US3657882A - Combustion apparatus - Google Patents

Combustion apparatus Download PDF

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Publication number
US3657882A
US3657882A US89396A US3657882DA US3657882A US 3657882 A US3657882 A US 3657882A US 89396 A US89396 A US 89396A US 3657882D A US3657882D A US 3657882DA US 3657882 A US3657882 A US 3657882A
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United States
Prior art keywords
seal
combination defined
transition pieces
transition
adjacent
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US89396A
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English (en)
Inventor
Birger O Hugoson
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Westinghouse Electric Corp
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Westinghouse Electric Corp
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Publication date
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Definitions

  • ABSTRACT In a gas turbine, the transition pieces ofthe combustor baskets are retained in assembled relation, and the joint between ad jacent transition pieces sealed by means of seal frames, uttached to the transition pieces, and seal members which slidably engage adjacent seal frames.
  • the structure reduces the tendency of the side walls of the transition pieces to buckle and simplifies the assembling of the transition pieces.
  • This invention relates, generally, to combustion apparatus and, more particularly, to combustion apparatus for a gas turbine power plant.
  • flanged seal frames are secured to adjacent sides of gas turbine combustor transition pieces at their outlet ends.
  • Inturned flanges on a seal member which is generally like an I-beam in shape, slidably engage the flanges on adjacent seal frames to retain the transition pieces in assembled relation.
  • the web portion of the seal member is disposed between adjacent seal frames to close 01f adjacent openings in sides of the transition pieces.
  • the seal member is exposed to substantially the same pressure and temperature on both sides, thereby reducing the buckling tendency.
  • FIG. 1 is an isometric view of portions of adjacent combustor baskets and seal members embodying principal features ofthe invention
  • F IG. 2 is an isometric view of one of the seal members utilized for retaining adjacent transition pieces of combustor baskets in assembled relation;
  • FIG. 3 is an enlarged fragmentary view of a portion of the structure shown in FIG. 1;
  • FIG. 4 is a view, in elevation, of half of an annular array of combustor baskets for a gas turbine assembled in closely spaced relation, and
  • FIG. 5 is an isometric view of a modified seal member, a portion being broken away for clearness.
  • the structure shown therein comprises a portion of a combustor basket which is of the canister type suitable for supplying a hot motivating fluid to the rotor of a gas turbine power plant in a manner well known in the art.
  • the portion of the combustor basket 10 shown includes a generally cylindrical intermediate section 12 and a transition piece 14 having a generally cylindrical upstream end portion 16 joined to the intermediate section 12, and a downstream portion 18 that progressively changes in contour from circular cross section as the jointure with the cylindrical intermediate section 12 to arcuate cross section at its outlet end portion 20.
  • the arcuate extent of the outlet 20 is such that, jointly with the outlets of the other combustor baskets, a complete annulus is provided for admitting the hot products of combustion from the combustor baskets 10 to the blades of a gas turbine (not shown), thereby providing full peripheral admission of motivating gases to the turbine.
  • the arcuate ends of the transition piece 18 may be strengthened by outwardly extending flanges 22 secured to the ends of the transition piece.
  • each side wall of each transition piece 18 is cut away to provide openings 24 in the side walls of the transition pieces.
  • Each opening 24 is disposed within a seal frame 26 secured to the side wall of the transition piece 18.
  • Each seal frame 26 comprises two angle members 28 each having one leg 30 attached to the side wall of a transition piece 18 and the other leg 32 providing an inwardly extending flange spaced from the transition piece.
  • the end of the leg 30 disposed nearest the outlet 20 of the transitionpiece is secured directly to the transition piece, as by welding, and the other end of the leg 30 is spaced from and attached to the transition piece by means of a generally triangular shaped gusset plate 34.
  • the space between the ends of the angle members 28 which are spaced from the transition piece 18 is closed by a gusset plate 36 having a concave edge secured to the transition piece 18, as by welding.
  • a seal member 38 is provided in order to retain the transition pieces 18in assembled relation, and to close off adjacent openings 24 in the transition pieces.
  • the seal member 38 is generally like an I-beam in shape having a web portion 40 and flanges 42 formed integrally with the web 40. The edges of each flange 42 are turned inwardly to form inturned flanges 44 spaced from the web 40.
  • the flanges 44 on the seal member 38 slidably engage the flanges 32 on adjacent seal frames 28 when the web 40 of the seal member is moved into position between two adjacent seal frames.
  • Seal strips 46 are secured to the web 40, as by welding, to engage the gusset plates 36 when the seal member 38 is installed.
  • the web portion of the seal member 38a comprises two plates 40a and 40b secured together in spaced relation to permit air circulation between the plates.
  • oppositely disposed indentations 48 on the plates may be secured together, as by spot welding.
  • the ends of the plates 40a and 40b may be secured together, as by welding.
  • the edges of the plates have inturned flanges 440 which function in the same manner as the flanges 44 to slidably engage the flanges 32 on adjacent seal frames 28 when the seal member 38a is installed. In this manner air is permitted to circulate between adjacent transition pieces, thereby aiding in cooling the transition pieces.
  • the invention provides an improved combustor transition piece arrangement and seal members which simplify the assembling of the transition pieces of combustor baskets in a gas turbine.
  • the seal frames and seal members retain the transition pieces in assembled relation and prevent escapement of the motivating fluid from the transition pieces. Furthermore, tendency of the transition pieces and the seal members to buckle is reduced.
  • Iclaim 1. ln combustion apparatus for a gas turbine power plant, in combination,
  • each seal frame comprises two angle members and gusset plates secured to the transition pieces.
  • one end of each of the angle members is secured directly to a transition piece and the other end is spaced from the transition piece by a triangular shaped gusset plate.
  • each seal member is generally like an I-beam in shape with a web portion and inturned flanges slidably engaging the angle members of two adjacent seal frames.
  • each seal member comprises two plates secured together in spaced relation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US89396A 1970-11-13 1970-11-13 Combustion apparatus Expired - Lifetime US3657882A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US8939670A 1970-11-13 1970-11-13

Publications (1)

Publication Number Publication Date
US3657882A true US3657882A (en) 1972-04-25

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Family Applications (1)

Application Number Title Priority Date Filing Date
US89396A Expired - Lifetime US3657882A (en) 1970-11-13 1970-11-13 Combustion apparatus

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US (1) US3657882A (enExample)
JP (1) JPS50692B1 (enExample)

Cited By (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297843A (en) * 1978-10-16 1981-11-03 Hitachi, Ltd. Combustor of gas turbine with features for vibration reduction and increased cooling
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
US5335502A (en) * 1992-09-09 1994-08-09 General Electric Company Arched combustor
US5414999A (en) * 1993-11-05 1995-05-16 General Electric Company Integral aft frame mount for a gas turbine combustor transition piece
US5706646A (en) * 1995-05-18 1998-01-13 European Gas Turbines Limited Gas turbine gas duct arrangement
US5761898A (en) * 1994-12-20 1998-06-09 General Electric Co. Transition piece external frame support
US6038861A (en) * 1998-06-10 2000-03-21 Siemens Westinghouse Power Corporation Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors
US6418727B1 (en) 2000-03-22 2002-07-16 Allison Advanced Development Company Combustor seal assembly
EP1270874A1 (de) * 2001-06-18 2003-01-02 Siemens Aktiengesellschaft Gasturbine mit einem Verdichter für Luft
US20030033794A1 (en) * 2001-08-14 2003-02-20 Peter Tiemann Combustion chamber arrangement for gas turbines
US6644032B1 (en) * 2002-10-22 2003-11-11 Power Systems Mfg, Llc Transition duct with enhanced profile optimization
US20040139746A1 (en) * 2003-01-22 2004-07-22 Mitsubishi Heavy Industries Ltd. Gas turbine tail tube seal and gas turbine using the same
US20060288707A1 (en) * 2005-06-27 2006-12-28 Siemens Power Generation, Inc. Support system for transition ducts
US20100031673A1 (en) * 2007-01-29 2010-02-11 John David Maltson Casing of a gas turbine engine
US20100037618A1 (en) * 2008-08-12 2010-02-18 Richard Charron Transition with a linear flow path for use in a gas turbine engine
US20100058763A1 (en) * 2008-09-11 2010-03-11 Rubio Mark F Segmented annular combustor
US20100077719A1 (en) * 2008-09-29 2010-04-01 Siemens Energy, Inc. Modular Transvane Assembly
WO2010019177A3 (en) * 2008-08-12 2010-09-02 Siemens Energy, Inc. Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
US20100236249A1 (en) * 2009-03-20 2010-09-23 General Electric Company Systems and Methods for Reintroducing Gas Turbine Combustion Bypass Flow
US20120085103A1 (en) * 2010-10-07 2012-04-12 General Electric Company Shim for sealing transition pieces
CN102654287A (zh) * 2011-02-28 2012-09-05 通用电气公司 燃烧室混合接头
US20120280460A1 (en) * 2011-05-06 2012-11-08 General Electric Company Two-piece side seal with covers
CN102808659A (zh) * 2011-06-03 2012-12-05 通用电气公司 用于涡轮系统中过渡管道的载荷部件
CN102913625A (zh) * 2011-08-01 2013-02-06 通用电气公司 燃烧器叶片密封装置
CN103375187A (zh) * 2012-04-24 2013-10-30 通用电气公司 包括过渡件的燃烧系统及使用铸造高温合金的形成方法
US20140127008A1 (en) * 2012-11-08 2014-05-08 General Electric Company Transition duct having airfoil and hot gas path assembly for turbomachine
US20150132117A1 (en) * 2013-11-08 2015-05-14 John J. Marra Gas turbine engine ducting arrangement having discrete insert
WO2015199694A1 (en) * 2014-06-26 2015-12-30 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transitions duct bodies
WO2015199693A1 (en) * 2014-06-26 2015-12-30 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transition duct bodljs
US9322335B2 (en) 2013-03-15 2016-04-26 Siemens Energy, Inc. Gas turbine combustor exit piece with hinged connections
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US20170342850A1 (en) * 2016-05-27 2017-11-30 General Electric Company Side Seal with Reduced Corner Leakage
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10584638B2 (en) 2016-03-25 2020-03-10 General Electric Company Turbine nozzle cooling with panel fuel injector
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US20220065454A1 (en) * 2020-08-31 2022-03-03 General Electric Company Cooling insert for a turbomachine
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US2702454A (en) * 1951-06-07 1955-02-22 United Aircraft Corp Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants
US2748567A (en) * 1949-10-13 1956-06-05 Gen Motors Corp Gas turbine combustion chamber with telescoping casing and liner sections
US3018624A (en) * 1954-03-02 1962-01-30 Bristol Siddeley Engines Ltd Flame tubes for use in combustion systems of gas turbine engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2748567A (en) * 1949-10-13 1956-06-05 Gen Motors Corp Gas turbine combustion chamber with telescoping casing and liner sections
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US2702454A (en) * 1951-06-07 1955-02-22 United Aircraft Corp Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants
US3018624A (en) * 1954-03-02 1962-01-30 Bristol Siddeley Engines Ltd Flame tubes for use in combustion systems of gas turbine engines

Cited By (89)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297843A (en) * 1978-10-16 1981-11-03 Hitachi, Ltd. Combustor of gas turbine with features for vibration reduction and increased cooling
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
US5335502A (en) * 1992-09-09 1994-08-09 General Electric Company Arched combustor
US5414999A (en) * 1993-11-05 1995-05-16 General Electric Company Integral aft frame mount for a gas turbine combustor transition piece
US5761898A (en) * 1994-12-20 1998-06-09 General Electric Co. Transition piece external frame support
US5706646A (en) * 1995-05-18 1998-01-13 European Gas Turbines Limited Gas turbine gas duct arrangement
US6038861A (en) * 1998-06-10 2000-03-21 Siemens Westinghouse Power Corporation Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors
US6418727B1 (en) 2000-03-22 2002-07-16 Allison Advanced Development Company Combustor seal assembly
EP1270874A1 (de) * 2001-06-18 2003-01-02 Siemens Aktiengesellschaft Gasturbine mit einem Verdichter für Luft
CN1328492C (zh) * 2001-06-18 2007-07-25 西门子公司 带有空气压缩机的燃气轮机
US6672070B2 (en) 2001-06-18 2004-01-06 Siemens Aktiengesellschaft Gas turbine with a compressor for air
US20030033794A1 (en) * 2001-08-14 2003-02-20 Peter Tiemann Combustion chamber arrangement for gas turbines
US6684620B2 (en) * 2001-08-14 2004-02-03 Siemens Aktiengesellschaft Combustion chamber arrangement for gas turbines
US6644032B1 (en) * 2002-10-22 2003-11-11 Power Systems Mfg, Llc Transition duct with enhanced profile optimization
WO2004038197A1 (en) * 2002-10-22 2004-05-06 Power Systems Mfg., Llc Transition duct with enhanced profile optimization
US20040139746A1 (en) * 2003-01-22 2004-07-22 Mitsubishi Heavy Industries Ltd. Gas turbine tail tube seal and gas turbine using the same
US6860108B2 (en) * 2003-01-22 2005-03-01 Mitsubishi Heavy Industries, Ltd. Gas turbine tail tube seal and gas turbine using the same
US20060288707A1 (en) * 2005-06-27 2006-12-28 Siemens Power Generation, Inc. Support system for transition ducts
US20070017225A1 (en) * 2005-06-27 2007-01-25 Eduardo Bancalari Combustion transition duct providing stage 1 tangential turning for turbine engines
US7584620B2 (en) 2005-06-27 2009-09-08 Siemens Energy, Inc. Support system for transition ducts
US7721547B2 (en) 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
US20100031673A1 (en) * 2007-01-29 2010-02-11 John David Maltson Casing of a gas turbine engine
US8402769B2 (en) * 2007-01-29 2013-03-26 Siemens Aktiengesellschaft Casing of a gas turbine engine having a radial spoke with a flow guiding element
WO2010019177A3 (en) * 2008-08-12 2010-09-02 Siemens Energy, Inc. Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
EP2530248A1 (en) * 2008-08-12 2012-12-05 Siemens Energy, Inc. Linear transition duct for a gas turbine
CN102119268B (zh) * 2008-08-12 2014-12-03 西门子能源公司 燃气轮机中使用的具有带排气口的线性流动路径的过渡件
US20100037618A1 (en) * 2008-08-12 2010-02-18 Richard Charron Transition with a linear flow path for use in a gas turbine engine
WO2010019175A3 (en) * 2008-08-12 2011-01-13 Siemens Energy, Inc. Transition duct for gas turbine combustor with inlet and outlet circumferentially offset
CN102119268A (zh) * 2008-08-12 2011-07-06 西门子能源公司 燃气轮机中使用的具有带排气口的线性流动路径的过渡件
US8065881B2 (en) 2008-08-12 2011-11-29 Siemens Energy, Inc. Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
US8113003B2 (en) 2008-08-12 2012-02-14 Siemens Energy, Inc. Transition with a linear flow path for use in a gas turbine engine
US7874138B2 (en) * 2008-09-11 2011-01-25 Siemens Energy, Inc. Segmented annular combustor
US20100058763A1 (en) * 2008-09-11 2010-03-11 Rubio Mark F Segmented annular combustor
US8230688B2 (en) 2008-09-29 2012-07-31 Siemens Energy, Inc. Modular transvane assembly
WO2010036426A3 (en) * 2008-09-29 2011-03-10 Siemens Energy, Inc. Modular transvane assembly
US20100077719A1 (en) * 2008-09-29 2010-04-01 Siemens Energy, Inc. Modular Transvane Assembly
US8281601B2 (en) * 2009-03-20 2012-10-09 General Electric Company Systems and methods for reintroducing gas turbine combustion bypass flow
US20100236249A1 (en) * 2009-03-20 2010-09-23 General Electric Company Systems and Methods for Reintroducing Gas Turbine Combustion Bypass Flow
US8225614B2 (en) * 2010-10-07 2012-07-24 General Electric Company Shim for sealing transition pieces
CN102444717B (zh) * 2010-10-07 2016-08-24 通用电气公司 用于密封过渡件的填隙片
CN102444717A (zh) * 2010-10-07 2012-05-09 通用电气公司 用于密封过渡件的填隙片
US20120085103A1 (en) * 2010-10-07 2012-04-12 General Electric Company Shim for sealing transition pieces
EP2492596A3 (en) * 2011-02-28 2014-01-15 General Electric Company Combustor mixing joint
US10030872B2 (en) 2011-02-28 2018-07-24 General Electric Company Combustor mixing joint with flow disruption surface
CN102654287A (zh) * 2011-02-28 2012-09-05 通用电气公司 燃烧室混合接头
CN102654287B (zh) * 2011-02-28 2016-02-17 通用电气公司 燃烧室混合接头
US20120280460A1 (en) * 2011-05-06 2012-11-08 General Electric Company Two-piece side seal with covers
US20120304653A1 (en) * 2011-06-03 2012-12-06 General Electric Company Load member for transition duct in turbine system
CN102808659A (zh) * 2011-06-03 2012-12-05 通用电气公司 用于涡轮系统中过渡管道的载荷部件
CN102808659B (zh) * 2011-06-03 2016-02-10 通用电气公司 用于涡轮系统中过渡管道的载荷部件
US8978388B2 (en) * 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
CN102913625A (zh) * 2011-08-01 2013-02-06 通用电气公司 燃烧器叶片密封装置
EP2554908A3 (en) * 2011-08-01 2015-12-23 General Electric Company Combustor leaf seal arrangement
CN103375187A (zh) * 2012-04-24 2013-10-30 通用电气公司 包括过渡件的燃烧系统及使用铸造高温合金的形成方法
US20140127008A1 (en) * 2012-11-08 2014-05-08 General Electric Company Transition duct having airfoil and hot gas path assembly for turbomachine
US9322335B2 (en) 2013-03-15 2016-04-26 Siemens Energy, Inc. Gas turbine combustor exit piece with hinged connections
US20150132117A1 (en) * 2013-11-08 2015-05-14 John J. Marra Gas turbine engine ducting arrangement having discrete insert
WO2015199693A1 (en) * 2014-06-26 2015-12-30 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transition duct bodljs
US9771813B2 (en) 2014-06-26 2017-09-26 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine
US9803487B2 (en) 2014-06-26 2017-10-31 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine
WO2015199694A1 (en) * 2014-06-26 2015-12-30 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transitions duct bodies
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10584638B2 (en) 2016-03-25 2020-03-10 General Electric Company Turbine nozzle cooling with panel fuel injector
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10641175B2 (en) 2016-03-25 2020-05-05 General Electric Company Panel fuel injector
US10641176B2 (en) 2016-03-25 2020-05-05 General Electric Company Combustion system with panel fuel injector
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10655541B2 (en) 2016-03-25 2020-05-19 General Electric Company Segmented annular combustion system
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US10690056B2 (en) 2016-03-25 2020-06-23 General Electric Company Segmented annular combustion system with axial fuel staging
US11002190B2 (en) 2016-03-25 2021-05-11 General Electric Company Segmented annular combustion system
US10724441B2 (en) 2016-03-25 2020-07-28 General Electric Company Segmented annular combustion system
US20170342850A1 (en) * 2016-05-27 2017-11-30 General Electric Company Side Seal with Reduced Corner Leakage
US10689995B2 (en) * 2016-05-27 2020-06-23 General Electric Company Side seal with reduced corner leakage
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US20220065454A1 (en) * 2020-08-31 2022-03-03 General Electric Company Cooling insert for a turbomachine
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11460191B2 (en) * 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

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