Having Expansible Connection Patents (Class 60/799)
  • Patent number: 11686248
    Abstract: A core duct assembly for a gas turbine engine includes a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.
    Type: Grant
    Filed: May 28, 2021
    Date of Patent: June 27, 2023
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian J Bousfield, Duncan A MacDougall
  • Patent number: 11649732
    Abstract: An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.
    Type: Grant
    Filed: March 11, 2021
    Date of Patent: May 16, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Robert A. White, III
  • Patent number: 11306613
    Abstract: A turbocharger (10A) has a back plate (41). The back plate (41) is provided with a plate section (41a) and a flange section (41c) which is formed radially outside the plate section (41a) and which is supported so as to be sandwiched between a bearing housing (16) and a turbine housing (31). The turbocharger (10A) is further provided with a flange heat shielding section (53) provided between the flange section (41c) and the bearing housing (16) and consisting of a material having lower heat conductivity than the turbine housing (31) and the back plate (41).
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: April 19, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Tsuyoshi Kitamura, Seiichi Ibaraki, Toyotaka Yoshida, Hiroshi Suzuki
  • Patent number: 11286882
    Abstract: An exhaust casing for a gas turbine engine comprises a shroud configured to surround an exhaust cone, and a heat shield attached to the shroud. The heat shield has a first end and a second end axially spaced apart from each other. A gap is defined radially between the shroud and the heat shield. The gap is configured to enclose at least a portion of an interface defined between at least one strut and the shroud. The exhaust casing is configured to surround the exhaust cone and configured to be connected to the exhaust cone via the at least one strut.
    Type: Grant
    Filed: November 28, 2018
    Date of Patent: March 29, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Assaf Farah, Marc Tardif, Daniel Summers-Lepine
  • Patent number: 11198523
    Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.
    Type: Grant
    Filed: April 5, 2019
    Date of Patent: December 14, 2021
    Assignees: MICHIGAN TECHNOLOGICAL UNIVERSITY, ORBION SPACE TECHNOLOGY, INC.
    Inventor: Lyon B. King
  • Patent number: 11098652
    Abstract: Isolation seals for gas turbine engines are described. The isolation seals include a first interface member configured to be fixedly attached to a first case structure, the first interface member being a full-hoop structure, a housing configured to be mounted to a second case structure, a connector pin arranged within the housing and moveable relative to the housing, and a second interface member located on an end of the connector pin, the second interface member being a full-hoop structure. The first interface member and the second interface member are engageable to form a seal therebetween.
    Type: Grant
    Filed: May 29, 2019
    Date of Patent: August 24, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Brandon T. Slaney
  • Patent number: 10961950
    Abstract: A fan nacelle, a gas turbine engine cell assembly, and an aircraft are provided. The fan nacelle includes a fan duct skin arranged in a fan duct to direct airflow from the fan of a Turbofan engine toward a fan nozzle. An exterior skin of the fan nacelle directs air flow around an exterior of the engine. The fan duct skin and the exterior skin terminate at a trailing edge, and a trailing edge portion of the exterior skin is one of parallel to and diverging from a trailing edge portion of the fan duct skin in an aft direction. In certain aspects, the trailing edge portion of the exterior skin is actuatable or inflatable to selectively divert from the trailing edge portion of the fan duct skin.
    Type: Grant
    Filed: November 3, 2016
    Date of Patent: March 30, 2021
    Assignee: THE BOEING COMPANY
    Inventor: Sean P. Howe
  • Patent number: 10941674
    Abstract: An assembly for a gas turbine engine includes a first casing, a second casing, and struts extending from the first casing to support the second casing. The assembly further includes a fairing and a multi-piece heat shield assembly. The fairing is disposed between the first casing and the second casing and around each of the struts. The multi-piece heat shield assembly includes a first shield extending between the first casing and the fairing, and a second shield extending between the fairing and the first casing. The multi-piece heat shield assembly further includes a third shield extending between the fairing and the second casing, and fourth and fifth heat shields extending from the third heat shield between the fairing and each of the struts.
    Type: Grant
    Filed: April 19, 2019
    Date of Patent: March 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong, Jonathan Ariel Scott, Darrell Weidner, Chris Bates
  • Patent number: 10344622
    Abstract: An assembly for rotational equipment with an axial centerline. The assembly includes a first component and a second component. Each of the components extends circumferentially around and axially along the centerline. The first component includes a flange and a lug aperture extending axially through the flange. The second component includes a mount base and a bayoneted lug on the mount base. The mount base is configured to axially engage the flange where the bayoneted lug extends through the lug aperture. A fastener secures the components together. The fastener projects axially into a fastener aperture in the mount base for an axial length that is less than or equal to an axial length of the bayoneted lug.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: July 9, 2019
    Assignee: United Technologies Corporation
    Inventor: Colin G. Amadon
  • Patent number: 9488110
    Abstract: A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: November 8, 2016
    Assignee: General Electric Company
    Inventors: George Joe-Kueng Chan, Victor Hugo Silva Correia, David Hannwacker, Robert Proctor
  • Patent number: 9121302
    Abstract: A diaphragm assembly includes a cylinder, a circular flange, and a diaphragm. The cylinder defines an axis and includes a first end and a second end opposite the first end. The circular flange is coaxial with the cylinder and at a greater radial distance from the axis than the cylinder. The diaphragm extends from the second end of the cylinder to the flange.
    Type: Grant
    Filed: July 12, 2012
    Date of Patent: September 1, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Loc Quang Duong, Xiaolan Hu
  • Publication number: 20150101345
    Abstract: A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position. While in the first position, the second seal member is circumferentially spaced from the outlet portion of the second transition duct. While in the second position, the second seal member extends across the leakage gap and creates a seal with the outlet portion of the second transition duct to substantially prevent leakage through the leakage gap.
    Type: Application
    Filed: October 15, 2013
    Publication date: April 16, 2015
    Inventors: Andrew G. Green, Miguel Bascones
  • Patent number: 8997496
    Abstract: An exhaust includes a wall that has a first composite material having a first coefficient of thermal expansion and a second composite material having a second coefficient of the thermal expansion that is less than the first coefficient of thermal expansion.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Gerard D. Pelletier, Charles P. Logan, Bryan William McEnerney, Jeffrey D. Haynes
  • Patent number: 8991192
    Abstract: A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure.
    Type: Grant
    Filed: September 24, 2009
    Date of Patent: March 31, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: David J. Wiebe, Timothy A. Fox
  • Patent number: 8973376
    Abstract: An interface (10) is provided between a combustor basket (12) and a transition (14) of a gas turbine engine (16). The interface (10) includes a tongue (18) formed in one of the combustor basket (12) and the transition (14), and a groove (20) formed in another of the combustor basket (12) and the transition (14). The tongue (18) is received within the groove (20) to define the interface (10). A sealing arrangement is also provided and includes an annular combustion outlet (12??) and an annular transition inlet (14??), with a labyrinth seal (72??) positioned between an end (68??) of the annular combustion outlet and an end (70??) of the annular transition inlet to form a labyrinth path (34??) there between. An inner diameter (24??) of the annular combustion outlet (12??) is axially aligned with an inner diameter (22??) of the annular transition outlet (14??).
    Type: Grant
    Filed: April 18, 2011
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Adam M. Foust, David J. Gloekler
  • Patent number: 8943840
    Abstract: A mounting assembly 2 for mounting a gearbox 10 to a gas turbine engine, comprising a mount ring 4 and a spigot pin 8 having a flange 22 at one end. The spigot pin 8 extends radially outwardly through a bore 14 in the mount ring 4 for engagement with a gearbox 10 and the flange 22 locates against a radially inner surface of the mount ring 4. The bore 14 supports the spigot pin 8 and dissipates forces exerted on the spigot pin 8, for example forces generated during a fan blade-off event.
    Type: Grant
    Filed: May 23, 2011
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce PLC
    Inventor: Keith Williams
  • Patent number: 8925326
    Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.
    Type: Grant
    Filed: May 24, 2011
    Date of Patent: January 6, 2015
    Assignee: General Electric Company
    Inventors: David William Cihlar, Patrick Benedict Melton, Robert Joseph Rohrssen
  • Patent number: 8925332
    Abstract: A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further includes a plurality of adjacent blades arranged along the first end and extending longitudinally and perpendicularly thereto. In particular, a portion of the blades has an accordion-shaped structure.
    Type: Grant
    Filed: September 30, 2013
    Date of Patent: January 6, 2015
    Assignee: Aircelle
    Inventors: Stephane Beilliard, Alexandre Phi
  • Patent number: 8919136
    Abstract: An after-body assembly for an aeroengine, the assembly comprising an annular part (60) made of metallic material secured to the aeroengine and an after-body part (20) made of ceramic matrix composite material, the after-body part (20) being mounted on the annular part (60) by resiliently flexible fastener tabs (70) and having a first end (71) fastened to the annular part (60) and a second end (72) fastened to the upstream portion of the after-body part (20). Each fastener tab (70) includes an axial abutment element (720) that extends radially from the second end (72) of the tab and having at least a portion thereof facing the first end (71). The fastener tab (70) also includes a radial abutment element (721) at the second end (72) of the tab, the radial abutment element (721) at least partially overlying the first end (71).
    Type: Grant
    Filed: September 8, 2009
    Date of Patent: December 30, 2014
    Assignee: Herakles
    Inventor: Eric Conete
  • Publication number: 20140352323
    Abstract: A flexible bellows assembly is disclosed for sealing an engine igniter for use with an engine. The bellows assembly includes a mounting arrangement that is operable to be secured to a combustor diffuser instead of the combustor liner. The bellows has a component that impinges upon a surface of the combustor liner so as to form a sealed chamber between a metal diffuser and a ceramic combustion liner. An igniter passes through the sealed chamber and provides ignition to the combustor.
    Type: Application
    Filed: December 11, 2013
    Publication date: December 4, 2014
    Applicant: Rolls-Royce Corporation
    Inventors: Russell Bennett, Michael S. Bell
  • Patent number: 8899010
    Abstract: A pulse detonation combustor including a plurality of nozzles engaged with one another via mating surfaces to support a gas discharge annulus in a circumferential direction. The pulse detonation combustor also including multiple pulse detonation tubes extending for the nozzles and a plurality of thermal expansion control joints coupled to the plurality of pulse detonation tubes. Each of the plurality of thermal expansion control joints is configured to facilitate independent thermal growth of each of the plurality of pulse detonation tubes. The thermal expansion control joints may be configured as a bellows expansion joint or a sliding expansion joint.
    Type: Grant
    Filed: November 17, 2010
    Date of Patent: December 2, 2014
    Assignee: General Electric Company
    Inventors: Ross Hartley Kenyon, Adam Rasheed, Paul Whitson Dom, Jr., Mark Joseph Pombles
  • Patent number: 8875520
    Abstract: A gas turbine engine adapter is provided. In one form the adapter is segmented and may be attached to a gas turbine engine support ring. The adapter can provide a channel that may receive part of a gas turbine engine component such as, but not limited to, a plug nozzle. The adapter can include a load bearing support to counteract axial forces experienced by the plug nozzle during operation of the gas turbine engine. A compressible seal can be provided between the plug nozzle and the adapter. A leaf seal can also be provided to seal between segments of the adapter. The plug nozzle can be discouraged from rotating relative to the adapter.
    Type: Grant
    Filed: December 9, 2009
    Date of Patent: November 4, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Gregory W. P. Zeaton, David L. Sutterfield, Sean F. Sullivan
  • Publication number: 20140311162
    Abstract: In a gas turbine, an exhaust casing and an exhaust chamber are connected by an exhaust chamber support that can absorb thermal expansion, and the exhaust chamber and an exhaust duct are connected by an exhaust duct support that can absorb thermal expansion. An insulator is mounted on an outer peripheral surface of the exhaust chamber, and the exhaust chamber support and the exhaust duct support are disposed outside the insulator in the form of a plurality of strips. Because the thermal stress at a connection portion of the exhaust chamber is reduced, the durability is enhanced.
    Type: Application
    Filed: July 2, 2014
    Publication date: October 23, 2014
    Inventors: Shinya HASHIMOTO, Kenichi ARASE
  • Patent number: 8863527
    Abstract: A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.
    Type: Grant
    Filed: April 30, 2009
    Date of Patent: October 21, 2014
    Assignee: Rolls-Royce Corporation
    Inventors: Marcus Timothy Holcomb, Todd Taylor, Randall E. Yount
  • Patent number: 8833087
    Abstract: A splitter is disclosed that can be coupled with a splitter support and used within a diffuser of a gas turbine engine. The splitter includes apertures for receiving a portion of the splitter support. The splitter support includes support arms that are adapted to be slidingly received within the apertures of the splitter.
    Type: Grant
    Filed: October 29, 2008
    Date of Patent: September 16, 2014
    Assignee: Rolls Royce Corporation
    Inventors: Edward Claude Rice, Stuart Bloom, John R. Louie
  • Publication number: 20140250899
    Abstract: An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The surrounding member includes at least two walls that form a variable flow gap therebetween. The inner member is oriented relative to the at least two walls of the surrounding member such that, based on the difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls.
    Type: Application
    Filed: December 13, 2013
    Publication date: September 11, 2014
    Applicant: Rolls-Royce Corporation
    Inventor: Thomas E. Bastnagel
  • Patent number: 8800292
    Abstract: A heat shield element arrangement including a heat shield element for a heat shield arranged on a supporting structure is provided. On each of the two opposing sides running parallel to the installation grooves the heat shield element includes a continuous screw head opening which penetrates the cold side and the hot side of the heat shield element substantially vertically and through which the screw head of the respective screw is arranged to be accessible to the supporting structure, and a spring element may be arranged under the respective screw, which spring element may be extended along the hot side of the heat shield element and the parallel installation groove of the supporting structure. An outer end of the spring element is embodied as a clamping retaining hook which is provided for the purpose of engaging in the laterally recessed retaining groove of the heat shield element.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: August 12, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Böttcher, Andre Kluge, Marco Link, Wilhelm Scheidtmann, Gerhard Simon, Thomas-Dieter Tenrahm, Marc Tertilt, Sabine Tüschen
  • Patent number: 8800300
    Abstract: In a gas turbine, an exhaust casing and an exhaust chamber are connected by an exhaust chamber support that can absorb thermal expansion, and the exhaust chamber and an exhaust duct are connected by an exhaust duct support that can absorb thermal expansion. An insulator is mounted on an outer peripheral surface of the exhaust chamber, and the exhaust chamber support and the exhaust duct support are disposed outside the insulator in the form of a plurality of strips. Because the thermal stress at a connection portion of the exhaust chamber is reduced, the durability is enhanced.
    Type: Grant
    Filed: January 27, 2009
    Date of Patent: August 12, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Shinya Hashimoto, Kenichi Arase
  • Patent number: 8739513
    Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.
    Type: Grant
    Filed: August 17, 2010
    Date of Patent: June 3, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Guy Lefebvre, Nicolas Grivas, Richard Bouchard, Denis Leclair, Eric Durocher
  • Patent number: 8726675
    Abstract: A scalloped flexure ring. An illustrative embodiment of the flexure ring includes a ring body having a first ring body edge and a generally scalloped second ring body edge and a plurality of spaced-apart ring fingers provided in the second ring body edge.
    Type: Grant
    Filed: September 7, 2007
    Date of Patent: May 20, 2014
    Assignee: The Boeing Company
    Inventors: William P. Keith, Michael L. Hand
  • Publication number: 20140053573
    Abstract: A gas turbine device includes an inlet casing and a stator diaphragm provided inside the inlet casing. The stator diaphragm has an integral inner stator shroud and an outer stator shroud and a plurality of stator vanes provided in a circumferential arrangement between the inner stator shroud and the outer stator shroud. A plurality of key slots is provided in a circumferential arrangement on the stator diaphragm and a corresponding plurality of key slots is provided in a circumferential arrangement on the inlet casing. The key slots provided on the stator diaphragm are aligned with the plurality of key slots provided on the inlet casing. A key is inserted into each of the plurality of key slots provided to prevent rotation of the stator diaphragm with respect to the inlet casing. The stator diaphragm is secured in an axial direction by a stator shear ring.
    Type: Application
    Filed: December 27, 2012
    Publication date: February 27, 2014
    Inventors: Ronald John Josefczyk, Carl John Schuster
  • Publication number: 20140033735
    Abstract: A gas turbomachine includes a casing having a first casing half including first and second edge portions and a second casing half including first and second edge sections. The first edge portion is configured and disposed to be joined to the first edge section to form a first horizontal joint and the second edge portion is configured and disposed to be joined to the second edge section to form a second horizontal joint. At least one of the first edge portion and the first edge section including a first fluid passage, and at least one of the second edge portion and second edge section including a second fluid passage. The first and second fluid passages are configured and disposed to guide heated fluid along respective ones of the first and second horizontal joints.
    Type: Application
    Filed: August 1, 2012
    Publication date: February 6, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Sendilkumaran Soundiramourty, Srinivasa Rao Pakkala
  • Patent number: 8636465
    Abstract: A thermal expansion joint apparatus includes an insert extending through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert, thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: January 28, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 8590316
    Abstract: The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).
    Type: Grant
    Filed: April 8, 2008
    Date of Patent: November 26, 2013
    Assignee: SNECMA Propulsion Solide
    Inventors: Eric Conete, Benoît Carrere, Laurent Baroumes
  • Publication number: 20130247585
    Abstract: A Brayton cycle heat engine includes a compressor, a combustion chamber, and a turbine. The Brayton cycle heat engine also includes a heat exchanger positioned at least partially within the combustion chamber. The heat exchanger is configured to deliver thermal energy to the combustion chamber from an external source, heating air entering the combustion chamber from the compressor, where the air exits the combustion chamber and drives the turbine.
    Type: Application
    Filed: March 21, 2012
    Publication date: September 26, 2013
    Inventor: Virgil Dewitt Perryman
  • Patent number: 8511972
    Abstract: A seal member for use in a channel between a transition seal structure and a vane seal structure in a gas turbine engine. The seal member includes a spring member and a sheathing assembly. A first end of the spring member is affixed to either the transition seal structure or the vane seal structure. The second end is free to move within the channel. The sheathing assembly includes a main body and a plate portion. The main body surrounds the spring member and is affixed to the second end thereof. The plate portion extends from the main body and is adapted to extend toward the other of the transition seal structure and the vane seal structure. The spring member provides a bias on the sheathing assembly such that the plate portion engages the other of the transition seal structure and the vane seal structure to limit leakage through the channel.
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: August 20, 2013
    Assignee: Siemens Energy, Inc.
    Inventor: Muzaffer Sutcu
  • Patent number: 8511098
    Abstract: An example engine assembly includes a first attachment structure secured to an engine casing or an engine liner, and a second attachment structure secured to the other of the engine casing or the engine liner. A sliding member is held by the first attachment structure and is slideable relative to the first attachment structure between a first position and a second position. A pin structure moves with the sliding member between the first position and the second position. A link is pivotally connected to the second attachment structure and the pin structure.
    Type: Grant
    Filed: June 12, 2008
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventor: Gonzalo F. Martinez
  • Patent number: 8479524
    Abstract: A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall which encloses the combustion chamber space and in the region of the combustion chamber outlet encloses a flow passage for hot gases which develop inside the combustion chamber, has a combustion chamber wall edge which freely terminates in the axial flow direction of the hot gases. The combustion chamber wall edge is formed with a profile which blocks or at least inhibits a diffuser effect when a cooling air flow, which is guided axially through the flow passages into the annular spatial area, flows over the combustion chamber wall edge.
    Type: Grant
    Filed: November 25, 2009
    Date of Patent: July 9, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: Madhavan Narasimhan Poyyapakkam, Fulvio Magni, Nadir Ince
  • Patent number: 8474267
    Abstract: A turbo machine is provided that includes a turbine nozzle having a wall. The wall provides spaced apart first and second surfaces. A combustor includes a liner having an annular lip that engages one of the first and second surfaces. A floating ring seal is supported by the liner in a slip-fit relationship, for example, using a retainer. The floating ring seal engages the other of the first and second surfaces. The floating ring seal is slidably moveable relative to the liner in a floating direction in response to movement of the liner in a radial direction.
    Type: Grant
    Filed: March 5, 2009
    Date of Patent: July 2, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Eric Andrew Nager
  • Publication number: 20130160455
    Abstract: An expander-generator is disclosed. The expander-generator is disposed within a hermetically-sealed housing and includes a high-pressure expander stage and a low-pressure expander stage. A working fluid, such as ammonia, is introduced into the high and low pressure expander stages and expanded therein so as to provide rotational torque to a shaft. A generator, such as a motor, pump, or compressor, may be coupled to a free end of the shaft such that rotation of the shaft will provide useful work for the generator.
    Type: Application
    Filed: September 14, 2010
    Publication date: June 27, 2013
    Applicant: DRESSER-RAND COMPANY
    Inventors: Patrice Leconte, Jean-Pierre G. Mullier, Herve Dourlens
  • Patent number: 8459041
    Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a leaf seal contacting the interface member to provide a seal between the interface member and the turbine section.
    Type: Grant
    Filed: November 9, 2011
    Date of Patent: June 11, 2013
    Assignee: General Electric Company
    Inventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
  • Patent number: 8453464
    Abstract: An air metering apparatus for a secondary air system of gas turbine engine includes a metering gap defined between surfaces comprised of one or more metals having one of similar coefficients of thermal expansion or similar thermal expansions at an operating temperature. Provided is an air metering gap which undergoes thermal growth in a way which provides a suitable air metering gap during engine running conditions.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: June 4, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Pierre-Yves Legare
  • Patent number: 8448444
    Abstract: A bracket for a combustor, and a method for mounting a transition piece in a combustor, are disclosed. The combustor has an impingement sleeve at least partially surrounding a transition piece and an outer casing at least partially surrounding the impingement sleeve. The bracket is mounted to the transition piece and connected to the outer casing. The method includes mounting a bracket to the transition piece, extending the bracket through an impingement sleeve, the impingement sleeve at least partially surrounding the transition piece, and connecting the bracket to an outer casing, the outer casing at least partially surrounding the impingement sleeve.
    Type: Grant
    Filed: February 18, 2011
    Date of Patent: May 28, 2013
    Assignee: General Electric Company
    Inventors: David William Cihlar, Patrick Benedict Melton
  • Patent number: 8429916
    Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.
    Type: Grant
    Filed: November 23, 2009
    Date of Patent: April 30, 2013
    Assignee: Honeywell International Inc.
    Inventors: Nagaraja S. Rudrapatna, Paul Yankowich, Amy Hanson
  • Patent number: 8429894
    Abstract: A bellows includes a flexible section including a series of convolutions extending between a first end and a second end. The convolutions are formed of a nano-grained aluminum alloy.
    Type: Grant
    Filed: September 22, 2008
    Date of Patent: April 30, 2013
    Assignee: Pratt & Whitney Rocketdyne, Inc.
    Inventors: Daniel P. Cap, Ronald Urquidi, Guido Canzona
  • Patent number: 8424312
    Abstract: The invention relates to an exhaust system (100) for channeling the streams from a by-pass gas turbine, the system comprising a stream channeling nozzle and an exhaust casing (110) for connecting the channeling nozzle to the outlet of the gas turbine, said channeling nozzle comprising a primary nozzle (120) fastened to the exhaust casing (110) and a secondary nozzle (130) placed around the primary nozzle. The exhaust system further comprises means for fastening the secondary nozzle (130) directly to the exhaust casing (110), said secondary nozzle being supported by the exhaust casing independently of the primary nozzle (120).
    Type: Grant
    Filed: May 7, 2008
    Date of Patent: April 23, 2013
    Assignee: Snecma Propulsion Solide
    Inventors: Eric Conete, Laurent Baroumes, Georges Habarou
  • Patent number: 8418495
    Abstract: An air cycle machine includes two turbines and a compressor mounted on an integral shaft. The integral shaft includes a plurality of shaft sections that are welded together and machined in a single set-up process into a desired shaft shape to provide highly aligned bearing surfaces. The shaft includes three stops that cooperate with three fasteners to secure the two turbines and the compressor on the shaft.
    Type: Grant
    Filed: September 20, 2005
    Date of Patent: April 16, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Brent J. Merritt, Craig M. Beers
  • Patent number: 8418473
    Abstract: An exemplary turbine engine link assembly includes a link extending longitudinally from a rod end and terminating at a hemispherical end. The rod end is secured to an engine liner or an engine casing. The hemispherical end is biased toward a corresponding hemispherical recess in the engine liner or in the other of the engine liner or the engine casing.
    Type: Grant
    Filed: June 2, 2008
    Date of Patent: April 16, 2013
    Assignee: United Technologies Corporation
    Inventors: Dale William Petty, Gonzalo F. Martinez
  • Patent number: 8418474
    Abstract: A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.
    Type: Grant
    Filed: September 29, 2008
    Date of Patent: April 16, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford
  • Patent number: 8388307
    Abstract: Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.
    Type: Grant
    Filed: July 21, 2009
    Date of Patent: March 5, 2013
    Assignee: Honeywell International Inc.
    Inventors: Jason Smoke, Stony Kujala, Gregory O. Woodcock, Bradley Reed Tucker