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WO2013060987A3 - Paroi annulaire de chambre de combustion à refroidissement amélioré au niveau des trous primaires et/ou de dilution - Google Patents

Paroi annulaire de chambre de combustion à refroidissement amélioré au niveau des trous primaires et/ou de dilution Download PDF

Info

Publication number
WO2013060987A3
WO2013060987A3 PCT/FR2012/052446 FR2012052446W WO2013060987A3 WO 2013060987 A3 WO2013060987 A3 WO 2013060987A3 FR 2012052446 W FR2012052446 W FR 2012052446W WO 2013060987 A3 WO2013060987 A3 WO 2013060987A3
Authority
WO
WIPO (PCT)
Prior art keywords
annular wall
cooling holes
holes
dilution
primary
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.)
Ceased
Application number
PCT/FR2012/052446
Other languages
English (en)
Other versions
WO2013060987A2 (fr
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
Turbomeca SA
SNECMA 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 Turbomeca SA, SNECMA SAS filed Critical Turbomeca SA
Priority to EP12790620.4A priority Critical patent/EP2771618B8/fr
Priority to CA2852393A priority patent/CA2852393C/fr
Priority to CN201280052210.4A priority patent/CN103958970B/zh
Priority to BR112014010215A priority patent/BR112014010215A8/pt
Priority to JP2014537695A priority patent/JP6177785B2/ja
Priority to EP17175880.8A priority patent/EP3267111B1/fr
Priority to US14/352,946 priority patent/US10551064B2/en
Priority to RU2014121037/06A priority patent/RU2575490C2/ru
Priority to IN3138DEN2014 priority patent/IN2014DN03138A/en
Publication of WO2013060987A2 publication Critical patent/WO2013060987A2/fr
Publication of WO2013060987A3 publication Critical patent/WO2013060987A3/fr
Anticipated expiration legal-status Critical
Ceased 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
    • F23R2900/03041—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)

Abstract

Paroi annulaire de chambre de combustion (10) de turbomachine, comportant un côté froid (16a, 18a) et un côté chaud (16b, 18b), une pluralité de trous primaires et de dilution (30) répartis selon une rangée circonférentielle pour permettre à de l'air circulant du côté froid (16a, 18a) de la paroi annulaire de pénétrer du côté chaud (16b, 18b) afin d'assurer la dilution d'un mélange air/carburant; et une pluralité d'orifices de refroidissement (32) pour permettre à l'air circulant du côté froid (16a, 18a) de la paroi annulaire de pénétrer du côté chaud (16b, 18b) afin de former un film d'air de refroidissement le long de la paroi annulaire, les orifices de refroidissement étant répartis selon une pluralité de rangées circonférentielles espacées axialement les unes des autres et les axes géométriques de chacun des orifices de refroidissement étant inclinés, dans une direction axiale D d'écoulement des gaz de combustion, d'un angle d'inclinaison A1 par rapport à une normale N à la paroi annulaire; La paroi comportant en outre une pluralité d'orifices additionnels de refroidissement (34) disposés directement en aval des trous de dilution et répartis selon une pluralité de rangées circonférentielles espacées axialement les unes des autres, les axes géométriques de chacun des orifices additionnels de refroidissement étant disposés dans un plan perpendiculaire à ladite direction axiale D et inclinés d'un angle d'inclinaison 82 par rapport à une normale N à ladite paroi annulaire.
PCT/FR2012/052446 2011-10-26 2012-10-25 Paroi annulaire de chambre de combustion à refroidissement amélioré au niveau des trous primaires et/ou de dilution Ceased WO2013060987A2 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP12790620.4A EP2771618B8 (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
CA2852393A CA2852393C (fr) 2011-10-26 2012-10-25 Paroi annulaire de chambre de combustion a refroidissement ameliore au niveau des trous primaires et/ou de dilution
CN201280052210.4A CN103958970B (zh) 2011-10-26 2012-10-25 涡轮机燃烧室的环形壁
BR112014010215A BR112014010215A8 (pt) 2011-10-26 2012-10-25 parede anular de câmara de combustão com resfriamento melhorado no nível dos orifícios primários e/ou de diluição
JP2014537695A JP6177785B2 (ja) 2011-10-26 2012-10-25 一次孔および／または希釈孔のレベルで冷却を改善した燃焼室の環状壁
EP17175880.8A EP3267111B1 (fr) 2011-10-26 2012-10-25 Paroi annulaire de chambre de combustion à refroidissement amelioré au niveau des trous primaires et/ou de dilution
US14/352,946 US10551064B2 (en) 2011-10-26 2012-10-25 Annular wall of a combustion chamber with improved cooling at the level of primary and/or dilution holes
RU2014121037/06A RU2575490C2 (ru) 2011-10-26 2012-10-25 Кольцевая стенка сгорания с улучшенным охлаждением на уровне первичных отверстий и/или отверстий разбавления
IN3138DEN2014 IN2014DN03138A (fr) 2011-10-26 2012-10-25

Applications Claiming Priority (2)

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
FR1159704 2011-10-26

Publications (2)

Publication Number Publication Date
WO2013060987A2 WO2013060987A2 (fr) 2013-05-02
WO2013060987A3 true WO2013060987A3 (fr) 2014-02-20

Family

ID=47221481

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2012/052446 Ceased 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

Country Status (9)

Country Link
US (1) US10551064B2 (fr)
EP (2) EP2771618B8 (fr)
JP (1) JP6177785B2 (fr)
CN (2) CN203147824U (fr)
BR (1) BR112014010215A8 (fr)
CA (1) CA2852393C (fr)
FR (1) FR2982008B1 (fr)
IN (1) IN2014DN03138A (fr)
WO (1) WO2013060987A2 (fr)

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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
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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
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
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
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10655541B2 (en) 2016-03-25 2020-05-19 General Electric Company Segmented annular combustion system
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
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
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
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
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
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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
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Also Published As

Publication number Publication date
EP3267111B1 (fr) 2022-02-16
JP2014531015A (ja) 2014-11-20
JP6177785B2 (ja) 2017-08-09
BR112014010215A2 (pt) 2017-06-13
CA2852393A1 (fr) 2013-05-02
CA2852393C (fr) 2020-08-04
IN2014DN03138A (fr) 2015-05-22
EP3267111A2 (fr) 2018-01-10
CN203147824U (zh) 2013-08-21
US10551064B2 (en) 2020-02-04
EP2771618B8 (fr) 2017-08-16
EP2771618B1 (fr) 2017-06-14
US20140260257A1 (en) 2014-09-18
FR2982008B1 (fr) 2013-12-13
EP2771618A2 (fr) 2014-09-03
WO2013060987A2 (fr) 2013-05-02
FR2982008A1 (fr) 2013-05-03
CN103958970B (zh) 2016-08-24
RU2014121037A (ru) 2015-12-10
EP3267111A3 (fr) 2018-02-28
BR112014010215A8 (pt) 2017-06-20
CN103958970A (zh) 2014-07-30

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