With Diversely Oriented Inlet Or Additional Inlet For Diverse Fluid (e.g., Heating, Cooling Or Mixed Working Fluid, Etc.) Patents (Class 415/116)
  • Patent number: 9828880
    Abstract: A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: Henry Grady Ballard, Jr., Ozgur Bozkurt, Kenneth Damon Black, Radu Ioan Danescu
  • Patent number: 9822698
    Abstract: A centrifugal compressor for a turbocharger includes a passive or semi-passive inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position solely by aerodynamic forces on the mechanism. The inlet-adjustment mechanism includes a plurality of flexible vanes collectively forming a duct, and an effective diameter of the air inlet at the inducer portion of the compressor wheel is determined by a trailing edge inside diameter of the duct. The vanes are movable solely or in part by aerodynamic forces exerted on the vanes by the air flowing to the compressor wheel. The duct has a tapering configuration when the vanes are in a relaxed state, but under aerodynamic force the vanes flex outwardly and increase the trailing edge inside diameter of the duct, thereby increasing an effective diameter of the air inlet.
    Type: Grant
    Filed: February 6, 2015
    Date of Patent: November 21, 2017
    Assignee: Honeywell International Inc.
    Inventors: Hani Mohtar, Stephane Pees, Pascal Delapierre, William Joseph Smith, Pascal Villemin
  • Patent number: 9803652
    Abstract: A centrifugal compressor having at least a diffuser is disclosed. The diffuser has an annular diffuser body having circumferentially spaced apart diffuser passages defining fluid paths through the diffuser body. The diffuser also has a plurality of diffusion members mounted to the annular diffuser body. Each diffusion member has a member inlet in fluid communication with a diffuser passage and a member outlet. Each diffusion member defines an aerodynamic throat disposed between the member inlet and the member outlet. The diffuser also has a fluid injection assembly with multiple injection conduits. Each injection conduit extends between a conduit inlet configured to receive a flow of compressible fluid from a supply and a conduit outlet communicating with a corresponding diffusion member downstream of the aerodynamic throat. The compressible fluid is injected through the conduit outlet into the diffusion members.
    Type: Grant
    Filed: February 10, 2014
    Date of Patent: October 31, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Peter Townsend, Vijay Kandasamy, Koundinya Upadrasta
  • Patent number: 9803491
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.
    Type: Grant
    Filed: December 31, 2012
    Date of Patent: October 31, 2017
    Assignee: United Technologies Corporation
    Inventors: Brian Ellis Clouse, David F. Cloud, Donna Clough
  • Patent number: 9803501
    Abstract: A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.
    Type: Grant
    Filed: January 28, 2015
    Date of Patent: October 31, 2017
    Assignee: United Technologies Corporation
    Inventor: Cheng-Zhang Wang
  • Patent number: 9790953
    Abstract: A multi or single-stage turbocompressor with at least one compressor wheel fastened to a shaft. The shaft is mounted in a turbocompressor housing which, behind the hub disc of the compressor wheel, includes an interior housing region as well as in front of the hub disc of the compressor wheel a front interior housing region. The driven compressor wheel delivers a fluid from an inlet channel to an outlet channel. The front interior housing region includes a wheel lateral space from which an extraction channel for the extraction of fluid is provided.
    Type: Grant
    Filed: April 15, 2008
    Date of Patent: October 17, 2017
    Assignee: MAN Diesel & Turbo SE
    Inventors: George Kleynhans, Peter Ortmann, Roger Suter
  • Patent number: 9770693
    Abstract: A homogenization apparatus for at least two fluid flows for homogeneous gas/air mixing in a gas engine, in which at least two fluid feed lines conducting different fluid flows and one fluid outflow line conducting the homogenized fluid are connected to a central homogenization space as mixing region. In a connection region upstream of the homogenization space, the fluid feed lines have in each case one line section with a flow deflection in one direction with a flow deflection which follows downstream in the other direction and are connected in such a way that the fluid flows are fed tangentially to the homogenization space with a swirl movement imparted to them, in such a way that a rotating, turbulent flow which assists the homogenization process is formed in the homogenization space.
    Type: Grant
    Filed: March 23, 2015
    Date of Patent: September 26, 2017
    Assignee: MAN TRUCK & BUS AG
    Inventors: Bruno Barciela, Joachim Weiβ
  • Patent number: 9759088
    Abstract: A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.
    Type: Grant
    Filed: May 15, 2012
    Date of Patent: September 12, 2017
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jacques René Bart
  • Patent number: 9752587
    Abstract: The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot.
    Type: Grant
    Filed: June 11, 2014
    Date of Patent: September 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Benjamin E. Fishler
  • Patent number: 9732885
    Abstract: A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: August 15, 2017
    Assignee: SNECMA
    Inventors: Arthur Cohin, Baghdad Achbari, Audrey Charrie, Aurélien René-Pierre Massot
  • Patent number: 9683444
    Abstract: An air hot part of a gas turbine engine, the hot part having an isogrid formed on a cool surface opposite to a hot surface, where an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: June 20, 2017
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Russell B Jones
  • Patent number: 9677423
    Abstract: An aft hub sealing assembly for a gas turbine engine is disclosed. The aft hub sealing assembly includes an aft hub, a bearing cap, an aft baffle, a first seal, and a second seal. The aft hub includes a body portion and a disk portion aft surface. The bearing cap includes a bearing cap inner portion spaced apart from the body portion. The aft baffle is located adjacent the disk portion. The aft baffle includes a baffle forward surface following a contour of the disk portion aft surface. The first seal is between the bearing cap inner portion and the body portion. The second seal is between the bearing cap inner portion and the body portion.
    Type: Grant
    Filed: June 20, 2014
    Date of Patent: June 13, 2017
    Assignee: Solar Turbines Incorporated
    Inventor: Leslie John Faulder
  • Patent number: 9677475
    Abstract: A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel. Compressor blades extend radially outward from the outer portion which provides an inner core flow path. A rotor spoke is configured to receive a first cooling flow and fluidly connect the outer portion to the cooling channel. The compressor rotor assembly has a coolant exit that is in fluid communication with the cooling channel. The compressor rotor assembly is configured to communicate the first cooling flow to the turbine rotor. A bleed source is configured to provide a second cooling flow. A combustor section includes an injector in fluid communication with the bleed source. The tangential onboard injector is configured to communicate the second cooling flow to the turbine rotor.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: June 13, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Patent number: 9664062
    Abstract: An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: May 30, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon
  • Patent number: 9657585
    Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.
    Type: Grant
    Filed: November 5, 2013
    Date of Patent: May 23, 2017
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yasuo Takahashi, Tetsuro Morisaki, Chihiro Myoren, Kohta Kawamura
  • Patent number: 9644642
    Abstract: An axial compressor that can remove an attachment within a groove of a casing and recover an effect of suppressing stall on rotor blades, and a gas turbine provided with the axial compressor, are provided. The axial compressor includes a compressor body 6 and a sprayer 9 for spraying droplets in suction gas of the compressor body 6 so that the droplets are introduced into the compressor body 6 and evaporate. The compressor body 6 includes a casing 11, a rotor 12, rotor blades 13, and stator vanes 14. A groove 21 is formed in an inner circumferential surface of the casing 11 so as to be positioned around rotor blades 13 arranged on a front stage side. A purge system 23 is provided that supplies high-pressure air to the groove 21 through communication holes 22.
    Type: Grant
    Filed: May 30, 2013
    Date of Patent: May 9, 2017
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yasuo Takahashi, Chihiro Myoren, Kohta Kawamura
  • Patent number: 9598974
    Abstract: A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.
    Type: Grant
    Filed: February 25, 2013
    Date of Patent: March 21, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eugene Gekht, Terrence Lucas, Thomas Francis Haslam-Jones, Danny Mills, Guy Bouchard
  • Patent number: 9541003
    Abstract: A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow.
    Type: Grant
    Filed: February 12, 2014
    Date of Patent: January 10, 2017
    Assignee: Rolls-Royce Corporation
    Inventor: Robert T. Duge
  • Patent number: 9534607
    Abstract: Provided is a compressor for use in a gas turbine engine, capable of preventing a creation of rust on an inner surface of the compressor casing, without complicating assembling process. The casing 15 of the compressor 3 accommodates rotor and stator blade wheels 13 and 17. The stator blade wheels 17 are supported on the inner surface of the casing 15 through outer flanges 30 thereof. Seal rings 52 are provided at inner surface portions of the casing 15 opposing the radially outward ends of the rotor blade wheels 13. The inner surface of the casing 15 is covered by the seal rings 52 and the outer flanges 30 of the stator blade wheels 17.
    Type: Grant
    Filed: March 2, 2011
    Date of Patent: January 3, 2017
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Takuya Ikeguchi, Koji Terauchi
  • Patent number: 9488060
    Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating.
    Type: Grant
    Filed: October 9, 2013
    Date of Patent: November 8, 2016
    Assignee: General Electric Company
    Inventor: Michael John Bowman
  • Patent number: 9488069
    Abstract: A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel (14) in which guide vanes and rotor vanes are arranged. The housing structure has an inner wall (2) that delimits the flow channel and an outer wall (1) that is closed off vis-à-vis the environment. A heat-protection plate (3) is arranged on the radial outside of the inner wall, and insulation (4) is arranged between the heat-protection plate and the outer wall. At least one cooling-air channel (6) is formed between the insulation and the radial inside of the outer wall, the cooling-air channel (6) having at least one air-guiding element (5) resting against the insulation.
    Type: Grant
    Filed: October 22, 2013
    Date of Patent: November 8, 2016
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Norbert Schinko, Christian Eichler, Sebastian Kaltenbach
  • Patent number: 9482112
    Abstract: A turbine has a first and second inner wall, an inner casing and a shield element. The first and second inner walls are mounted to the inner casing such that an inner volume for working fluid is separated from an outer volume for cooling fluid. The first and second inner walls and inner casing are arranged to form a cavity in outer volume. The shield element is arranged inside cavity to separate cavity in an inner and outer region in a radially outer position to the inner region. A gap is formed between the first and second inner walls for working fluid between the inner volume and inner region. The shield element is arranged in cavity to form a fluid inlet for injecting cooling fluid from outer region to inner region for generating a predefined recirculation of working fluid and cooling fluid inside inner region.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: November 1, 2016
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Andrew Down
  • Patent number: 9458731
    Abstract: The present application provides a turbine shroud cooling system for a gas turbine engine. The turbine shroud cooling system may include a number of variable area cooling shrouds with tuning pins and a number of fixed area cooling shrouds with anti-rotation pins. The variable area cooling shrouds may include modulated cooling shrouds. The fixed area shrouds may include non-modulated shrouds.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: October 4, 2016
    Assignee: General Electric Company
    Inventors: Charles Lewis Davis, III, Terry Howard Strout, Pawel Piotr Kolniak
  • Patent number: 9446417
    Abstract: Centrifuges have been designed in the past for centrifuging multi-welled containers, but they are limited in centripetal acceleration or have a large footprint. The invention provides a centrifuge with a high centripetal acceleration and imbalance tolerance while maintaining a small footprint and being able to integrate with laboratory automation equipment. Methods and apparatuses for centrifugation include a rotor assembly positioned within a shield assembly suspended in a centrifuge. The rotor assembly is operably connected to the motor for rotating payloads (e.g., multi-welled containers) around an axis. The shield assembly is positioned such that the center of mass is aligned with the axis of rotation of the rotor assembly and the plane containing the rotational imbalance force vector. This alignment allows rotation of the container with an acceleration of at least 2000 g (or at least 3000 g, 4000 g, 5000 g, etc.).
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: September 20, 2016
    Assignee: BioNex Solutions, Inc.
    Inventors: Stephen Gaudio, Eric Rollins
  • Patent number: 9435848
    Abstract: In an embodiment, a chuck to support a solar cell in hot spot testing is provided. This embodiment of the chuck comprises a base portion and a support portion disposed above the base portion. The support portion is configured to support the solar cell above the base portion and to define a cavity between a bottom surface of the solar cell and the base portion that thermally separates a portion of the bottom surface of the solar cell from the base portion.
    Type: Grant
    Filed: July 22, 2015
    Date of Patent: September 6, 2016
    Assignee: SunPower Corporation
    Inventors: Jose Francisco Capulong, Emmanuel Abas
  • Patent number: 9433126
    Abstract: A centrifugal fan includes an impeller and a housing. The housing includes an upper plate, a lower plate and a side wall, wherein the upper plate axially corresponds to the lower plate, a side wall is formed between the upper plate and the lower plate, an axial inlet is formed on the upper plate, a lateral outlet is formed on the side wall, the impeller is disposed in the housing and corresponds to the inlet, and a flow path communicates the inlet to the outlet. The housing further includes a guiding groove, and at least one auxiliary inlet is formed in the guiding groove.
    Type: Grant
    Filed: September 13, 2012
    Date of Patent: August 30, 2016
    Assignee: DELTA ELECTRONICS, INC.
    Inventor: Chao-Wen Lu
  • Patent number: 9422824
    Abstract: Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.
    Type: Grant
    Filed: October 18, 2012
    Date of Patent: August 23, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, David Martin Johnson, Radu Ioan Danescu
  • Patent number: 9416684
    Abstract: A structure and method are provided for preventing or at least minimizing thermally-induced structural distortions, such as may occur when a steam turbine is cooling down. The steam turbine may include an inner housing and an outer housing. An intermediate space is formed between the inner housing and the outer housing, and sealing steam may be injected into the intermediate space to avoid the formation of temperature strata in the interspace and thus prevent the outer housing from bowing.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: August 16, 2016
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Frank Deister, Ingo Forster, Daniel Gloss, Christian Musch, Heinrich Stuer, Frank Truckenmuller
  • Patent number: 9416672
    Abstract: A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner.
    Type: Grant
    Filed: October 11, 2013
    Date of Patent: August 16, 2016
    Assignee: MTU AERO ENGINES AG
    Inventors: Manfred Feldmann, Janine Sangl, Sebastian Kaltenbach, Joachim Lorenz
  • Patent number: 9404379
    Abstract: Embodiments of the present disclosure include a gas turbine shroud assembly. The shroud assembly may include a shroud structure that defines a first cooling chamber and a second cooling chamber. The shroud assembly may also include a first impingement plate disposed within the first cooling chamber and a second impingement plate disposed within the second cooling chamber. Further, the shroud assembly may include one or more cooling channels formed within the shroud structure. The cooling channels may be configured to connect the first cooling chamber with the second cooling chamber. The shroud assembly may also include a flow of cooling air in communication with the first cooling chamber. In this manner, the flow of cooling air may flow from the first cooling chamber to the second cooling chamber by way of the one or more cooling channels.
    Type: Grant
    Filed: April 2, 2013
    Date of Patent: August 2, 2016
    Assignee: General Electric Company
    Inventor: Niraj K. Mishra
  • Patent number: 9371776
    Abstract: A jet engine having an air intake and a compression section having first and second separate flow paths coupled to the air intake, the second flow path containing a fuel rich, fuel air mixture having an equivalence rate above the mixture flammability limit, the first flow path containing only air, a burner turbine section, the compression section being coupled directly to the burner turbine section, and means for injecting air from the first flow path into the fuel rich fuel air mixture of the said flow path in the burner turbine section to generate intraturbine diffusion layer burning of said fuel air mixture.
    Type: Grant
    Filed: August 20, 2013
    Date of Patent: June 21, 2016
    Inventor: Darren Levine
  • Patent number: 9353641
    Abstract: A turbine engine including a controller controlling clearance between tips of moving blades of a high-pressure turbine and an outer casing surrounding the blades, by cooling the outer casing by the impact of air taken from a high-pressure compressor stage of the engine, and by electric heating of top and bottom portions of the outer casing.
    Type: Grant
    Filed: September 7, 2010
    Date of Patent: May 31, 2016
    Assignee: SNECMA
    Inventor: Vincent Philippot
  • Patent number: 9353634
    Abstract: A turbine blade cooled by an automatically variable internal flow of cooling fluid. The blade includes orifices situated under the blade root via which the cooling fluid penetrates, and an adjustment plate including holes situated in register with the orifices, the adjustment plate having a coefficient of expansion that is different from the coefficient of expansion of the blade root.
    Type: Grant
    Filed: October 16, 2009
    Date of Patent: May 31, 2016
    Assignee: SNECMA
    Inventors: Regis Grohens, Renaud Gabriel Constant Royan
  • Patent number: 9322415
    Abstract: A high pressure compressor includes an inner case wall, a plurality of flanges extending outwardly from the inner case wall, a shield that surrounds at least a portion of at least one of the plurality of flanges to define a chamber that at least partially encases at least one of the plurality of flanges, and a passage at least partially defined by the shield that allows air to circulate into the chamber.
    Type: Grant
    Filed: October 29, 2012
    Date of Patent: April 26, 2016
    Assignee: United Technologies Corporation
    Inventor: Philip Robert Rioux
  • Patent number: 9309777
    Abstract: A tip clearance control device adapted to control the clearance of a rotating aerofoil structure with a surrounding casing portion, and a method of controlling the tip clearance of a rotating aerofoil structure with a surrounding casing portion. The device includes a member operatively connected to the casing portion; the member having at least a first configuration in which the casing portion is at a first radial position and a second configuration in which the casing portion is at a second radial position, wherein the configuration of the member is controlled by magnetic flux in a magnetic circuit which includes at least one ferromagnetic element including ferromagnetic material, where the configuration of the member is responsive to the temperature of the ferromagnetic element.
    Type: Grant
    Filed: July 12, 2012
    Date of Patent: April 12, 2016
    Assignee: ROLLS-ROYCE plc
    Inventors: John R. Webster, Nicolas Evanno, Brian Handley
  • Patent number: 9255489
    Abstract: A section of a gas turbine engine includes a case structure having a first coefficient of thermal expansion. A continuous, ring-shaped liner has a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion. A flexible leaf member operatively connects the liner to the case structure. The leaf member is configured to accommodate diametrical change in the liner throughout various fan section operating temperatures.
    Type: Grant
    Filed: February 6, 2012
    Date of Patent: February 9, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: John C. DiTomasso, Thomas J. Robertson, Gregory E. Reinhardt
  • Patent number: 9255479
    Abstract: A high-pressure compressor (12), in particular in a gas turbine (10), has a compressor rotor (17) which is surrounded by a stator (18, 19) thereby forming a main flow channel (25) and which is delimited at the compressor outlet by an end face (30) substantially extending in the radial direction, along which end face cooling air (21) is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face (30) is provided with a first system (23, 24) for improving the heat transfer between the cooling air (21) and the end face (30).
    Type: Grant
    Filed: December 5, 2012
    Date of Patent: February 9, 2016
    Assignee: ALSTOM TECHNOLOGY LTD
    Inventors: Ernst Pauli, Sergey Shchukin, Daniel Seng
  • Patent number: 9238971
    Abstract: A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.
    Type: Grant
    Filed: October 18, 2012
    Date of Patent: January 19, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, David Martin Johnson, Radu Ioan Danescu
  • Patent number: 9206815
    Abstract: A centrifugal fan includes a plurality of fan blades arranged spaced apart from each other in a circumferential direction. The fan blade has an inner edge portion disposed on an inner peripheral side and an outer edge portion disposed on an outer peripheral side. The fan blade has a blade surface including a pressure surface and a suction surface. When cut along a plane orthogonal to a rotation axis of the fan, the fan blade has a blade cross section having concave portions formed at the pressure surface and the suction surface. A plurality of fan blades include fan blades having blade cross sections of different shapes. With such a configuration, the fan has an excellent air-blowing capacity while preventing noise. A molding die for use in production of the fan and a fluid feeder including the fan are also provided.
    Type: Grant
    Filed: March 7, 2011
    Date of Patent: December 8, 2015
    Assignee: SHARP KABUSHIKI KAISHA
    Inventors: Yukishige Shiraichi, Masaki Ohtsuka
  • Patent number: 9188136
    Abstract: A disc for a fan rotor (with a pilot to connect to a rotating shaft, a hub and a plurality of blades) includes a flat circular portion connecting to the pilot at an inner edge and to the hub at an outer edge; a plurality of first circular cooling holes of a first diameter located around the inner edge of the disc; and a plurality of second circular cooling holes of a second diameter located around the outer edge of the disc, wherein the second diameter is larger than the first diameter.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: November 17, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Darryl A. Colson, Brent J. Merritt, Danielle Mansfield-Marcoux
  • Patent number: 9175607
    Abstract: A heat-resistant apparatus comprising a plurality of rigid, fireproof panels mounted to an inner surface of an inner fixed structure (IFS) of an aircraft thrust reverser. The plurality of panels may include fixed panels and floating panels, with the fixed panels fastened directly to the IFS and the floating panels fastened to the fixed panels in a substantially checkered arrangement along the inner surface of the IFS. The fixed and floating panels may each comprise a rigid core surrounded by various fireproof or heat resistant materials. The fixed and floating panels may be configured and affixed to the IFS such that air from an engine's fan may flow through a space between the panels and the IFS, providing additional cooling and heat resistance.
    Type: Grant
    Filed: January 18, 2011
    Date of Patent: November 3, 2015
    Assignee: Spirit AeroSystems, Inc.
    Inventor: John M. Welch
  • Patent number: 9169729
    Abstract: A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).
    Type: Grant
    Filed: September 26, 2012
    Date of Patent: October 27, 2015
    Assignee: Solar Turbines Incorporated
    Inventor: Hongzhou Xu
  • Patent number: 9157331
    Abstract: The present invention comprises a gas turbine engine with a compressor for generating compressed air, a turbine comprising upstream and downstream rows of vanes, vane carrier structure surrounding at least one row of vanes and plenum structure at least partially surrounding the vane carrier structure capable of impinging compressed air onto the vane carrier structure. The gas turbine engine further comprises fluid supply structure including first fluid path structure defining a first path for compressed air to travel to the plenum structure, second fluid path structure defining a second path for compressed air to travel toward the downstream row of vanes, and fluid control structure selectively controlling fluid flow to the first and second fluid path structures.
    Type: Grant
    Filed: December 8, 2011
    Date of Patent: October 13, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventor: Vincent P. Laurello
  • Patent number: 9151179
    Abstract: The present embodiments are generally directed toward systems and methods for cooling one or more shroud segments of a gas turbine engine. For example, in a first embodiment, a shroud segment is provided that is configured to at least partially surround a turbine blade of a turbine engine. The shroud segment includes a body and a microchannel disposed in the body. The microchannel is configured to flow a cooling fluid through the body.
    Type: Grant
    Filed: April 13, 2011
    Date of Patent: October 6, 2015
    Assignee: General Electric Company
    Inventors: Benjamin Paul Lacy, Stephen William Tesh, David Wayne Weber
  • Patent number: 9151163
    Abstract: A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area.
    Type: Grant
    Filed: November 29, 2012
    Date of Patent: October 6, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Matthias Siebel, Heinz Rauschmair, Andreas Hoelzel
  • Patent number: 9151164
    Abstract: A turbine vane of a gas turbine engine is provided with a hollow core in the leading edge of the outer platform thereof. The core is interconnected with the leading edge core of the airfoil whereby to create a cooling air stream having a dual purpose and cooling both the leading edge of the outer platform and of the airfoil and thereby reducing cooling air consumption. The cooling air enters the core of the outer platform through an inlet port and exits through cooling holes provided in the leading edge of the airfoil.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: October 6, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Marc Tardif, Sri Sreekanth, Eric Durocher
  • Patent number: 9127549
    Abstract: A turbine shroud cooling assembly for a gas turbine system includes an outer shroud component disposed within a turbine section of the gas turbine system and proximate a turbine section casing, wherein the outer shroud component includes at least one airway for ingesting an airstream. Also included is an inner shroud component disposed radially inward of, and fixedly connected to, the outer shroud component, wherein the inner shroud component includes a plurality of microchannels extending in at least one of a circumferential direction and an axial direction for cooling the inner shroud component with the airstream from the at least one airway.
    Type: Grant
    Filed: April 26, 2012
    Date of Patent: September 8, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Benjamin Paul Lacy, David Edward Schick, David Wayne Weber
  • Patent number: 9109842
    Abstract: A fuel air heat exchanger for a gas turbine engine having fuel and air conduits in heat exchange relationship with one another, and a distribution conduit in heat exchange relationship with a component to be cooled. The distribution conduit is in fluid communication with the outlet of each air conduit. The heat exchanger also includes a secondary air inlet in fluid communication with the distribution conduit and a flow selection member selectively movable between first and second configurations. In the first configuration, the flow selection member closes the fluid communication between the secondary inlet and the distribution conduit. In the second configuration, the flow selection member opens the fluid communication between the secondary air inlet and the distribution conduit.
    Type: Grant
    Filed: February 24, 2012
    Date of Patent: August 18, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Eduardo Hawie
  • Patent number: 9103225
    Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
    Type: Grant
    Filed: June 4, 2012
    Date of Patent: August 11, 2015
    Assignee: United Technologies Corporation
    Inventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
  • Patent number: 9097142
    Abstract: A first structural static component having an outer diameter is aligned with a second structural static component having an inner diameter to the centerline of a gas turbine engine rotating assembly. The first static component is centered inside the second static component leaving a gap between the outer diameter of the first component and the inner diameter of the second component to permit them to mate at operating temperatures. Tabs and slots are placed on the periphery of the static components to align the static components with the centerline at build temperature.
    Type: Grant
    Filed: June 5, 2012
    Date of Patent: August 4, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: David Ronald Adair, Pete Simpson