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: 11415007
    Abstract: A gas turbine engine includes a shroud ring, a vane ring, and a secondary flow assembly. The shroud ring extends around an associated turbine wheel and includes a carrier segment and a blade track segment comprising ceramic matrix composite materials. The blade track segment and the carrier segment defining a shroud cavity radially therebetween. The vane ring includes a heat shield comprising ceramic matrix composite materials that forms an outer platform, an inner platform, and an airfoil defining a heat shield cavity radially through the heat shield. The secondary flow assembly includes a recirculating flow circuit having a discharge tube and a vane pressurizing tube; and the secondary flow assembly is configured to cool the blade track segment. The flow circuit is further configured to pressurize the heat shield cavity thereby providing a seal against the gases from the primary gas path entering the heat shield cavity.
    Type: Grant
    Filed: January 24, 2020
    Date of Patent: August 16, 2022
    Inventors: Michael J. Whittle, Keith Sadler, Matthew D. Thomason, Andrew Holt
  • Patent number: 11391289
    Abstract: Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a capacity control valve that has a curved surface facing a flow of refrigerant from the first stage to the second stage. The capacity control valve can allow or obstruct flow through the side stream injection port. The capacity control valve can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. The side stream injection port and the capacity control valve can be ring-shaped. The side stream injection port and the capacity control valve can allow at least some of the side stream to be introduced on a side of the capacity control valve opposite the curved surface.
    Type: Grant
    Filed: April 30, 2020
    Date of Patent: July 19, 2022
    Assignee: TRANE INTERNATIONAL INC.
    Inventors: Rick T. James, Yuanjie Wu, Christopher Glen Thilges, Mark W. Harrison, Jon Christopher Johnson
  • Patent number: 11391177
    Abstract: A turbocharger includes a turbine housing configured to house a turbine rotor provided on one side of a rotor shaft; and a bearing housing configured to house a bearing that rotatably supports the rotor shaft, in which at least one cooling water flow path through which cooling water flows is formed in at least one of the turbine housing and the bearing housing, and the at least one cooling water flow path is formed such that a plurality of flow path cross sections are present in, of a cross-section including an axis of the rotor shaft, a half cross-section divided by the axis.
    Type: Grant
    Filed: April 8, 2021
    Date of Patent: July 19, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yutaka Fujita, Tadashi Kanzaka
  • Patent number: 11377960
    Abstract: A low-pressure compressor for an axial-flow turbomachine, such as a jet engine, includes an annular row of vanes and a between-vanes passage with a connecting surface that links the pressure surface of a first vane to the suction surface of a second vane of the row. The connecting surface includes a main protuberance which includes a first elevation and a second elevation that are spaced apart from one another.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: July 5, 2022
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Stéphane Hiernaux
  • Patent number: 11357127
    Abstract: A plenum for processing one or more byproducts output from a generator, and systems and methods thereof, can have the plenum in the form of a hollow elongate rectangular box having a first end and a second end opposite the first end. The plenum can have a frame and a sidewall fixed to the frame, and can be adapted to be oriented vertically when operatively coupled to receive the one or more byproducts from the generator. The sidewall can include an opening adapted to receive heated air from the generator as one of the byproducts from the generator.
    Type: Grant
    Filed: July 16, 2020
    Date of Patent: June 7, 2022
    Assignee: Caterpillar Inc.
    Inventors: Praveen Venugopal, Timothy D. Collins, Andrew Philip McKeown, Nicholas Murray, Joseph W. Brunton, Karl A. Hagen, Damian Grant
  • Patent number: 11346245
    Abstract: A steam-turbine unit has a steam turbine and an option for cooling the steam turbine by forced cooling, wherein cooling air is drawn through the steam turbine via a suction device and a drainage line of the live-steam valve is used as the access option.
    Type: Grant
    Filed: January 28, 2015
    Date of Patent: May 31, 2022
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Edwin Gobrecht, Stefan Riemann, Gerta Zimmer
  • Patent number: 11346248
    Abstract: A nozzle segment for a gas turbine engine comprises an outer band having a cooling air inlet, an inner band having a first cooling air outlet, and a nozzle airfoil comprising a cooling flow passage arranged to receive the cooling air as a cooling air stream. A first channel and a second channel are arranged within the cooling flow passage. A deflector is arranged to divide the cooling air stream into a first cooling air stream in the first channel and a second cooling air stream in the second channel, respectively. The deflector deflects the first cooling air stream obliquely to a suction sidewall in the first channel, wherein the first channel is configured to transport the first cooling air stream along the first channel in a swirly flow.
    Type: Grant
    Filed: February 3, 2021
    Date of Patent: May 31, 2022
    Assignee: General Electric Company Polska Sp. Z o.o.
    Inventors: Tomasz Bulsiewics, Leszek Marek Rzeszutek, Maciej Michal Stańczyk, Dariusz Olczak, Jaroslaw Stec
  • Patent number: 11333171
    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 18, 2020
    Date of Patent: May 17, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shakeel Nasir, Nick Nolcheff, Cristopher Frost
  • Patent number: 11286934
    Abstract: A vacuum pump system is provided that includes a main vacuum pump that is connected to a chamber that is to be evacuated. An auxiliary pump is connected to an outlet of the main vacuum pump. Furthermore, a sealing gas supply device is connected to the main vacuum pump. The sealing gas supply device is switched on and off with the aid of a control device as a function of a predetermined control variable. Additionally, a method for controlling the vacuum pump system.
    Type: Grant
    Filed: November 23, 2017
    Date of Patent: March 29, 2022
    Assignee: Leybold GmbH
    Inventors: Max Pelikan, Raffaello Ghislotti, Dirk Schiller, Daniel Reinhard
  • Patent number: 11286802
    Abstract: A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.
    Type: Grant
    Filed: October 9, 2019
    Date of Patent: March 29, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Aaron D. Sippel, Jeffrey M. Crutchfield, Jeffrey A. Walston
  • Patent number: 11274605
    Abstract: A method for shimming a thrust bearing for an accessory power take off shaft to obtain optimal meshing of bevel gears within the internal gearbox (IGB) without disassembly of the IGB is enabled by relocating the thrust bearing from the engine sump. The accessory gearbox (AGB) is driven from a power off-take from the turbine spool via the IGB. The radial position of the power take-off bevel gear is established by a radial position of the thrust bearing attached to the exterior of the casing via a housing. Candidate shims are selected from a set each having different thicknesses, the shims are formed of two halves and placed between the housing and the engine casing to adjust the radial position of the thrust bearing and consequently the power take-off bevel gear, without requiring the disassembly of the IGB.
    Type: Grant
    Filed: August 30, 2019
    Date of Patent: March 15, 2022
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Timothy David Sheridan, Joseph Swift, Daniel Feinstein, Caleb Camara
  • Patent number: 11268404
    Abstract: A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.
    Type: Grant
    Filed: May 22, 2020
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: David W. Morganson, Lawrence A. Binek
  • Patent number: 11242764
    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 an elongated seal body having a seal face that bounds a gas path and an opposed impingement face. The seal body defines an internal cavity extending in a circumferential direction between opposed mate faces and extending in a radial direction between walls of the seal body defining the seal and impingement faces. A baffle divides the internal cavity into at least a first region and a second region. The first region has a first section extending transversely from a second section. The first section has a component in the radial direction, and the second section has a component in an axial direction such that the second region is defined between the baffle and the walls of the seal body defining the seal face. A method of sealing is also disclosed.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: February 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Winston Gregory Smiddy, Dominic J. Mongillo
  • Patent number: 11236768
    Abstract: An exhaust gas recirculation (EGR) system that utilizes an insulated separation wall that separates the hot, humid EGR gas duct from the cool, dry inlet air duct in the upstream proximity of the compressor inlet of the associated turbocharger compressor. This insulated separation wall inhibits the condensation of water droplets and the formation of ice particles near the mixing point of the EGR gases and inlet air in the upstream proximity of the compressor inlet, such that the turbocharger compressor wheel, blades, and other components are not subsequently damaged by the condensed water droplets or formed ice particles. The added insulation in this cold sink area essentially thermally isolates the hot, humid EGR gas flow from the cool, dry inlet air flow until the actual mixing point of the flows.
    Type: Grant
    Filed: September 4, 2020
    Date of Patent: February 1, 2022
    Assignee: Volvo Car Corporation
    Inventor: Ola Rolandson
  • Patent number: 11220928
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: August 24, 2020
    Date of Patent: January 11, 2022
    Assignee: Rolls-Royce Corporation
    Inventors: Alexandra Baucco, Aaron D. Sippel, Ted J. Freeman
  • Patent number: 11221014
    Abstract: An impeller and a centrifugal fan having the impeller are provided. The impeller rotates about a central axis, and includes: a cup portion, provided with a bottom portion and a cylindrical portion; a base portion, extending from a radially outermost end of the cup portion toward a radially outer side; a plurality of vanes, located on the radially outer side of the cup portion; and a ring portion, connected with end portions of the vanes on the radially outer side. The impeller further includes a plurality of rib portions, formed on a surface of a side opposite to another side of the base portion where the vanes are provided. Each of the rib portions is disposed axially opposite to at least a portion of a corresponding one of the vanes, and the rib portion and the vane is separated by the base portion.
    Type: Grant
    Filed: January 9, 2020
    Date of Patent: January 11, 2022
    Assignee: NIDEC CORPORATION
    Inventors: Qiang Ma, Toshifumi Fukui, Fengwen Yang
  • Patent number: 11215074
    Abstract: A flow regulating system for increasing a flow of cooling fluid supplied to a cooling system of a component of a gas turbine system is provided. The flow regulating system includes: a pneumatic circuit embedded within a section of the component, the pneumatic circuit including a set of interconnected pneumatic passages; and a pressure-actuated switch fluidly coupled to the pneumatic circuit. The pressure-actuated switch is activated in response to a formation of a breach in the section of the component and an exposure of at least one of the pneumatic passages of the pneumatic circuit embedded in the section of the component. The activation of the pressure-actuated switch increases the flow of cooling fluid supplied to the cooling system of the component.
    Type: Grant
    Filed: July 8, 2019
    Date of Patent: January 4, 2022
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Matthew Troy Hafner, Lyndsay Marie Kibler
  • Patent number: 11215118
    Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.
    Type: Grant
    Filed: December 12, 2019
    Date of Patent: January 4, 2022
    Assignees: Airbus (S.A.S.), Airbus Operations (S.A.S.), Airbus Operations, S.L.
    Inventors: Bruno Medda, Thomas Stevens, Julien Cayssials, Adeline Soulie, Didier Poirier, Pierre-Alain Pinault, Esteban Martino González, Juan Tomas Prieto Padilla, Diego Barron Vega
  • Patent number: 11215061
    Abstract: Disclosed is a blade, having: a blade root; a blade body that extends radially from the blade root to a blade tip, the blade body having a pressure side and a suction side each extending from a leading edge of the blade body to a trailing edge of the blade body; a squealer pocket located in the blade tip; and a first wearable tip-rub-portion located radially above the squealer pocket, and extending between the pressure side and the suction side, the first wearable tip-rub-portion terminating at a first wearable tip-rub-portion distal end.
    Type: Grant
    Filed: February 4, 2020
    Date of Patent: January 4, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Anton G. Banks, Lane Mikal Thornton
  • Patent number: 11209017
    Abstract: A system includes an inlet duct disposed about an inlet axis, wherein the inlet duct is configured to direct an airflow along the inlet axis to a compressor inlet. The inlet includes an inlet heating system and a heating portion having a longitudinal axis that is substantially perpendicular to the inlet axis. The inlet heating system includes a first conduit substantially parallel to the longitudinal axis that is configured to distribute a heated fluid directly to the airflow via a first set of openings of a first end zone of the first conduit and a second set of openings of a second zone of the first conduit. The first end zone is configured to receive the heated fluid from a heating source, the second zone is coupled to the first end zone, and the second zone is configured to receive the heated fluid from the first end zone.
    Type: Grant
    Filed: August 24, 2018
    Date of Patent: December 28, 2021
    Assignee: General Electric Company
    Inventors: Alan Eskandar, Valery Ivanovich Ponyavin, Hua Zhang, Christopher Conrad Frese
  • Patent number: 11208896
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: October 20, 2020
    Date of Patent: December 28, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Alexandra Baucco, Aaron D. Sippel, Ted J. Freeman
  • Patent number: 11187244
    Abstract: Embodiments of the present disclosure describe a reflux device blade and a compressor. The reflux device blade includes a blade main body, a hollow cavity is formed in the blade main body, and an air supplement hole is formed in the blade main body. When the hollow reflux device blade is adopted, the supplemental air entering the hollow cavity of the reflux device blade through an air supplement channel forms jet flow on a suction surface of the reflux device blade to blow off a low-speed low-energy area formed on the suction surface, so as to reduce the airflow mixing loss, prevent the intake distortion of a second-stage impeller, and improve the operation range of the compressor.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: November 30, 2021
    Assignees: Gree Electric Appliances (Wuhan) Co., Ltd., Gree Electric Appliances, Inc. of Zhuhai
    Inventors: Zengyue Liu, Ruixing Zhong, Nan Jiang, Caiyun Jiang, Yuhui Chen, Yi Zhou, Liandong Lei, Xinwang Ouyang
  • 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: 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: 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: 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: 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: 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: 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: 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: 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: 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: 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