With Passage In Blade, Vane, Shaft Or Rotary Distributor Communicating With Working Fluid Patents (Class 415/115)
  • Patent number: 11143106
    Abstract: The present disclosure is directed to a propulsion system including a wall defining a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween, a nozzle assembly disposed at the combustion chamber inlet, the nozzle assembly configured to provide a fuel/oxidizer mixture to the combustion chamber, a turbine nozzle coupled to the wall and positioned at the combustion chamber outlet, wherein the turbine nozzle defines a cooling circuit within the turbine nozzle, and a casing positioned radially adjacent to the wall, wherein a channel structure is positioned between the casing and the wall, the channel structure in fluid communication with the cooling circuit within the turbine nozzle, and wherein a flowpath is formed between the wall and the casing, the flowpath in fluid communication from the cooling circuit at the turbine nozzle to the nozzle assembly to provide a flow of oxidizer to the thereto.
    Type: Grant
    Filed: November 6, 2019
    Date of Patent: October 12, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Joseph Zelina, Sibtosh Pal, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • Patent number: 11143038
    Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge.
    Type: Grant
    Filed: February 26, 2014
    Date of Patent: October 12, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: San Quach, Matthew A. Devore
  • Patent number: 11136890
    Abstract: The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface.
    Type: Grant
    Filed: March 25, 2020
    Date of Patent: October 5, 2021
    Assignee: General Electric Company
    Inventors: Jan Emeric Agudo, Martin James Jasper
  • Patent number: 11136892
    Abstract: A rotor blade for a gas turbine, includes a blade extending in a radial direction, with a blade body having a peripheral wall with pressure-side and suction-side wall sections, a plate-shaped crown base connected to the peripheral wall in the region of the blade tip, and a sweep edge extending along the peripheral wall, the peripheral wall and the crown base defining a cavity in the blade body, the sweep edge being aligned on the outer side with the peripheral wall and protruding radially over the crown base, and cooling channels are embodied in the blade body, extending from the cavity to cooling fluid outlets provided in the sweep edge. At least one recess being formed in the front surface of the sweep edge, into which at least some of the cooling channels flow such that the cooling fluid outlets are entirely arranged in a bottom region of the recess.
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: October 5, 2021
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Markus Gill, Christian Gindorf, Andreas Heselhaus, Robert Kunte, Marcel Schlösser, Andrew Carlson, Ross Peterson
  • Patent number: 11136917
    Abstract: An airfoil, a turbine and a gas turbine having enhanced cooling performance are provided. The airfoil including a leading edge and a trailing edge may include: a first cooling passage connected to the leading edge; a second cooling passage connected to the trailing edge; a third cooling passage formed between the first cooling passage and the second cooling passage; a shock tube installed in the first cooling passage and configured to form an auxiliary cooling passage between the shock tube and the leading edge, and to include a plurality of dispersion hole in the shock tube; and a flow guide member installed on the shock tube and configured to guide a flow of air that is drawn from the third cooling passage into the first cooling passage.
    Type: Grant
    Filed: January 7, 2020
    Date of Patent: October 5, 2021
    Inventors: Ye Jee Kim, Vincent Galoul
  • Patent number: 11131212
    Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.
    Type: Grant
    Filed: December 6, 2017
    Date of Patent: September 28, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Adam P. Generale, Ky H. Vu
  • Patent number: 11125116
    Abstract: A lifting jig can lift a rotor and a diaphragm of a steam turbine including a casing that covers the rotor that can be divided with a division surface and the diaphragm that can be divided into an upper half diaphragm and a lower half diaphragm with a division surface. A lifting jig has a diaphragm fixing unit that can be fixed to the upper half diaphragm, a first rotor supporting unit that is integrally formed with a diaphragm fixing unit and can support one end portion of the rotor in an axial direction, and a second rotor supporting unit that is integrally formed with the diaphragm fixing unit and can support the other end portion of the rotor in the axial direction.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: September 21, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Yuichi Sasaki, Kyoichi Ikeno
  • Patent number: 11118467
    Abstract: A stationary component of a turbine section of a turbine engine system includes a hollow vane assembly with an interior rib separating a first interior compartment from a second interior compartment. The first and second interior compartments are configured to receive the cooling fluid. The cooling fluid is allowed to communicate between the first and second interior compartments. The stationary component also includes a diaphragm attached to the hollow vane assembly. The diaphragm is configured to receive the cooling fluid from the hollow vane assembly. The diaphragm includes a chamber and a tube extending through the chamber. The tube is configured to isolate the chamber from the cooling fluid while delivering the cooling fluid from the hollow vane assembly to the wheelspace area.
    Type: Grant
    Filed: July 26, 2017
    Date of Patent: September 14, 2021
    Assignee: General Electric Company
    Inventors: Jason A. Neville, Mitchell Merrill, Stephen Newman, Jaime Maldonado
  • Patent number: 11118457
    Abstract: A method of heating a fan blade of a gas turbine engine for anti-icing includes emitting jets of heated air from a radial fin disposed upstream from a radially inward portion of a fan blade airfoil, the jets of heated air being directed by outlet orifices in a downstream direction substantially parallel to a flow of incoming air over the fan blade airfoil.
    Type: Grant
    Filed: October 21, 2019
    Date of Patent: September 14, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Ivakitch, David Menheere, Paul Stone
  • Patent number: 11111794
    Abstract: A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.
    Type: Grant
    Filed: February 5, 2019
    Date of Patent: September 7, 2021
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David Bitzko, Shawn M. McMahon, Alex J. Schneider
  • Patent number: 11111804
    Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.
    Type: Grant
    Filed: March 11, 2019
    Date of Patent: September 7, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Weston Behling, Jason Leroux, Robert B. Fuller, Steven D. Roberts
  • Patent number: 11111823
    Abstract: A turbine ring assembly includes adjacent ring sectors forming a turbine ring, each ring sector having a platform with an inner face defining the inner face of the turbine ring and an outer face from which an upstream lug and a downstream lug extend along the radial direction. Each ring sector includes a first groove present in the platform in the vicinity of the inner face of the platform, a second groove present in the platform in the vicinity of the outer face of the platform, an upstream groove extending into the upstream lug and a downstream groove extending into the downstream lug. A first sealing tab extends into the first groove. A second sealing tab extends into the second groove. An upstream sealing tab extends into the upstream groove. A downstream sealing tab extends into the downstream groove. The second sealing tab includes at least one opening.
    Type: Grant
    Filed: April 4, 2019
    Date of Patent: September 7, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Jarrossay, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen
  • Patent number: 11105212
    Abstract: Disclosed is a tangential on-board injector (TOBI) system that includes an annulus and a plurality of cooling airflow passages disposed about the annulus. Each cooling airflow passage of the plurality of cooling airflow passages includes an inlet opening having a polygonal inlet cross-section, the inlet opening having an inlet cross-sectional area. Each cooling airflow passage of the plurality of cooling airflow passages further includes an outlet opening having an outlet cross-section and an outlet cross-sectional area. The inlet cross-sectional area is greater in magnitude than the outlet cross-sectional area. Also disclosed are additive manufacturing methods for manufacturing the tangential on-board injector system and gas turbine engines that incorporate the tangential on-board injector system.
    Type: Grant
    Filed: January 29, 2019
    Date of Patent: August 31, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Michael Ryan Wedig, Jeffrey D Harrison, Mark C Morris, Raymond Gage
  • Patent number: 11105215
    Abstract: A flow path component includes a base portion that extends between a first circumferential side and a second circumferential side. A first wall and a second wall extend radially outward from the base portion. The first wall is axially spaced from the second wall to form a passage between the first and second walls. A slot is formed in the first circumferential side. A notch in the base portion extends in a radial direction from the passage to the slot.
    Type: Grant
    Filed: November 6, 2019
    Date of Patent: August 31, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carson A. Roy Thill, Jaime A. Arbona, Justin K. Bleil, Danielle Mahoney, Andrew D. Keene
  • Patent number: 11098602
    Abstract: Disclosed is a turbine vane having a turbine vane airfoil extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side that extend from the leading edge to the trailing edge, wherein a plurality of cavities defined by a plurality of ribs extending from the pressure side to the suction side is formed in the turbine vane airfoil, at least one of the cavities is provided with a plurality of insert supports protruding inward from an inner surface of the turbine vane airfoil, and the insert supports are arranged in a circumferential direction of the cavity and arranged in a plurality of rows arranged in a radial direction.
    Type: Grant
    Filed: March 7, 2019
    Date of Patent: August 24, 2021
    Inventors: Hyuk Hee Lee, Sung Chul Jung
  • Patent number: 11098612
    Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.
    Type: Grant
    Filed: November 18, 2019
    Date of Patent: August 24, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Winston Gregory Smiddy, San Quach, Matthew D. Parekh, Jeffrey T. Morton
  • Patent number: 11092028
    Abstract: This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extension ring (160) coupled to the diaphragm and positioned adjacent to the tip shroud (152), and a tip balance slit (200).
    Type: Grant
    Filed: February 1, 2018
    Date of Patent: August 17, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Brian Robert Haller, Adrian Clifford Lord, Philip David Hemsley
  • Patent number: 11092025
    Abstract: A combustor assembly for a gas turbine engine includes a TOBI module that includes a TOBI housing. The TOBI housing has a slot. A vane includes a dovetail removably received within the slot. The TOBI housing includes an axially extending TOBI nozzle array. The TOBI housing includes a plenum. A cooling passage fluidly connects the plenum to the vane. The TOBI housing includes passages configured to provide cooling fluid to the vane. The TOBI housing includes a first passageway further connecting the TOBI nozzle to the plenum.
    Type: Grant
    Filed: October 30, 2019
    Date of Patent: August 17, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Meggan Harris
  • Patent number: 11085644
    Abstract: A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.
    Type: Grant
    Filed: July 11, 2019
    Date of Patent: August 10, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Si-Man Amy Lao, Sri Sreekanth
  • Patent number: 11078801
    Abstract: A vane stage with a longitudinal axis designed to be fitted in a turbine engine compressor. The van stage has an annular row of mobile vanes arranged upstream from an annular row of stator vanes. The annular row of stator vanes has a radially internal annular platform bearing radial blades, an upstream annular portion of which is arranged upstream from the blades and is surrounded radially outwards by a downstream annular portion of an annular platform of the upstream row of mobile vanes. The upstream annular portion of the annular platform of the annular row of stator vanes has a radially external annular face from which fins extend, which are distributed around the longitudinal axis and extend radially outwards towards the downstream annular portion of the platform of the annular row of mobile vanes.
    Type: Grant
    Filed: July 23, 2019
    Date of Patent: August 3, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Damien Bernard Emeric Guegan, Sébastien Claude Cochon, Pierre-Hugues Ambroise Maxime Victor Retiveau
  • Patent number: 11078802
    Abstract: A gas turbine engine assembly includes a first component, a second component, and a seal. The first component is spaced apart from the second component to form a gap between the first component and the second component. The seal is configured to block gases from flowing in the gap between the first component and the second component.
    Type: Grant
    Filed: May 10, 2019
    Date of Patent: August 3, 2021
    Inventors: Anthony G. Razzell, Michael J. Whittle, Steven Hillier
  • Patent number: 11073036
    Abstract: A gas turbine engine component includes a main body. A cooling passage is within the main body. The cooling passage is defined by a first wall opposite a second wall. The cooling passage has an inlet on the second wall. A protrusion is formed on the first wall arranged across from the inlet.
    Type: Grant
    Filed: June 3, 2019
    Date of Patent: July 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Matthew James Bennison, Paul M. Lutjen, Ken F. Blaney
  • Patent number: 11073023
    Abstract: Vanes for gas turbine engines are described. The vanes include an airfoil body extending between a first platform and a second platform, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side and at least one skin core cavity comprising a first skin core cavity, wherein the first skin core cavity defines a throughflow passage through the vane between the first platform and the second platform, wherein the at least one skin core cavity is defined between an external hot wall of the vane and an internal cold wall of the vane.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: July 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Corey D. Anderson
  • Patent number: 11073025
    Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of the first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.
    Type: Grant
    Filed: April 10, 2018
    Date of Patent: July 27, 2021
    Assignee: SAFRAN
    Inventors: Sylvain Paquin, Romain Pierre Cariou, Thomas Michel Flamme, Adrien Bernard Vincent Rollinger
  • Patent number: 11066948
    Abstract: There is provided a rotary machine including a rotary shaft; a plurality of rotor blades extending outward from the rotary shaft in a radial direction of the rotary shaft, and are provided with gaps therebetween in a peripheral direction of the rotary shaft; a casing surrounding the rotor blades radially outside the rotor blades, and in which a recessed portion as a cavity accommodates tips of the rotor blades; a sealing portion extending from one of a bottom surface of the recessed portion and the tip of the rotor blade, and having a clearance with the other; a jet flow passage through which a fluid is jetted rearward in a rotation direction of the rotary shaft in the cavity; and a valve which is capable of switching a flow condition of the jet flow with turning the valve on an opening state and a closing state.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: July 20, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Kazuyuki Matsumoto
  • Patent number: 11066998
    Abstract: A compressor rotor includes a first outer cavity formed in a rotor main body and into which air on a high-pressure side of blades is to be introduced, a first inner cavity formed in the rotor main body on an inner side in a radial direction of the first outer cavity; and a first communication passage which connects the first outer cavity and the first inner cavity to each other in the radial direction of the first outer cavity. Along an entire length of the first communication passage from the first outer cavity to the first inner cavity, the first communication passage is inclined toward a forward side of a rotation direction of the rotor main body.
    Type: Grant
    Filed: March 30, 2017
    Date of Patent: July 20, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yoshiko Oya, Yoshiyuki Okabe, Masato Araki
  • Patent number: 11060408
    Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.
    Type: Grant
    Filed: February 3, 2020
    Date of Patent: July 13, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Alex J. Schneider, Parth Jariwala, Nicholas M. LoRicco, Ryan Lundgreen, David A. Niezelski, Jeffrey T. Morton
  • Patent number: 11053850
    Abstract: A gas turbine includes a turbine blade including a leading edge, a trailing edge, and a plurality of partition walls defining a cooling passage for passing cooling air inside the turbine blade, a first partition wall of the plurality of partition walls facing the leading edge; and an injection nozzle disposed in the first partition wall to cool an inner surface of the leading edge. The injection nozzle includes a nozzle protrusion protruding from the first partition wall toward the leading edge and surrounding an injection hole formed in the first partition wall. Thus, a flow direction of cooling fluid to be supplied to the leading edge can be guided, and deformation and damage to turbine blade components can be prevented.
    Type: Grant
    Filed: August 30, 2018
    Date of Patent: July 6, 2021
    Inventor: Jae Yeon Choi
  • Patent number: 11047242
    Abstract: A component for a fluid flow engine, such as a gas turbine, includes a first side, e.g. a top side and a second side, e.g. a bottom side, wherein the component further includes a mesh of interior channels for guiding a fluid through the component, wherein a fluid inlet being in fluid communication with channels of the mesh is provided at the first side and at the second side, respectively, and wherein the mesh is further arranged and configured such that channels originating from the fluid inlet of the first side and channels originating from the fluid inlet of the second side are interlaced such that a fluid entering the component is at least partly guided according to opposing directions in the mesh.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: June 29, 2021
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Johannes Fölbach, Lovis Phlippen, Eike Reuter
  • Patent number: 11033992
    Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: June 15, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ian A. Macfarlane, Peter Townsend, Hong Yu
  • Patent number: 11035234
    Abstract: An airfoil for a working fluid path of a turboengine extends along a spanwidth direction from a base to a tip. An aerodynamic body thereof includes a suction side surface, a pressure side surface, a leading edge, a trailing edge and a tip, the tip of the aerodynamic body having a tip cross section and a cross-sectional contour circumscribing the tip cross section. A rim extends to the tip of the airfoil and follows the cross-sectional contour on the pressure side, the suction side and extends over the leading edge of the airfoil, the rim delimiting a tip cavity which is open at the tip of the airfoil. The rim is further open at the trailing edge of the airfoil such that the tip cavity is open at the trailing edge of the airfoil.
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: June 15, 2021
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Shailendra Naik, Christian Sommer
  • Patent number: 11035255
    Abstract: The present disclosure relates to a blade of a guide vane assembly of a turbomachine fitted with a cooling system, generally including an insert arranged inside an internal cavity of said blade, connected to a cooling air inlet of the blade and designed to cool the surface of the internal cavity of the blade, and a bleed device configured to bleed some of the cooling air inside the insert and designed to send this bled cooling air to a central hub of the turbomachine. The bleed device of the blade may further include a bleed head arranged in the internal cavity of the blade and passing through an opening of the insert, and configured to bleed some of the cooling air inside the insert.
    Type: Grant
    Filed: November 10, 2016
    Date of Patent: June 15, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Baptiste Hallouin, Jean-Luc Breining, Damien Laberny
  • Patent number: 11035240
    Abstract: A turbine vane assembly and a gas turbine including the turbine vane assembly are capable of adjusting a flow rate and a supply pressure of seal air by adjusting the area of a purge hole. The turbine vane assembly includes a turbine vane disposed between an outer platform and an inner platform; a U-ring unit formed of opposite sides that face each other and are each coupled to the inner platform to form a cavity; a first purge hole formed in one side of the U-ring unit to communicate with each of the cavity and a first wheel space, the first purge hole having an area that is adjustable in size; and a second purge hole formed in the other sides of the U-ring unit to communicate with each of the cavity and a second wheel space, the second purge hole having an area that is adjustable in size.
    Type: Grant
    Filed: November 22, 2018
    Date of Patent: June 15, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Dong Hwa Kim
  • Patent number: 11028722
    Abstract: The present disclosure is directed to a blade track assembly used in a gas turbine engine. The blade track assembly includes blade track segments made from ceramic matrix composite materials and a tip clearance control system for adjusting the inner diameter of the blade track assembly during use in an engine.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: June 8, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Patent number: 11028701
    Abstract: A structure for cooling a turbine airfoil includes: a cooling passage formed between first and second airfoil walls; a lattice structure body formed by stacking a plurality of ribs so as to form a lattice pattern; a cooling medium discharge port provided at a downstream end portion of the cooling passage for discharging cooling medium to the outside; an exposed wall portion formed as a portion of the second airfoil wall extending beyond the cooling medium discharge port to the outside; and a flat surface portion formed in the cooling passage from an outlet of the lattice structure body to the cooling medium discharge port and at which the wall surfaces of the first and second airfoil walls are formed as flat surfaces.
    Type: Grant
    Filed: December 27, 2017
    Date of Patent: June 8, 2021
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Tomoko Tsuru, Katsuhiko Ishida
  • Patent number: 11028832
    Abstract: The invention relates to a wind turbine comprising a floating base designed as a semi-submersible, a tower arranged on the floating base, at least two arms extending from the tower, a respective energy conversion unit arranged at the free end of each arm, and a cable system connecting the base to the energy conversion units and connecting the energy conversion units to one another in order to introduce the thrust forces acting on the tower, the arms and the energy conversion units into the base, wherein the cable system has a pre-tensioning, the value of which is greater than the loads to be expected during the operation of the wind turbine and acting against the pre-tensioning.
    Type: Grant
    Filed: April 28, 2017
    Date of Patent: June 8, 2021
    Assignee: Aerodyn Consulting Singapore PTE LTD
    Inventor: Sonke Siegfriedsen
  • Patent number: 11028700
    Abstract: An airfoil includes a cooling passage circuit that has a first plenum, a skincore passage, a first connector passage, a second plenum, and a second connector passage. The first plenum is in a first platform and extends adjacent a first side, a trailing end, and a second side of and airfoil section. The skincore passage is embedded in the first side of the airfoil section and extends longitudinally. The first connector passage is longitudinally spaced from an internal core cavity in the airfoil section so as to extend around the cavity. The first connector passage connects the first plenum with the skincore passage. The second plenum is in the second platform and extends adjacent the first side, the trailing end, and the second side of the airfoil section. The second connector passage connects the skincore passage with the second plenum.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: June 8, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Patent number: 11028703
    Abstract: An airfoil including a pressure sidewall and a suction sidewall extending from a root section of the airfoil to a tip region of the airfoil and a leading edge and a trailing edge defines a chord length of the airfoil therebetween. A tip shelf is formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall with a tip shelf discourager that extends from the tip shelf.
    Type: Grant
    Filed: June 7, 2018
    Date of Patent: June 8, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Emma J. Place
  • Patent number: 11021959
    Abstract: A radial inflow turbine includes a turbine wheel having a blade, in which a hub-side end of a leading edge of the blade is located radially inward relative to a shroud-side end of the leading edge, and a housing having a scroll part and a bend part deflecting a flow of a working fluid flowing radially inward from the scroll part, along an axial direction. The turbine wheel has at least one through hole bypassing the blade.
    Type: Grant
    Filed: September 21, 2017
    Date of Patent: June 1, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Ryo Takata
  • Patent number: 11021967
    Abstract: An apparatus and method of forming an engine component having an outer wall forming an interior. The interior can be separated into two or more flow paths or flow channels. The two flow paths can be formed by casting having one or more core ties connecting the flow paths during casting. One or more core tie holes can be formed remnant of the core ties during casting in order to fluidly couple the two or more flow paths or flow channels.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: June 1, 2021
    Assignee: General Electric Company
    Inventors: Kirk D. Gallier, Cedric Carlton Lowe
  • Patent number: 11021976
    Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven D. Porter, John T. Ols, Kyle C. Lana
  • Patent number: 11021961
    Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: June 1, 2021
    Assignee: General Electric Company
    Inventors: Jeffrey Douglas Rambo, Kirk Douglas Gallier, Brandon Wayne Miller, Craig Alan Gonyou, Kevin Robert Feldmann, Justin Paul Smith
  • Patent number: 11021987
    Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the support structure via a carrier. At least one of the plurality of segments has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first hook extends from the base portion near the first axial side and faces towards the second axial side. A second hook extends from the base portion near the second axial side and faces towards the first axial side. A slot is in the second hook configured to receive a pin.
    Type: Grant
    Filed: May 15, 2019
    Date of Patent: June 1, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, William M. Barker, Daniel J. Whitney, Danielle Mahoney, William Wangard, III
  • Patent number: 11021978
    Abstract: A shroud of a stator vane includes a suction-side passage, a pressure-side passage, and a plurality of rear-end passages. The plurality of rear-end passages are disposed to be aligned in a lateral direction between the suction-side passage extending along a suction-side end surface and the pressure-side passage extending along a pressure-side end surface, and open at a rear end surface. A suction-side first rear-end passage closest to the suction-side passage among the plurality of rear-end passages gradually extends closer to the suction-side passage toward a downstream side. A pressure-side first rear-end passage closest to the pressure-side passage among the plurality of rear-end passages gradually extends closer to the pressure-side passage toward the downstream side.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: June 1, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventor: Yoshio Fukui
  • Patent number: 11015483
    Abstract: Various embodiments include a compressor casing and a method of assembly. The compressor casing comprises a first and an adjacent, second annular casing segments each comprising an annular radially-extending flange with mounting holes; at least one annular recess disposed on at least one annular side mating face of the adjacent flanges of the adjacent segments; at least one set of stress-relief holes disposed through at least one flange of the adjacent segments; and at least one annular leak-resistant plate disposed within the at least one annular recess having at least a third set of mounting holes. All sets of mounting holes are substantially aligned with each other and receive a plurality of respective fasteners, and the at least one annular plate is clamped between the adjacent segments and seals the at least one set of stress-relief holes for preventing leakage therethrough.
    Type: Grant
    Filed: March 9, 2018
    Date of Patent: May 25, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Vishnu Das K, Carlos Ivan Flores, Atanu Saha, Vinaykumar Shrimantrao Patil
  • Patent number: 11015453
    Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.
    Type: Grant
    Filed: November 22, 2017
    Date of Patent: May 25, 2021
    Assignee: General Electric Company
    Inventors: Aaron Ezekiel Smith, Matthew Thomas Beyer, Gregory Terrence Garay, Zachary Daniel Webster
  • Patent number: 11015481
    Abstract: A cooled structure has a leading edge, a trailing edge, a first side portion orthogonal to each of the leading and trailing edge, and a second side portion opposite the first side portion and substantially orthogonal to each of the leading and trailing edge. The cooled structure includes a substrate surface defined by boundaries including the leading edge, trailing edge, first side and second side portion. A first set of cooling channels beneath the substrate surface extends from a first set of inlets proximate to the first side portion to a first set of exits proximate to the second side portion. A second set of cooling channels beneath the substrate surface extends from a second set of inlets proximate to the second side portion to a second set of exits proximate to the first side portion. Each first inlet overlaps with an exit of the second set of exits.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: May 25, 2021
    Assignee: General Electric Company
    Inventor: Benjamin Paul Lacy
  • Patent number: 11015454
    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source radially inward of the platform. The second passage is configured to receive cooling air from the first passage near the tip. A root flag passage is configured to purge the cooling air from the second passage near the trailing edge.
    Type: Grant
    Filed: May 1, 2018
    Date of Patent: May 25, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy J. Jennings, Carey Clum
  • Patent number: 11008871
    Abstract: A turbine blade of a turbine rotor blade ring, having a suction side, a pressure side and a cooling air duct through which a cooling medium is conveyable for cooling the turbine blade. It is provided that the cooling air duct has in at least one section a course such that its cross-sectional surface increases in the flow direction of the cooling medium up to a maximum in a first, widening partial section, its cross-sectional surface decreases in a second, narrowing partial section behind the maximum, and the cooling medium in the second, narrowing partial section is accelerated with a directional component in the direction of the suction side of the turbine blade. The invention furthermore relates to a method for conveying a cooling medium in a turbine blade of a turbine rotor blade ring.
    Type: Grant
    Filed: November 5, 2018
    Date of Patent: May 18, 2021
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Jerrit Daehnert, Josu Guridi
  • Patent number: 10995673
    Abstract: An exemplary gas turbine engine assembly includes 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 turbines are mounted for rotation about a common rotational axis within an engine static structure. The first and second turbine shafts are coaxial with one another. First and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox has a set of gears. A compressor is driven by the first towershaft. The engine assembly further includes a starter generator assembly, and a transmission coupling the starter generator assembly to the first set of gears.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: May 4, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry