of at least 30 mm. | 04-18-2013 |
| 20130101405 | FAN, MOLDING DIE, AND FLUID FEEDER - A cross-flow fan includes a plurality of fan blades. The fan blade has an inner edge portion arranged on an inner circumferential side and an outer edge portion arranged on an outer circumferential side. In the fan blade, a blade surface extending between the inner edge portion and the outer edge portion and constituted of a positive pressure surface and a negative pressure surface is formed. The fan blade has such a blade cross-sectional shape that a large-thickness portion at which a thickness between the positive pressure surface and the negative pressure surface is greatest is arranged closer to the inner edge portion. A recess recessed in the blade surface is formed at a position closer to the inner edge portion where the large-thickness portion is arranged, than to the outer edge portion. | 04-25-2013 |
| 20130115069 | Vertical Axis Wind Turbine - A vertical axis wind turbine formed from a concentric arrangement of fixed stator blades to provide fluid flow acceleration into an arrangement of rotatable blades secured to a generator for invoking electrical power generation. The stator blades are maintained in a fixed position by use of an upper and lower stator plate. The rotor blades include an upper and lower plate, the upper plate coupled to the upper stator plate, and the lower rotor plate coupled to the generator. The amount of stator and rotor blades may be scaled in number and size depending upon the type of generator to be driven and associated mechanical energy to be obtained. The stator blades are designed for air deflection in a direction for optimal rotor blade rotation by accelerating air flow into a pre-swirl before the flow contacts the rotor blades. Each stator blade is oriented at a sufficient stagger angle so that an angle of the relative velocity does not exceed the stall angle of said rotor blade. | 05-09-2013 |
| 20130115068 | WIND TURBINE ROTOR AND WIND TURBINE - A wind turbine comprising: a shaft ( | 05-09-2013 |
| 20130121815 | HERMETICALLY SEALED COMPRESSOR - A hermetically sealed compressor in which heat generation and insulation breakdown are hardly to occur at the connection portion between a lead wire of a motor and an external terminal is configured as follows. The compressor main body and the motor are integrally structured. The flow path of a fluid to be compressed is communicated with the internal space of the motor. The stator ( | 05-16-2013 |
| 20120237344 | ADVANCED BOOSTER SYSTEM - A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile. | 09-20-2012 |
| 20130129494 | AXIAL TURBOMACHINE COMPRESSOR OUTER CASING - The invention relates to a casing, particularly of an axial turbomachine compressor. This casing comprises a support of cylindrical overall shape made of composite material, a metal ring fitted by bonding to the internal surface of the support, and a layer of abradable material fitted by plasma spray onto the internal surface of the metal ring. The metal ring is preferably made of stainless steel and is preferably perforated. The perforation allows better keying of the adhesive and allows the degassing thereof. The external surface of the metal ring is preferably sandblasted prior to bonding. Its internal surface is also preferably sandblasted prior to the plasma spraying of the abradable material. | 05-23-2013 |
| 20130129493 | TURBINE - A turbine is provided including an annular turbine blade body ( | 05-23-2013 |
| 20100266395 | Inlet Swirl Control for Turbochargers - An inlet duct, an induction system, and a system are disclosed for directing an inlet flow into an inlet compressor for use in an internal combustion engine. An example inlet duct may include one or more relief features disposed on an inner surface of the inlet duct. The one or more relief features may be made integral with the inlet duct. The one or more relief features may be disposed to protrude into the inlet flow to cause the inlet flow to swirl before reaching the inlet compressor. | 10-21-2010 |
| 20110299980 | GAS TURBINE ENGINE AND A GAS TURBINE ENGINE COMPONENT - A gas turbine engine component providing a gas flow passage is provided, which gas flow passage surrounds an inner passage surface, an outer passage surface forming an outer delimitation of said gas flow passage. In an aspect, the trace of the inner passage surface in a cross-section perpendicular to a central axis of the component presents at least one substantially straight portion. In another aspect, where a plurality of circumferentially spaced blades extends between the inner and outer passage surfaces, two portions of the trace, in a cross-section perpendicular to a central axis of the component, of the outer passage surface between two adjacent blades are substantially straight and oriented in an angle in relation to each other so as to form a concavity in the gas flow passage. | 12-08-2011 |
| 20090317245 | Method of forming a rotating blade assembly - A method of forming a blade assembly for a gas turbine engine, the method comprising mounting turbine blades on a rotor in a number of radial stages. Sacrificial supports are placed on the blades, and nozzle guide vanes are located on the supports. The rotor is introduced into a casing, and the guide vanes are mounted to the casing. | 12-24-2009 |
| 20120171025 | VANE WITH SPAR MOUNTED COMPOSITE AIRFOIL - A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame. | 07-05-2012 |
| 20100119362 | Shrouded Turbine Assembly - A turbine that allows for the conversion of the kinetic energy of waterway to mechanical power for use in an energy accepting apparatus is described. The turbine has complimentary components that improve the power efficiency of the turbine. The turbine may include a blade shroud and a plurality of blades that are connected to the blade shroud. On the external surface of the blade shroud, a drive mechanism and/or a brake mechanism may be disposed. An inlet nozzle and outlet diffuser may be used in combination with the turbine. The turbine may be useful in a number of settings, including, but not limited to, streams, rivers, dams, ocean currents, or tidal areas that have continuous or semi-continuous water flow rates and windy environments. | 05-13-2010 |
| 20090087308 | WIND 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, single and multi-stage ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of wind turbines, so that its operating efficiency routinely exceeds the Betz limit. 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. | 04-02-2009 |
| 20100080695 | TURBINE NOZZLE FOR A GAS TURBINE ENGINE - A turbine nozzle includes: a hollow, airfoil-shaped turbine vane; and an arcuate first band disposed at a first end of the turbine vane, the first band having a flowpath face adjacent the turbine vane, and an opposed back face. The back face includes at least one open pocket, the at least one pocket defined in part by a bottom wall recessed from the back face, opposed ends of the bottom wall merging with the back face. The bottom wall is substantially free of interior corners. | 04-01-2010 |
| 20090280006 | TURBINE HOUSING WITH INTEGRATED RIBS - A flow direction system ( | 11-12-2009 |
| 20090274554 | Fluid flow machine including rotors with small rotor exit angles - A fluid flow machine includes at least one rotor blade row designed for high work coefficients, which—in its center section and/or averaged over the blade height—provides for an essentially swirl-free relative outflow. The respective rotor, in its trailing edge area, is essentially orientated in meridional direction, which essentially corresponds to the meridional flow direction. | 11-05-2009 |
| 20090297343 | PRECAST GROOVES FOR A STATOR BLADE ASSEMBLY - A stator, including a blade assembly with an inner circumferential surface and a plurality of pre-formed grooves in the inner circumferential surface and an outer race with an outer circumferential surface and a plurality of protrusions at least partially engaged with the plurality of pre-formed grooves. The plurality of protrusions is frictionally engaged with the plurality of pre-formed grooves. In one embodiment, the inner circumferential surface includes an area circumferentially disposed between first and second protrusions from the plurality of protrusions and a portion of the area is displaced radially inward by the engagement of the pluralities of grooves and protrusions. | 12-03-2009 |
| 20110200429 | IMPELLER AND BLOWER FAN INCLUDING THE SAME - An impeller includes a substantially cylindrical cup portion arranged to rotate about a center axis, a plurality of blades fixed to an outer circumferential surface of the cup portion for unitary rotation with the cup portion to draw air from one axial side and discharge the air to the other axial side, and an annular connector portion arranged to interconnect the blades. The connector portion has a substantially cylindrical shape in a position spaced apart about 70% to about 90% of the radial length of the blades from the base of each of the blades on the outer circumferential surface of the cup portion, and the ratio of a total axial height of the connector portion to a total radial gap between the outer circumferential surface of the cup portion and the inner circumferential surface of the connector portion is equal to or smaller than about 0.9. | 08-18-2011 |
| 20100111683 | FLUID FLOW MACHINE - A fluid flow engine ( | 05-06-2010 |
| 20100111682 | CRENELATED TURBINE NOZZLE - A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween. One of the flanges is crenelated to improve nozzle life. | 05-06-2010 |
| 20100061845 | GUIDING DEVICE OF A FLOW MACHINE AND GUIDE VANE FOR SUCH A GUIDING DEVICE - A guide device for a turbomachine, particularly a steam turbine, with a guide vane ring and a plurality of guide vanes which are fastened to the guide vane ring so as to be distributed along the circumference of the guide vane ring. The guide vane ring has a groove, and the guide vanes also have grooves which are aligned with the groove of the guide vane ring in the assembled state. The guide vanes are fixed in their radial position at the guide vane ring by means of a retaining ring which engages in the groove of the guide vane ring and in the grooves of the guide vanes. | 03-11-2010 |
| 20080267771 | Gas turbine with a guide vane - A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body. | 10-30-2008 |
| 20090162193 | TURBINE INLET GUIDE VANE WITH SCALLOPED PLATFORM AND RELATED METHOD - A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability. | 06-25-2009 |
| 20110229314 | HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE - An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane. | 09-22-2011 |
| 20090208331 | CENTRIFUGAL COMPRESSOR ASSEMBLY AND METHOD - A centrifugal compressor assembly for compressing refrigerant in a 250-ton capacity or larger chiller system comprising a motor, preferably a compact, high energy density motor or permanent magnet motor, for driving a shaft at a range of sustained operating speeds under the control of a variable speed drive. Another embodiment of the centrifugal compressor assembly comprises a mixed flow impeller and a vaneless diffuser sized such that a final stage compressor operates with an optimal specific speed range for targeted combinations of head and capacity, while a non-final stage compressor operates above the optimum specific speed of the final stage compressor. Another embodiment of the centrifugal compressor assembly comprises an integrated inlet flow conditioning assembly comprising a flow conditioning nose, a plurality of inlet guide vanes and a flow conditioning body that positions inlet guide vanes to condition flow of refrigerant into an impeller to achieve a target approximately constant angle swirl distribution with minimal guide vane turning. | 08-20-2009 |
| 20110229315 | HIGH EFFICIENCY ROTOR BLADES FOR A FLUID TURBINE - A shrouded fluid turbine includes an impeller surrounded by a turbine shroud. The turbine shroud has a plurality of mixing lobes on a trailing edge, resulting in the trailing edge having a circular crenellated shape. An ejector shroud is located downstream of the turbine shroud, an inlet end of the ejector shroud surrounding the mixing lobes of the turbine shroud. The impeller is a rotor/stator assembly. In particular, the rotor comprises a rotor hub formed from a cylindrical sidewall and has seven rotor blades extending radially from the hub. It has been found that seven rotor blades optimizes the total-to-total efficiency of the shrouded fluid turbine. | 09-22-2011 |
| 20120141260 | STEAM TURBINE SINGLET INTERFACE FOR MARGIN STAGE NOZZLES WITH PINNED OR BOLTED INNER RING - A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved. | 06-07-2012 |
| 20110058937 | NACELLE CONFIGURATIONS FOR A SHROUDED WIND TURBINE - A shrouded wind turbine comprises a shroud disposed about an impeller. The impeller surrounds a nacelle body which is shaped to enhance smooth flow of wind through the impeller. Some embodiments include an inlet and an outlet in the nacelle body, allowing airflow through an interior cavity. Other nacelle bodies may be tapered, flared, include mixing lobes around a trailing edge, or may have other shapes that enhance fluid flow. Some nacelle bodies include an annular groove that promotes flow attachment. Maintaining airflow attachment to the nacelle body within the turbine increases the energy generation capacity of the wind turbine. | 03-10-2011 |
| 20110150640 | Labyrinth Seal in a Stationary Gas Turbine - A segmented inner ring for holding guide blades is provided. A lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially. Also a stationary gas turbine comprising a segmented inner ring is provided. | 06-23-2011 |
| 20090035130 | SHAPE OF GAS PASSAGE IN AXIAL-FLOW GAS TURBINE ENGINE - An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripheral concave portions (Cc | 02-05-2009 |
| 20100068045 | INLET GUIDE VANE - An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches. | 03-18-2010 |
| 20100054930 | TURBINE VANE WITH HIGH TEMPERATURE CAPABLE SKINS - A turbine vane assembly includes an airfoil extending between an inner shroud and an outer shroud. The airfoil can include a substructure having an outer peripheral surface. At least a portion of the outer peripheral surface is covered by an external skin. The external skin can be made of a high temperature capable material, such as oxide dispersion strengthened alloys, intermetallic alloys, ceramic matrix composites or refractory alloys. The external skin can be formed, and the airfoil can be subsequently bi-cast around or onto the skin. The skin and the substructure can be attached by a plurality of attachment members extending between the skin and the substructure. The skin can be spaced from the outer peripheral surface of the substructure such that a cavity is formed therebetween. Coolant can be supplied to the cavity. Skins can also be applied to the gas path faces of the inner and outer shrouds. | 03-04-2010 |
| 20100316493 | 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 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. | 12-16-2010 |
| 20110150641 | STEAM TURBINE AND STEAM TURBINE BLADE - A steam turbine | 06-23-2011 |
| 20080279679 | Multivane segment mounting arrangement for a gas turbine - A mounting arrangement ( | 11-13-2008 |
| 20080199310 | Axial flow turbine - An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight. | 08-21-2008 |
| 20100172748 | METHODS AND APPARATUS FOR REDUCING NOZZLE STRESS - A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane. | 07-08-2010 |
| 20110189002 | TURBINE GUIDE VANE - A turbine guide vane ( | 08-04-2011 |
| 20110020118 | TURBINE NOZZLE ASSEMBLY INCLUDING RADIALLY-COMPLIANT SPRING MEMBER FOR GAS TURBINE ENGINE - Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE. | 01-27-2011 |
| 20110110773 | TURBOMACHINE COMPRESSOR - Turbomachine compressor comprising variable-pitch vanes comprising an aerofoil section connected by a mounting plate ( | 05-12-2011 |
| 20080267772 | AEROFOIL MEMBERS FOR A TURBOMACHINE - A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centred on the axis of a turbomachine. Pressure and suction surfaces of neighbouring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row comprises at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. | 10-30-2008 |
| 20120207591 | COOLING SYSTEM HAVING REDUCED MASS PIN FINS FOR COMPONENTS IN A GAS TURBINE ENGINE - A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil. | 08-16-2012 |
| 20110052381 | COMBUSTOR TURBINE INTERFACE FOR A GAS TURBINE ENGINE - A turbine vane downstream of a combustor section includes an arcuate outer vane platform defined about an axis, the arcuate outer vane platform includes a segment of the arcuate outer vane platform along the axis which follows an outer combustor liner panel structure and an arcuate inner vane platform defined about the axis, the arcuate inner vane platform includes a segment of the arcuate inner vane platform along the axis which follows an inner combustor liner panel structure. | 03-03-2011 |
| 20120301285 | CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE TURBINE - A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring. | 11-29-2012 |
| 20100310360 | GUIDE VANE ASSEMBLY - A guide vane assembly for a turbomachine, comprising a guide vane and a liner: the guide vane comprising an aerofoil portion having a radially outer platform, wherein one of the outer platform and the liner has a hook element, the hook element comprising an opening and a circumferentially extending channel, and the other one of the outer platform and the liner comprises a retaining element having a head portion, wherein in an operational orientation the head portion located within the channel and is too wide to be withdrawn through the opening of the hook element. | 12-09-2010 |
| 20120063892 | BIDIRECTIONAL FAN HAVING SELF-ADJUSTING VANE - A bidirectional centrifugal fan having a self-adjusting vane is disclosed. In one embodiment, the fan includes a driving disc having a pivot pin extending therefrom; a vane pivotably attached to the pivot pin, the vane including an aperture extending at least partially therethrough; and a trailing disc including a guide arm for receiving the aperture of the vane. | 03-15-2012 |
| 20110103943 | Device for a Horizontally Split Turbomachine Housing, Guide Disc Segment and Guide Blade Carrier for a Horizontally Split Turbomachine Housing - A guide disc segment for a horizontally split turbomachine housing is provided. The guide disc segment includes a plurality of guide blades and an outer ring segment. The guide blades are fixed to the outer ring segment along an inner circumference. The outer ring segment can be rolled into or out of a guide blade carrier of the turbomachine housing. The outer ring segment has, along an outer circumference, a toothing into which a drive device engages. A tangential force can be applied to the outer ring segment by the toothing such that the guide disc segment can be driven during the rolling into or rolling out of the outer ring segment. | 05-05-2011 |
| 20120163964 | AXIAL RETENTION FEATURE FOR GAS TURBINE ENGINE VANES - A case assembly for a gas turbine engine is provided that includes an outer case with circumferentially spaced individual bosses that include a recess. A vane assembly is received in the outer case. An axial retention ring has uninstalled and installed conditions. The axial retention ring outside of the recess is in the uninstalled condition and received in the recess in the installed condition. An anti-rotation feature, such as a ring, is arranged between the bosses in a locking condition to prevent rotation of the axial retention ring between the installed and uninstalled conditions. | 06-28-2012 |
| 20110123322 | FLOW PASSAGE FOR GAS TURBINE ENGINE - Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage defined by the suction and pressure surface of two adjacent airfoils and endwalls (disposed proximal to the radially inner and outer ends of the airfoils). The flow passage includes a ridge disposed in one of the endwalls adjacent a suction surface of one of the airfoils, the ridge extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side to a downstream location proximal to the trailing edge of the suction surface. | 05-26-2011 |
| 20100196150 | BOUNDARY LAYER WIND TURBINE WITH TANGENTIAL ROTOR BLADES - A wind turbine having rotor assembly with a plurality of stacked disks ( | 08-05-2010 |
| 20120321454 | WIND POWER GENERATION APPARATUS - A wind power generation apparatus includes a wind collecting hood, a rotary shaft, a rotary structure and a wind guiding structure. The wind collecting hood is a hollow circular barrel to form an airflow passage. The rotary shaft is located in the airflow passage of the wind collecting hood. The rotary structure is mounted onto the rotary shaft. The wind guiding structure is fastened to the wind collecting hood and located at the front end of the rotary structure. The wind guiding structure directs direction of airflow and accelerates the airflow to become swirling airflow to directly blow the rotary structure at optimal angles, thus capability of driving the rotary structure to rotate by wind is increased and starting wind power of the rotary structure is reduced. The rotary structure is still rotated at where the wind is smaller to provide electric power. | 12-20-2012 |
| 20110158795 | CENTRIFUGAL PUMP IMPELLERS - A centrifugal pump impeller includes front and back shrouds and a plurality of pumping vanes therebetween, each pumping vane having a leading edge in the region of an impeller inlet and a trailing edge, the front shroud has an arcuate inner face in the region of the impeller inlet, the arcuate inner face having a radius of curvature (R | 06-30-2011 |
| 20120275911 | Gas Turbine Stator Vane - A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion. | 11-01-2012 |
| 20120093635 | AXIAL FLOW FAN - An axial flow fan includes an impeller rotatable about a central axis with a plurality of rotor vanes, a motor that drives the impeller, a base portion that supports the motor, a housing that includes an intake vent, an exhaust vent, and an inner peripheral surface surrounding the impeller and the motor, and a plurality of stator vanes that respectively connects the base portion and the housing, wherein the inner peripheral surface includes a first inner peripheral surface arranged to increase a distance from the central axis toward the intake vent or the exhaust vent in an axial direction, and a recess provided between the first inner peripheral surface and a stator vane included in the plurality of stator vanes and facing the first inner peripheral surface. Thus, airflow is allowed to smoothly pass through the housing, resulting in a decrease in noise generated in the fan. | 04-19-2012 |
| 20120328426 | AIR TURBINE STARTER TURBINE NOZZLE AIRFOIL - A vane profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Z-coordinates. | 12-27-2012 |
| 20130022454 | AIR TURBINE STARTER - A blade profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Z-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip. | 01-24-2013 |
| 415193000 | Plural, axially spaced vane sets | 10 |
| 20090123276 | STEAM TURBINE - A steam turbine is provided having a rotor which rotates around a machine axis, and a stator which concentrically encompasses the rotor with clearance, between which an annular passage is formed which is exposed to throughflow by steam in the axial direction and in which a multiplicity of rotor blades, which are fastened on the rotor, and fixed stator blades are arranged in a plurality of stages, wherein the stator blades of the last stage have a sweep with a sweep angle which changes in sign over the relative blade height. | 05-14-2009 |
| 20100111684 | TURBINE AIRFOIL CLOCKING - An assembly of airfoils in a turbine engine, the assembly comprising: at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row; wherein the first airfoil row and the third airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; and wherein at least a majority of the mid-channel points of the airfoils in the third airfoil row are positioned circumferentially within +/−25% pitch of the third airfoil row with respect to the location at which a wake flow during a selected operating condition from the first airfoil row is determined to enter the third airfoil row. | 05-06-2010 |
| 20130089415 | GAS TURBINE WITH OPTIMIZED AIRFOIL ELEMENT ANGLES - A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 3, 5 and 7. | 04-11-2013 |
| 20090169371 | STATOR CASCADE OF TURBO TYPE FLUID MACHINE - In the invention, stator blades are arranged in such a manner that respective intervals between the adjacent stator blades (SV) become unequal at least partly. If the stator blades are arranged as mentioned above, there are formed wave fronts having different moving directions and phases, and these wave fronts are interfered with each other so as to be attenuated. Accordingly, an interference noise is reduced. Therefore, in accordance with the invention, it is possible to reduce an interference noise without enlarging a rotor stator blade interval as well as reducing a used amount of a sound absorption material. | 07-02-2009 |
| 20090068001 | STEAM TURBINE - A steam turbine has a stationary section, a turbine rotor, nozzle diaphragms, and a nozzle box. The stationary section includes a casing. The turbine rotor includes moving blade stages arranged in an axial direction. Each of the moving blade stages is provided with moving blades arranged in a circumferential direction, and rotatably provided in the casing. Each of the nozzle diaphragms has turbine nozzles arranged in the circumferential direction provided substantially coaxially with the turbine rotor by being secured to the stationary section. The nozzle box is supported on the stationary section and arranged at an upstream part of the moving blade stages substantially coaxially with the turbine rotor so as to lead steam flowing toward the turbine moving blades. The nozzle box holds at least two stages of the nozzle diaphragms. | 03-12-2009 |
| 20100158678 | AIRFOIL SHAPE FOR A TURBINE NOZZLE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. | 06-24-2010 |
| 20100172749 | WALL OF TURBO MACHINE AND TURBO MACHINE - The invention relates to wall of a turbo machine having a cascade of blades. The wall includes: a first platform facing a first passage between blades in the cascade of blades; and a second platform facing a second passage between adjacent cascade of blades on an upstream side and cascade of blades on a downstream side, and having a circumferential outline having a distribution of radial positions. According to the invention, loss due to disturbance of flow through the gap of axially adjacent walls can be reduced. | 07-08-2010 |
| 20110318174 | Compressor Rectifier Architecture - The present invention relates to a turbomachine rectifier comprising a plurality of stator vanes ( | 12-29-2011 |
| 415194000 | Diverse size or spacing in different spaced vane sets | 2 |
| 20090155062 | METHOD OF DESIGNING A MULTISTAGE TURBINE FOR A TURBOMACHINE - A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the airfoils of said rows to straighten out the wakes from the trailing edges of said airfoils, then in angularly positioning the rows in such a manner that the wakes from the airfoils of the stator (or rotor) airfoils impact against the leading edges of the stator (or rotor, respectively) airfoils of the rows situated downstream, in order to achieve multistage aerodynamic coupling simultaneously over the turbine as a whole. | 06-18-2009 |
| 20080286095 | Centrifugal Compressor Return Passages Using Splitter Vanes - A return section in a multistage centrifugal compressor includes a plurality of circumferentially positioned flow vanes, and a plurality of splitter vanes disposed between the flow vanes. The splitter vanes serve to minimize or eliminate regions of reverse or separated flow, resulting in improved compressor performance. | 11-20-2008 |
