FR3015010B1 - Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif - Google Patents

Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif

Info

Publication number
FR3015010B1
FR3015010B1 FR1362504A FR1362504A FR3015010B1 FR 3015010 B1 FR3015010 B1 FR 3015010B1 FR 1362504 A FR1362504 A FR 1362504A FR 1362504 A FR1362504 A FR 1362504A FR 3015010 B1 FR3015010 B1 FR 3015010B1
Authority
FR
France
Prior art keywords
cooling orifices
combustion chamber
contra
annular wall
cooling
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.)
Active
Application number
FR1362504A
Other languages
English (en)
Other versions
FR3015010A1 (fr
Inventor
Francois Leglaye
Patrick Lutz
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
Original Assignee
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1362504A priority Critical patent/FR3015010B1/fr
Priority to US14/564,588 priority patent/US20150167977A1/en
Priority to CN201420780003.7U priority patent/CN204460286U/zh
Priority to GB1422165.9A priority patent/GB2522769A/en
Publication of FR3015010A1 publication Critical patent/FR3015010A1/fr
Application granted granted Critical
Publication of FR3015010B1 publication Critical patent/FR3015010B1/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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • 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
    • 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
    • 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)

Abstract

Il est proposé une paroi annulaire (14) pour chambre de combustion de turbomachine, comprenant des orifices de refroidissement (40) destinés à permettre la circulation d'air de refroidissement au travers de la paroi annulaire et présentant chacun un axe d'injection d'air (42) orienté orthogonalement à un axe longitudinal (18) de la paroi annulaire. Les orifices de refroidissement se répartissent en des premières rangées annulaires (44) d'orifices de refroidissement orientés dans une première direction circonférentielle (C1) depuis une face extérieure (46) jusqu'à une face intérieure (48) de la paroi annulaire, et en des deuxièmes rangées annulaires (50) d'orifices de refroidissement orientés dans une seconde direction circonférentielle (C2) opposée à la première direction circonférentielle depuis la face extérieure jusqu'à la face intérieure de la paroi annulaire.
FR1362504A 2013-12-12 2013-12-12 Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif Active FR3015010B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR1362504A FR3015010B1 (fr) 2013-12-12 2013-12-12 Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif
US14/564,588 US20150167977A1 (en) 2013-12-12 2014-12-09 Annular wall for turbomachine combustion chamber comprising cooling orifices conducive to counter-rotation
CN201420780003.7U CN204460286U (zh) 2013-12-12 2014-12-11 用于涡轮机燃烧室的环形壁,用于涡轮机的环形燃烧室和涡轮机
GB1422165.9A GB2522769A (en) 2013-12-12 2014-12-12 Annular wall for turbomachine combustion chamber comprising cooling orifices conducive to counter-rotation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1362504A FR3015010B1 (fr) 2013-12-12 2013-12-12 Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif

Publications (2)

Publication Number Publication Date
FR3015010A1 FR3015010A1 (fr) 2015-06-19
FR3015010B1 true FR3015010B1 (fr) 2016-01-22

Family

ID=50137864

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1362504A Active FR3015010B1 (fr) 2013-12-12 2013-12-12 Paroi annulaire pour chambre de combustion de turbomachine comprenant des orifices de refroidissement a effet contra-rotatif

Country Status (4)

Country Link
US (1) US20150167977A1 (fr)
CN (1) CN204460286U (fr)
FR (1) FR3015010B1 (fr)
GB (1) GB2522769A (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10352244B2 (en) * 2014-04-25 2019-07-16 Mitsubishi Hitachi Power Systems, Ltd. Combustor cooling structure
GB201514390D0 (en) * 2015-08-13 2015-09-30 Rolls Royce Plc A combustion chamber and a combustion chamber segment
US10041677B2 (en) 2015-12-17 2018-08-07 General Electric Company Combustion liner for use in a combustor assembly and method of manufacturing
CN111911962A (zh) * 2020-08-18 2020-11-10 西北工业大学 一种新型火焰筒壁面冷却结构

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
FR2714154B1 (fr) * 1993-12-22 1996-01-19 Snecma Chambre de combustion comportant une paroi munie d'une multiperforation.
US6408629B1 (en) * 2000-10-03 2002-06-25 General Electric Company Combustor liner having preferentially angled cooling holes
US7146816B2 (en) * 2004-08-16 2006-12-12 Honeywell International, Inc. Effusion momentum control
US20060037323A1 (en) * 2004-08-20 2006-02-23 Honeywell International Inc., Film effectiveness enhancement using tangential effusion
US7628020B2 (en) * 2006-05-26 2009-12-08 Pratt & Whitney Canada Cororation Combustor with improved swirl
US7942006B2 (en) * 2007-03-26 2011-05-17 Honeywell International Inc. Combustors and combustion systems for gas turbine engines
JP5923936B2 (ja) * 2011-11-09 2016-05-25 株式会社Ihi フィルム冷却構造及びタービン翼

Also Published As

Publication number Publication date
CN204460286U (zh) 2015-07-08
GB2522769A (en) 2015-08-05
US20150167977A1 (en) 2015-06-18
FR3015010A1 (fr) 2015-06-19

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