CA2685342A1 - Cooling holes for gas turbine combustor liner having a non-uniform diameter therethrough - Google Patents

Cooling holes for gas turbine combustor liner having a non-uniform diameter therethrough Download PDF

Info

Publication number
CA2685342A1
CA2685342A1 CA002685342A CA2685342A CA2685342A1 CA 2685342 A1 CA2685342 A1 CA 2685342A1 CA 002685342 A CA002685342 A CA 002685342A CA 2685342 A CA2685342 A CA 2685342A CA 2685342 A1 CA2685342 A1 CA 2685342A1
Authority
CA
Canada
Prior art keywords
shell
liner
cooling
diameter
combustor
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.)
Abandoned
Application number
CA002685342A
Other languages
English (en)
French (fr)
Inventor
Marie Ann Mcmasters
David Louis Burrus
George Chia-Chun Hsiao
Hongtao Zhang
Hukam Chand Mongia
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
Individual
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 Individual filed Critical Individual
Publication of CA2685342A1 publication Critical patent/CA2685342A1/en
Abandoned legal-status Critical Current

Links

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
    • F23R3/02—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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

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)
CA002685342A 2007-05-01 2008-03-04 Cooling holes for gas turbine combustor liner having a non-uniform diameter therethrough Abandoned CA2685342A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US11/743,126 2007-05-01
US11/743,126 US20080271457A1 (en) 2007-05-01 2007-05-01 Cooling Holes For Gas Turbine Combustor Having A Non-Uniform Diameter Therethrough
PCT/US2008/055758 WO2008137201A1 (en) 2007-05-01 2008-03-04 Cooling holes for gas turbine combustor liner having a non-uniform diameter therethrough

Publications (1)

Publication Number Publication Date
CA2685342A1 true CA2685342A1 (en) 2008-11-13

Family

ID=39645559

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002685342A Abandoned CA2685342A1 (en) 2007-05-01 2008-03-04 Cooling holes for gas turbine combustor liner having a non-uniform diameter therethrough

Country Status (5)

Country Link
US (1) US20080271457A1 (enExample)
EP (1) EP2153133A1 (enExample)
JP (1) JP2010526274A (enExample)
CA (1) CA2685342A1 (enExample)
WO (1) WO2008137201A1 (enExample)

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DE102009007164A1 (de) * 2009-02-03 2010-08-12 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zum Ausbilden einer Kühlluftöffnung in einer Wand einer Gasturbinenbrennkammer sowie nach dem Verfahren hergestellte Brennkammerwand
US8307657B2 (en) * 2009-03-10 2012-11-13 General Electric Company Combustor liner cooling system
US20100263384A1 (en) * 2009-04-17 2010-10-21 Ronald James Chila Combustor cap with shaped effusion cooling holes
US8371814B2 (en) * 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
US8529193B2 (en) * 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US9052113B1 (en) * 2011-06-06 2015-06-09 General Electric Company Combustor nozzle and method for modifying the combustor nozzle
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
US9194585B2 (en) * 2012-10-04 2015-11-24 United Technologies Corporation Cooling for combustor liners with accelerating channels
US9309809B2 (en) * 2013-01-23 2016-04-12 General Electric Company Effusion plate using additive manufacturing methods
WO2014126619A1 (en) * 2013-02-14 2014-08-21 United Technologies Corporation Combustor liners with u-shaped cooling channels
JP6438000B2 (ja) * 2013-03-15 2018-12-19 プレジデント アンド フェローズ オブ ハーバード カレッジ 低孔隙率オーゼティックシート
US11112115B2 (en) * 2013-08-30 2021-09-07 Raytheon Technologies Corporation Contoured dilution passages for gas turbine engine combustor
EP3066388B1 (en) * 2013-11-04 2024-04-10 RTX Corporation Turbine engine combustor heat shield with multi-angled cooling apertures
US10190773B2 (en) * 2013-11-05 2019-01-29 United Technologies Corporation Attachment stud on a combustor floatwall panel with internal cooling holes
US10359194B2 (en) * 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
GB201419327D0 (en) 2014-10-30 2014-12-17 Rolls Royce Plc A cooled component
US20160258623A1 (en) * 2015-03-05 2016-09-08 United Technologies Corporation Combustor and heat shield configurations for a gas turbine engine
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US20180266687A1 (en) * 2017-03-16 2018-09-20 General Electric Company Reducing film scrubbing in a combustor
US11149948B2 (en) * 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
US11022307B2 (en) * 2018-02-22 2021-06-01 Raytheon Technology Corporation Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
US11306659B2 (en) 2019-05-28 2022-04-19 Honeywell International Inc. Plug resistant effusion holes for gas turbine engine
US11371701B1 (en) 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
US11885495B2 (en) 2021-06-07 2024-01-30 General Electric Company Combustor for a gas turbine engine including a liner having a looped feature
US11959643B2 (en) 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
US11774098B2 (en) 2021-06-07 2023-10-03 General Electric Company Combustor for a gas turbine engine
US12152777B2 (en) 2021-06-07 2024-11-26 General Electric Company Combustor for a gas turbine engine
US12146660B2 (en) 2021-06-07 2024-11-19 General Electric Company Combustor for a gas turbine engine
US12085283B2 (en) 2021-06-07 2024-09-10 General Electric Company Combustor for a gas turbine engine
CN115493163B (zh) * 2022-09-06 2024-02-20 清华大学 燃烧室火焰筒及燃烧室火焰筒高效冷却方法
JP2025101969A (ja) * 2023-12-26 2025-07-08 三菱重工業株式会社 燃焼器及びガスタービン

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2221979B (en) * 1988-08-17 1992-03-25 Rolls Royce Plc A combustion chamber for a gas turbine engine
US5660525A (en) * 1992-10-29 1997-08-26 General Electric Company Film cooled slotted wall
US5528904A (en) * 1994-02-28 1996-06-25 Jones; Charles R. Coated hot gas duct liner
JPH09119322A (ja) * 1995-10-27 1997-05-06 Ishikawajima Harima Heavy Ind Co Ltd 航空機エンジンの冷却ライナ
US6383602B1 (en) * 1996-12-23 2002-05-07 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream which flows through a substrate, and related articles of manufacture
DE59808269D1 (de) * 1998-03-23 2003-06-12 Alstom Switzerland Ltd Filmkühlungsbohrung
CA2288557C (en) * 1998-11-12 2007-02-06 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor cooling structure
US6408629B1 (en) * 2000-10-03 2002-06-25 General Electric Company Combustor liner having preferentially angled cooling holes
US7093439B2 (en) * 2002-05-16 2006-08-22 United Technologies Corporation Heat shield panels for use in a combustor for a gas turbine engine
US7328580B2 (en) * 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
JP4898253B2 (ja) * 2005-03-30 2012-03-14 三菱重工業株式会社 ガスタービン用高温部材
EP1712739A1 (de) * 2005-04-12 2006-10-18 Siemens Aktiengesellschaft Bauteil mit Filmkühlloch

Also Published As

Publication number Publication date
US20080271457A1 (en) 2008-11-06
JP2010526274A (ja) 2010-07-29
EP2153133A1 (en) 2010-02-17
WO2008137201A1 (en) 2008-11-13

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Legal Events

Date Code Title Description
EEER Examination request

Effective date: 20130117

FZDE Discontinued

Effective date: 20150427