Including Additional Means Causing Or Controlling Fluid Flow For Heat Exchanging, Lubricating Or Sealing Patents (Class 415/175)
  • Patent number: 11702991
    Abstract: Sealing arrangements and turbomachines are provided. A sealing arrangement includes a transition duct having an upstream end and a downstream end. The transition duct includes an aft frame that circumferentially surrounds the downstream end of the transition duct. A first stage nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly is coupled to the aft frame. The sealing assembly includes a flexible sealing element that extends from the aft frame, across the gap, to the first stage nozzle. The flexible sealing element is forced into sealing engagement with the first stage nozzle by pressure from a compressed working fluid. The sealing assembly further includes a heat shield disposed between the flexible sealing element and the aft frame. The heat shield terminates within the gap.
    Type: Grant
    Filed: September 30, 2020
    Date of Patent: July 18, 2023
    Assignee: General Electric Company
    Inventors: Emily Klara Happ, Lucas John Stoia
  • Patent number: 11555496
    Abstract: A centrifugal pump including an outer case; an inner case; a first unit and a second unit placed in fluid communication with each other, each unit including a plurality of impellers; the inner case includes two half-parts joined along a connection plane containing the axis of rotation; a connecting element is placed between the first unit and the second unit, the connecting element is engaged with a last impeller of the first unit and with a last impeller of the second unit.
    Type: Grant
    Filed: August 3, 2016
    Date of Patent: January 17, 2023
    Assignee: NUOVO PIGNONE TECNOLOGIE SRL
    Inventors: Donato Antono Ripa, Fabrizio Milone, Giulio Elicio
  • Patent number: 11499534
    Abstract: The present disclosure relates to a heat dissipation system, a wind generating set, and a heat dissipation supporting platform. The heat dissipation system includes: a supporting platform, the supporting platform including a body portion, the body portion including an inlet, an outlet, a flow channel communicating the inlet with the outlet, and a mounting position for mounting a functional device, the inlet, the outlet and the flow channel together form a medium circulation passage; and a heat exchange apparatus which communicates with the medium circulation passage and delivers the cooling medium into the medium circulation passage, the cooling medium flowing through the inlet and the flow channel and flowing out from the outlet to exchange heat with the functional device.
    Type: Grant
    Filed: October 30, 2018
    Date of Patent: November 15, 2022
    Assignee: XINJIANG GOLDWIND SCIENCE & TECHNOLOGY CO., LTD.
    Inventors: Zhigang Yao, Hongkui Shi, Ruiqing Shen
  • Patent number: 11377965
    Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
    Type: Grant
    Filed: March 6, 2017
    Date of Patent: July 5, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Shawn J. Gregg, Dominic J. Mongillo, Michael Leslie Clyde Papple, Russell J. Bergman, Mohammed Ennacer
  • Patent number: 11371378
    Abstract: An apparatus for controlling tip clearance between a turbine casing and a turbine blade is provided. The apparatus for controlling tip clearance includes a casing surrounding the turbine blade, a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof, and a ring segment mounted radially inside the cooling plate.
    Type: Grant
    Filed: March 18, 2021
    Date of Patent: June 28, 2022
    Inventors: Seung Min Lee, Yong Hwan Kwon, Dong II Kim, Jin Woong Ha
  • Patent number: 11352979
    Abstract: A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.
    Type: Grant
    Filed: April 24, 2020
    Date of Patent: June 7, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Yuk-Kwan Brian Yuen, Christopher T. Anglin, Matthew Nickerson, Daniel S. Rogers
  • Patent number: 11313454
    Abstract: A lubrication system for a gas turbine engine, the system comprising: a gearbox, the gearbox comprising a sump; an oil tank; a primary gearbox lubrication system configured to pump oil from the oil tank to lubricate the gearbox with a gearbox primary feed; a secondary gearbox lubrication system, configured to lubricate the gearbox with oil from the sump when the oil level in the sump reaches a predetermined level; wherein the system is configured to increase the oil level in the sump to at least the predetermined level in response to a failure of the primary gearbox lubrication system.
    Type: Grant
    Filed: April 2, 2019
    Date of Patent: April 26, 2022
    Assignee: ROLLS-ROYCE PLC
    Inventor: Neil J. Davies
  • Patent number: 11293306
    Abstract: An expansion turbine configured such that even when pressure of process gas steeply changes, the amount of process gas leaking from a gap between an impeller and a cover is made small. The expansion turbine includes a gas supply passage which is connected to any one of a gas supply passage and a gas discharge passage and through which gas is supplied to a region located between a rotor member and a casing member.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: April 5, 2022
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Yuichi Saito, Hidetsugu Ishimaru, Ryota Takeuchi, Toshimitsu Adachi, Daisuke Kariya, Naoto Sakai
  • Patent number: 11280196
    Abstract: In one embodiment, a power generation system includes a pulse detonation engine including a combustion chamber, a linear power generator including a working chamber, and a nozzle positioned between the combustion chamber and the working chamber that expands exhaust gas expelled from the combustion chamber, wherein the nozzle increases thermodynamic efficiency of the system.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: March 22, 2022
    Assignee: BOARD OF REGENTS, THE UNIVERSITY OF TEXAS SYSTEM
    Inventors: Eric M. Braun, Frank K. Lu
  • Patent number: 11261739
    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a first cavity, a second cavity, and a rib extending from a suction sidewall to a pressure sidewall and separating the first cavity from the second cavity. The rib includes a central portion, a first edge portion extending from the pressure sidewall to the central portion, and a second edge portion extending from the suction sidewall to the central portion. The rib defines one or more communication openings from the first cavity to the second cavity in the first or second edge portion.
    Type: Grant
    Filed: January 5, 2018
    Date of Patent: March 1, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Nicholas M. LoRicco
  • Patent number: 11248533
    Abstract: A gas turbine engine for an aircraft. The gas turbine engine for an aircraft comprising: an engine core comprising an annular gas passage, a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a power gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The engine further has a recirculatory lubricant system which feeds lubricant to and scavenges lubricant from the power gearbox. The engine further has a circumferential row of inlet guide vanes, located downstream of the fan at an air inlet of the annular gas passage. The recirculatory lubricant system includes one or more return passages for lubricant scavenged from the power gearbox, the return passages crossing the annular gas passage through one or more of the inlet guide vanes.
    Type: Grant
    Filed: May 5, 2020
    Date of Patent: February 15, 2022
    Assignee: ROLLS-ROYCE PLC
    Inventor: Nicholas E Chilton
  • Patent number: 11242856
    Abstract: A submersible well pump has diffusers fixed within the housing and an impeller mounted between each of the diffusers. Spacer sleeves located between and in abutment with hubs of adjacent ones of the impellers define a stack wherein the impellers rotate in unison with the shaft and are axially movable in unison with each other relative to the shaft. A stop shoulder on the shaft abuts the lower end of the stack. A spring mounted in compression around the shaft in abutment with the upper end of the stack urges the lower end of the stack against the stop shoulder. Upward movement of the stack requires further compression of the spring. Up thrust and down thrust gaps between each impeller and adjacent diffusers prevent up thrust and down thrust from being transferred to any of the diffusers.
    Type: Grant
    Filed: October 8, 2019
    Date of Patent: February 8, 2022
    Assignee: BAKER HUGHES HOLDINGS LLC
    Inventors: Spencer Smith, Eric Tolley
  • Patent number: 11162457
    Abstract: A fan system of a turbine includes a fan mid shaft made of a coated steel material configured to extend along a center axis of a turbine. The fan mid shaft having an inner diameter surface. The fan system includes a dry film lubricant that is configured to be applied to at least a portion of the inner diameter surface of the fan mid shaft.
    Type: Grant
    Filed: August 11, 2017
    Date of Patent: November 2, 2021
    Assignee: General Electric Company
    Inventors: Deepika Sachdeva, Mohammad Kashfuddoja, Anshul Kaushik, Mark Alan Rhoads, Andrew Jenkins
  • Patent number: 11156114
    Abstract: A turbomachine including at least one stator vane sector (10) and a fluid distribution circuit (22), the stator vane sector comprising at least one vane (12), a fluid inlet (25a), a fluid outlet (25b), and a channel (24a) providing fluid flow connection between the fluid inlet and the fluid outlet while extending at least in part in the vane (12), the vane and the channel being adapted, to enable heat to be exchanged between a hot fluid passing through the channel and a stream of cold air passing through the vane sector, the fluid distribution circuit (22) presenting a feed pipe (22a) and a recovery pipe (22b), the fluid inlet (25a) being in fluid flow connection with a branch tapping (23a) of the feed pipe (22a) while the fluid outlet (25b) is in fluid flow connection with a branch tapping (23b) of the recovery pipe (22b).
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: October 26, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien Chalaud, Christian Vessot
  • Patent number: 11085304
    Abstract: A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.
    Type: Grant
    Filed: June 7, 2018
    Date of Patent: August 10, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Jeremy Styborski, Alex J. Schneider
  • Patent number: 11060530
    Abstract: A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.
    Type: Grant
    Filed: January 4, 2018
    Date of Patent: July 13, 2021
    Assignee: General Electric Company
    Inventors: Gregory Michael Petrasko, Jeffrey Douglas Rambo
  • Patent number: 11028698
    Abstract: A small gas turbine engine with a ceramic turbine to allow for higher turbine inlet temperatures, where a metallic compressor is secured to a ceramic shaft extending from a ceramic turbine to form a single piece ceramic shaft and turbine, where a threaded nut secures a split ring retainer on the compressor end of the ceramic shaft. A hollow thrust runner is compressed between the compressor disk and the turbine disk by the threaded nut to secure rotor together. A centering spring forms a tight fit between the metallic thrust runner and the ceramic shaft on the turbine side.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: June 8, 2021
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, Edwin L Kite
  • Patent number: 10975877
    Abstract: A combined bearing for a turbomachine is disclosed. The combined bearing comprises in combination: a radial bearing member, a thrust bearing member and a bearing-fluid impeller of a bearing-fluid boosting pump in fluid communication with the thrust bearing member and the radial bearing member.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: April 13, 2021
    Assignee: NUOVO PIGNONE SRL
    Inventors: Vito Manzari, Donato Antonio Ripa, Fabrizio Milone
  • Patent number: 10822973
    Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one exemplary aspect, a gas turbine engine includes a first rotor blade stage and a second rotor blade stage. The gas turbine engine also includes a shroud formed from a plurality of shroud segments that each have a body and a vane extending from the body. The vane is disposed within the flow path between the first rotor blade stage and the second rotor blade stage to form at least a portion of a nozzle stage. Further, the body of the shroud segment defines an outer wall of the flow path and spans from the first rotor blade stage to the second rotor blade stage. An impingement baffle segment couples the shroud segment with a casing of the gas turbine engine.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Alan Joseph Parvis, Dane Michael Dale, Ryan Christian Goff
  • Patent number: 10822963
    Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: November 3, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Brandon W. Spangler, Adam P. Generale
  • Patent number: 10822962
    Abstract: A platform for an airfoil of a gas turbine engine having an axis extending from a front of the gas turbine engine to a rear of the gas turbine engine. The platform includes a leading edge configured to face towards the front of the gas turbine engine. The platform further includes a trailing edge opposite the leading edge. The platform further includes a radially outer surface that defines a pocket for receiving a cooling airflow. The platform further includes a cover coupled to the radially outer surface to at least partially enclose the pocket and defining a plurality of air inlet holes configured to port at least a portion of the cooling airflow into the pocket.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: November 3, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ky H. Vu, Adam P. Generale
  • Patent number: 10815803
    Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port. A method of cooling a component is also disclosed.
    Type: Grant
    Filed: July 25, 2019
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Scott D. Lewis, Dominic J. Mongillo, Jr., Mark F. Zelesky, Bret M. Teller, Russell Deibel, Matthew S. Gleiner
  • Patent number: 10787912
    Abstract: Baffles and airfoils for installation within gas turbine engines are provided. The baffles include a baffle side wall extending between a first end and a second end and a baffle divider within the baffle side wall, wherein the baffle divider and the baffle side wall define a first cavity and a second cavity. The first cavity is located at a first side at the first end and the second cavity is located at a second side at the first end and the baffle divider includes a spiral portion such that the first cavity is transitioned toward the second side and the second cavity is transitioned toward the first side.
    Type: Grant
    Filed: April 25, 2018
    Date of Patent: September 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • Patent number: 10781710
    Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: September 22, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Rebecca R. Dunnigan, Billie W. Bunting, Ted Guevel, Randall Lee Greenberg
  • Patent number: 10746026
    Abstract: A gas turbine engine component includes an airfoil that includes a trailing edge feed cavity. A baffle is located in the trailing edge feed cavity and includes a plurality of pressure side cooling openings in fluid communication with a corresponding one of a plurality of pressure side cooling passages. A plurality of suction side cooling openings are in fluid communication with a corresponding one of a plurality of suction side cooling passages.
    Type: Grant
    Filed: January 5, 2018
    Date of Patent: August 18, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Nicholas M. LoRicco
  • Patent number: 10746033
    Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: August 18, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Jose R. Paulino
  • Patent number: 10746192
    Abstract: A rotary machine includes a first impeller which rotates about an axis integrally with a rotating shaft, and a casing which covers the rotating shaft and the first impeller. The first impeller includes a circular-disk-shaped first disk part centered on the axis, a plurality of blade parts which extend from a surface facing a first side of the first disk part in an axial direction toward the first side in the axial direction and disposed at intervals in a circumferential direction, and an extension shaft which extends from a surface facing a second side of the first disk part in the axial direction toward the second side in the axial direction centered on the axis. An end portion of the extension shaft on the second side in the axial direction is connectable to an end portion of the rotating shaft on the first side in the axial direction.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: August 18, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventor: Masahiko Murata
  • Patent number: 10738701
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.
    Type: Grant
    Filed: August 30, 2017
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
  • Patent number: 10704394
    Abstract: A flow passage forming plate includes a plate main body, a peripheral wall, and a ledge. The plate main body has a gas path surface facing a side of a gas flow passage, and an inner surface facing the opposite side from the gas path surface. The peripheral wall protrudes along a peripheral edge of the plate main body, from the inner surface toward an opposite-flow-passage side. The ledge protrudes along an inner wall surface of the peripheral wall, from the inner surface toward the opposite-flow-passage side. The ledge receives an impingement plate having a plurality of through-holes. The ledge is disposed only in a part of an inner wall surface of the peripheral wall.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: July 7, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Tadakazu Sakaguchi, Hiroshi Shimizu, Shinji Yoshida, Yoshio Fukui, Masamitsu Kuwabara
  • Patent number: 10704419
    Abstract: Turbine distributor sector for an aircraft turbine engine, including an external annular platform sector and an internal annular platform sector, the sectors being coaxial and being connected together by blade assemblies including inner cavities cooled by gas circulation, the external platform sector including through openings of which radially internal ends open into the inner cavities, wherein the external platform sector includes inner ducts for supplying the cavities with gas, the ducts including air outlets opening into the openings and air inlets opening onto a portion of the external annular surface of the external platform sector.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: July 7, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Josserand Jacques Andre Bassery, Jean-Charles Marcel Bernard Coetard, Raphael Jean Philippe Dupeyre, Etienne Leon Francois, Ba-Phuc Tang
  • Patent number: 10697307
    Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: June 30, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Nicholas M. LoRicco, Ricardo Trindade, Dominic J. Mongillo, Jr.
  • Patent number: 10697310
    Abstract: Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: June 30, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Corey D. Anderson, Jeremy Styborski
  • Patent number: 10690060
    Abstract: A finger seal for a gas turbine engine is disclosed. The finger seal includes a first leg, a second leg, a third leg, a fourth leg, a first bend segment disposed between the first leg and the second leg, a second bend segment disposed between the second leg and the third leg, and a third bend segment disposed between the third leg and the fourth leg. The third bend segment is radially outward of the first bend segment relative to an axial centerline of the gas turbine engine.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: June 23, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Kevin W. White, Randall J. Brown
  • Patent number: 10669870
    Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.
    Type: Grant
    Filed: January 23, 2015
    Date of Patent: June 2, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: John E. Wilber
  • Patent number: 10648351
    Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.
    Type: Grant
    Filed: December 6, 2017
    Date of Patent: May 12, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Adam P. Generale, Ky H. Vu
  • Patent number: 10570764
    Abstract: A sealing system may include a bulb seal coupled to a first component and a spring coupled to a second component. The bulb seal may contact the spring to form a seal between the first component and the second component. The bulb seal may be relatively stiff when new and cause the spring to compress. The bulb seal may be relatively flexible as it ages, and the spring may cause the bulb seal to compress. The bulb seal and the spring may maintain a seal throughout the life of the sealing system. The sealing system may maintain a constant separation between the first component and the second component throughout the life of the sealing system.
    Type: Grant
    Filed: April 1, 2016
    Date of Patent: February 25, 2020
    Assignee: ROHR, INC.
    Inventor: Ann Elizabeth Khidekel
  • Patent number: 10570769
    Abstract: A machine having a shaft with a stage having a first shaft section having a first diameter, a second shaft section having a second diameter that is shorter than the first, forming a radially extending rotatable shaft end surface; a housing; and a bearing supporting the shaft on the housing by its second shaft section, and lubricated by a lubrication fluid. A sealing chamber has a sealing fluid that prevents the lubrication from leaving the bearing, and is axially limited by the shaft end surface and bearing end side, and radially inwardly limited by the second shaft section released from the bearing. A radially extending and stationary separator plate is in the sealing chamber to achieve an aerodynamic shielding of the bearing end side from the shaft end surface. When the shaft is rotating, the region between the separator plate and the bearing end side is substantially non-rotational.
    Type: Grant
    Filed: July 21, 2015
    Date of Patent: February 25, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventors: Joachim Krützfeldt, Oliver Schneider
  • Patent number: 10557376
    Abstract: A turbine engine unit for lubricating a bearing holder. A turbine engine unit is provided, including an inter-turbine housing that includes a hub including a bearing holder, a ferrule extending around and at a distance from the hub, at least one arm extending radially between the hub and the ferrule, and at least one lead-through for lubricating the bearing holder. The lead-through includes a first pipe having an end portion that can be screwed onto the hub so as to place the first pipe in fluid communication with the bearing holder, an intermediate portion secured to the end portion placed inside the arm when the end portion is screwed onto the hub, and a clamping portion secured to the end portion and rotatable by a clamping tool. The turbine engine unit is characterized in that the clamping portion is located between the screwable end portion and the intermediate portion. A corresponding turbine engine unit assembly method is also provided.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: February 11, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Philippe Pierre Vincent Bouiller, Frederic Francois Jean-Yves Patard
  • Patent number: 10408071
    Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.
    Type: Grant
    Filed: August 26, 2014
    Date of Patent: September 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Scott D. Lewis, Dominic J. Mongillo, Jr., Mark F. Zelesky, Bret M. Teller, Russell Deibel, Matthew S. Gleiner
  • Patent number: 10392949
    Abstract: A spinner for a gas turbine engine comprises an outer shell for defining an airflow path when mounted in a gas turbine engine. An inner surface is provided with a plurality of webs. A gas turbine engine and a fan section for a gas turbine engine are also disclosed.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: August 27, 2019
    Assignee: United Technologies Corporation
    Inventors: James T. Roach, Grant O. Cook, III, Colin J. Kling, James F. O'Brien, Shari L. Bugaj
  • Patent number: 10393019
    Abstract: Assemblies and methods for providing injection air to influence flow in a flow passage defined by a fan of a gas turbine engine are disclosed. In one embodiment, the method comprises: receiving air into an interior of a nose cone; increasing the pressure of the air in the interior of the nose cone and directing the pressurized air; and discharging the air into the flow passage defined by the fan.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: August 27, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hien Duong
  • Patent number: 10344843
    Abstract: A torque converter is provided. The torque converter includes a stator, a turbine, a bushing provided at an inner circumferential surface of the turbine and a thrust bearing provided axially between the turbine and the stator. The bushing contacts an inner circumferential surface of the thrust bearing for piloting the turbine bearing. A method of forming a torque converter is also provided. The method includes providing a bushing at an inner circumferential surface of a turbine; and providing a thrust bearing axially between the turbine and a stator such that the bushing contacts an inner circumferential surface of the thrust bearing to pilot the turbine bearing.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: July 9, 2019
    Assignee: Schaeffler Technologies AG & Co. KG
    Inventor: Timothy Hess
  • Patent number: 10309227
    Abstract: A trailing edge cooling system for a turbine blade is disclosed. The system may include a cooling circuit including an outward leg, and a return leg positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge of the turbine blade. The cooling circuit may also include a plurality of turn legs. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: June 4, 2019
    Assignee: General Electric Company
    Inventors: David Wayne Weber, Sandip Dutta
  • Patent number: 10247419
    Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.
    Type: Grant
    Filed: August 1, 2017
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Mark F. Zelesky, Andrew D. Burdick
  • Patent number: 10233834
    Abstract: A turbocharger (1) with an axial flow turbine stage (2) includes a compressor stage (4) using active casing treatment (50) for choke flow improvement. With switchable slots (52, 54), one of the slots (52) may be between the compressor's full and splitter blades (27, 23) and one of the slots (54) can be located downstream of the compressor's splitter blades (23) to maximize choke flow capacity. In turbochargers with a wastegate assembly, a pneumatic actuator (32) may control both a wastegate control valve (30) and an active casing treatment slot selection valve (56).
    Type: Grant
    Filed: July 17, 2014
    Date of Patent: March 19, 2019
    Assignee: BorgWarner Inc.
    Inventors: Michael E. McGahey, Michael Ausbrooks
  • Patent number: 10215190
    Abstract: A cooling system is provided for cooling a motor that drives a compressor in a liquefaction system. The coolant used for cooling the motor includes portions of a discharge from a compressor. The coolant for the motor is generated from a vapor component of the discharge from the compressor. The discharge from the compressor is cooled and the vapor component is separated from a liquid component and treated prior to being introduced into the motor. Remaining portions of the discharge from the compressor are routed to cold boxes producing a compressed refrigerant.
    Type: Grant
    Filed: May 31, 2016
    Date of Patent: February 26, 2019
    Assignee: GE Oil & Gas, Inc.
    Inventors: Philippe Augy, Shukui Zhao, David Kennedy, Pierre Laboube, Ravikumar Vipperla
  • Patent number: 10156149
    Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the airfoil having a fillet at the trailing edge proximate the at least one endwall.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: December 18, 2018
    Assignee: General Electric Company
    Inventors: Neil Ristau, Russell Pierson DeForest, William Ladd Rutherford
  • Patent number: 10126003
    Abstract: Provided is an outdoor unit of an air conditioner capable of obtaining stable air blowing performance without enlarging a blower fan and decreasing the amount of air per unit area (wind velocity distribution) passing through the heat exchanger even if the capacity of the heat exchanger is enlarged by optimizing a relative arrangement and a configuration of a heat exchanger and a blower and effectively utilizing the wind of the blower which is conventionally wasted. The rotation shaft of the first blower is disposed closer to the center line in the lateral direction of the housing than the center line in a lateral direction of the left blower chamber, and the rotation shaft of the second blower is disposed closer to the center line in the lateral direction of the housing than the center line in a lateral direction of the right blower chamber.
    Type: Grant
    Filed: February 2, 2017
    Date of Patent: November 13, 2018
    Assignee: FUJITSU GENERAL LIMITED
    Inventors: Kenta Nezu, Satoshi Kasugai
  • Patent number: 10107188
    Abstract: A forced induction apparatus for an engine includes a first forced induction device including a first bearing and a first oil passage that passes by the first bearing and a second forced induction device including a second bearing, a second oil passage that passes by the second bearing, and a drain passage that is in communication with the first oil passage. The second forced induction device is located below the first forced induction device, and the drain passage receives oil from the first oil passage and discharges the oil out of the second forced induction device.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: October 23, 2018
    Assignees: KABUSHIKI KAISHA TOYOTA JIDOSHOKKI, TOYOTA JIDOSHA KABUSHIKI KAISHA
    Inventors: Tsuyoshi Uesugi, Koichi Yonezawa
  • Patent number: 10100737
    Abstract: A cooling arrangement (100), including: a substrate having a pocket (24) defined by a rib side surface (28) and a bottom surface (26); a feature (112) formed in the rib side surface; and an impingement plate (102). In an installed configuration (116) a resilience of the impingement plate enables an interference between the impingement plate and the feature that locks the impingement plate in an installed position (118). An elastic compression of the impingement plate from the installed configuration eliminates the interference.
    Type: Grant
    Filed: May 16, 2013
    Date of Patent: October 16, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: David A. Little, Clifford E. Johnson