EP3267111A3 - Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern - Google Patents

Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern Download PDF

Info

Publication number
EP3267111A3
EP3267111A3 EP17175880.8A EP17175880A EP3267111A3 EP 3267111 A3 EP3267111 A3 EP 3267111A3 EP 17175880 A EP17175880 A EP 17175880A EP 3267111 A3 EP3267111 A3 EP 3267111A3
Authority
EP
European Patent Office
Prior art keywords
annular wall
orifices
rows
cooling
dilution holes
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.)
Granted
Application number
EP17175880.8A
Other languages
English (en)
French (fr)
Other versions
EP3267111A2 (de
EP3267111B1 (de
Inventor
Matthieu François RULLAUD
Bernard Joseph Jean-Pierre Carrere
Hubert Pascal Verdier
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.)
Safran Aircraft Engines SAS
Safran Helicopter Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Safran Helicopter Engines SAS
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 Safran Aircraft Engines SAS, Safran Helicopter Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3267111A2 publication Critical patent/EP3267111A2/de
Publication of EP3267111A3 publication Critical patent/EP3267111A3/de
Application granted granted Critical
Publication of EP3267111B1 publication Critical patent/EP3267111B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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

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)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
EP17175880.8A 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern Active EP3267111B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1159704A FR2982008B1 (fr) 2011-10-26 2011-10-26 Paroi annulaire de chambre de combustion a refroidissement ameliore au niveau des trous primaires et de dilution
PCT/FR2012/052446 WO2013060987A2 (fr) 2011-10-26 2012-10-25 Paroi annulaire de chambre de combustion à refroidissement amélioré au niveau des trous primaires et/ou de dilution
EP12790620.4A EP2771618B8 (de) 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP12790620.4A Division-Into EP2771618B8 (de) 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern
EP12790620.4A Division EP2771618B8 (de) 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern

Publications (3)

Publication Number Publication Date
EP3267111A2 EP3267111A2 (de) 2018-01-10
EP3267111A3 true EP3267111A3 (de) 2018-02-28
EP3267111B1 EP3267111B1 (de) 2022-02-16

Family

ID=47221481

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12790620.4A Active EP2771618B8 (de) 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern
EP17175880.8A Active EP3267111B1 (de) 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP12790620.4A Active EP2771618B8 (de) 2011-10-26 2012-10-25 Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern

Country Status (9)

Country Link
US (1) US10551064B2 (de)
EP (2) EP2771618B8 (de)
JP (1) JP6177785B2 (de)
CN (2) CN103958970B (de)
BR (1) BR112014010215A8 (de)
CA (1) CA2852393C (de)
FR (1) FR2982008B1 (de)
IN (1) IN2014DN03138A (de)
WO (1) WO2013060987A2 (de)

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FR2982008B1 (fr) * 2011-10-26 2013-12-13 Snecma Paroi annulaire de chambre de combustion a refroidissement ameliore au niveau des trous primaires et de dilution
US9127843B2 (en) * 2013-03-12 2015-09-08 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
FR3019270B1 (fr) * 2014-03-31 2016-04-15 Snecma Paroi annulaire de chambre de combustion a orifices de refroidissement ameliores au niveau des jonctions brides
CN104791848A (zh) * 2014-11-25 2015-07-22 西北工业大学 一种采用叶栅通道多斜孔冷却方式的燃烧室火焰筒壁面
US20160258623A1 (en) * 2015-03-05 2016-09-08 United Technologies Corporation Combustor and heat shield configurations for a gas turbine engine
FR3037107B1 (fr) * 2015-06-03 2019-11-15 Safran Aircraft Engines Paroi annulaire de chambre de combustion a refroidissement optimise
US10520193B2 (en) 2015-10-28 2019-12-31 General Electric Company Cooling patch for hot gas path components
US10041677B2 (en) * 2015-12-17 2018-08-07 General Electric Company Combustion liner for use in a combustor assembly and method of manufacturing
JP6026028B1 (ja) * 2016-03-10 2016-11-16 三菱日立パワーシステムズ株式会社 燃焼器用パネル、燃焼器、燃焼装置、ガスタービン、及び燃焼器用パネルの冷却方法
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10641176B2 (en) 2016-03-25 2020-05-05 General Electric Company Combustion system with panel fuel injector
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a 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
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
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in 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
US10337738B2 (en) * 2016-06-22 2019-07-02 General Electric Company Combustor assembly for a turbine engine
CN106247402B (zh) * 2016-08-12 2019-04-23 中国航空工业集团公司沈阳发动机设计研究所 一种火焰筒
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
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
US10890327B2 (en) 2018-02-14 2021-01-12 General Electric Company Liner of a gas turbine engine combustor including dilution holes with airflow features
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11029027B2 (en) 2018-10-03 2021-06-08 Raytheon Technologies Corporation Dilution/effusion hole pattern for thick combustor panels
FR3090746B1 (fr) * 2018-12-20 2021-06-11 Safran Aircraft Engines Tuyere de post combustion comportant une chemise a perforation obliques
FR3098569B1 (fr) 2019-07-10 2021-07-16 Safran Aircraft Engines Paroi annulaire pour chambre de combustion de turbomachine comprenant des trous primaires, des trous de dilution et des orifices de refroidissement inclines
US12247738B2 (en) * 2020-01-17 2025-03-11 Rtx Corporation Convection cooling at low effusion density region of combustor panel
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
CN112607040A (zh) * 2020-12-31 2021-04-06 西北工业大学 一种用以飞行器高温部件的壁面交错斜孔射流冷却技术
US11774100B2 (en) * 2022-01-14 2023-10-03 General Electric Company Combustor fuel nozzle assembly
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

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US20070084219A1 (en) * 2005-10-18 2007-04-19 Snecma Performance of a combustion chamber by multiple wall perforations
US20070169484A1 (en) * 2006-01-24 2007-07-26 Honeywell International, Inc. Segmented effusion cooled gas turbine engine combustor
US20090084110A1 (en) * 2007-09-28 2009-04-02 Honeywell International, Inc. Combustor systems with liners having improved cooling hole patterns
US20110023495A1 (en) * 2009-07-30 2011-02-03 Honeywell International Inc. Effusion cooled dual wall gas turbine combustors

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US5289686A (en) * 1992-11-12 1994-03-01 General Motors Corporation Low nox gas turbine combustor liner with elliptical apertures for air swirling
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US6408629B1 (en) * 2000-10-03 2002-06-25 General Electric Company Combustor liner having preferentially angled cooling holes
US6513331B1 (en) * 2001-08-21 2003-02-04 General Electric Company Preferential multihole combustor liner
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JP2004257335A (ja) * 2003-02-27 2004-09-16 Kawasaki Heavy Ind Ltd ポーラス金属を用いたガスタービン部品及びその製造方法
US7216485B2 (en) * 2004-09-03 2007-05-15 General Electric Company Adjusting airflow in turbine component by depositing overlay metallic coating
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US7669422B2 (en) * 2006-07-26 2010-03-02 General Electric Company Combustor liner and method of fabricating same
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US8104288B2 (en) * 2008-09-25 2012-01-31 Honeywell International Inc. Effusion cooling techniques for combustors in engine assemblies
FR2982008B1 (fr) * 2011-10-26 2013-12-13 Snecma Paroi annulaire de chambre de combustion a refroidissement ameliore au niveau des trous primaires et de dilution

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070084219A1 (en) * 2005-10-18 2007-04-19 Snecma Performance of a combustion chamber by multiple wall perforations
US20070169484A1 (en) * 2006-01-24 2007-07-26 Honeywell International, Inc. Segmented effusion cooled gas turbine engine combustor
US20090084110A1 (en) * 2007-09-28 2009-04-02 Honeywell International, Inc. Combustor systems with liners having improved cooling hole patterns
US20110023495A1 (en) * 2009-07-30 2011-02-03 Honeywell International Inc. Effusion cooled dual wall gas turbine combustors

Also Published As

Publication number Publication date
JP6177785B2 (ja) 2017-08-09
EP2771618B8 (de) 2017-08-16
US10551064B2 (en) 2020-02-04
US20140260257A1 (en) 2014-09-18
EP2771618B1 (de) 2017-06-14
RU2014121037A (ru) 2015-12-10
CA2852393A1 (fr) 2013-05-02
BR112014010215A2 (pt) 2017-06-13
WO2013060987A2 (fr) 2013-05-02
JP2014531015A (ja) 2014-11-20
CN203147824U (zh) 2013-08-21
CA2852393C (fr) 2020-08-04
BR112014010215A8 (pt) 2017-06-20
EP3267111A2 (de) 2018-01-10
CN103958970B (zh) 2016-08-24
FR2982008A1 (fr) 2013-05-03
FR2982008B1 (fr) 2013-12-13
IN2014DN03138A (de) 2015-05-22
EP2771618A2 (de) 2014-09-03
EP3267111B1 (de) 2022-02-16
WO2013060987A3 (fr) 2014-02-20
CN103958970A (zh) 2014-07-30

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