FR3071907B1 - Chambre de combustion de moteur aeronautique - Google Patents

Chambre de combustion de moteur aeronautique Download PDF

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Publication number
FR3071907B1
FR3071907B1 FR1759148A FR1759148A FR3071907B1 FR 3071907 B1 FR3071907 B1 FR 3071907B1 FR 1759148 A FR1759148 A FR 1759148A FR 1759148 A FR1759148 A FR 1759148A FR 3071907 B1 FR3071907 B1 FR 3071907B1
Authority
FR
France
Prior art keywords
combustion chamber
engine combustion
aeronautical engine
deflector
circulation
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
FR1759148A
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English (en)
Other versions
FR3071907A1 (fr
Inventor
Francois Leglaye
Alain Rene Cayre
Julien Marc Matthieu Leparoux
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
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 filed Critical Safran Aircraft Engines SAS
Priority to FR1759148A priority Critical patent/FR3071907B1/fr
Publication of FR3071907A1 publication Critical patent/FR3071907A1/fr
Application granted granted Critical
Publication of FR3071907B1 publication Critical patent/FR3071907B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/42—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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)

Abstract

L'invention concerne une chambre (9) de combustion de moteur aéronautique, qui comprend un cloisonnement (15) de la circulation d'air de refroidissement entre des orifices (124) ménagés dans un fond de chambre (116), pour assurer une circulation d'air sur une face amont du déflecteur (122) de protection thermique fixé sur ledit fond de chambre, et les bords radialement externe (122a) et radialement interne (122b) du déflecteur (122).
FR1759148A 2017-09-29 2017-09-29 Chambre de combustion de moteur aeronautique Active FR3071907B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1759148A FR3071907B1 (fr) 2017-09-29 2017-09-29 Chambre de combustion de moteur aeronautique

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1759148A FR3071907B1 (fr) 2017-09-29 2017-09-29 Chambre de combustion de moteur aeronautique
FR1759148 2017-09-29

Publications (2)

Publication Number Publication Date
FR3071907A1 FR3071907A1 (fr) 2019-04-05
FR3071907B1 true FR3071907B1 (fr) 2021-02-12

Family

ID=60382401

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1759148A Active FR3071907B1 (fr) 2017-09-29 2017-09-29 Chambre de combustion de moteur aeronautique

Country Status (1)

Country Link
FR (1) FR3071907B1 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
GB2247522B (en) * 1990-09-01 1993-11-10 Rolls Royce Plc Gas turbine engine combustor
US6487861B1 (en) * 2001-06-05 2002-12-03 General Electric Company Combustor for gas turbine engines with low air flow swirlers
DE112007002152T5 (de) * 2006-09-14 2009-07-23 Solar Turbines Inc., San Diego Prallplattenkuppelanordnung für einen Turbinenmotor
US9377198B2 (en) * 2012-01-31 2016-06-28 United Technologies Corporation Heat shield for a combustor
US20140083111A1 (en) * 2012-09-25 2014-03-27 United Technologies Corporation Gas turbine asymmetric fuel nozzle combustor

Also Published As

Publication number Publication date
FR3071907A1 (fr) 2019-04-05

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