JP6188127B2 - タービンシステム内での後期噴射を備えたトランジッションダクト - Google Patents

タービンシステム内での後期噴射を備えたトランジッションダクト Download PDF

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Publication number
JP6188127B2
JP6188127B2 JP2013034087A JP2013034087A JP6188127B2 JP 6188127 B2 JP6188127 B2 JP 6188127B2 JP 2013034087 A JP2013034087 A JP 2013034087A JP 2013034087 A JP2013034087 A JP 2013034087A JP 6188127 B2 JP6188127 B2 JP 6188127B2
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Japan
Prior art keywords
transition
transition duct
outlet
fuel
inlet
Prior art date
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Active
Application number
JP2013034087A
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English (en)
Japanese (ja)
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JP2013231576A5 (enExample
JP2013231576A (ja
Inventor
ジェフリー・スコット・ルベグ
ロニー・レイ・ペンテコスト
ジェームズ・スコット・フラナガン
ウォン−ウック・キム
ケヴィン・ウエストン・マクマハン
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
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Publication of JP2013231576A5 publication Critical patent/JP2013231576A5/ja
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Publication of JP6188127B2 publication Critical patent/JP6188127B2/ja
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Classifications

    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
JP2013034087A 2012-04-30 2013-02-25 タービンシステム内での後期噴射を備えたトランジッションダクト Active JP6188127B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/459,516 US9133722B2 (en) 2012-04-30 2012-04-30 Transition duct with late injection in turbine system
US13/459,516 2012-04-30

Publications (3)

Publication Number Publication Date
JP2013231576A JP2013231576A (ja) 2013-11-14
JP2013231576A5 JP2013231576A5 (enExample) 2016-04-07
JP6188127B2 true JP6188127B2 (ja) 2017-08-30

Family

ID=47843080

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2013034087A Active JP6188127B2 (ja) 2012-04-30 2013-02-25 タービンシステム内での後期噴射を備えたトランジッションダクト

Country Status (5)

Country Link
US (1) US9133722B2 (enExample)
EP (1) EP2660519B1 (enExample)
JP (1) JP6188127B2 (enExample)
CN (1) CN103375262B (enExample)
RU (1) RU2013108686A (enExample)

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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
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US20160265782A1 (en) * 2015-03-10 2016-09-15 General Electric Company Air shield for a fuel injector of a combustor
EP3325887A1 (en) * 2015-07-24 2018-05-30 Siemens Aktiengesellschaft Gas turbine transition duct with late lean injection having reduced combustion residence time
EP3289185A1 (en) * 2015-08-06 2018-03-07 Siemens Aktiengesellschaft Transition ducts of a gas turbine combustor
JP6625427B2 (ja) * 2015-12-25 2019-12-25 川崎重工業株式会社 ガスタービンエンジン
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
US10227883B2 (en) 2016-03-24 2019-03-12 General Electric Company Transition duct assembly
US10145251B2 (en) 2016-03-24 2018-12-04 General Electric Company Transition duct assembly
US10260360B2 (en) * 2016-03-24 2019-04-16 General Electric Company Transition duct assembly
US10260752B2 (en) * 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10260424B2 (en) * 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10415831B2 (en) 2016-10-27 2019-09-17 General Electric Company Combustor assembly with mounted auxiliary component
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
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
FR3101670B1 (fr) * 2019-10-08 2021-10-08 Safran Aircraft Engines Injecteur pour une turbine haute pression

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Also Published As

Publication number Publication date
EP2660519B1 (en) 2015-12-16
RU2013108686A (ru) 2014-09-10
US20130283804A1 (en) 2013-10-31
CN103375262A (zh) 2013-10-30
US9133722B2 (en) 2015-09-15
JP2013231576A (ja) 2013-11-14
EP2660519A1 (en) 2013-11-06
CN103375262B (zh) 2016-12-07

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