CN100529543C - 用于气体涡轮发动机燃烧室的环型整体的波纹衬套 - Google Patents

用于气体涡轮发动机燃烧室的环型整体的波纹衬套 Download PDF

Info

Publication number
CN100529543C
CN100529543C CNB031105769A CN03110576A CN100529543C CN 100529543 C CN100529543 C CN 100529543C CN B031105769 A CNB031105769 A CN B031105769A CN 03110576 A CN03110576 A CN 03110576A CN 100529543 C CN100529543 C CN 100529543C
Authority
CN
China
Prior art keywords
bushing
adjacent
corrugations
wavelength
amplitude
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
Application number
CNB031105769A
Other languages
English (en)
Chinese (zh)
Other versions
CN1450304A (zh
Inventor
G·法默
S·M·德瓦尼
J·L·范迪克
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.)
General Electric Co
Original Assignee
General Electric Co
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
Application filed by General Electric Co filed Critical General Electric Co
Publication of CN1450304A publication Critical patent/CN1450304A/zh
Application granted granted Critical
Publication of CN100529543C publication Critical patent/CN100529543C/zh
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
CNB031105769A 2002-04-10 2003-04-10 用于气体涡轮发动机燃烧室的环型整体的波纹衬套 Expired - Lifetime CN100529543C (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/119649 2002-04-10
US10/119,649 US6655147B2 (en) 2002-04-10 2002-04-10 Annular one-piece corrugated liner for combustor of a gas turbine engine

Publications (2)

Publication Number Publication Date
CN1450304A CN1450304A (zh) 2003-10-22
CN100529543C true CN100529543C (zh) 2009-08-19

Family

ID=28453992

Family Applications (1)

Application Number Title Priority Date Filing Date
CNB031105769A Expired - Lifetime CN100529543C (zh) 2002-04-10 2003-04-10 用于气体涡轮发动机燃烧室的环型整体的波纹衬套

Country Status (5)

Country Link
US (1) US6655147B2 (enExample)
EP (1) EP1353127B1 (enExample)
JP (1) JP4256709B2 (enExample)
CN (1) CN100529543C (enExample)
DE (1) DE60334172D1 (enExample)

Families Citing this family (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1312865A1 (de) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Ringbrennkammer für eine Gasturbine
US6725667B2 (en) * 2002-08-22 2004-04-27 General Electric Company Combustor dome for gas turbine engine
US6779268B1 (en) * 2003-05-13 2004-08-24 General Electric Company Outer and inner cowl-wire wrap to one piece cowl conversion
FR2867507B1 (fr) * 2004-03-15 2006-06-23 Snecma Moteurs Pontet de positionnement et son utilisation au canal support de tuyere d'un turbopropulseur
US8015818B2 (en) * 2005-02-22 2011-09-13 Siemens Energy, Inc. Cooled transition duct for a gas turbine engine
US7976274B2 (en) * 2005-12-08 2011-07-12 General Electric Company Methods and apparatus for assembling turbine engines
DE102005060704A1 (de) * 2005-12-19 2007-06-28 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer
US7908867B2 (en) * 2007-09-14 2011-03-22 Siemens Energy, Inc. Wavy CMC wall hybrid ceramic apparatus
US8202588B2 (en) * 2008-04-08 2012-06-19 Siemens Energy, Inc. Hybrid ceramic structure with internal cooling arrangements
US8327648B2 (en) * 2008-12-09 2012-12-11 Pratt & Whitney Canada Corp. Combustor liner with integrated anti-rotation and removal feature
US8904799B2 (en) * 2009-05-25 2014-12-09 Majed Toqan Tangential combustor with vaneless turbine for use on gas turbine engines
US8327644B2 (en) * 2009-11-06 2012-12-11 Jhrg Inc. Micro-turbine combustor
US8707708B2 (en) * 2010-02-22 2014-04-29 United Technologies Corporation 3D non-axisymmetric combustor liner
RU2530685C2 (ru) * 2010-03-25 2014-10-10 Дженерал Электрик Компани Структуры ударного воздействия для систем охлаждения
US20120208141A1 (en) * 2011-02-14 2012-08-16 General Electric Company Combustor
EP2788685B1 (en) * 2011-12-05 2020-03-11 General Electric Company Multi-zone combustor
US8960525B2 (en) * 2013-01-31 2015-02-24 General Electric Company Brazing process and plate assembly
WO2014123850A1 (en) 2013-02-06 2014-08-14 United Technologies Corporation Gas turbine engine component with upstream-directed cooling film holes
WO2014189556A2 (en) 2013-02-08 2014-11-27 United Technologies Corporation Gas turbine engine combustor liner assembly with convergent hyperbolic profile
US10914470B2 (en) 2013-03-14 2021-02-09 Raytheon Technologies Corporation Combustor panel with increased durability
EP3044511B1 (en) 2013-09-11 2021-10-06 Raytheon Technologies Corporation Combustor, gas turbine engine comprising such a combustor, and method
EP3037728B1 (en) * 2014-12-22 2020-04-29 Ansaldo Energia Switzerland AG Axially staged mixer with dilution air injection
CN104896514A (zh) * 2015-05-13 2015-09-09 广东电网有限责任公司电力科学研究院 燃气轮机主燃烧室防振隔热壁
CN105605605A (zh) * 2016-01-25 2016-05-25 西北工业大学 一种地面燃机燃烧室的防振冷却壁
US10495309B2 (en) * 2016-02-12 2019-12-03 General Electric Company Surface contouring of a flowpath wall of a gas turbine engine
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10641175B2 (en) 2016-03-25 2020-05-05 General Electric Company Panel fuel injector
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for 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
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of 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
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
US10738646B2 (en) 2017-06-12 2020-08-11 Raytheon Technologies Corporation Geared turbine engine with gear driving low pressure compressor and fan at common speed, and failsafe overspeed protection and shear section
US10612555B2 (en) 2017-06-16 2020-04-07 United Technologies Corporation Geared turbofan with overspeed protection
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
CN116928696A (zh) * 2022-03-31 2023-10-24 通用电气公司 用于燃烧器的衬套组件
US11898755B2 (en) 2022-06-08 2024-02-13 General Electric Company Combustor with a variable volume primary zone combustion chamber
US11835236B1 (en) 2022-07-05 2023-12-05 General Electric Company Combustor with reverse dilution air introduction
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages
CN117366623B (zh) * 2023-10-18 2025-08-29 哈电发电设备国家工程研究中心有限公司 一种燃气轮机燃烧室导流衬套

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3398527A (en) * 1966-05-31 1968-08-27 Air Force Usa Corrugated wall radiation cooled combustion chamber
US4833881A (en) * 1984-12-17 1989-05-30 General Electric Company Gas turbine engine augmentor
US4696431A (en) * 1985-11-29 1987-09-29 United Technologies Corporation Augmentor liner support band having finger positioners
US4930729A (en) * 1986-05-22 1990-06-05 Rolls-Royce Plc Control of fluid flow
US5181379A (en) * 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
US5233828A (en) 1990-11-15 1993-08-10 General Electric Company Combustor liner with circumferentially angled film cooling holes
CA2056592A1 (en) 1990-12-21 1992-06-22 Phillip D. Napoli Multi-hole film cooled combustor liner with slotted film starter
GB9127505D0 (en) 1991-03-11 2013-12-25 Gen Electric Multi-hole film cooled afterburner combustor liner
JP2597800B2 (ja) * 1992-06-12 1997-04-09 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン用燃焼器
US5363654A (en) 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US5460002A (en) 1993-05-21 1995-10-24 General Electric Company Catalytically-and aerodynamically-assisted liner for gas turbine combustors
FR2716933B1 (fr) * 1994-03-03 1996-04-05 Snecma Elément de chemise de protection thermique pour turbomachine et ses procédés de fabrication.

Also Published As

Publication number Publication date
EP1353127B1 (en) 2010-09-15
JP2003329245A (ja) 2003-11-19
EP1353127A2 (en) 2003-10-15
JP4256709B2 (ja) 2009-04-22
CN1450304A (zh) 2003-10-22
EP1353127A3 (en) 2005-01-12
US6655147B2 (en) 2003-12-02
DE60334172D1 (de) 2010-10-28
US20030192320A1 (en) 2003-10-16

Similar Documents

Publication Publication Date Title
CN100529543C (zh) 用于气体涡轮发动机燃烧室的环型整体的波纹衬套
US6568187B1 (en) Effusion cooled transition duct
US6725667B2 (en) Combustor dome for gas turbine engine
US6705087B1 (en) Swirler assembly with improved vibrational response
US5197289A (en) Double dome combustor
US6761031B2 (en) Double wall combustor liner segment with enhanced cooling
JP2593596B2 (ja) ガスタービンエンジン燃焼器用のドームアセンブリ
EP0378505B1 (en) Combustor fuel nozzle arrangement
US8646277B2 (en) Combustor liner for a turbine engine with venturi and air deflector
CN103672971B (zh) 用于燃烧器的声音阻尼器布置
CN1441198B (zh) 用于燃气涡轮发动机燃烧器的波纹式壳体及其成形方法
US20080271457A1 (en) Cooling Holes For Gas Turbine Combustor Having A Non-Uniform Diameter Therethrough
US6851263B2 (en) Liner for a gas turbine engine combustor having trapped vortex cavity
EP1156281A3 (en) Gas turbine combustor
JPS59119116A (ja) 燃焼器ライナ
JPH0423170B2 (enExample)
US20120208141A1 (en) Combustor
US7222488B2 (en) Fabricated cowl for double annular combustor of a gas turbine engine
EP1426558A2 (en) Gas turbine transition piece with dimpled surface and cooling method for such a transition piece
WO2013143627A1 (en) An improved hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions
US7559203B2 (en) Cooled support boss for a combustor in a gas turbine engine
US7578134B2 (en) Methods and apparatus for assembling gas turbine engines
US11828194B2 (en) Nozzle blade for a turbine engine, nozzle, turbine engine and method for manufacturing same

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
CX01 Expiry of patent term
CX01 Expiry of patent term

Granted publication date: 20090819