FR2999277B1 - Paroi annulaire de chambre de combustion en aval d'un compresseur centrifuge - Google Patents

Paroi annulaire de chambre de combustion en aval d'un compresseur centrifuge Download PDF

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Publication number
FR2999277B1
FR2999277B1 FR1261796A FR1261796A FR2999277B1 FR 2999277 B1 FR2999277 B1 FR 2999277B1 FR 1261796 A FR1261796 A FR 1261796A FR 1261796 A FR1261796 A FR 1261796A FR 2999277 B1 FR2999277 B1 FR 2999277B1
Authority
FR
France
Prior art keywords
annular wall
combustion chamber
centrifugal compressor
air
cooling 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.)
Active
Application number
FR1261796A
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English (en)
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FR2999277A1 (fr
Inventor
Jean-Francois CABRE
Andre Commaret Patrice
Francois LEGLAYE
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
Safran Aircraft Engines SAS
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.)
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Publication date
Application filed by Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1261796A priority Critical patent/FR2999277B1/fr
Publication of FR2999277A1 publication Critical patent/FR2999277A1/fr
Application granted granted Critical
Publication of FR2999277B1 publication Critical patent/FR2999277B1/fr
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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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Paroi annulaire (30) d'une chambre de combustion de turbomachine disposée en aval d'un compresseur centrifuge, comportant un côté froid et un côté chaud, cette paroi annulaire comportant une pluralité de trous de refroidissement (44) chacun inclinés d'un angle d'inclinaison (β par rapport à une normale N à la paroi annulaire et répartis selon une pluralité de rangées espacées axialement les unes des autres, pour permettre à l'air circulant du côté froid de la paroi annulaire de pénétrer du côté chaud, afin de former un film d'air de refroidissement le long de cette paroi annulaire, les axes géométriques de perçage de chacun des trous de refroidissement étant orientés selon une direction d'écoulement de l'air (F2) circulant autour de la paroi annulaire, de façon à garder tout le long de la paroi annulaire une alimentation en air sensiblement axiale au travers de ces trous de refroidissement.
FR1261796A 2012-12-07 2012-12-07 Paroi annulaire de chambre de combustion en aval d'un compresseur centrifuge Active FR2999277B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1261796A FR2999277B1 (fr) 2012-12-07 2012-12-07 Paroi annulaire de chambre de combustion en aval d'un compresseur centrifuge

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1261796A FR2999277B1 (fr) 2012-12-07 2012-12-07 Paroi annulaire de chambre de combustion en aval d'un compresseur centrifuge
FR1261796 2012-12-07

Publications (2)

Publication Number Publication Date
FR2999277A1 FR2999277A1 (fr) 2014-06-13
FR2999277B1 true FR2999277B1 (fr) 2018-08-17

Family

ID=47741118

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1261796A Active FR2999277B1 (fr) 2012-12-07 2012-12-07 Paroi annulaire de chambre de combustion en aval d'un compresseur centrifuge

Country Status (1)

Country Link
FR (1) FR2999277B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10041677B2 (en) * 2015-12-17 2018-08-07 General Electric Company Combustion liner for use in a combustor assembly and method of manufacturing

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US6513331B1 (en) * 2001-08-21 2003-02-04 General Electric Company Preferential multihole combustor liner
US7546737B2 (en) * 2006-01-24 2009-06-16 Honeywell International Inc. Segmented effusion cooled gas turbine engine combustor
US7954326B2 (en) * 2007-11-28 2011-06-07 Honeywell International Inc. Systems and methods for cooling gas turbine engine transition liners

Also Published As

Publication number Publication date
FR2999277A1 (fr) 2014-06-13

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