With Passage In Blade, Vane, Shaft Or Rotary Distributor Communicating With Working Fluid Patents (Class 415/115)
  • Patent number: 10808572
    Abstract: A gas turbine engine that includes a turbomachinery core operable to produce a core gas flow and that includes a combustor. A first duct is positioned downstream of and in flow communication with the combustor. A component is positioned within the first duct and extends between radially outward and radially inward walls of the first duct. The component that includes a first cooling passageway formed therein. The first cooling passageway extends between an inlet communicating with the first duct and positioned facing towards the turbomachinery core, and an outlet communicating with a pressure sink.
    Type: Grant
    Filed: April 2, 2018
    Date of Patent: October 20, 2020
    Assignee: General Electric Company
    Inventors: James Michael Hoffman, Jeffrey Ryan Trimmer, Dennis Robert Jonassen, Mark Stephen Zlatic, Patrick John Lonneman
  • Patent number: 10808546
    Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
    Type: Grant
    Filed: March 27, 2019
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
  • Patent number: 10808548
    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10808616
    Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, a turbine section, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said turbine section.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, William K. Ackermann
  • Patent number: 10808549
    Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Dominic J. Mongillo, Jr.
  • Patent number: 10801342
    Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to the second end-of-cluster vane at an interface that includes an angled load interface therebetween; and a multiple of base vanes between the first end-of-cluster vane and the neighbor vane, the angled load interface different than an interface between each of the multiple of base vane.
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark David Ring, Scot A Webb, Mark J Rogers, Gerald D Cassella, Charles H Warner, Eric A Kuehne, Jonathan J Earl, Matthew M Zietala, Neil L Tatman, Randall J Butcher, Matthew R Willett, Nicholas R Leslie
  • Patent number: 10801344
    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A skin core cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The skin core cooling passage is divided by a wall into two discrete first and second skin core cooling passages each supplied with cooling fluid from opposing sides.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nicholas M. LoRicco, Steven Bruce Gautschi
  • Patent number: 10801345
    Abstract: A blade outer air seal segment assembly includes a blade outer air seal segment configured to connect with an adjacent blade outer air seal segment to form part of a rotor shroud. A cooling channel is disposed in the first turbine blade outer air seal segment. The cooling channel extends at least partially between a first circumferential end portion and a second circumferential end portion. At least one inlet aperture provides a cooling airflow to the cooling channel. A series of trip strips in the cooling channel cause turbulence in the cooling airflow. The trip strips include at least one chevron shaped trip strip having a first and second leg joined at an apex arranged adjacent the inlet aperture. The trip strips also include at least one trip strip having a single skewed line.
    Type: Grant
    Filed: February 11, 2019
    Date of Patent: October 13, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dominic J. Mongillo
  • Patent number: 10794281
    Abstract: Instrumented airflow path components configured to determine airflow path distortion in an airflow path of a gas turbine engine (e.g., using for propulsion of an aircraft) are provided. In one embodiment, a gas turbine engine for an aircraft can include a compressor section, a combustion section, and turbine section in series flow. The compressor section, combustion section, and turbine section define at a portion of an engine airflow path for the gas turbine engine. The gas turbine engine further includes one or more members extending at least partially into the engine airflow path of the gas turbine engine and one or more pressure sensor devices at least partially integrated into the one or more members extending at least partially into the engine airflow path. The one or more pressure sensor devices are configured to obtain measurements for determining a distortion condition for the gas turbine engine.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: October 6, 2020
    Assignee: General Electric Company
    Inventors: Brian Francis Nestico, Brian K. Kestner, Brandon Wayne Miller
  • Patent number: 10794212
    Abstract: A rotor, installable in a casing of a turbine and configured to be rotated by a flow of combustion gas and cooled by a flow of compressed air, has an improved structure to keep a tip clearance constant during operation of a gas turbine. The rotor includes a disk having an outer circumferential surface; a platform installed on the outer circumferential surface of the disk; and a blade airfoil formed on an upper surface of the platform, the blade airfoil having an airfoil end situated opposite to the platform, the airfoil end having an upstream side and a downstream side with respect to a flow direction of the combustion gas, wherein the blade airfoil is formed so that, when the rotor is installed in the casing, the downstream side of the airfoil end is closer to an inner surface of the casing than the upstream side of the airfoil end.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: October 6, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Ki Baek Kim
  • Patent number: 10794289
    Abstract: Features and methods for modulating a flow of cooling fluid to gas turbine engine components are provided. In one embodiment, an airfoil is provided having a flow modulation insert for modulating a flow of cooling fluid received in a cavity of a body of the airfoil. In another embodiment, a shroud is provided comprising a cooling channel for a flow of cooling fluid and an insert that varies in position to modulate the flow of cooling fluid through the cooling channel. In yet another embodiment, a method for operating a gas turbine engine having a cooling circuit for cooling one or more components of the gas turbine engine comprises increasing power provided to the engine and decreasing power provided to the engine to modulate a position of a flow modulation insert located in the cooling circuit and thereby modulate the flow of cooling fluid through the cooling circuit.
    Type: Grant
    Filed: August 9, 2016
    Date of Patent: October 6, 2020
    Assignee: General Electric Company
    Inventors: Robert Charles Groves, II, Kirk Douglas Gallier, Charles William Craig, III
  • Patent number: 10794207
    Abstract: A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.
    Type: Grant
    Filed: September 11, 2014
    Date of Patent: October 6, 2020
    Assignee: RATHEON TECHNOLOGIES CORPORATION
    Inventor: Matthew Andrew Hough
  • Patent number: 10787920
    Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.
    Type: Grant
    Filed: October 12, 2016
    Date of Patent: September 29, 2020
    Assignee: General Electric Company
    Inventors: Christophe Jude Day, Kenneth Edward Seitzer, Michael Alan Hile, Thomas Alan Wall, Carol Anne Venn, Anthony Paul Greenwood
  • Patent number: 10787911
    Abstract: A gas turbine engine airfoil includes an outer wall including a suction side, a pressure side, a leading edge, and a trailing edge, the outer wall defining an interior chamber of the airfoil. The airfoil further includes cooling structure provided in the interior chamber. The cooling structure defines an interior cooling cavity and includes a plurality of cooling fluid outlet holes, at least one of which is in communication with a pressure side cooling circuit and at least one of which is in communication with a suction side cooling circuit. At least one of the pressure and suction side cooling circuits includes: a plurality of rows of airfoils, wherein radially adjacent airfoils within a row define segments of cooling channels. Outlets of the segments in one row align aerodynamically with inlets of segments in an adjacent downstream row such that the cooling channels have a serpentine shape.
    Type: Grant
    Filed: June 11, 2018
    Date of Patent: September 29, 2020
    Assignees: SIEMENS ENERGY, INC., MIKRO SYSTEMS, INC.
    Inventors: Ching-Pang Lee, Benjamin Heneveld
  • Patent number: 10781697
    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: September 22, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10773344
    Abstract: An electrode for electrical discharge machining (EDM) may comprise a diffuser portion and a tapered portion defining the tip of the electrode. A method for forming a film cooling hole may comprise moving a tool with respect to a film cooled gaspath component, forming a diffuser of the film cooling hole in response to the moving, and forming a tapered surface between a metering section and the diffuser of the film cooling hole.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: September 15, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Scott D. Lewis, Stephen Lynch, Shane Haydt
  • Patent number: 10774658
    Abstract: A rotor blade for use in combustion turbine engine. The rotor blade may include: an airfoil assembled from two radially stacked non-integral sections in which a body section resides inboard of a cap section; an outboard tip of the airfoil that is enclosed by a tip plate having a tip rail; and a cooling configuration that includes cooling channels for directing a coolant through the rotor blade. Each of the cooling channels may include segments, in which: a supply segment extends radially through the airfoil, the supply segment being radially defined between a floor and ceiling; a rail segment extends through an interior of the tip rail; and a connecting segment extends between the supply segment and rail segment. For each of the one or more cooling channels, the ceiling of the supply segment may be defined within the cap section of the airfoil.
    Type: Grant
    Filed: July 28, 2017
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventor: Christopher William Kester
  • Patent number: 10775115
    Abstract: Thermal spray coating methods and thermal spray coated articles are disclosed. The thermal spray coating method includes positioning a covering on a cooling channel of a component, and thermal spraying a feedstock onto the covering. The covering prohibits the feedstock from entering the cooling channel in the component and is not removed from the component. In another embodiment, the thermal spray coating method includes providing a component comprising a substrate material, providing a cooling channel on a surface of the component, positioning a covering on the cooling channel, and thermal spraying a feedstock onto the component and the covering, the feedstock comprising a bond coat material. The covering prohibits the bond coat material from entering the cooling channel. The thermal spray coated article includes a component, a cooling channel, a covering on the cooling channel, and a thermally sprayed coating on the component and the covering.
    Type: Grant
    Filed: August 29, 2013
    Date of Patent: September 15, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Jon Conrad Schaeffer
  • Patent number: 10774662
    Abstract: A vane stage segment is provided including an outer wall segment, an inner wall segment, and an airfoil. The outer wall segment is configured to be coupled to other outer wall segments to form an outer wall of the vane stage. The inner wall segment is spaced radially inward from the outer wall segment. At least one of the inner wall segment or the outer wall segment is separable between a forward portion and an aft portion. The airfoil extends between the outer wall segment and the inner wall segment.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: September 15, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Elise A. M. Brown, Emma L. Mitchell, Elyse M. McMillen, David L. Tondreau, III, Eric T. Koenig, Linnea L. Taketa
  • Patent number: 10774665
    Abstract: A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.
    Type: Grant
    Filed: July 31, 2018
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: John Ellington Greene, Neelesh Nandkumar Sarawate
  • Patent number: 10774746
    Abstract: Systems and methods for cooling one or more components of a gas turbine are provided. One system may include an expansion device and one or more conduits. The expansion device may be operatively coupled to the gas turbine and configured to convert a pressure drop of a stream of compressed process fluid to mechanical energy. The expansion device may be further configured to at least partially drive the gas turbine with the mechanical energy. The one or more conduits may fluidly couple the expansion device and the gas turbine. The one or more conduits may be configured to direct an expanded stream of the compressed process fluid to the one or more components of the gas turbine to cool the one or more components.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: September 15, 2020
    Assignee: DRESSER-RAND COMPANY
    Inventor: Jason M. Kerth
  • Patent number: 10774668
    Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor assembly that includes a first turbine rotor and a second turbine rotor. The first turbine rotor includes an outer rotor and a plurality of outer rotors extended inwardly along a radial direction from the outer rotor. The second turbine rotor includes an inner rotor and a plurality of inner rotor airfoils extended outwardly along the radial direction from the inner rotor. The plurality of outer rotor airfoils and inner rotor airfoils are disposed in alternating arrangement along a longitudinal direction. One or more rotating seal interfaces are defined between the first turbine rotor and the second turbine rotor.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: Richard Alan Wesling, Darek Tomasz Zatorski
  • Patent number: 10774655
    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.
    Type: Grant
    Filed: March 13, 2018
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Gina Cavallo
  • Patent number: 10767491
    Abstract: A turbine blade including a root bearing an aerofoil extending in a direction of span and ending in a tip, this aerofoil including a leading edge and a trailing edge which are connected by a pressure face wall and a suction face wall, the trailing edge including on the pressure face side cooling slots. The trailing edge includes one or more first slots close to the root, which are supplied via a lower cavity; one or more last slots near the tip which are supplied via an upper cavity; intermediate slots situated between the first slots and the last slots supplied with air via a downstream line set; and wherein the lower cavities and upper cavities and the downstream line set are supplied distinctly at the level of the root.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: September 8, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrice Eneau, Sebastien Serge Francis Congratel, Charlotte Marie Dujol, Philippe Picot
  • Patent number: 10767509
    Abstract: A component for a gas turbine engine, includes an external surface bounding a hot gas path of the gas turbine engine, and a cooling passage configured to deliver a cooling airflow therethrough. The cooling passage includes an internal surface located opposite the external surface, together defining a component wall. A plurality of trip strip features are located along the internal surface having a trip strip height extending from the internal surface and a trip strip width extending along the internal surface in a flow direction of the cooling airflow through the cooling passage. A ratio of a trip strip pitch between adjacent trip strip features in a width direction and the trip strip height is less than 5. One or more cooling film bleed holes extend from the internal surface to the external surface and are located between adjacent trip strip features of the plurality of trip strip features.
    Type: Grant
    Filed: October 3, 2017
    Date of Patent: September 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dominic J. Mongillo, Jr.
  • Patent number: 10767501
    Abstract: An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: September 8, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Joseph Anthony Weber, Srikanth Chandrudu Kottilingam, Brian Lee Tollison
  • Patent number: 10767493
    Abstract: A turbine section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.
    Type: Grant
    Filed: February 1, 2019
    Date of Patent: September 8, 2020
    Assignee: Rolls-Royce plc
    Inventors: Michael J. Whittle, Steven Hillier
  • Patent number: 10760426
    Abstract: An apparatus and method for controlling a flow of fluid through a nozzle assembly including a set of nozzles. The nozzles can have a set of airfoils defining a throat between the airfoils. One or more exhaust holes can be provided in the airfoils downstream of the throat. A fluid supply line can be fluidly coupled to the exhaust holes for selectively supplying a flow of fluid through the exhaust holes.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Paul Hadley Vitt, Brian David Keith
  • Patent number: 10760431
    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: September 7, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Zachary Daniel Webster, Aaron Ezekiel Smith, Kirk D. Gallier
  • Patent number: 10760491
    Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold in communication with said mid-span pre-diffuser inlet and said combustor section.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: September 1, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, William K. Ackermann
  • Patent number: 10753215
    Abstract: A turbine vane of a turbine engine such as a turbojet. The vane includes a base supporting a blade that extends in a spanwise direction and ends in an apex. The blade includes a pressure-side wall and a suction-side wall, each ending at an end edge at the apex of the blade. The blade includes, at the apex thereof, a closed wall extending from the pressure-side wall to the suction-side wall so as to define, with the end edges, a tub shape. The pressure-side wall is curved inward so as to deviate from the spanwise direction in the region of the blade apex preceding the tub, between the base and the pressure-side end edge.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: August 25, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Laurent Patrick Robert Coudert, Erwan Daniel Botrel
  • Patent number: 10753228
    Abstract: A turbomachinery component for a turbomachine includes feed manifold, a return manifold and a sidewall. The feed manifold is configured to receive a coolant stream therein and includes a plurality of feed plenums. The return manifold includes a plurality of return plenums. The sidewall defines a plurality of feed channels and a plurality of return channels therein. The sidewall further includes an inner surface and an outer surface opposite the inner surface. Each feed channel is in fluid communication with at least one of the feed plenums. Each return channel is in fluid communication with at least one of the return plenums. The sidewall further at least partially defines a plurality of microchannels. Each microchannel is in fluid communication with one of the feed channels and one of the return channels.
    Type: Grant
    Filed: August 11, 2016
    Date of Patent: August 25, 2020
    Assignee: General Electric Company
    Inventors: James Fredric Wiedenhoefer, James Albert Tallman, Brian Gene Brzek
  • Patent number: 10753207
    Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: August 25, 2020
    Assignee: General Electric Company
    Inventors: Nicholas William Rathay, Thomas Earl Dyson, Brendon James Leary, Gregory Terrence Garay, Gustavo Adolfo Ledezma, David Wayne Weber, Aaron Ezekiel Smith
  • Patent number: 10746029
    Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge and a trailing edge and defines a chord extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and includes a leading edge wall and a trailing edge wall and defines a tip shroud cavity. The tip shroud cavity includes a leading edge portion at least partially defined by the leading edge wall and positioned largely upstream of fifty percent of the chord. The tip shroud cavity also includes a trailing edge portion at least partially defined by the trailing edge wall and positioned largely downstream of fifty percent of the chord. An intermediate portion of the tip shroud cavity fluidly couples the leading edge portion of the tip shroud cavity and the trailing edge portion of the tip shroud cavity.
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: August 18, 2020
    Assignee: General Electric Company
    Inventors: Jeffrey Clarence Jones, Robert Alan Brittingham
  • Patent number: 10738644
    Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.
    Type: Grant
    Filed: August 30, 2017
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
  • Patent number: 10738621
    Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Stephen Mark Molter, Mark Edward Stegmiller, Shawn Michael Pearson, Steven Robert Brassfield
  • Patent number: 10738636
    Abstract: An airfoil adapted for use in a gas turbine engine is disclosed herein. The airfoil includes a spar defining an interior space and a cover sheet extending around at least a portion of the spar. The cover sheet is bonded to the spar to define a cooling cavity between the spar and the cover sheet.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: August 11, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Mark O'Leary
  • Patent number: 10738651
    Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Brad Wilson VanTassel, Joseph Anthony Weber, Bryan David Lewis, Travis J Packer
  • Patent number: 10738637
    Abstract: An airflow deflector is provided that includes at least one liner attachment flange, a deflector panel, and at least one deflector leg. The at least one liner attachment flange has a liner side surface and an opposing outer surface. The at least one deflector leg extends between and is attached to the at least one liner attachment flange. The at least one deflector leg extends a distance between the deflector panel and the liner attachment flange to maintain the deflector panel a separation distance from the liner attachment flange. The airflow deflector is configured for insertion of the at least one deflector leg and the deflector panel within a liner aperture.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Edward Guevel, Rebecca R. Dunnigan, Mark W. Colebrook, Austin R. O'Mara
  • Patent number: 10738619
    Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
    Type: Grant
    Filed: January 2, 2015
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Lane Thornton, Matthew A. Devore, Dominic J. Mongillo, Steven Bruce Gautschi
  • Patent number: 10738618
    Abstract: A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.
    Type: Grant
    Filed: October 21, 2016
    Date of Patent: August 11, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Shinya Hashimoto, Keita Takamura
  • Patent number: 10738620
    Abstract: A gas turbine engine includes a first vane of a turbine section, a second vane of the turbine section, an impingement plate that includes a first impingement hole and a second impingement hole, and a pipe that supplies a fluid. The first vane includes a first platform. The second vane includes a second platform and a baffle. A first portion of the fluid traverses the first impingement hole and impinges on a first surface of the first platform. A second portion of the fluid traverses the second impingement hole and impinges on a second surface of the second platform. A third portion of the fluid bypasses the impingement plate and enters the baffle.
    Type: Grant
    Filed: April 18, 2018
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Corey D. Anderson, Jeremy Styborski
  • Patent number: 10731477
    Abstract: An airfoil includes an airfoil body having a pressure side and a suction side that each radially extend between a first radial boundary end and a second radial boundary end and each axially extend between a leading edge and a trailing edge. The airfoil body defines a plurality of first skin core passages disposed proximate the suction side and radially extend from the first radial boundary end towards the second radial boundary end, and a plurality of second skin core passages that radially extend toward the second radial boundary end and circumferentially extend towards the suction side proximate the second radial boundary end.
    Type: Grant
    Filed: September 11, 2017
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: San Quach, Jeffrey T. Morton
  • Patent number: 10731478
    Abstract: A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a first edge, a second edge, having a tip end opposite from the root end. The turbine blade further including a base rib extending from the base and into the airfoil, a center divider extending from adjacent the first edge towards the second edge, a center rib disposed between the center divider and the second edge, extending from adjacent the center divider towards the tip end and extending from adjacent the center divider towards the root end, a tip center rib extending from adjacent the second edge towards the first edge, a tip rib extending from adjacent the tip center rib towards the base, a dividing rib and a first channel.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: August 4, 2020
    Assignee: Solar Turbines Incorporated
    Inventors: Hongzhou Xu, Kevin Liu, Michael D. Fox
  • Patent number: 10731479
    Abstract: A blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint retaining a lateral edge of a damper seal received in the cavity, wherein the lateral edge of the damper seal extends between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion extend towards the root when the damper seal is located in the cavity and wherein the damper restraint extends along and adjacent to a portion of the lateral edge of the damper seal.
    Type: Grant
    Filed: January 3, 2017
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Charles Thistle, Mohamed Hassan
  • Patent number: 10731469
    Abstract: A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine having an external pressure, and wherein the component body includes at least one internal cavity having an internal pressure. At least one inlet opening is formed in an outer surface of the component body to direct hot exhaust gas flow into the at least one internal cavity, and there is at least one outlet from the internal cavity. The internal pressure is less than an inlet external pressure at the inlet opening and the internal pressure is greater than an outlet external pressure at the outlet opening to controllably ingest hot exhaust gas via the inlet opening and expel the hot exhaust gas via the outlet opening to maintain a laminar boundary layer along the outer surface of the component body.
    Type: Grant
    Filed: September 6, 2017
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: JinQuan Xu, James Tilsley Auxier
  • Patent number: 10731473
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel A. Snyder, Tracy A. Propheter-Hinckley, Dominic J. Mongillo
  • Patent number: 10724391
    Abstract: An apparatus and method relating to an airfoil for a turbine engine and cooling channels within the airfoil. The airfoil includes an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. Further, the airfoil includes ribs located within the interior and a flow enhancer extending between the ribs.
    Type: Grant
    Filed: April 7, 2017
    Date of Patent: July 28, 2020
    Assignee: General Electric Company
    Inventors: David Allen Flodman, Robert Francis Manning
  • Patent number: 10724380
    Abstract: A gas turbine engine turbine blade includes internal structural support radially supporting aerodynamic fairing. Strut radially extends away from root of support. Fairing includes hollow fairing airfoil surrounding strut and extending from fairing platform to blade tip shroud at tip of the fairing airfoil. A support cap attached to radially outer end of strut outwardly restrains fairing. Seal teeth may extend outwardly from the support cap. Internal cooling air flow path may extend radially through support. Fairing may be made from material lighter in weight than the support. Fairing material may be ceramic matrix composite and support material may be metallic. Blades may be mounted in rim of disk by roots disposed in slots through rim. Annular plate mounted to, upstream of, and proximate web of disk defines in part cooling airflow path to slot.
    Type: Grant
    Filed: August 7, 2017
    Date of Patent: July 28, 2020
    Assignee: General Electric Company
    Inventors: Robert Charles Groves, II, Ronald Scott Bunker
  • Patent number: 10724382
    Abstract: A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part.
    Type: Grant
    Filed: August 12, 2016
    Date of Patent: July 28, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Sergei Riazantsev, Stefan Rofka, Robert Marmilic, Hanspeter Knopfel, Sergey Shchukin