JP4124585B2 - 選択的に傾斜させた冷却孔を有する燃焼器ライナ - Google Patents

選択的に傾斜させた冷却孔を有する燃焼器ライナ Download PDF

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Publication number
JP4124585B2
JP4124585B2 JP2001305905A JP2001305905A JP4124585B2 JP 4124585 B2 JP4124585 B2 JP 4124585B2 JP 2001305905 A JP2001305905 A JP 2001305905A JP 2001305905 A JP2001305905 A JP 2001305905A JP 4124585 B2 JP4124585 B2 JP 4124585B2
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Japan
Prior art keywords
group
cooling holes
film cooling
holes
liner
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Expired - Fee Related
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JP2001305905A
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English (en)
Japanese (ja)
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JP2002139220A5 (enExample
JP2002139220A (ja
Inventor
タリク・ケイ・ハリス
マイケル・バーク・ブリスキー
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General Electric Co
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General Electric Co
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    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
JP2001305905A 2000-10-03 2001-10-02 選択的に傾斜させた冷却孔を有する燃焼器ライナ Expired - Fee Related JP4124585B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/678,069 US6408629B1 (en) 2000-10-03 2000-10-03 Combustor liner having preferentially angled cooling holes
US09/678069 2000-10-03

Publications (3)

Publication Number Publication Date
JP2002139220A JP2002139220A (ja) 2002-05-17
JP2002139220A5 JP2002139220A5 (enExample) 2005-04-21
JP4124585B2 true JP4124585B2 (ja) 2008-07-23

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JP2001305905A Expired - Fee Related JP4124585B2 (ja) 2000-10-03 2001-10-02 選択的に傾斜させた冷却孔を有する燃焼器ライナ

Country Status (3)

Country Link
US (1) US6408629B1 (enExample)
EP (1) EP1195559B1 (enExample)
JP (1) JP4124585B2 (enExample)

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US7186084B2 (en) * 2003-11-19 2007-03-06 General Electric Company Hot gas path component with mesh and dimpled cooling
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FR2892180B1 (fr) * 2005-10-18 2008-02-01 Snecma Sa Amelioration des perfomances d'une chambre de combustion par multiperforation des parois
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US7546737B2 (en) * 2006-01-24 2009-06-16 Honeywell International Inc. Segmented effusion cooled gas turbine engine combustor
US7669422B2 (en) * 2006-07-26 2010-03-02 General Electric Company Combustor liner and method of fabricating same
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US7726131B2 (en) * 2006-12-19 2010-06-01 Pratt & Whitney Canada Corp. Floatwall dilution hole cooling
US8171736B2 (en) * 2007-01-30 2012-05-08 Pratt & Whitney Canada Corp. Combustor with chamfered dome
US7942006B2 (en) * 2007-03-26 2011-05-17 Honeywell International Inc. Combustors and combustion systems for gas turbine engines
US20080271457A1 (en) * 2007-05-01 2008-11-06 General Electric Company Cooling Holes For Gas Turbine Combustor Having A Non-Uniform Diameter Therethrough
FR2922630B1 (fr) * 2007-10-22 2015-11-13 Snecma Paroi de chambre de combustion a dilution et refroidissement optimises,chambre de combustion et turbomachine en etant munies
US7954326B2 (en) * 2007-11-28 2011-06-07 Honeywell International Inc. Systems and methods for cooling gas turbine engine transition liners
US20090188256A1 (en) * 2008-01-25 2009-07-30 Honeywell International Inc. Effusion cooling for gas turbine combustors
US20090199563A1 (en) * 2008-02-07 2009-08-13 Hamilton Sundstrand Corporation Scalable pyrospin combustor
US9068743B2 (en) * 2009-02-26 2015-06-30 8 Rivers Capital, LLC & Palmer Labs, LLC Apparatus for combusting a fuel at high pressure and high temperature, and associated system
WO2010099452A2 (en) * 2009-02-26 2010-09-02 Palmer Labs, Llc Apparatus and method for combusting a fuel at high pressure and high temperature, and associated system and device
US8986002B2 (en) * 2009-02-26 2015-03-24 8 Rivers Capital, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US8397511B2 (en) * 2009-05-19 2013-03-19 General Electric Company System and method for cooling a wall of a gas turbine combustor
US9897320B2 (en) * 2009-07-30 2018-02-20 Honeywell International Inc. Effusion cooled dual wall gas turbine combustors
US9416970B2 (en) * 2009-11-30 2016-08-16 United Technologies Corporation Combustor heat panel arrangement having holes offset from seams of a radially opposing heat panel
US9810081B2 (en) 2010-06-11 2017-11-07 Siemens Energy, Inc. Cooled conduit for conveying combustion gases
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FR2979416B1 (fr) * 2011-08-26 2013-09-20 Turbomeca Paroi de chambre de combustion
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US9625151B2 (en) * 2012-09-25 2017-04-18 United Technologies Corporation Cooled combustor liner grommet
US9404654B2 (en) 2012-09-26 2016-08-02 United Technologies Corporation Gas turbine engine combustor with integrated combustor vane
US9482432B2 (en) 2012-09-26 2016-11-01 United Technologies Corporation Gas turbine engine combustor with integrated combustor vane having swirler
US9335050B2 (en) 2012-09-26 2016-05-10 United Technologies Corporation Gas turbine engine combustor
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9638057B2 (en) 2013-03-14 2017-05-02 Rolls-Royce North American Technologies, Inc. Augmented cooling system
EP3077726B1 (en) * 2013-12-06 2021-03-03 United Technologies Corporation Cooling a combustor heat shield proximate a quench aperture
US10317080B2 (en) 2013-12-06 2019-06-11 United Technologies Corporation Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
FR3015010B1 (fr) * 2013-12-12 2016-01-22 Snecma Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif
CN107076416B (zh) 2014-08-26 2020-05-19 西门子能源公司 用于燃气涡轮发动机中的声共振器的薄膜冷却孔装置
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US10041677B2 (en) * 2015-12-17 2018-08-07 General Electric Company Combustion liner for use in a combustor assembly and method of manufacturing
US11015529B2 (en) 2016-12-23 2021-05-25 General Electric Company Feature based cooling using in wall contoured cooling passage
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CN110573799A (zh) 2017-03-07 2019-12-13 八河流资产有限责任公司 用于操作燃气涡轮机的灵活燃料燃烧室的系统和方法
US20180266687A1 (en) 2017-03-16 2018-09-20 General Electric Company Reducing film scrubbing in a combustor
US10753283B2 (en) 2017-03-20 2020-08-25 Pratt & Whitney Canada Corp. Combustor heat shield cooling hole arrangement
US10816202B2 (en) 2017-11-28 2020-10-27 General Electric Company Combustor liner for a gas turbine engine and an associated method thereof
JP7458370B2 (ja) 2018-07-23 2024-03-29 ８ リバーズ キャピタル，エルエルシー 無炎燃焼による発電のためのシステムおよび方法
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Also Published As

Publication number Publication date
EP1195559A2 (en) 2002-04-10
EP1195559A3 (en) 2002-05-15
JP2002139220A (ja) 2002-05-17
EP1195559B1 (en) 2012-09-05
US6408629B1 (en) 2002-06-25

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