With Diversely Oriented Inlet Or Additional Inlet For Diverse Fluid (e.g., Heating, Cooling Or Mixed Working Fluid, Etc.) Patents (Class 415/116)
  • Patent number: 11149588
    Abstract: An exhaust chamber of a steam turbine includes a casing, an inner flow guide portion disposed in the casing so as to define an outer boundary of a diffuser passage communicating with an outlet of a last stage blade in the steam turbine, and an outer flow guide portion disposed on an outer peripheral side of the inner flow guide portion in the casing. The exhaust chamber has an exhaust chamber outlet on a lower side thereof. The outer flow guide portion is disposed at least around an upper half region of the inner flow guide portion.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: October 19, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Yoshihiro Kuwamura
  • Patent number: 11111811
    Abstract: A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: July 2, 2019
    Date of Patent: September 7, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael M. Joly, Zaffir A. Chaudhry, Simon W. Evans, Gorazd Medic, Dilip Prasad
  • Patent number: 11098613
    Abstract: A retention device for at least one cooling tube of a cooling system of a turbomachine casing, the casing extending around an axial direction of the turbomachine, the retention device includes a fixing plate suited to being made integral with the casing and a retention element for the cooling tube. The retention device includes an adjustment system configured to adjust the relative position of the retention element with respect to the fixing plate and to absorb a relative movement between the retention element and the fixing plate.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: August 24, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Didier Noël Durand, Nicolas Delaporte, Anthony Pierre Beguin
  • Patent number: 11092014
    Abstract: A blade track system includes a blade track configured to be positioned around a plurality of blades of a gas turbine engine. The blade track includes: a full-hoop body, an inlet port, and an exit port. The full-hoop body includes an outer surface and an inner surface. The inner surface defines an internal cooling channel extending within the full-hoop body. The inlet port and the exit port are each integrated with the full-hoop body and in fluid communication with the internal cooling channel.
    Type: Grant
    Filed: April 6, 2020
    Date of Patent: August 17, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Corina Moga, Tony Lambert, Shaling Starr
  • Patent number: 11085641
    Abstract: A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: August 10, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Nagaraja S. Rudrapatna, Atul Verma, David Chou, Christopher Zollars
  • Patent number: 11021986
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends circumferentially between first and second mate faces and an engagement portion along the first mate face. A support has an interface portion that extends from a mounting portion. The interface portion abuts the engagement portion to limit relative movement, and the mounting portion defines an aperture that receives a fastener to mechanically attach the mounting portion to an engine static structure. A portion of the fastener is circumferentially aligned with the first mate face. The fastener defines a first cooling passage that delivers cooling flow at a location adjacent to the first mate face.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: June 1, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Winston Gregory Smiddy, Paul M. Lutjen
  • Patent number: 11021981
    Abstract: A gas turbine engine includes a main compressor section and a turbine section. The turbine section has a first turbine blade and vane and a downstream turbine component. A tap is configured to tap air from the compressor section at a location upstream of a most downstream location. The tap is connected to a heat exchanger. The heat exchanger is connected to a cooling compressor. The cooling compressor is connected to the downstream turbine component. A second tap is configured to tap air from a location in the main compressor section. The second tap is connected through a check valve to a line leading to the downstream turbine component.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Frederick M. Schwarz
  • Patent number: 10989201
    Abstract: A centrifugal compressor includes: a rotating shaft; a first impeller; a second impeller which is disposed on a downstream side of the first impeller; a return flow path which guides a first fluid flowing to a radially outer side from the first impeller toward a radially inner side; an introduction flow path which introduces the fluid guided to the radially inner side to the second impeller; an intermediate suction flow path which additionally supplies a second fluid to the second impeller; and a curved flow path which is connected to a downstream side of the introduction flow path and the intermediate suction flow path, and guides the first fluid and the second fluid to the second impeller, wherein a side surface on an upstream side of the introduction flow path is disposed on the downstream side from a return position of the return flow path.
    Type: Grant
    Filed: March 23, 2017
    Date of Patent: April 27, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Shuichi Yamashita, Akihiro Nakaniwa, Ryosuke Saito, Shinichiro Tokuyama
  • Patent number: 10989222
    Abstract: One exemplary embodiment of this disclosure relates to a refrigerant compressor. The compressor includes an axial section having a plurality of blades and vanes and a centrifugal section having an impeller. The centrifugal section is arranged downstream of the axial section.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: April 27, 2021
    Inventor: Justin Jongsik Oh
  • Patent number: 10989069
    Abstract: A steam turbine cooling unit for a steam turbine includes a coolant steam path provided to penetrate a casing along a superheated steam supply tube to reach a gap; and a coolant steam supplying unit configured to supply coolant steam flowing through the coolant steam path along the superheated steam supply tube to reach the gap, and having: (i) a pressure higher than a pressure of superheated steam to be supplied by the superheated steam supply tube; and (ii) a temperature lower than a temperature of the superheated steam to be supplied by the superheated steam supply tube.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: April 27, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Takumi Matsumura, Toyoharu Nishikawa, Katsuhisa Hamada
  • Patent number: 10968772
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: April 6, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Patent number: 10961866
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal is also disclosed.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: March 30, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Patent number: 10953960
    Abstract: In accordance with one embodiment, a self-propelled emissions control servicing watercraft that does not require transportation by tugboat and utilizes a hydraulic power unit that supplies hydraulic power to a hydraulic positioning arm during “service mode” and alternately uses the same hydraulic power unit to supply hydraulic power to hydraulic propulsion thrusters during “mobile mode”.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: March 23, 2021
    Inventor: Robert John Sharp
  • Patent number: 10935035
    Abstract: A closed impeller includes: a housing provided with an opening; an insert inserted into one side of the opening; and an impeller body inserted into the other side of the opening, and including a plurality of blades and a shroud covering the plurality of blades, wherein the insert is provided with an inflow channel guiding a fluid into an inlet of the impeller body, and wherein a clearance between an outer surface of the insert and an inner surface of the housing forms a circulation flow channel connecting the other end of the inflow channel with a portion where one end of the inflow channel meets the inlet of the impeller body.
    Type: Grant
    Filed: October 26, 2017
    Date of Patent: March 2, 2021
    Assignee: HANWHA POWER SYSTEMS CO., LTD
    Inventors: Robert Pelton, Se Woong Jung
  • Patent number: 10934871
    Abstract: A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Peter Broadhead, Aaron D. Sippel, David J. Thomas, Joseph P. Lamusga
  • Patent number: 10920602
    Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along the engine case for a turbine of a gas turbine engine. The distribution manifold may include a passageway for a thermal fluid, an inlet configured to direct the thermal fluid into the passageway, an inner surface extending along and facing the outer surface of the engine case, and a plurality of outlets configured to direct the thermal fluid onto the outer surface of the engine case. The thermal fluid may include bypass air. A component may add kinetic energy to the thermal fluid.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: February 16, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Adrian Carl Sitler, Andrew Eifert, Ryan C. Humes
  • Patent number: 10914187
    Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.
    Type: Grant
    Filed: September 11, 2017
    Date of Patent: February 9, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, ChaiDee Woods Brown
  • Patent number: 10907492
    Abstract: A gas turbine engine includes a turbine blade rotating about an axis of rotation defining an axial direction. A blade outer air seal is positioned radially outward of a radially outer tip of the turbine blade. The blade outer air seal has a forward support and an aft support. The forward support is supported on a forward hook from a blade outer air seal support. The aft support is supported on an aft hook from the blade outer air seal support. The blade outer air seal has a central web extending between the forward support and the aft support and radially outwardly of the turbine blade radially outer tip. A radially outer chamber is defined radially outwardly of the central web, and axially intermediate the forward support and the aft support. The radially outer chamber is divided into at least two separate subchambers maintained at two different pressures. A forward subchamber is at a higher pressure than an aft subchamber. A seal separator separates the forward and aft subchambers.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: February 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Thomas E. Clark, William M. Barker
  • Patent number: 10907487
    Abstract: A turbine shroud assembly includes a shroud support and a shroud segment. The shroud support structure includes a forward support rail and an aft support rail. The forward support rail includes forward first engagement structures and the aft support rail includes aft first engagement structures. The shroud segment includes a forward segment rail and an aft segment rail. The forward segment rail includes forward second engagement structures positioned on a forward segment rail periphery and the aft segment rail includes second engagement structures positioned on an aft segment rail periphery. The forward first engagement structures radially and circumferentially engage with the forward second engagement structures and the aft first engagement structures radially and circumferentially engage with the aft second engagement structures to radially and circumferentially interlock the shroud segment to the shroud support structure.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: February 2, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Luke Zurmehly, Jason Smoke, Kent L Kime, Blake Petersen
  • Patent number: 10900370
    Abstract: A tip clearance control (TCC) system 100 is provided to control the gap 176 between the tips of turbine blades 172 of a gas turbine engine 10 and the casing 174 within which they rotate. The inlet 120 to the TCC system is provided in a bifurcation panel 110 that extends across a bypass duct 22 of the gas turbine engine 10. The inlet is provided on a first major surface 112 of the bifurcation panel 110 that is defined such that the direction (R) that points through the bifurcation panel from the first major surface 112 to a second major surface 114 corresponds to the fan rotation direction. This provides a particularly effective and/or efficient TCC system 100.
    Type: Grant
    Filed: November 5, 2018
    Date of Patent: January 26, 2021
    Assignee: ROLLS-ROYCE plc
    Inventor: Zahid M. Hussain
  • Patent number: 10883372
    Abstract: A gas turbine component, for forming part of a stage of the turbine, operable to change cooling scheme, includes an airfoil profiled section, a cooling passageway, film holes and interchangeable connectors. The profiled section includes pressure and suction sides joined together at chordally opposite leading and trailing edges. The cooling passageway extends between the pressure and suction sides along the leading edge to enabling cooling fluid to flow therefrom. The film holes are configured on the cooling passageway to enable the flow of a portion of the cooling fluid to a portion of the profiled section. The interchangeable connectors configured to the cooling passageway, one at a time, to change the cooling scheme. An insert may also be provided to close and open the film holes.
    Type: Grant
    Filed: January 26, 2015
    Date of Patent: January 5, 2021
    Assignee: General Electric Technology GMBH
    Inventors: Joergen Ferber, Petr Vitalievich Laletin
  • Patent number: 10871170
    Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: December 22, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shakeel Nasir, Nick Nolcheff, Cristopher Frost
  • Patent number: 10844728
    Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and defining a pressure side and a suction side 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. A plurality of outlets and a plurality of scalloped portions can extend proximate the trailing edge.
    Type: Grant
    Filed: April 17, 2019
    Date of Patent: November 24, 2020
    Assignee: General Electric Company
    Inventors: Tingfan Pang, Helen Ogbazion Gabregiorgish, Zachary Daniel Webster, Gregory Terrence Garay, Steven Robert Brassfield, Daniel Endecott Osgood
  • Patent number: 10830059
    Abstract: A turbine blade having a base and an airfoil, the base including cooling air inlets and an internal cooling air passageway, and the airfoil including an internal multi-bend heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, and a tip flag cooling system.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: November 10, 2020
    Assignee: Solar Turbines Incorporated
    Inventors: Andrew T. Meier, Nnawuihe Okpara, Stephen Edward Pointon, Jeffrey S. Carullo
  • Patent number: 10830076
    Abstract: A guide vane located in a fan air flow in an aircraft twin-spool turbomachine, the vane being made with an extrados body and an intrados body between which there is a thermal conduction matrix. Furthermore, the attachment devices between the two spools are arranged outside the aerodynamic part of the vane.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: November 10, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Cedric Zaccardi, Christophe Marcel Lucien Perdrigeon, Paul Antoine Foresto, Adrien Jacques Philippe Fabre
  • Patent number: 10822985
    Abstract: A method of forming a gas turbine engine component includes the steps of (a) forming an intermediate portion, (b) forming cooling circuit structure into at least an outer layer of the intermediate portion, (c) providing an outer layer over the formed cooling circuits to close off the cooling circuits, such that there are laminate on both a radially inner and a radially outer side of the cooling circuits, and (d) forming an inlet and an outlet to the cooling circuits through the outer layer. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: August 29, 2018
    Date of Patent: November 3, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Thomas E. Clark, Winston Gregory Smiddy, Daniel J. Whitney, William M. Barker
  • Patent number: 10815829
    Abstract: The turbine housing assembly includes a housing surrounding a plurality of turbine shroud segments mounted to support members of the housing. Impingement holes extend through the housing and have outlet openings communicating with a cavity between the shroud segments and the support. A deflector rail protrudes axially away from the support members into the cavity. The deflector rail defines a flow-redirecting surface to redirect the cooling air flow from the impingement holes radially outwardly, away from the turbine shroud segments.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kapila Jain, Patricia Phutthavong, Marc Tardif, Ho-Wing Leung
  • Patent number: 10815815
    Abstract: A method of actuating a Blade Outer Air Seal (BOAS) includes moving a retractor against a portion of a BOAS segment to move the BOAS segment from a first position to a second position that is radially outside the first position. The BOAS segment is seated against a support structure when in the first position and spaced from the support structure when in the second position.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Brian Duguay
  • Patent number: 10815812
    Abstract: A blade outer air seal (BOAS) is provided. The BOAS comprising: a seal body having a forward side, an aft side opposite the forward side, a radially inward side, and a radially outward side opposite the radially inward side; and a relief gap within the seal body to allow a portion of the radially inward side to expand into the relief gap when the seal body is heated.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel Barak, Joseph F. Englehart
  • Patent number: 10808561
    Abstract: The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.
    Type: Grant
    Filed: May 27, 2018
    Date of Patent: October 20, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Klaus Pirker, Lukasz Sosnowka, Bernd Kislinger, Rudolf Stanka, Marcin Regulski
  • Patent number: 10801354
    Abstract: A gas turbine engine includes a first case, a second case, and a fastener. The first case has a first flange defining a first opening. The second case has a second flange defining a second opening. The second flange abuts the first flange. The fastener extends through the first opening and the second opening. The fastener defines a first bore that extends through a fastener head along an axis towards an outlet port defined by a fastener shank.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: October 13, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Philip Robert Rioux, Nicholas R. Leslie
  • Patent number: 10801351
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: October 13, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Kevin L. Rugg, Winston Gregory Smiddy
  • Patent number: 10774664
    Abstract: A gas turbine having an annular flowpath defined between concentric inner radial and outer radial boundaries. A plenum is positioned just outboard of the outer radial boundary that wraps circumferentially in spaced relation thereto. The height of the plenum is defined radially between a floor and ceiling. The plenum includes an inlet formed through the ceiling at a first end and spaced outlet ports formed through the floor. The plenum includes a divider baffle that spans the width of the plenum and extends between the first end and the second end of the plenum so to divide the plenum into radially stacked first and second compartments. The first compartment connects directly to the inlet, while the second compartment connects directly to the outlet ports. The height of the first compartment tapers between a greater height at the first end and a lesser height at the second end of the plenum.
    Type: Grant
    Filed: June 8, 2017
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: John Rogers Mason, III, Zhongman Ding, John Lesley DuBose
  • Patent number: 10774742
    Abstract: A compressor rotor includes a first disk and a conical section connected to the first disk. The conical section includes at least one flow hole. A bore cavity is defined between the conical section and the first disk. The bore cavity is arranged in fluid communication with the at least one flow hole. An anti-vortex tube is disposed within the at least one flow hole of the conical section and includes at least one feature arranged in contact with a surface of the conical section to restrict movement of the anti-vortex tube out of engagement with the conical section.
    Type: Grant
    Filed: March 21, 2018
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Konstantinos Panagiotis Giannakopoulos, Erica J. Harvie
  • Patent number: 10767863
    Abstract: An annular assembly for a gas turbine engine and a method of making the annular assembly. The annular assembly comprises a supporting member comprising metal and including a support hole therethrough, and a liner tile made of ceramic matrix composite material. A plurality of the liner tile form an annular liner to shield hot combustion gases produced by the gas turbine engine. The liner tile is disposed adjacent the supporting member. A connecting member comprising ceramic material has a base element and a stem. The base element is embedded in the liner tile during construction of the liner tile to form an integrated structure therewith. A distal end of the stem passes through the support hole and is mated with a retaining member to retain the liner tile adjacent the supporting member.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: September 8, 2020
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted Joseph Freeman, Bruce E. Varney, Andrew Joseph Lazur
  • Patent number: 10753220
    Abstract: A blade outer air seal includes a base portion that extends between a leading edge and a trailing edge. A forward wall and an aft wall extend radially outward from the base portion to a radially outer portion. The radially outer portion is spaced from the base portion.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: August 25, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, Daniel J. Whitney
  • Patent number: 10738642
    Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The supported component includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend into the carrier to couple the supported component with the carrier.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 11, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Jun Shi, Jeffrey A. Walston, Aaron D. Sippel
  • Patent number: 10731498
    Abstract: The present disclosure relates generally to blade outer air seal section mount including a resilient spring element that acts to provide re-centering forces to the blade outer air seal section when non-uniform forces applied to the blade outer air seal section causing it to move away from its nominal position.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10731562
    Abstract: A combustor panel may comprise a panel wall comprising a proximal surface and a distal surface. A standoff may be formed over the distal surface of the panel wall. An aperture may be formed through the standoff and may extend from a face of the standoff to the proximal surface of the panel wall. The face of the first standoff may be oriented at an angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall.
    Type: Grant
    Filed: July 17, 2017
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, Jonathan Lemoine
  • Patent number: 10731502
    Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: William K. Ackermann, Matthew P. Forcier, Paul J. Hiester
  • Patent number: 10731507
    Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: August 4, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Eric W. Engebretsen, Daniel E. Molnar, Jr., Matthew J. Kappes
  • Patent number: 10731472
    Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: August 4, 2020
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10723196
    Abstract: An HVAC system according to an example of the present disclosure includes a blower rotatable about an axis. The blower has a first blower section and a second blower section fluidly isolated from the first blower section. An inlet assembly at an axial end of the blower includes a first compartment configured to control fluid flow through the first blower section and a second compartment configured to control fluid flow through the second blower section.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: July 28, 2020
    Assignee: AIR INTERNATIONAL (US) INC.
    Inventors: Wayne Wright, Richard Hoyle
  • Patent number: 10718267
    Abstract: Various embodiments of the present disclosure address problems associated with non-uniform flow of cooling air by providing a turbine engine including a cooling air chamber in fluid communication with a cooling air source, a turbine chamber, and multiple conduits fluidly connecting the cooling air chamber and the turbine chamber. The system is configured such that, when cooling air is flowing from a cooling air source the static pressure within the cooling fluid chamber is substantially uniform and such that the mass flow rates of cooling air through the conduits and into the turbine chamber are substantially uniform.
    Type: Grant
    Filed: December 14, 2017
    Date of Patent: July 21, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Matthew M. Miller, Renée M. Wiley
  • Patent number: 10711629
    Abstract: The present disclosure is directed to a method of operating an active clearance control system for an interdigitated turbine engine. The method includes flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section; and adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine. The present disclosure is further directed to a gas turbine engine including a low speed turbine rotor comprising an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The engine further includes a turbine frame at least partially surrounding the low speed turbine rotor; a seal assembly disposed between the outer shroud of the low speed turbine rotor and the turbine frame; and a fifth manifold coupled to the turbine frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: July 14, 2020
    Assignee: Generl Electric Company
    Inventors: Gert Johannes van der Merwe, Darek Tomasz Zatorski
  • Patent number: 10711796
    Abstract: A multistage centrifugal compressor is described. The compressor comprises a casing and a shaft rotatingly supported in the casing by at least a first bearing and a second bearing. At least one in-between-bearing impeller is mounted on the shaft, between the first bearing and the second bearing. An overhung impeller is mounted at one end of the shaft. A first diaphragm arrangement is further located in the casing. The first diaphragm arrangement comprises return a channel assembly with a plurality of stationary return channel blades defining a plurality of return vanes for redirecting compressed gas from an exit location of the overhung impeller to an inlet location of the in-between-bearings impeller. The first diaphragm arrangement houses one of the first bearing and second bearing.
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: July 14, 2020
    Assignee: NUOVO PIGNONE SRL
    Inventors: Vittorio Michelassi, Ismail Hakki Sezal, Christian Aalburg
  • Patent number: 10697313
    Abstract: A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have a higher temperature capability than that of the wall.
    Type: Grant
    Filed: February 1, 2017
    Date of Patent: June 30, 2020
    Assignee: General Electric Company
    Inventor: Victor Hugo Silva Correia
  • Patent number: 10689997
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body having a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The seal body defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines a plurality of apertures to the internal cavity. A housing is mounted to the seal such that the impingement face is exposed to define a plenum between the housing and the impingement face. The housing defines a plurality of cooling passages, and each of the plurality of cooling passages define a passage axis that is oriented such that a projection of the passage axis intersects the seal body. A method of sealing is also disclosed.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: June 23, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Winston Gregory Smiddy, Paul M. Lutjen
  • Patent number: 10689998
    Abstract: Shrouds and methods for forming turbine components are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a cooling passage defined in the shroud, the cooling passage extending generally circumferentially through the shroud.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: David Scott Stapleton, Robert Charles Groves, II
  • Patent number: RE48320
    Abstract: The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20i, 201+1), wherein a free axial path length (af) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a1) of a rotation locking member (10) of the outer sealing ring (af?a1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a2) of a radial mounting rail (23) of the outer sealing ring (af?a2), and/or an axial offset (a3, a4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit and pi is at least as large as a difference between a maximum outer diameter of the outer sealing ring and a minimum inner diameter of the flow channel inlet of the housing.
    Type: Grant
    Filed: November 15, 2018
    Date of Patent: November 24, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Walter Gieg, Petra Kufner, Rudolf Stanka