CN107429920B - 火焰面燃烧器定外形的衬套 - Google Patents

火焰面燃烧器定外形的衬套 Download PDF

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Publication number
CN107429920B
CN107429920B CN201580074243.2A CN201580074243A CN107429920B CN 107429920 B CN107429920 B CN 107429920B CN 201580074243 A CN201580074243 A CN 201580074243A CN 107429920 B CN107429920 B CN 107429920B
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CN
China
Prior art keywords
combustion liner
coating
arrival end
thickness
combustion
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.)
Active
Application number
CN201580074243.2A
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English (en)
Chinese (zh)
Other versions
CN107429920A (zh
Inventor
P.J.斯图塔福德
H.里兹卡拉
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
H2 IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from US14/549,922 external-priority patent/US10060630B2/en
Application filed by Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Publication of CN107429920A publication Critical patent/CN107429920A/zh
Application granted granted Critical
Publication of CN107429920B publication Critical patent/CN107429920B/zh
Active legal-status Critical Current
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Classifications

    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/42—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
    • 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
    • F23R3/54—Reverse-flow combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
CN201580074243.2A 2014-11-21 2015-11-20 火焰面燃烧器定外形的衬套 Active CN107429920B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US14/549922 2014-11-21
US14/549,922 US10060630B2 (en) 2012-10-01 2014-11-21 Flamesheet combustor contoured liner
PCT/US2015/061926 WO2016099805A2 (en) 2014-11-21 2015-11-20 Flamesheet combustor contoured liner

Publications (2)

Publication Number Publication Date
CN107429920A CN107429920A (zh) 2017-12-01
CN107429920B true CN107429920B (zh) 2019-11-05

Family

ID=56127814

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201580074243.2A Active CN107429920B (zh) 2014-11-21 2015-11-20 火焰面燃烧器定外形的衬套

Country Status (5)

Country Link
EP (1) EP3221643B1 (ko)
JP (1) JP6824165B2 (ko)
KR (1) KR102405991B1 (ko)
CN (1) CN107429920B (ko)
WO (1) WO2016099805A2 (ko)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10684014B2 (en) 2016-08-04 2020-06-16 Raytheon Technologies Corporation Combustor panel for gas turbine engine
US10823410B2 (en) 2016-10-26 2020-11-03 Raytheon Technologies Corporation Cast combustor liner panel radius for gas turbine engine combustor
US11859819B2 (en) 2021-10-15 2024-01-02 General Electric Company Ceramic composite combustor dome and liners

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0136071A1 (en) * 1983-08-26 1985-04-03 Westinghouse Electric Corporation Varying thickness thermal barrier for combustion turbine baskets
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine
US6047539A (en) * 1998-04-30 2000-04-11 General Electric Company Method of protecting gas turbine combustor components against water erosion and hot corrosion
US6408610B1 (en) * 2000-07-18 2002-06-25 General Electric Company Method of adjusting gas turbine component cooling air flow
CN101050867A (zh) * 2006-02-27 2007-10-10 三菱重工业株式会社 燃烧器
EP2466205A1 (en) * 2009-08-13 2012-06-20 Mitsubishi Heavy Industries, Ltd. Combustor

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3364169B2 (ja) * 1999-06-09 2003-01-08 三菱重工業株式会社 ガスタービン及びその燃焼器
US6573474B1 (en) * 2000-10-18 2003-06-03 Chromalloy Gas Turbine Corporation Process for drilling holes through a thermal barrier coating
US20030203224A1 (en) * 2001-07-30 2003-10-30 Diconza Paul Josesh Thermal barrier coating of intermediate density
US20030202269A1 (en) * 2002-04-29 2003-10-30 Jack Chen Method for storing or rescuing data or information
JP2004092392A (ja) * 2002-07-12 2004-03-25 Toshiba Corp 遮熱コーティング施工方法
US7216485B2 (en) * 2004-09-03 2007-05-15 General Electric Company Adjusting airflow in turbine component by depositing overlay metallic coating
US7237384B2 (en) * 2005-01-26 2007-07-03 Peter Stuttaford Counter swirl shear mixer
US7581402B2 (en) * 2005-02-08 2009-09-01 Siemens Energy, Inc. Turbine engine combustor with bolted swirlers
US20070202269A1 (en) * 2006-02-24 2007-08-30 Potter Kenneth B Local repair process of thermal barrier coatings in turbine engine components
US7540152B2 (en) * 2006-02-27 2009-06-02 Mitsubishi Heavy Industries, Ltd. Combustor
US8146364B2 (en) * 2007-09-14 2012-04-03 Siemens Energy, Inc. Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber
US8586172B2 (en) * 2008-05-06 2013-11-19 General Electric Company Protective coating with high adhesion and articles made therewith
US8397511B2 (en) * 2009-05-19 2013-03-19 General Electric Company System and method for cooling a wall of a gas turbine combustor
US20110048017A1 (en) * 2009-08-27 2011-03-03 General Electric Company Method of depositing protective coatings on turbine combustion components
JP5320352B2 (ja) * 2010-07-15 2013-10-23 三菱重工業株式会社 遮熱コーティング部材及びその製造方法ならびに遮熱コート材料、ガスタービン及び焼結体
US9897317B2 (en) * 2012-10-01 2018-02-20 Ansaldo Energia Ip Uk Limited Thermally free liner retention mechanism
US10088162B2 (en) * 2012-10-01 2018-10-02 United Technologies Corporation Combustor with grommet having projecting lip
US9347669B2 (en) * 2012-10-01 2016-05-24 Alstom Technology Ltd. Variable length combustor dome extension for improved operability
US9765973B2 (en) * 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0136071A1 (en) * 1983-08-26 1985-04-03 Westinghouse Electric Corporation Varying thickness thermal barrier for combustion turbine baskets
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine
US6047539A (en) * 1998-04-30 2000-04-11 General Electric Company Method of protecting gas turbine combustor components against water erosion and hot corrosion
US6408610B1 (en) * 2000-07-18 2002-06-25 General Electric Company Method of adjusting gas turbine component cooling air flow
CN101050867A (zh) * 2006-02-27 2007-10-10 三菱重工业株式会社 燃烧器
EP2466205A1 (en) * 2009-08-13 2012-06-20 Mitsubishi Heavy Industries, Ltd. Combustor

Also Published As

Publication number Publication date
JP6824165B2 (ja) 2021-02-03
JP2017536524A (ja) 2017-12-07
KR102405991B1 (ko) 2022-06-10
WO2016099805A3 (en) 2016-10-27
EP3221643A4 (en) 2018-09-05
EP3221643A2 (en) 2017-09-27
EP3221643B1 (en) 2020-02-26
WO2016099805A2 (en) 2016-06-23
KR20170106302A (ko) 2017-09-20
CN107429920A (zh) 2017-12-01

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Effective date of registration: 20210617

Address after: London, England

Patentee after: H2 IP UK Ltd.

Address before: London, England

Patentee before: ANSALDO ENERGIA IP UK Ltd.

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