Combustor Or Fuel System Patents (Class 60/800)
  • Patent number: 10612780
    Abstract: A combustion chamber arrangement comprises an annular combustion chamber, an outer casing, an inner casing and a stage of outlet guide vanes arranged at the downstream end of the combustion chamber interconnecting the outer casing and the inner casing. The combustion chamber comprises an upstream wall structure, a radially inner cowl is removably secured to a radially inner axially extending flange by fasteners and a radially outer wall structure and a radially outer cowl are removably secured to a radially outer axially extending flange by fasteners. The flange is slidably mounted on the radially inner wall structure. The flange has at least one recess in its radially inner surface and the fasteners are arranged in the recess in the radially inner surface of the flange. The cowl abuts the radially outer surface of the flange and the radially inner wall structure abuts the radially inner surface of the flange.
    Type: Grant
    Filed: December 15, 2017
    Date of Patent: April 7, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Thomas G. Mulcaire
  • Patent number: 10598037
    Abstract: An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L1); and a second annular air-sealing lip extending from the attachment base over a second length (L2) lower than the first length and facing the first lip.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: March 24, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Bruno Alexandre Didier Jacon, Damien Clément Didier Cordier, Gonzague Marie Come Jacques André Elluin, Florian Benjamin Kévin Lacroix, Philippe Didier Edmon André Libéral Nabias, Julien Vitra
  • Patent number: 10571127
    Abstract: The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip. The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: February 25, 2020
    Assignee: Mitsubishi Hitachi Power Sytems, Ltd.
    Inventors: Keisuke Miura, Yasuhiro Akiyama, Tomohiro Asai, Kazuki Abe, Mitsuhiro Karishuku, Satoshi Dodo, Akinori Hayashi, Yoshitaka Hirata, Noboru Okuyama
  • Patent number: 10550767
    Abstract: A method of installing a segment of a recuperator within an exhaust duct of a gas turbine engine, including positioning the segment such that its exhaust inlet is in fluid flow communication with the turbine section and its exhaust outlet is adapted to deliver an exhaust flow to atmosphere, engaging its air inlet to a plenum in fluid flow communication with the compressor discharge, and engaging its air outlet to another plenum containing the combustor. One of engaging the air inlet and engaging the air outlet includes forming a rigid connection providing sealed fluid flow communication with the corresponding plenum, and the other of engaging the air inlet and engaging the air outlet includes forming a floating connection providing sealed fluid flow communication with the corresponding plenum. The floating connection allows relative movement of the segment within the exhaust duct.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: February 4, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu
  • Patent number: 10429070
    Abstract: A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner formed integrally of a ceramic matrix composite material. The combustor dome defines a plurality of openings for receiving a respective plurality of fuel air injector hardware assemblies and may extend continuously along a circumferential direction.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: October 1, 2019
    Assignee: General Electric Company
    Inventors: David Andrew Hannwacker, Stephen John Howell
  • Patent number: 10344977
    Abstract: A combustion chamber arrangement has an annular outer wall and an annular inner wall having an upstream row of tiles and a downstream row of tiles. The outer wall has a concave bend which is less than 175°. The downstream end of the upstream tiles and the upstream end of the downstream tiles are adjacent the concave bend. The downstream ends of the upstream tiles are spaced at a greater distance from the inner surface of the annular outer wall than the upstream end of the downstream tiles. The upstream tiles have curved lips extending in a downstream direction which overlap but are spaced radially from the upstream ends of the downstream tiles. The outer wall has a row of apertures to direct coolant onto the outer surfaces of the curved lips and the upstream tiles has a row of apertures extending to the inner surfaces of the curved lips.
    Type: Grant
    Filed: January 31, 2017
    Date of Patent: July 9, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Thomas G Mulcaire, Robert A Hicks, Marcus Foale
  • Patent number: 10030872
    Abstract: A mixing joint for adjacent can combustors may include a first can combustor with a first combustion flow and a first wall, a second can combustor with a second combustion flow and a second wall, and a flow disruption surface positioned about the first wall and the second wall to promote mixing of the first combustion flow and the second combustion flow.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: July 24, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Gunnar Leif Siden, Clint L. Ingram
  • Patent number: 9896966
    Abstract: A tie rod includes a gusset which extends between a rod and a base.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: February 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Dale William Petty
  • Patent number: 9803487
    Abstract: A transition duct system for routing a gas flow in a combustion turbine engine is provided. The transition duct system includes one or more converging flow joint inserts forming a trailing edge at an intersection between adjacent transition ducts. The converging flow joint insert may be contained within a converging flow joint insert receiver and may be disconnected from the transition duct bodies by which the converging flow joint insert is positioned. Being disconnected eliminates stress formation within the converging flow joint insert, thereby enhancing the life of the insert. The converging flow joint insert may be removable such that the insert can be replaced once worn beyond design limits.
    Type: Grant
    Filed: June 26, 2014
    Date of Patent: October 31, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: David J. Wiebe, Andrew Carlson, Kyle C. Stoker
  • Patent number: 9482107
    Abstract: A sealing element is provided for sealing a leak path between a radial outer platform of a turbine nozzle and a carrier ring for carrying said radial outer platform. The carrier ring has an axially facing carrier ring surface and the radial outer platform has an axially facing platform surface. The carrier ring surface forms a first sealing surface and the platform surface forming a second sealing surface. The first and second sealing surfaces is aligned in a plane with a radial gap between them. The sealing element includes a leaf seal adapted to cover the gap between the first and second sealing surfaces, and an impingement plate for allowing impingement cooling of a radial outer surface of the radial outer platform. The impingement plate is adapted to be fixed to the turbine nozzle. The sealing element may be part of a nozzle arrangement of a gas turbine.
    Type: Grant
    Filed: September 28, 2009
    Date of Patent: November 1, 2016
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Stephen Batt
  • Patent number: 9297536
    Abstract: A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber there between. The annular combustor is free of any rigid attachments directly between the static structure and the annular outer shell. The annular outer shell includes a radially-outwardly extending flange. A stop member is rigidly connected with the static structure and is located adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited.
    Type: Grant
    Filed: May 1, 2012
    Date of Patent: March 29, 2016
    Assignee: United Technologies Corporation
    Inventors: Jonathan Jeffery Eastwood, Kevin Joseph Low
  • Patent number: 9284969
    Abstract: A thermal expansion joint suited for metal sheet component assemblies and method of connection is described. The expansion joint connection is formed by overlapping edge portions of components which are subject to different temperatures. Slot apertures are formed in the edge portion of a first component at predetermined locations and hole apertures are formed in the edge portion of the second component and disposed for confronting alignment with the slot apertures. A connecting sleeve is disposed in each hole aperture and projects through the hole and associated slot and a retention washer is secured over an end of the connecting sleeve on the other side of the second component. A fastener extends through the retention washer and the connecting sleeve to clampingly interconnect the overlapped edge portions of the first and second components.
    Type: Grant
    Filed: February 24, 2012
    Date of Patent: March 15, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 9285121
    Abstract: A cooling circuit of a gas turbine passes an airflow through a combustor section that includes a plurality of mixing tubes for transporting a fuel/air mixture and a perforated plate including a plurality of impingement holes and a plurality of tube holes for accommodating the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the perforated plate and the mixing tubes. The impingement holes and the annulus areas are configured to pass the airflow through the perforated plate. A flow management device modifies an effective size of the annulus areas to control a distribution of the airflow through the impingement holes and the annulus areas of the perforated plate to enhance cooling efficiency.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: March 15, 2016
    Assignee: General Electric Company
    Inventors: Christopher Paul Keener, Jason Thurman Stewart, Thomas Edward Johnson, Jonathan Dwight Berry
  • Patent number: 9249678
    Abstract: A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.
    Type: Grant
    Filed: June 27, 2012
    Date of Patent: February 2, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: John Alfred Simo, Patrick Benedict Melton, Richard Martin DiCintio, Christopher Paul Willis
  • Patent number: 9243561
    Abstract: A combustor head arrangement including a heatshield including an aperture therethrough. A meter panel having a cold side and a hot side, an aperture and a slot. At least one of the meter panel and the heatshield has a retaining feature on the cold side; one of the meter panel and the heatshield has an anti-rotation feature. The arrangement includes a burner seal sized to fit through the aperture in the meter panel from the hot side towards the cold side. The burner seal has a tang configured to pass through the slot when the burner seal is in a first orientation and to be retained by the retaining feature and the anti-rotation feature when the burner seal is rotated to a second orientation. Also a method of assembling the combustor head.
    Type: Grant
    Filed: December 4, 2012
    Date of Patent: January 26, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Michael Lawrence Carlisle
  • Patent number: 9212567
    Abstract: A gas duct for a gas turbine through which exhaust gases from the gas turbine are discharged to an outside includes a concentric inner casing and an outer casing disposed at a distance from the inner casing and concentrically encompassing the inner casing. A plurality of radial support struts interconnect the inner casing and the outer casing. Each of the support struts, the inner casing and the outer casing each have a heat-resistant lining disposed so as to provide protection against heat from the exhaust gases. The heat-resistant the linings of each of the support struts, the inner casing and the outer casing are divided in each case into a plurality of separate segments that are fastened to a support structure in an arrangement that provides an individual entirely or almost stress-free thermal expansion of each of the plurality of separate segments in an expansion plane.
    Type: Grant
    Filed: September 4, 2012
    Date of Patent: December 15, 2015
    Assignee: ALSTOM TECHNOLOGY LTD
    Inventors: Marc Rauch, Tobias Steffen, Joachim Krautzig, Amin Busekros, Juergen Pacholleck
  • Patent number: 9188342
    Abstract: Embodiments of the present application can provide systems and methods for dampening combustor dynamics. According to one embodiment, the system may include a micromixer. The system may also include at least one annular resonator disposed within the micromixer adjacent to a cap face plate or an impingement plate of the micromixer. The at least one annular resonator may include a first side including a number of holes forming a cold side hole pattern, a second side including a number of holes forming a hot side hole pattern, and a cavity substantially defined by the first side and the second side.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: November 17, 2015
    Assignee: General Electric Company
    Inventors: Patrick Benedict Melton, James Harold Westmoreland
  • Patent number: 9175855
    Abstract: The present application provides a combustion nozzle for use with a gas turbine engine. The combustion nozzle may include a number of mixing tubes, an outer shell surrounding the mixing tubes, and a floating aft plate assembly. The floating plate assembly may enclose the outer shell. The mixing tubes may extend through the aft plate assembly.
    Type: Grant
    Filed: October 29, 2012
    Date of Patent: November 3, 2015
    Assignee: General Electric Company
    Inventors: Daniel Gerritt Wegerif, Jonathan Dwight Berry, Carl Robert Barker
  • Patent number: 9175857
    Abstract: One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
    Type: Grant
    Filed: July 23, 2012
    Date of Patent: November 3, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Patrick Benedict Melton, Robert Joseph Rohrssen, Thomas Edward Johnson
  • Patent number: 9127553
    Abstract: Disclosed herein are apparatuses, methods, and systems for transition piece contouring. In an embodiment, a high thermal stress section of a transition piece and a low thermal stress section of a transition piece is a determined. The low thermal stress section of the transition piece may be contoured to intercept hot gas flow.
    Type: Grant
    Filed: April 13, 2012
    Date of Patent: September 8, 2015
    Assignee: General Electric Company
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia
  • Patent number: 9109447
    Abstract: A combustion system including a transition piece and method of forming the transition piece using a cast nickel-based superalloy is provided. The transition piece includes a body defining a flowpath and enclosure, the body having a circular inlet section for receiving combustion product from the combustor and an outlet end for flowing the combustor products into a first stage nozzle of a gas turbine. The transition piece comprises a one-piece single casting construction of the circular inlet section, the body, and the outlet end. The transition piece is formed from a nickel-based superalloy. The transition piece has a thick-to-thin ratio of wall thickness of thick transition to wall thickness of thin transition of about 1.1 to about 2.5.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: August 18, 2015
    Assignee: General Electric Company
    Inventors: Kevin Weston McMahan, Arthur Peck, Nicholas Vlessis
  • Patent number: 9097211
    Abstract: An example gas turbine engine includes an engine casing and an engine liner within the engine casing. One of the engine casing or the engine liner includes a first attachment structure. The other of the engine casing or the engine liner defines a track guide. A slideable member is moveable within the track guide between an engaged position and a disengaged position. The slideable member includes a second attachment structure engageable with the first attachment structure to secure the engine liner relative the engine casing when the slideable member is in the engaged position.
    Type: Grant
    Filed: June 6, 2008
    Date of Patent: August 4, 2015
    Assignee: United Technologies Corporation
    Inventors: Gonzalo F. Martinez, Gary J. Dillard
  • Publication number: 20150128610
    Abstract: A sealing component (61) for a turbine (15) positionable at an interface between a transition section (21) for carrying exhaust gas and a turbine inlet section (32). A U-shaped section (45) includes first and second legs (67, 69). When the sealing component is positioned at the interface, the legs extend about the turbine axis. A seal flange (75) connects to the U-shaped section. The positioned sealing component extends about the axis and in a direction away from the first leg. The seal flange faces the inner surface (76) of the flange. A flexible strip (79), positioned radially outward with respect to the seal flange, extends about the axis and extends along the axis between the U-shaped section and the flange. The flexible strip acts as a spring member pressing against the outer surface (96) of the flange.
    Type: Application
    Filed: November 12, 2013
    Publication date: May 14, 2015
    Inventors: Anil L. Salunkhe, Dustin C. Boudin
  • Publication number: 20150107264
    Abstract: A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.
    Type: Application
    Filed: October 22, 2013
    Publication date: April 23, 2015
    Inventors: David J. Wiebe, Richard C. Charron, Jay A. Morrison
  • Patent number: 9010127
    Abstract: A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame.
    Type: Grant
    Filed: March 2, 2012
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventors: Christopher Paul Willis, William Lawrence Byrne, David William Cihlar, Donald Timothy Lemon, Patrick Benedict Melton
  • 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: 8997501
    Abstract: A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint.
    Type: Grant
    Filed: June 2, 2011
    Date of Patent: April 7, 2015
    Assignee: General Electric Company
    Inventors: David William Cihlar, Patrick Benedict Melton, John Drake Vanselow
  • 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: 8978383
    Abstract: A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly.
    Type: Grant
    Filed: March 26, 2012
    Date of Patent: March 17, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • 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
  • Publication number: 20150052910
    Abstract: The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor.
    Type: Application
    Filed: August 23, 2013
    Publication date: February 26, 2015
    Applicant: General Electric Company
    Inventors: Devin Patrick Perkins, William Lawrence Byrne
  • Patent number: 8955332
    Abstract: A gas turbine combustor including a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions which are corner portions of the transition piece flow sleeve in a sectional direction thereof.
    Type: Grant
    Filed: July 8, 2014
    Date of Patent: February 17, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Takeo Saitou, Yasuyuki Watanabe, Shouhei Yoshida
  • Patent number: 8950192
    Abstract: A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an outer shell delimiting the combustor and splittable at a parting plane; a plenum enclosing the outer shell; a rotor; a turbine vane carrier encompassing the rotor; a plurality of stator vanes disposed on the vane carrier, and at least two sealing segments forming a ring, each of the at least two sealing segments having an inner edge and a head and a foot section and being movably mounted on the inner edge by the foot section to the outer shell and by the head section to the turbine vane carrier so as to mechanically connect the combustor to the turbine vane carrier.
    Type: Grant
    Filed: August 16, 2010
    Date of Patent: February 10, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Remigi Tschuor, Russell Bond Jones, Luis J. Rodriguez, Hartmut Haehnle, Marion Duggan (-Oneil)
  • Patent number: 8931170
    Abstract: A split fuel control module for a gas turbine engine and method of installation. The split fuel control module includes a first frame unit, a second frame unit, a segmented fuel path, and a distributed fuel controller. The first frame unit and the second frame unit are joined together at a frame unit interface. The segmented fuel path includes an upstream fuel interface fixed to the first frame unit and a downstream fuel interface fixed to the second frame unit and detachably coupled to the upstream fuel interface at the frame unit interface. A first portion of the distributed fuel controller is fixed to the first frame unit, and a second portion of the distributed fuel controller is fixed to the second frame unit.
    Type: Grant
    Filed: December 12, 2012
    Date of Patent: January 13, 2015
    Assignee: Solar Turbines Inc.
    Inventors: Darren Matthew Stratton, Gregory Lee Landrum
  • 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: 8919137
    Abstract: An assembly for use in a late lean injection system of a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the assembly comprising: a boss rigidly secured to the inner radial wall, the boss being configured to define a hollow passageway through the inner radial wall; a transfer tube slideably engaged within the boss; a stop formed on the transfer tube; and damping means positioned between the boss and the stop.
    Type: Grant
    Filed: August 5, 2011
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia
  • Patent number: 8899048
    Abstract: A combustion system for a gas turbine engine includes a housing defining a pressure vessel. A master injector is mounted to the housing for injecting fuel along a central axis defined through the pressure vessel. A plurality of slave injectors is included. Each slave injector is disposed radially outward of and substantially parallel to the master injector for injecting fuel and air in an injection plume radially outward of fuel injected through the master injector. The master injector and slave injectors are configured and adapted so the injection plume of the master injector intersects with the injection plumes of the slave injectors. The slave injectors can be staged for reduced power operation.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: December 2, 2014
    Assignee: Delavan Inc.
    Inventors: Lev Alexander Prociw, Andy W. Tibbs
  • 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
  • Patent number: 8863528
    Abstract: A combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture.
    Type: Grant
    Filed: July 27, 2006
    Date of Patent: October 21, 2014
    Assignee: United Technologies Corporation
    Inventors: Jun Shi, David J. Bombara, Jason Lawrence, Richard S. Tuthill, Jeffrey D. Melman
  • 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: 8833084
    Abstract: A tile is provided for lining the hot side of a wall of a combustor. The tile has a tile body with one or more bosses protruding from the cold side thereof. The or each boss extends, in use, through the wall of the combustor and has a threaded recess formed therein for threadingly connecting with a bolt which is inserted into the recess from the cold side of the combustor wall. The bolt fastens the tile to the combustor wall.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: September 16, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Michael Lawrence Carlisle
  • 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
  • Patent number: 8820045
    Abstract: A drain assembly for an auxiliary power unit having a hot zone formed by a combustor case comprises a fire enclosure, a drain fitting, a discharge port and a piston seal. The fire enclosure encapsulates the hot zone of the combustor case. The drain fitting connects to the fire enclosure. The discharge port extends from the combustor case into the drain fitting. The piston seal is positioned between the drain fitting and the discharge port.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: September 2, 2014
    Assignee: United Technologies Corporation
    Inventors: Brian C. DeDe, David Lau, David Ronald Adair, Christine Ingrid Schade
  • Publication number: 20140223921
    Abstract: A gas turbine includes a compressor, an annular combustion chamber, and a turbine, a combustion chamber shell of the combustion chamber adjoining the turbine inlet in a transition region in order to introduce the hot gases generated in the combustion chamber into the downstream turbine such that a thermal expansion-induced relative movement between the combustion chamber and the turbine inlet is possible. Combustion chamber shell support elements distributed on the periphery come into contact with a conical contour on the shaft cover due to the thermal expansion that occurs during operation and are supported on said contour. An improvement with respect to loading and service life is achieved in that the conical contour and the machine axis form an angle that allows the combustion chamber shell support elements to slide onto the conical contour.
    Type: Application
    Filed: April 17, 2014
    Publication date: August 14, 2014
    Inventors: Remigi TSCHUOR, Sinisa Narancic, Guenter Filkorn
  • Patent number: 8769963
    Abstract: A combustor-to-transition seal (301) includes a spring clip assembly (322, 422, 522) and a first spring metal ring (340, 441) or a ring assembly (440,540) that includes the first spring metal ring (441) and a second spring metal ring (442). Such combustor-to-transition seal (301) provides a first seal (321) and a second seal (331, 531) when at a junction of a combustor (108, 308, 508) and a transition (114, 314, 514). In an embodiment, the first spring metal ring (340) has a plurality of apertures (342) through the ring (340) that provide effusion cooling of the ring (340). The plurality of apertures (342) regulates a flow of cooling fluid to maintain an acceptable temperature of the ring (340). In an alternative embodiment, the second spring metal ring (442) has grooves (446) that regulate a flow of cooling fluid to maintain an acceptable temperature of the ring assembly (440).
    Type: Grant
    Filed: January 30, 2007
    Date of Patent: July 8, 2014
    Assignee: Siemens Energy, Inc.
    Inventor: William R. Ryan
  • Patent number: 8763406
    Abstract: A turbomachine combustion chamber in which a chamber end wall presents an opening for receiving a pre-vaporization bowl, and including a device for injecting air and fuel mounted on the axis thereof, the bowl being floatingly mounted relative to the chamber end wall to move in a predetermined radial direction and flaring downstream so as to form a collar, a deflector forming a thermal shield being made integrally with the bowl beside the chamber end wall so that the floating movement of the bowl-and-deflector assembly takes place in a sliding plane situated between the deflector and the chamber end wall.
    Type: Grant
    Filed: March 6, 2009
    Date of Patent: July 1, 2014
    Assignee: Snecma
    Inventors: Christophe Pieussergues, Denis Jean Maurice Sandelis
  • Patent number: 8756935
    Abstract: A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.
    Type: Grant
    Filed: June 10, 2009
    Date of Patent: June 24, 2014
    Assignee: SNECMA
    Inventors: Sylvain Duval, Didier Hippolyte Hernandez, Romain Nicolas Lunel
  • Patent number: 8745989
    Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.
    Type: Grant
    Filed: April 9, 2009
    Date of Patent: June 10, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Aleksander Kojovic, David C. Jarmon, Jun Shi, Shaoluo L. Butler
  • Publication number: 20140144148
    Abstract: A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.
    Type: Application
    Filed: November 27, 2012
    Publication date: May 29, 2014
    Applicant: United Technologies Corporation
    Inventors: Jonathan M. Jause, Kevin Joseph Low, David Kwoka
  • 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