JP6584634B2 - 燃焼滞留時間が短縮された遅延希薄噴射を有するガスタービントランジションダクト - Google Patents

燃焼滞留時間が短縮された遅延希薄噴射を有するガスタービントランジションダクト Download PDF

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JP6584634B2
JP6584634B2 JP2018503579A JP2018503579A JP6584634B2 JP 6584634 B2 JP6584634 B2 JP 6584634B2 JP 2018503579 A JP2018503579 A JP 2018503579A JP 2018503579 A JP2018503579 A JP 2018503579A JP 6584634 B2 JP6584634 B2 JP 6584634B2
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Prior art keywords
flow
cone
combustion
acceleration structure
turbine engine
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JP2018503579A
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English (en)
Japanese (ja)
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JP2018526603A (ja
Inventor
レイ ラスター ウォルター
レイ ラスター ウォルター
エンリケ ポルティーヨ ビルバオ ファン
エンリケ ポルティーヨ ビルバオ ファン
エイ． フォックス ティモシー
エイ． フォックス ティモシー
エル． パワーズ グラント
エル． パワーズ グラント
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Siemens AG
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Siemens AG
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
JP2018503579A 2015-07-24 2015-07-24 燃焼滞留時間が短縮された遅延希薄噴射を有するガスタービントランジションダクト Expired - Fee Related JP6584634B2 (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2015/041948 WO2017018982A1 (en) 2015-07-24 2015-07-24 Gas turbine transition duct with late lean injection having reduced combustion residence time

Publications (2)

Publication Number Publication Date
JP2018526603A JP2018526603A (ja) 2018-09-13
JP6584634B2 true JP6584634B2 (ja) 2019-10-02

Family

ID=53785745

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2018503579A Expired - Fee Related JP6584634B2 (ja) 2015-07-24 2015-07-24 燃焼滞留時間が短縮された遅延希薄噴射を有するガスタービントランジションダクト

Country Status (5)

Country Link
US (1) US20180187563A1 (zh)
EP (1) EP3325887A1 (zh)
JP (1) JP6584634B2 (zh)
CN (1) CN107923621B (zh)
WO (1) WO2017018982A1 (zh)

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US20180245792A1 (en) * 2017-02-24 2018-08-30 General Electric Company Combustion System with Axially Staged Fuel Injection
US10823418B2 (en) * 2017-03-02 2020-11-03 General Electric Company Gas turbine engine combustor comprising air inlet tubes arranged around the combustor
US11187415B2 (en) 2017-12-11 2021-11-30 General Electric Company Fuel injection assemblies for axial fuel staging in gas turbine combustors
US11137144B2 (en) 2017-12-11 2021-10-05 General Electric Company Axial fuel staging system for gas turbine combustors
US10816203B2 (en) 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
US11248789B2 (en) 2018-12-07 2022-02-15 Raytheon Technologies Corporation Gas turbine engine with integral combustion liner and turbine nozzle
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps

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US6047550A (en) * 1996-05-02 2000-04-11 General Electric Co. Premixing dry low NOx emissions combustor with lean direct injection of gas fuel
US7721547B2 (en) 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
JP4409566B2 (ja) * 2006-12-19 2010-02-03 川崎重工業株式会社 希薄予混合型燃焼装置とその制御方法
US8375726B2 (en) 2008-09-24 2013-02-19 Siemens Energy, Inc. Combustor assembly in a gas turbine engine
US8230688B2 (en) * 2008-09-29 2012-07-31 Siemens Energy, Inc. Modular transvane assembly
US8276389B2 (en) * 2008-09-29 2012-10-02 Siemens Energy, Inc. Assembly for directing combustion gas
US8701383B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection system configuration
US8689559B2 (en) * 2009-03-30 2014-04-08 General Electric Company Secondary combustion system for reducing the level of emissions generated by a turbomachine
US8991192B2 (en) * 2009-09-24 2015-03-31 Siemens Energy, Inc. Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine
US8752386B2 (en) * 2010-05-25 2014-06-17 Siemens Energy, Inc. Air/fuel supply system for use in a gas turbine engine
US20130239585A1 (en) * 2012-03-14 2013-09-19 Jay A. Morrison Tangential flow duct with full annular exit component
US9133722B2 (en) * 2012-04-30 2015-09-15 General Electric Company Transition duct with late injection in turbine system
US9551492B2 (en) * 2012-11-30 2017-01-24 General Electric Company Gas turbine engine system and an associated method thereof
US9482434B2 (en) * 2013-03-15 2016-11-01 General Electric Company Methods relating to downstream fuel and air injection in gas turbines
US9322556B2 (en) * 2013-03-18 2016-04-26 General Electric Company Flow sleeve assembly for a combustion module of a gas turbine combustor
US9316396B2 (en) * 2013-03-18 2016-04-19 General Electric Company Hot gas path duct for a combustor of a gas turbine
US9316155B2 (en) * 2013-03-18 2016-04-19 General Electric Company System for providing fuel to a combustor
US9383104B2 (en) * 2013-03-18 2016-07-05 General Electric Company Continuous combustion liner for a combustor of a gas turbine
EP2808610A1 (de) * 2013-05-31 2014-12-03 Siemens Aktiengesellschaft Gasturbinen-Brennkammer mit Tangentialeindüsung als späte Mager-Einspritzung
US20150052905A1 (en) * 2013-08-20 2015-02-26 General Electric Company Pulse Width Modulation for Control of Late Lean Liquid Injection Velocity
US9574498B2 (en) * 2013-09-25 2017-02-21 General Electric Company Internally cooled transition duct aft frame with serpentine cooling passage and conduit
US10139111B2 (en) * 2014-03-28 2018-11-27 Siemens Energy, Inc. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine
WO2016032436A1 (en) * 2014-08-26 2016-03-03 Siemens Energy, Inc. Cooling system for fuel nozzles within combustor in a turbine engine
US20160281992A1 (en) * 2015-03-24 2016-09-29 General Electric Company Injection boss for a unibody combustor
WO2018026382A1 (en) * 2016-08-03 2018-02-08 Siemens Aktiengesellschaft Ducting arrangement with injector assemblies configured to form a shielding flow of air injected into a combustion stage in a gas turbine engine
US10095218B2 (en) * 2016-08-03 2018-10-09 Siemens Aktiengesellschaft Method and computer-readable model for additively manufacturing ducting arrangement with injector assemblies forming a shielding flow of air

Also Published As

Publication number Publication date
WO2017018982A1 (en) 2017-02-02
CN107923621A (zh) 2018-04-17
CN107923621B (zh) 2020-03-10
JP2018526603A (ja) 2018-09-13
EP3325887A1 (en) 2018-05-30
US20180187563A1 (en) 2018-07-05

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