EP3267111A3 - Paroi annulaire de chambre de combustion à refroidissement amelioré au niveau des trous primaires et/ou de dilution - Google Patents

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

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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
German (de)
English (en)
Other versions
EP3267111B1 (fr
EP3267111A2 (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
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/fr
Publication of EP3267111A3 publication Critical patent/EP3267111A3/fr
Application granted granted Critical
Publication of EP3267111B1 publication Critical patent/EP3267111B1/fr
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)

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 ou 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 θ1 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 la direction axiale D et inclinés d'un angle d'inclinaison θ2 par rapport à une normale N à la paroi annulaire, et au niveau d'une zone de transition (28B, 30B) formée en aval de la pluralité de rangées d'orifices additionnels, au moins deux rangées d'orifices dont les axes géométriques de chacun des orifices sont inclinés, par rapport à un plan perpendiculaire à la direction axiale D, d'une inclinaison déterminée différente pour chacune des deux rangées.
EP17175880.8A 2011-10-26 2012-10-25 Paroi annulaire de chambre de combustion à refroidissement amelioré au niveau des trous primaires et/ou de dilution Active EP3267111B1 (fr)

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
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
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

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP12790620.4A Division 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
EP12790620.4A Division-Into 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

Publications (3)

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

Family

ID=47221481

Family Applications (2)

Application Number Title Priority Date Filing Date
EP17175880.8A Active 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
EP12790620.4A Active 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

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP12790620.4A Active 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

Country Status (9)

Country Link
US (1) US10551064B2 (fr)
EP (2) EP3267111B1 (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
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
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10655541B2 (en) 2016-03-25 2020-05-19 General Electric Company Segmented annular combustion system
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle 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
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for 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
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of 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
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US11156362B2 (en) 2016-11-28 2021-10-26 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
US20210222879A1 (en) * 2020-01-17 2021-07-22 United Technologies 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
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
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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Also Published As

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

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