With Passage In Blade, Vane, Shaft Or Rotary Distributor Communicating With Working Fluid Patents (Class 415/115)
  • Patent number: 11459903
    Abstract: In the turbine of a gas turbine engine, disk cavities exist between stator and rotor assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the stator and rotor assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be mounted to the stator assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within the disk cavities to circulate the hot gas back out into the hot gas flow path.
    Type: Grant
    Filed: June 10, 2021
    Date of Patent: October 4, 2022
    Assignee: Solar Turbines Incorporated
    Inventors: Yong W. Kim, John F. Lockyer
  • Patent number: 11459897
    Abstract: Airfoils for gas turbine engines are described. The airfoils include a leading edge, a trailing edge, a pressure side exterior wall, and a suction side exterior wall. A plurality of cooling passages are formed within the airfoil. A plurality of first interior ribs extend from the pressure side exterior wall to the suction side exterior wall, and a plurality of second interior ribs extend from the suction side exterior wall toward the pressure side exterior wall and intersect with a first interior rib. At least one pressure side main body cooling passage is defined between the pressure side exterior wall and two first interior ribs of the plurality of first interior ribs and at least one suction side main body cooling passage is defined between the suction side exterior wall, a first interior rib, and a second interior rib.
    Type: Grant
    Filed: April 27, 2020
    Date of Patent: October 4, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Dominic J. Mongillo, Jr.
  • Patent number: 11459900
    Abstract: According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, includes: a blade effective part disposed in the working fluid flow path; an outer circumferential sidewall having a plate-shaped part that is connected to a radially outer end portion of the blade effective part, and hooks each extending radially outward and circumferentially from the plate-shaped part and having a tip engaged with the casing; and an inner circumferential sidewall connected to a radially inner end portion of the blade effective part. At least one slit is formed at the rear hook or front hook to divide the hook in a circumferential direction, and the hook has a seal member to seal the slit.
    Type: Grant
    Filed: June 9, 2021
    Date of Patent: October 4, 2022
    Assignee: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION
    Inventors: Norikazu Takagi, Tsuguhisa Tashima, Daisuke Nomura, Yoshifumi Iwasaki, Shogo Iwai, Takahiro Ono
  • Patent number: 11454124
    Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side, and a second side. Radially-extending ribs partition the interior cavity of the airfoil into first and second cooling channels and a radial cooling passage that is situated between the first and second cooling channels. The cooling channels extend to respective first and second channel ends. A turn channel connects the first and second channel ends. The turn channel splits at the first channel end into first and second channel legs such that there is a region between the first and second channel legs. The channels legs merge at the second channel end. The radial cooling passage extends through the region between the first and second channel legs.
    Type: Grant
    Filed: November 18, 2019
    Date of Patent: September 27, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Brandon W. Spangler
  • Patent number: 11454125
    Abstract: A turbine blade for a gas turbine engine. The turbine blade includes a cooling path for a coolant, routing the coolant through an internal cooling cavity and out through a plurality of cooling holes formed proximate a trailing edge of the turbine blade. Each of the cooling holes including a diffusing region designed so that a coolant does not separate from a radially inward sidewall of the diffusing region.
    Type: Grant
    Filed: July 19, 2021
    Date of Patent: September 27, 2022
    Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
    Inventors: Gene Chong, Andres Jaramillo, Kibaek Kim
  • Patent number: 11448074
    Abstract: An airfoil having a leading edge and a trailing edge is provided. The airfoil includes a rear cooling path connected to the trailing edge to discharge air to the trailing edge, a plurality of cooling fins formed in the rear cooling path, and a flow guide rod connecting the cooling fins to support the cooling fins, wherein each of the plurality of cooling fins includes an upper fin portion protruding upward from an upper portion of the flow guide rod, a lower fin portion protruding downward from a lower portion of the flow guide rod, and an intermediate fin portion inserted through the flow guide rod.
    Type: Grant
    Filed: December 27, 2021
    Date of Patent: September 20, 2022
    Inventors: Jung Shin Park, Ki Hoon Yang, Ki Don Lee, Hyung Hee Cho, Hee Seung Park, Seok Min Choi, Yong Jin Kim, Su Won Kim
  • Patent number: 11448075
    Abstract: A vane arc segment includes a hollow ceramic airfoil section that has walls that define an internal cavity, a trailing edge, a leading edge, a pressure side, and a suction side. A structural spar piece supports the hollow ceramic airfoil section. The spar piece includes a first spar platform, a hollow leg that has a proximal end at the spar platform and an opposed distal end. The hollow leg extends into the internal cavity of the hollow ceramic airfoil section and has an outer surface with raised bearing pads. Multiple ones of the bearing pads contact the walls of the hollow ceramic airfoil section to support the hollow ceramic airfoil section. A second spar platform is secured with the distal end of the leg.
    Type: Grant
    Filed: November 2, 2020
    Date of Patent: September 20, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Robert A. White, III
  • Patent number: 11448076
    Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.
    Type: Grant
    Filed: March 26, 2021
    Date of Patent: September 20, 2022
    Assignee: General Electric Company
    Inventors: Zachary Daniel Webster, Gregory Terrence Garay, Steven Robert Brassfield
  • Patent number: 11448094
    Abstract: A support assembly for a gas turbine engine is provided. The support assembly includes an outer casing, an inner structure, a strut and a mechanical fastener. The outer casing defines a longitudinal central axis. The inner structure includes a platform and a support portion disposed around the platform. The platform defines an aperture therethrough and the support portion defines a slot therethrough adjacent to the platform. The slot at least partially surrounds the platform and extends axially towards the aperture by an axial slot length along the longitudinal central axis. The strut extends generally radially from the inner structure to the outer casing. The mechanical fastener is received through the aperture of the platform.
    Type: Grant
    Filed: November 17, 2021
    Date of Patent: September 20, 2022
    Assignee: ROLLS-ROYCE plc
    Inventor: Wojciech Kuziemko
  • Patent number: 11448093
    Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.
    Type: Grant
    Filed: February 19, 2021
    Date of Patent: September 20, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Steven Whitaker, Daniel C. Crites, Mark C. Morris, Ardeshir Riahi
  • Patent number: 11441447
    Abstract: A ring-segment surface-side member is included in a ring segment disposed at a position opposite to a turbine blade on a stationary side of a gas turbine, serves as a part of a combustion gas flow path through which combustion gas flows, and is formed of a ceramic matrix composite. The ring-segment surface-side member includes: a surface portion forming the combustion gas flow path; a turned-back portion including a first part extending outward in a radial direction of the gas turbine from the surface portion and a second part extending toward a central line of the surface portion from an end part of the first part; and a protrusion portion extending outward from the turned-back portion in the radial direction of the gas turbine.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: September 13, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yamato Shiramasa, Ryuta Ito, Takayuki Kurimura, Yoshifumi Tsuji
  • Patent number: 11434767
    Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
    Type: Grant
    Filed: October 25, 2019
    Date of Patent: September 6, 2022
    Assignee: General Electric Company
    Inventors: Matthew Troy Hafner, Lyndsay Marie Kibler, Brad Wilson VanTassel, Benjamin Paul Lacy, Zachary John Snider, Christopher Donald Porter, Srikanth Chandrudu Kottilingam
  • Patent number: 11428166
    Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.
    Type: Grant
    Filed: November 12, 2020
    Date of Patent: August 30, 2022
    Assignee: Solar Turbines Incorporated
    Inventors: Scott L. Stafford, Juan Yin, Steven D. Gray
  • Patent number: 11421550
    Abstract: A ring segment, a turbine, and a gas turbine having improved cooling performance are provided. The ring segment may include a shielding wall mounted to a turbine casing which accommodates a turbine blade and configured to face an inner circumferential surface of the turbine casing, a first hook part and a second hook part configured to protrude from the shielding wall toward the turbine casing to be coupled to the turbine casing, a main cavity formed between the first hook part and the second hook part, a plurality of first cooling passages configured to connect the main cavity and first side surfaces facing each other of the shielding wall, a plurality of second cooling passages configured to extend in a direction crossing the first cooling passage and connect the main cavity and second side surfaces facing each other of the shielding wall, and a chamber configured to be connected to the first cooling passages.
    Type: Grant
    Filed: June 1, 2020
    Date of Patent: August 23, 2022
    Assignee: DOOSAN ENERBILITY CO., LTD.
    Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
  • Patent number: 11421597
    Abstract: A tangential on-board injector (TOBI) having: a body defining an annular passageway, discharge nozzles; a rotating component configured to be mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; and flow passages circumferentially distributed about the axis of rotation and in fluid communication with the nozzles and the seal, the flow passages located upstream of the seal relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles, each of the flow passages extending along a respective passage axis, the passage axis of at least one of the flow passages having a tangential component at an outlet of the at least one of the flow passages that is different than a tangential component of an exit flow axis of at least one of the plurality of discharge nozzles.
    Type: Grant
    Filed: October 18, 2019
    Date of Patent: August 23, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Gabriel Naccache, Christopher Gover, Alexander Smith, Alain Martel, Matthieu Boudreau
  • Patent number: 11414999
    Abstract: A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.
    Type: Grant
    Filed: October 22, 2019
    Date of Patent: August 16, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: JinQuan Xu
  • Patent number: 11415020
    Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.
    Type: Grant
    Filed: December 4, 2019
    Date of Patent: August 16, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Ky H. Vu, Brian R. Pelletier
  • Patent number: 11415010
    Abstract: A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner platform to an outer platform and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a plurality of vanes attached to the inner and outer platforms and the inner platform having an attached first and second endfaces and a flow surface surrounding opposing ends of a vane of the plurality of vanes, the flow surface terminating circumferentially at the first and second endfaces and terminating axially at forward and aft edges, and the inner platform may include a platform corner portion comprising the flow surface attached to the first endface at the forward edge and attached to the second endface at the aft edge.
    Type: Grant
    Filed: July 5, 2021
    Date of Patent: August 16, 2022
    Inventors: Gene Chong, Darryl Eng, IkSang Lee, JaeBin Lee, Hyunwoo Joo, Andres Jaramillo, Kibaek Kim
  • Patent number: 11415000
    Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.
    Type: Grant
    Filed: June 4, 2018
    Date of Patent: August 16, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
  • Patent number: 11401818
    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: August 6, 2018
    Date of Patent: August 2, 2022
    Assignee: General Electric Company
    Inventors: Daniel Endecott Osgood, Zachary Daniel Webster, Gregory Terrence Garay, Kevin Robert Feldmann
  • Patent number: 11401820
    Abstract: A cooling structure on a trailing-edge cutback of a turbine blade, including a plurality of lands, a trailing edge cutback and a dimple group. Adjacent lands are arranged on wall surfaces at two sides of the trailing edge cutback. The wall surfaces are each provided with the dimple group including multiple dimples. An extension direction of at least one dimple forms an inclined angle with the land on one side, and/or an extension direction of at least one dimple forms an inclined angle with the land on the opposite side. The cooling air enters the trailing edge, and after passing through pin fins, then flows over the dimples along the cutback surface to generate a spiral vortex which is guided to the lands on both sides thereof.
    Type: Grant
    Filed: January 20, 2022
    Date of Patent: August 2, 2022
    Assignee: Shanghai Jiao Tong University
    Inventors: Yu Rao, Yuyang Liu, Peng Zhang, Shijia Chen
  • Patent number: 11401819
    Abstract: During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.
    Type: Grant
    Filed: December 17, 2020
    Date of Patent: August 2, 2022
    Assignee: Solar Turbines Incorporated
    Inventors: Nnawuihe Asonye Okpara, Aaron J. Dick, Donald Joseph Bognatz, Marius Dumitrascu, Estevan Daniel Negrete
  • Patent number: 11401830
    Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge, and at least one cooling cavity disposed within the platform. A pair of circumferential edges connects the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A support hook protrudes radially outward from a leading edge of the platform. A boss structure protrudes radially outward from the platform and defining a solid kinetic energy path from an inner diameter of the platform to a radially outward facing surface of the boss structure, wherein the boss structure extends less than a circumferential length of the platform.
    Type: Grant
    Filed: September 6, 2019
    Date of Patent: August 2, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Christina G Ciamarra
  • Patent number: 11396819
    Abstract: Components for gas turbine engines are described. The components include an airfoil having a leading edge cavity with a baffle portion and a leading edge portion. A baffle is installed within the baffle portion and includes a first metering flow aperture. A first support element retention feature is located within the leading edge cavity. A first axial extending rib extends between an aft end of the cavity and a forward end proximate the first support element retention feature and is formed on an interior surface of the airfoil. A first axial extending flow channel extends along the first axial extending rib between an exterior surface of the baffle and an interior surface of the airfoil and the first metering flow aperture is located proximate the aft end of the first axial extending flow channel to generate a forward flowing cooling flow.
    Type: Grant
    Filed: April 17, 2020
    Date of Patent: July 26, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, Jr., Daniel P. Preuss
  • Patent number: 11391208
    Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.
    Type: Grant
    Filed: May 20, 2021
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Ivakitch, David Menheere, Paul Stone
  • Patent number: 11391211
    Abstract: A turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath; a fuel delivery system for providing a flow of fuel to the combustion section; and a waste heat recovery system. The waste heat recovery system includes a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both; a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath, or both; a thermal transfer bus including a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus.
    Type: Grant
    Filed: November 28, 2018
    Date of Patent: July 19, 2022
    Assignee: General Electric Company
    Inventors: Justin Paul Smith, Brandon Wayne Miller, Thomas Helmut Ripplinger
  • Patent number: 11391170
    Abstract: A turbine of a turbo engine including a casing and a turbine nozzle stage, the turbine nozzle stage including an outer metal shroud secured to the casing, an inner metal shroud, and a plurality of ring sectors made of ceramic-matrix composite material forming a crown extending between the outer metal shroud and the inner metal shroud and having an internal shroud and an external shroud, each ring sector having an internal platform forming a portion of the internal shroud, an external platform forming a portion of the external shroud, and at least one blade extending between the external platform and the internal platform and secured thereto. Each sector is fixed to the outer metal shroud using at least one assembly including a screw and a nut, the screw passing through the outer platform of the sector and the outer metal shroud.
    Type: Grant
    Filed: April 17, 2019
    Date of Patent: July 19, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Clément Jarrossay, Nicolas Paul Tableau
  • Patent number: 11384644
    Abstract: A structure for cooling a turbine airfoil includes: a cooling passage formed between a first airfoil wall curved as to be concave relative to a high-temperature gas passage and a second airfoil wall curved so as to be convex relative to the high-temperature gas passage; lattice structure bodies each formed by stacking a plurality of ribs in a lattice pattern; a partition body provided between the adjacent lattice structure bodies; a cooling medium discharge port for discharging a cooling medium within the cooling passage to the outside; and an exposed wall portion formed as a portion of the second airfoil wall extending beyond the cooling medium discharge port to the outside. At outlet portions of the lattice structure bodies adjacent to each other across the partition body, adjacent first rib sets and second rib sets are inclined in opposite directions relative to the partition body, respectively.
    Type: Grant
    Filed: September 3, 2019
    Date of Patent: July 12, 2022
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Tomoko Tsuru, Katsuhiko Ishida
  • Patent number: 11377973
    Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.
    Type: Grant
    Filed: May 16, 2019
    Date of Patent: July 5, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Eddy Keomorakott Souryavongsa, Thomas Alain De Gaillard, Teddy Fixy, Gilles Pierre-Marie Notarianni
  • Patent number: 11377958
    Abstract: A flow-straightener vane of a bypass turbomachine includes a plurality of vane sections stacked radially with respect to a longitudinal axis (X) along a stacking line (L) between a root end and a tip end. Each vane section has a pressure-face surface and a suction-face surface extending axially between an upstream leading edge and a downstream trailing edge. Between the leading and trailing edges of each vane section there is formed a profile chord (CA) the length of which is substantially constant between the tip end and the root end, and the stacking line (L) exhibits a curvature in a plane passing more or less through the axis (X) and through the stacking line (L), situated in the vicinity of the tip end and oriented from downstream towards upstream.
    Type: Grant
    Filed: August 28, 2018
    Date of Patent: July 5, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Kevin Morgane Lemarchand, Norman Bruno André Jodet, Guillaume Martin, Laurent Soulat
  • Patent number: 11371361
    Abstract: A turbine blade tip includes a tip cap disposed over a blade airfoil and having a pressure side edge and a suction side edge. A notch is formed by a radially inward step adjacent to the suction side edge of the tip cap. The notch is defined by a radially extending step wall and a radially outward facing land. The step wall extends radially inward from the suction side edge of the tip cap to the land, whereby the land is positioned radially inward in relation to a radially outer surface of the tip cap. The notch extends along at least a portion of the suction sidewall in a direction from the leading edge to the trailing edge. In a further aspect, a method is provided for servicing a blade that includes machining a suction side notch as described above.
    Type: Grant
    Filed: August 7, 2018
    Date of Patent: June 28, 2022
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Ali Akturk, Taylor Hynds, Krishan Mohan, David Monk, Jose L. Rodriguez
  • Patent number: 11371353
    Abstract: A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: June 28, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hidekatsu Atsumi, Norihiko Motoyama, Shuji Tanigawa
  • Patent number: 11371360
    Abstract: Component for gas turbine engines are described. The components include an airfoil body having leading and trailing edges and pressure and suction sides. The airfoil has a leading edge cavity located proximate the leading edge defined between the leading edge and a separator rib and between the pressure side and the suction side. An insert member is installed within the leading edge cavity. The insert member has one or more metering flow apertures at an aft end and one or more impingement apertures at a forward end and at least one axially extending rib along an exterior surface thereof. At least one axial extending flow channel passage is defined along the axial extending rib between an exterior of the insert member and an interior of the airfoil body. Air flow through the metering flow apertures flows into the axial extending flow channel passage and flows forward toward the leading edge.
    Type: Grant
    Filed: June 5, 2019
    Date of Patent: June 28, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Adam P. Generale, Dominic J. Mongillo
  • Patent number: 11371359
    Abstract: A turbine blade for a gas turbine engine has: an airfoil extending along a span from a base to a tip and along a chord from a leading edge to a trailing edge, the airfoil having a pressure side and a suction side, a tip pocket at the tip of the airfoil, the tip pocket at least partially surrounded by a peripheral tip wall defining a portion of the pressure and suction sides; at least one internal cooling passage in the airfoil and having at least one outlet communicating with the tip pocket; and a reinforcing bump located on the pressure side of the airfoil and protruding from a baseline surface of the peripheral tip wall to a bump end located into the tip pocket, the reinforcing bump overlapping a location where a curvature of a concave portion of the pressure side of the airfoil is maximal.
    Type: Grant
    Filed: November 26, 2020
    Date of Patent: June 28, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Lecuyer, Othmane Leghzaouni
  • Patent number: 11359646
    Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
    Type: Grant
    Filed: August 29, 2019
    Date of Patent: June 14, 2022
    Assignee: General Electric Company
    Inventors: Sesha Subramanian, Monty Lee Shelton, Robert Proctor, Mohamed Musthafa Thoppil, Venkateswararao Gurram, Josiah Warren Joiner, Wojciech Sak
  • Patent number: 11359502
    Abstract: A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.
    Type: Grant
    Filed: February 18, 2020
    Date of Patent: June 14, 2022
    Assignee: General Electric Company
    Inventor: Jacob John Kittleson
  • Patent number: 11359497
    Abstract: A vane arc segment includes an airfoil section, a spar, and a baffle. The spar supports the airfoil section and has a leg that extends in an internal cavity of the airfoil section. The leg is spaced from the airfoil wall such that there is a gap there between. The baffle divides the gap into a plenum space between the leg and the baffle and an impingement space between the baffle and the airfoil wall. The baffle has impingement holes directed toward the airfoil wall that connect the plenum space and the impingement space. The impingement space is of substantially uniform thickness and the plenum space is of non-uniform thickness along a portion of the span length of the airfoil section.
    Type: Grant
    Filed: December 21, 2020
    Date of Patent: June 14, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E. Sobanski, Tyler G. Vincent
  • Patent number: 11346230
    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: May 31, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Alex J. Schneider, Parth Jariwala, Nicholas M. LoRicco, Ryan Lundgreen, David A. Niezelski, Jeffrey T. Morton
  • Patent number: 11346250
    Abstract: A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: May 31, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Pommier, Mathieu Bissardon, Mathieu Delalandre, Stephane Nicolas Piron, Olivier Renon
  • Patent number: 11339669
    Abstract: A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.
    Type: Grant
    Filed: July 4, 2018
    Date of Patent: May 24, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Yoshifumi Tsuji, Ryuta Ito, Hiroyuki Otomo, Satoshi Hada, Susumu Wakazono
  • Patent number: 11339718
    Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: May 24, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Patent number: 11333023
    Abstract: A gas turbine engine article includes a cooling passage network embedded in an article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from a cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The array of pedestals includes first pedestals arranged in a first row and second pedestals arranged in a second, adjacent row. The first pedestals and the second pedestals define inter-row sub-passages there between. Each of the inter-row sub-passages has an inlet mouth, an outlet mouth, and a compound channel connecting the inlet mouth and the outlet mouth. The compound channel includes a first channel length over which the inter-row sub-passage has a constant cross-section and a second channel length over which the inter-row sub-passage has a non-constant cross-section.
    Type: Grant
    Filed: October 7, 2019
    Date of Patent: May 17, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Allan N. Arisi, Tracy A. Propheter-Hinckley
  • Patent number: 11333029
    Abstract: A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.
    Type: Grant
    Filed: October 20, 2014
    Date of Patent: May 17, 2022
    Assignee: NUOVO PIGNONE SRL
    Inventors: Giacomo Bencini, Marco Grilli, Lorenzo Cosi
  • Patent number: 11326458
    Abstract: An aerofoil for a turbine blade, having a leading edge onto which a hot gas can flow and from which a suction-side wall and a pressure-side wall extend to a trailing edge of the aerofoil, the aerofoil extending in a direction transverse thereto from a root-side end having an aerofoil height of 0% to a tip-side end having an aerofoil height of 100%, and having at least two rows of cooling holes arranged along the leading edge, which cooling holes are at a mutual spacing which can be measured perpendicularly to the leading edge. In order to provide a turbine blade which can be used, with reduced cooling complexity, for additional reliable cooling of the leading edge in various operating conditions, the at least two rows of cooling holes are arranged at least in part in a wavy line along the leading edge.
    Type: Grant
    Filed: May 3, 2019
    Date of Patent: May 10, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Fathi Ahmad, Daniela Koch, Marco Schüler
  • Patent number: 11326457
    Abstract: A blade includes an airfoil portion including a pressure surface and a suction surface each extending between a leading edge and a trailing edge along a spanwise direction, and at least one communication hole extending m the airfoil portion and having a first and a second opening end opening to the pressure and suction surface, respectively. The first opening end is located on a first cross-section perpendicular to the spanwise direction at a first position in the spanwise direction, the second opening end is located on a second cross-section perpendicular to the spanwise direction at a second position in the spanwise direction, and a dimensionless blade chord length position of the first opening end with respect to the leading edge on the first cross-section is larger than a dimensionless blade chord length position of the second opening end with respect to the leading edge on the second cross-section.
    Type: Grant
    Filed: November 21, 2019
    Date of Patent: May 10, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Yasuro Sakamoto
  • Patent number: 11326620
    Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: April 30, 2021
    Date of Patent: May 10, 2022
    Assignee: General Electric Company
    Inventors: Matthew John McKeever, Michael James Healy, Bruce Clark Busbey, Damir Novak, Robin Charles Payne, Thomas Peter Sommer, Olivier Anthony Bron, Carlos Alberto Cardoza, Lukasz Marcin Maczka, Damir Fanjak, Lance William Smith, Alex David Hollanshead, Wilfried Rick, Yu Wang
  • Patent number: 11313235
    Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.
    Type: Grant
    Filed: March 17, 2015
    Date of Patent: April 26, 2022
    Inventors: Ronald Scott Bunker, Frederick Alan Buck, Robert David Briggs, Gulcharan Singh Brainch, Kevin Robert Feldmann
  • Patent number: 11300000
    Abstract: The present invention relates to a panel for tip clearance control formed by: a first perforated sheet adapted for being seated on the turbine casing; a second sheet arranged on said first sheet and configured for being attached to the first sheet leaving a gap between both sheets; and a third sheet arranged between both first sheet and second sheet such that respective spaces in fluid connection by at least one hole are configured: a distribution chamber and an impingement chamber, both chambers extending from one end of the panel to the other. The panel further comprises a closure element together with a sealing element at one of its lateral ends for allowing the passage of fluid with another adjacent panel, whereas the sealing element is configured for allowing relative movement between both adjoining panels.
    Type: Grant
    Filed: September 30, 2020
    Date of Patent: April 12, 2022
    Assignee: ITP EXTERNALS, S.L.
    Inventor: José Francisco Beltrán París
  • Patent number: 11299995
    Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a hollow spar leg that extends from the spar platform and through the hollow airfoil section. The hollow spar leg has an internal passage for receiving cool air there through, a clevis mount, and a pin fairing. The clevis mount is distal from the spar platform and protrudes from the second fairing platform. The clevis mount includes first and second prongs with aligned holes. A pin extends through the aligned holes. The pin fairing extends over the pin between the first and second prongs for guiding the cooling air around the pin. There is a support platform adjacent the second fairing platform. The pin locks the support platform to the spar leg.
    Type: Grant
    Filed: March 3, 2021
    Date of Patent: April 12, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E. Sobanski, Tyler G. Vincent, Bryan P. Dube
  • Patent number: 11293304
    Abstract: A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.
    Type: Grant
    Filed: May 2, 2018
    Date of Patent: April 5, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Brandon W. Spangler