With Passage In Blade, Vane, Shaft Or Rotary Distributor Communicating With Working Fluid Patents (Class 415/115)
  • Patent number: 11959389
    Abstract: A turbine shroud segment has a shroud body including a platform having forward and aft hooks extending from a radially outer surface of the platform for engagement with a shroud support structure of a turbine support case. A pin receiving hole is defined in the shroud body. An anti-rotation pin is engaged in the pin receiving hole. The anti-rotation pin projects outwardly from the pin receiving hole for engagement with a corresponding anti-rotation abutment on the shroud support structure.
    Type: Grant
    Filed: June 11, 2021
    Date of Patent: April 16, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jocelyn Bisson, Guy Lefebvre
  • Patent number: 11952918
    Abstract: A stator vane includes a platform that defines an opening. The stator vane further includes an airfoil that has a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. At least one of the base or the tip includes a protrusion. The protrusion extends into the opening of the platform such that the platform surrounds the protrusion of the airfoil. The stator vane further includes a braze joint disposed between and fixedly coupling the platform and the protrusion of the airfoil. The stator vane further includes a cooling circuit defined in at least one of the protrusion or the platform to cool the braze joint.
    Type: Grant
    Filed: July 20, 2022
    Date of Patent: April 9, 2024
    Assignee: GE Infrastructure Technology LLC
    Inventors: Matthew Troy Hafner, John M. Matthews, Zachary John Snider
  • Patent number: 11933192
    Abstract: A turbine vane includes an airfoil having a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, and an outer shroud disposed opposite to the inner shroud at the other end of the airfoil to support the airfoil, wherein a corner part is formed at a portion where the airfoil and the inner shroud or the outer shroud meet, the corner part including a first round portion connected in an arc shape to the inner shroud or the outer shroud, a first inclined portion connected to the first round portion and outwardly extending in an inclined shape, and a second round portion connected to the first inclined portion and outwardly extending in an arc shape.
    Type: Grant
    Filed: September 25, 2022
    Date of Patent: March 19, 2024
    Assignee: DOOSAN ENERBILITY CO., LTD.
    Inventor: Hyun Woo Joo
  • Patent number: 11927110
    Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.
    Type: Grant
    Filed: January 24, 2022
    Date of Patent: March 12, 2024
    Assignee: General Electric Company
    Inventors: Zachary Daniel Webster, Aaron Ezekiel Smith, Gregory Terrence Garay, Kirk D. Gallier
  • Patent number: 11913359
    Abstract: The disclosure provides a nozzle adapted for placement within a flowpath of a turbomachine. The nozzle includes an airfoil having a suction side; a pressure side opposing the suction side; a leading edge between the pressure side and the suction side; a trailing edge opposing the leading edge and between the pressure side and the suction side; a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region. An endwall is connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge, and the leading edge. The trailing edge of the airfoil has an elliptical shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE I.
    Type: Grant
    Filed: June 30, 2023
    Date of Patent: February 27, 2024
    Assignee: GE Infrastructure Technology LLC
    Inventors: James Robert Einwaechter, Matthew Scott Lutz, Michael John Williams, Jr.
  • Patent number: 11913350
    Abstract: The present invention relates to a turbine injector comprising an annular ring extending around a longitudinal axis and having a radially outer edge and a radially inner edge. The crown has a plurality of channels for fluidly connecting the radially outer edge to the radially inner edge, each channel extending in a radial plane of the ring and having an inlet opening near the outer edge and an outlet opening near the radially inner edge, the orientation of each channel varying progressively according to a tangential component between the inlet section of the inlet opening and the outlet section of the outlet opening.
    Type: Grant
    Filed: October 8, 2020
    Date of Patent: February 27, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jérôme Claude George Lemonnier, Franck Davy Boisnault, Nicolas Li Yen Kuhn, Antoine Bruno Van Noort
  • Patent number: 11905849
    Abstract: Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.
    Type: Grant
    Filed: October 17, 2022
    Date of Patent: February 20, 2024
    Assignee: RTX CORPORATION
    Inventors: Brandon W. Spangler, David R. Pack
  • Patent number: 11905975
    Abstract: A compressor includes a housing and a mixed-flow rotor mounted within the housing. The mixed-flow rotor includes a blade and a rotor hub with an interior flow passage. The blade includes an internal channel between a pressure surface and a suction surface of the blade. The internal channel extends radially within the blade and is in fluidic communication with the interior flow passage. The blade also includes a plurality of air outlets formed on the blade proximate a leading edge of the blade. The plurality of air outlets extends into the blade to fluidically connect with the internal channel.
    Type: Grant
    Filed: August 10, 2022
    Date of Patent: February 20, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Ousmane Gaye, Viktor Kilchyk
  • Patent number: 11905881
    Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.
    Type: Grant
    Filed: August 24, 2021
    Date of Patent: February 20, 2024
    Assignee: General Electric Company
    Inventors: Daniel Endecott Osgood, Jonathan Russell Ratzlaff, Kirk D. Gallier
  • Patent number: 11898572
    Abstract: An impeller wake vortex dissipation device under stall condition of a mixed flow pump includes a guide vane and a wake vortex dissipation device. The pump is evenly divided into n guide vane channels by N evenly distributed guide vanes. A wake vortex dissipation device is set in each guide vane channel, and one end of the wake vortex dissipation device is fixedly connected to the inner wall of the pump body. Therefore, each wake vortex dissipation device is located in the middle and upper part of the guide vane channel and does not occupy the lower guide vane channel; the wake vortex dissipation device is provided with a dissipative hole pair, which are used to dissipate the energy of the wake vortex of the impeller.
    Type: Grant
    Filed: July 16, 2021
    Date of Patent: February 13, 2024
    Assignee: JIANGSU UNIVERSITY
    Inventors: Wei Li, Leilei Ji, Ling Zhou, Yong Zhu, Sizhuo Ma, Handong Qi
  • Patent number: 11898459
    Abstract: Disclosed is a turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes being located in an airfoil of the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.
    Type: Grant
    Filed: July 1, 2022
    Date of Patent: February 13, 2024
    Assignee: RTX CORPORATION
    Inventors: Emma J. Place, Dominic J. Mongillo, Jr., Jeremy B Fredette
  • Patent number: 11898463
    Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings. Each ring is comprised of inner and outer platform sections, a suction side wall that extends between the inner and outer platforms, and a pressure side wall that extends between the inner and outer platforms. the first ring mates at an interface with the second ring such that the suction side wall of the first ring and the pressure side wall of the second ring together form an airfoil that circumscribes an internal cavity. The interface along the airfoil includes a gap that is configured to emit cooling air from the internal cavity.
    Type: Grant
    Filed: March 29, 2021
    Date of Patent: February 13, 2024
    Assignee: RTX CORPORATION
    Inventor: Jon E. Sobanski
  • Patent number: 11891954
    Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine.
    Type: Grant
    Filed: August 12, 2021
    Date of Patent: February 6, 2024
    Assignees: General Electric Company Polska sp. z o.o., General Electric Company
    Inventors: Adam Tomasz Paziński, Miroslaw Sobaniec, Christopher N. Delametter
  • Patent number: 11891920
    Abstract: A turbine stator vane includes: a vane body which includes: an airfoil portion which has a serpentine flow passage inside thereof, the serpentine flow passage including a plurality of cooling flow passages and a plurality of turn-back flow passages; a shroud disposed on at least one of a tip end side or a root end side, in the vane height direction, of the airfoil portion; and a lid portion fixed to the airfoil portion. The lid portion forming the turn-back flow passage and being provided as a separate member from the airfoil portion. The lid portion has an inner wall surface width formed to be greater than the flow-passage width of the cooling passage formed in the airfoil portion, and a minimum value of a thickness of the lid portion is smaller than a thickness of a part of the shroud to which the lid portion is mounted.
    Type: Grant
    Filed: March 30, 2020
    Date of Patent: February 6, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hidemichi Koyabu, Satoshi Hada
  • Patent number: 11885241
    Abstract: A turbine nozzle assembly includes at least one airfoil and an outer endwall coupled to a radial outer end of the at least one airfoil. A mounting rail is coupled to the outer endwall and extends at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall. A stress relief structure is defined in the mounting rail. The stress relief structure includes an end opening defined in a radial outer surface of the mounting rail, a slot defined through the rail thickness of the mounting rail and coupled to the end opening, and an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot. The oblong opening is arranged asymmetrically in a circumferential direction relative to the slot to relieve stress where prevalent in the mounting rail.
    Type: Grant
    Filed: July 28, 2022
    Date of Patent: January 30, 2024
    Assignee: General Electric Company
    Inventors: Lauren Elizabeth Rogers, William Scott Zemitis, Kristen Barbara Coletti
  • Patent number: 11885230
    Abstract: An airfoil for a gas turbine engine. The airfoil includes a unique cooling path for a coolant, routing the coolant through a cooling cavity, through a column of crossover passages and through a pin array near a trailing edge of the airfoil. The crossover passages produce impingement cooling and the pin array produces convective cooling. This combination of impingement cooling and convective cooling results in increased cooling of the airfoil and better aeromechanical life objectives.
    Type: Grant
    Filed: March 16, 2021
    Date of Patent: January 30, 2024
    Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO. LTD.
    Inventors: Hyunwoo Joo, W. David Day, Walter Marussich, Jeff Greenberg
  • Patent number: 11885240
    Abstract: A gas turbine engine is provided having a static structure including a flowpath wall. A fluid circuit is extended through the flowpath wall and includes a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit, in which the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit.
    Type: Grant
    Filed: July 20, 2021
    Date of Patent: January 30, 2024
    Assignees: General Electric Company Polska sp.z o.o, General Electric Deutschland Holding GmbH
    Inventors: Tomasz Edward Berdowski, Mirosław Sobaniec, Maciej Czerwiński, Ashish Sharma, Piotr Jerzy Kuliński
  • Patent number: 11879355
    Abstract: An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.
    Type: Grant
    Filed: August 5, 2022
    Date of Patent: January 23, 2024
    Assignee: General Electric Company
    Inventors: David Raju Yamarthi, Vasanth Kumar Balaramudu, Vishnu Vardhan Venkata Tatiparthi, Paul Mathew, Douglas Lorrimer Armstrong, Gary Willard Bryant, Jr., Nuthi Srinivas
  • Patent number: 11879356
    Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.
    Type: Grant
    Filed: June 29, 2022
    Date of Patent: January 23, 2024
    Assignee: General Electric Company
    Inventors: Daniel Endecott Osgood, Zachary Daniel Webster, Gregory Terrence Garay, Kevin Robert Feldmann
  • Patent number: 11873821
    Abstract: A cylindrical gap is formed between a production pipe and a pump stator, the pump stator has a tubular pump casing that surrounds a plurality of pump bodies, the pump casing is provided with a penetrating portion that penetrates the pump casing in a radial direction and communicates with the gap, and the penetrating portion is formed in a portion of the pump casing that faces a pump body, which is located in an intermediate stage of the plurality of pump bodies, in the radial direction.
    Type: Grant
    Filed: February 26, 2020
    Date of Patent: January 16, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kimihiko Mitsuda, Shuhei Sasaki
  • Patent number: 11873734
    Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
    Type: Grant
    Filed: October 12, 2020
    Date of Patent: January 16, 2024
    Assignee: General Electric Company
    Inventors: Anquan Wang, Ryan Christopher Jones, Paul Christopher Schilling, Craig Alan Gonyou
  • Patent number: 11867196
    Abstract: A centrifugal compressor and a method of operating a centrifugal compressor. The centrifugal compressor includes: an impeller configured to suction a gas to be compressed; a diffuser disposed downstream of the impeller to pressurize the gas, the diffuser comprising a movable ring, a main passage in which the gas flows past the ring, and an openable branch passage; and a circulation loop comprising an inlet and an outlet, the outlet being in communication with an inlet of the impeller; the branch passage is disposed to be in communication with the main passage and the circulation loop when the ring moves into the main passage so that a portion of the gas in the main passage passes through the circulation loop and returns to the impeller so as to be suctioned, and to be closed when the ring is withdrawn from the main passage.
    Type: Grant
    Filed: October 6, 2022
    Date of Patent: January 9, 2024
    Assignee: CARRIER CORPORATION
    Inventors: Lei Yu, Vishnu M. Sishtla, Sheng Chen
  • Patent number: 11865556
    Abstract: Various implementations include, an out-of-plane feedback-type fluidic oscillator. including a first portion, a second portion, a middle portion coupled between the first portion and the middle portion, and an axis of rotation. The middle portion includes a first side, a second side opposite and spaced apart from the first side, and a middle plane, an interaction chamber, a fluid supply inlet, an outlet nozzle, a first feedback a channel, and a second feedback channel. The first side is coupled to the first portion, and the second side is coupled to the second portion. The first side, the second side, and the middle plane extend circumferentially around the axis of rotation. The middle plane is disposed equally distanced from the first side and the second side. The fluid stream oscillates as it flows through the interaction chamber such that the fluid stream oscillates as the fluid stream exits the outlet nozzle.
    Type: Grant
    Filed: May 28, 2020
    Date of Patent: January 9, 2024
    Assignee: Ohio State Innovation Foundation
    Inventors: Mohammad Arif Hossain, Jeffrey P. Bons, James W. Gregory, Ali Ameri
  • Patent number: 11867089
    Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.
    Type: Grant
    Filed: August 3, 2022
    Date of Patent: January 9, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ryan C. Humes
  • Patent number: 11867079
    Abstract: In a flange cooling structure of a gas turbine engine, one of a first flange and a second flange is a high pressure flange that faces a first region, and the other of the first flange and the second flange is a low pressure flange that faces a second region. A contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.
    Type: Grant
    Filed: February 18, 2021
    Date of Patent: January 9, 2024
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Hayato Hirota, Tateki Sakimoto, Atsunori Arai, Tatsuya Okuwa, Hikaru Maesato
  • Patent number: 11859511
    Abstract: Airfoils and methods of cooling an airfoil are provided. The airfoil may comprise a spar; a coversheet on the spar; and a dual feed circuit between the spar and the coversheet. The dual feed circuit may include a first dam, a second dam spaced apart from the first dam along the chord axis of the spar, a first inlet disposed adjacent to the first dam, a second inlet disposed adjacent to the second dam, a circuit outlet disposed between the first inlet and the second inlet, and a plurality of diamond and/or hexagonal pedestals disposed on an outer surface of the spar. The diamond and/or hexagonal pedestals may form a plurality of cooling channels between the first inlet, the second inlet, and the circuit outlet. There may be no other circuit inlets are located between the first inlet and the second inlet.
    Type: Grant
    Filed: November 5, 2021
    Date of Patent: January 2, 2024
    Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATION
    Inventors: Brett Barker, Eric Koenig, Jerry Layne, Jeffrey F. Rhodes
  • Patent number: 11846237
    Abstract: An exemplary gas turbine engine assembly includes a fan section including a fan, a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox includes a set of gears. A compressor is driven by the first towershaft. A transmission couples a starter generator assembly to the set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft in response to rotation of the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft in response to rotation of the second towershaft.
    Type: Grant
    Filed: March 9, 2021
    Date of Patent: December 19, 2023
    Assignee: RTX CORPORATION
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry
  • Patent number: 11846203
    Abstract: A turbine vane airfoil and a turbine nozzle that includes the turbine vane airfoil. The turbine vane airfoil includes an airfoil defining a chamber proximate a surface, and an impingement tube. The impingement tube includes a first wall and a second wall. The first wall defines a plurality of first apertures, and each has a first upstream surface portion opposite a first downstream surface portion. The second wall defines a plurality of second apertures, and each has a second upstream surface portion opposite a second downstream surface portion. Each of the first apertures cooperate with a respective one of the second apertures to direct a cooling fluid onto the surface, and the first downstream surface portion of at least one of the first apertures includes a first point that is collinear with a second point of the second downstream surface portion of the respective one of the second apertures.
    Type: Grant
    Filed: January 17, 2023
    Date of Patent: December 19, 2023
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Mark Morris, Daniel Crites, Steven Whitaker
  • Patent number: 11846202
    Abstract: A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.
    Type: Grant
    Filed: February 24, 2020
    Date of Patent: December 19, 2023
    Assignee: Turbogen Ltd.
    Inventor: David Lior
  • Patent number: 11834962
    Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.
    Type: Grant
    Filed: April 8, 2020
    Date of Patent: December 5, 2023
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Satoshi Hada, Yoshifumi Okajima, Kunihiko Waki
  • Patent number: 11835000
    Abstract: Methods and systems for a gas turbine engine comprising a modulated bleed valve are provided. The gas turbine engine may comprise a turbine nozzle coupled to a controller, a modulated bleed valve in communication with the controller, and a tangible, non-transitory memory providing instructions to the controller to perform operations. The operations may include receiving parameter values from the parameter sensor at various times, determining desired bleed airflows to flow through the modulated bleed valve at various times, and/or commanding the modulated bleed valve to assume an open configuration or a closed configuration at various times. The modulated bleed valve may be configured to allow bleed airflow to bypass a nozzle choke area of the turbine nozzle and join a nozzle airflow.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: December 5, 2023
    Assignee: RTX Corporation
    Inventors: Victor Pascu, Anthony C. Jones
  • Patent number: 11834994
    Abstract: A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.
    Type: Grant
    Filed: August 6, 2020
    Date of Patent: December 5, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Saki Matsuo, Satoshi Hada, Tomoko Morikawa, Hiroyuki Otomo
  • Patent number: 11834961
    Abstract: A dual-wall airfoil configured for coolant transfer includes a spar having a pressure side wall and a suction side wall each including raised features on an outer surface thereof. An interior of the spar includes coolant cavities. An inner surface of a pressure side coversheet is in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and an inner surface of a suction side coversheet is in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The pressure side flow pathways and/or the suction side flow pathways include cooling circuit(s) configured to transfer coolant between the coolant cavities.
    Type: Grant
    Filed: January 31, 2023
    Date of Patent: December 5, 2023
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: Brett Barker
  • Patent number: 11826830
    Abstract: At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.
    Type: Grant
    Filed: June 30, 2020
    Date of Patent: November 28, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sandip Dutta, Zachary Snider, Srikanth Chandrudu Kottilingam, Stephen Wassynger, Joseph Moroso
  • Patent number: 11828194
    Abstract: A nozzle blade for a turbine engine includes a blade body in which at least one through-cavity is provided extending between an inner end of the blade and an outer end of the blade and housing, respectively, a first and a second liner, the first liner extending along a trailing edge of the blade, the second liner extending along a leading edge of the blade, wherein each of the first and second liners includes an intertwining system suitable for linking the first liner to the second liner, independently of the blade body.
    Type: Grant
    Filed: February 24, 2021
    Date of Patent: November 28, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Jonathan Yvetot
  • Patent number: 11828195
    Abstract: A woven fibrous preform of a hollow aerodynamic profile of a turbomachine vane or blade, has a non-interlinked trailing edge and a draping of two 3D woven fibrous textures.
    Type: Grant
    Filed: November 8, 2021
    Date of Patent: November 28, 2023
    Assignee: SAFRAN CERAMICS
    Inventors: Clément Marie Benoît Roussille, Matthieu Arnaud Gimat, Julien André Roger Mateo
  • Patent number: 11821365
    Abstract: The present application provides an inducer seal configured to provide a flow of air to a rotor shaft within a turbine of a gas turbine engine. The inducer seal includes a ring plate having an outer surface with a circumferential channel and an inner surface having an abradable seal. A number of inducer slots are positioned in the ring plate that extend from the outer surface to the inner surface such that the flow of air may pass therethrough in a tangential direction relative to rotation of the rotor shaft to cool the rotor shaft.
    Type: Grant
    Filed: January 31, 2022
    Date of Patent: November 21, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Christopher P. Cox, Lucas Wedmore
  • Patent number: 11815105
    Abstract: A regenerative blower-compressor includes an impeller mounted to a drive shaft within a housing including a channel extending from an inlet adjacent to a low fluid-pressure region of the channel to an outlet adjacent to a high fluid-pressure region of the channel, the impeller extends radially outward through an annular volume within the housing from the drive shaft to blades in the channel and is configured to rotate for rotating the blades through the channel for forcing fluid through the channel from the inlet to the outlet in response to rotation of the drive shaft, the drive shaft extends from the impeller within the annular volume to into a shaft chamber within the housing configured to receive fluid from the high fluid-pressure region of the channel, and a port configured to vent fluid directly from the shaft chamber to into the low fluid-pressure region of the channel.
    Type: Grant
    Filed: June 19, 2019
    Date of Patent: November 14, 2023
    Inventor: Joel Jack Oakman
  • Patent number: 11815020
    Abstract: A tangential on-board injector (TOBI), comprising: a body defining an annular passageway to receive cooling air, the TOBI defining a plurality of discharge nozzles; a rotating component mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; a plurality of vanes circumferentially distributed about the axis of rotation and located downstream of the plurality of discharge nozzles relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles and upstream of the seal; and flow passages defined between the plurality of vanes, a flow passage of the flow passages extending along a passage axis, the passage axis having a tangential component at an outlet of the flow passage that is different than a tangential component of an exit flow axis of a nozzle of the plurality of discharge nozzles.
    Type: Grant
    Filed: July 20, 2022
    Date of Patent: November 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gabriel Naccache, Christopher Gover, Alexander Smith, Alain Martel, Matthieu Boudreau
  • Patent number: 11815047
    Abstract: A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.
    Type: Grant
    Filed: August 3, 2022
    Date of Patent: November 14, 2023
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ryan C. Humes
  • Patent number: 11815022
    Abstract: A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component that has platform with an internal cooling passage fed by first and second inlets that respectively receive fluid from the first and second cooling sources. The second inlet is downstream from the first inlet.
    Type: Grant
    Filed: August 5, 2022
    Date of Patent: November 14, 2023
    Assignee: RTX CORPORATION
    Inventors: Daniel P. Preuss, Dominic J. Mongillo, Jr., Timothy J. Jennings
  • Patent number: 11808167
    Abstract: A turbine engine blade includes an airfoil with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge and downstream by a trailing edge. A cooling circuit has an internal cavity extending inside the airfoil and a plurality of outlet openings, each oriented substantially along a longitudinal axis X. Each outlet opening communicates with the cavity and is arranged in the vicinity of the trailing edge. A calibration device is arranged in the cavity and provided with calibration conduits arranged substantially opposite the outlet openings. The calibration conduits each include an oblong transverse section which is substantially perpendicular to the longitudinal axis.
    Type: Grant
    Filed: March 16, 2020
    Date of Patent: November 7, 2023
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Jérémy Jacques Attilio Fanelli, Romain Pierre Cariou, Vianney Simon, Ba-Phuc Tang
  • Patent number: 11808176
    Abstract: A vane assembly includes an airfoil extending from a platform. The platform has a flange that extends radially outward and circumferentially across the platform. A vane cover is arranged adjacent the platform that defines an impingement gap between the platform and the vane cover. The vane cover has a wall that defines a slot. The flange is arranged at least partially within the slot.
    Type: Grant
    Filed: May 4, 2021
    Date of Patent: November 7, 2023
    Assignee: RTX CORPORATION
    Inventor: Robert A. White, III
  • Patent number: 11808178
    Abstract: A diffuser case for a gas turbine engine including: a pre-diffuser; a diffuser case defining a dump region, an inner plenum, and an outer plenum, the pre-diffuser being fluidly connected to the inner plenum and the outer plenum through the dump region; a tangential onboard injector module fluidly connected to the inner plenum through inlet orifice located in the diffuser case proximate an aft end of the inner plenum; and an inlet extender initiating at the inlet orifice of the tangential onboard injector module, extends through the inner plenum, and terminates at a distal end proximate the pre-diffuser.
    Type: Grant
    Filed: August 5, 2019
    Date of Patent: November 7, 2023
    Assignee: RTX CORPORATION
    Inventors: Robin Prenter, Ricardo Trindade, Ryan Lundgreen
  • Patent number: 11802484
    Abstract: A turbine blade includes: an airfoil portion extending in a blade height direction and having a pressure surface and a suction surface each of which extends between a leading and trailing edges; a shroud portion disposed on a blade tip side of the airfoil portion; a fillet portion formed by a curved surface and connected to an end portion of the shroud portion on a side of the airfoil portion; at least one first cooling hole extending along the blade height direction within the airfoil portion; at least one cooling cavity disposed at least partially within the shroud portion and communicating with the at least one first cooling hole; and a second cooling hole connected to the at least one cooling cavity and opening to a surface of the shroud portion. The airfoil portion has a reference airfoil in which a maximum blade thickness is minimum at a reference position.
    Type: Grant
    Filed: November 9, 2020
    Date of Patent: October 31, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Kazuya Nishimura
  • Patent number: 11795828
    Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.
    Type: Grant
    Filed: March 16, 2020
    Date of Patent: October 24, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matthieu Simon, Jean-Luc Bacha, Paul Danre, Léandre Ostino
  • Patent number: 11788416
    Abstract: Airfoils for gas turbine engines are describe. The airfoils include a leading edge having an interior surface with an inflection point line extending radially between a root and a tip of the airfoil. The inflection point line is defined at a location of minimum radii that separates a pressure side and a suction side of the airfoil body. An interlaced trip strip array is arranged along the leading edge and includes a chevron trip strip having an apex and ligaments extending from the apex to form a chevron shape and a skew trip strip arranged proximate to the chevron trip strip with a leading end proximate the inflection point line. The skew trip strip is positioned adjacent to the chevron trip strip such that a gap is formed between the skew trip strip and one of the ligaments of the chevron trip strip.
    Type: Grant
    Filed: June 11, 2021
    Date of Patent: October 17, 2023
    Assignee: RTX CORPORATION
    Inventor: Dominic J. Mongillo, Jr.
  • Patent number: 11788424
    Abstract: Sealing ring for a wheel of an aircraft turbomachine turbine, the ring having an annular body extending around an axis of revolution and including an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further including an annular wall extending around the annular body and at a radial distance from the body, the annular wall including openings through which cooling air flows by impact on the outer surface, wherein the body and the wall are integrally formed.
    Type: Grant
    Filed: May 20, 2020
    Date of Patent: October 17, 2023
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Louis Guedot, Fabien Hourquet, Eloi Duflos, Patrice Postel
  • Patent number: 11781440
    Abstract: A flow path component includes a platform that extends between a first side and a second side. A slot is in the first side. The slot divides the platform into a first portion and a second portion at the first side. There is a groove along the first side in the first portion.
    Type: Grant
    Filed: March 9, 2021
    Date of Patent: October 10, 2023
    Assignee: RTX CORPORATION
    Inventors: Tyler G. Vincent, Daniel Carlson
  • Patent number: 11781433
    Abstract: A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.
    Type: Grant
    Filed: December 8, 2022
    Date of Patent: October 10, 2023
    Assignee: RTX CORPORATION
    Inventors: Carlos Calixtro, Yanhu Guo, Nelson D. Gonzalez