FR2942640B1 - Chambre de post-combustion pour turbomachine - Google Patents

Chambre de post-combustion pour turbomachine

Info

Publication number
FR2942640B1
FR2942640B1 FR0900932A FR0900932A FR2942640B1 FR 2942640 B1 FR2942640 B1 FR 2942640B1 FR 0900932 A FR0900932 A FR 0900932A FR 0900932 A FR0900932 A FR 0900932A FR 2942640 B1 FR2942640 B1 FR 2942640B1
Authority
FR
France
Prior art keywords
turbomachine
post
combustion chamber
combustion
chamber
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
FR0900932A
Other languages
English (en)
Other versions
FR2942640A1 (fr
Inventor
Dominique Maurice Jacques Lains
Nicolas Christian Raymond Leblond
Denis Jean Maurice Sandelis
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 FR0900932A priority Critical patent/FR2942640B1/fr
Priority to US12/694,622 priority patent/US8490402B2/en
Publication of FR2942640A1 publication Critical patent/FR2942640A1/fr
Application granted granted Critical
Publication of FR2942640B1 publication Critical patent/FR2942640B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2207/00—Ignition devices associated with burner
    • 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)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Processes For Solid Components From Exhaust (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
FR0900932A 2009-03-02 2009-03-02 Chambre de post-combustion pour turbomachine Active FR2942640B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR0900932A FR2942640B1 (fr) 2009-03-02 2009-03-02 Chambre de post-combustion pour turbomachine
US12/694,622 US8490402B2 (en) 2009-03-02 2010-01-27 Afterburner chamber for a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0900932A FR2942640B1 (fr) 2009-03-02 2009-03-02 Chambre de post-combustion pour turbomachine

Publications (2)

Publication Number Publication Date
FR2942640A1 FR2942640A1 (fr) 2010-09-03
FR2942640B1 true FR2942640B1 (fr) 2011-05-06

Family

ID=41112638

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0900932A Active FR2942640B1 (fr) 2009-03-02 2009-03-02 Chambre de post-combustion pour turbomachine

Country Status (2)

Country Link
US (1) US8490402B2 (fr)
FR (1) FR2942640B1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2994712B1 (fr) * 2012-08-27 2018-04-13 Safran Aircraft Engines Procede d'assemblage d'une tuyere et d'un carter d'echappement d'une turbomachine
FR3085435B1 (fr) * 2018-09-05 2021-06-18 Safran Aircraft Engines Turbomachine a double flux
FR3097298B1 (fr) 2019-06-12 2021-06-04 Safran Aircraft Engines Bougie intégrée au bras accroche-flamme
GB202006964D0 (en) * 2020-05-12 2020-06-24 Rolls Royce Plc Afterburner strut with integrated fueld feed lines
GB2582529B (en) * 2020-06-25 2021-03-24 Qureshi Sarah A supersonic turbofan engine
GB2615335B (en) * 2022-02-04 2024-05-08 Rolls Royce Plc A reheat assembly
CN115200043B (zh) * 2022-07-21 2023-08-04 中国航发沈阳发动机研究所 一种环形稳定器点火加力燃烧室

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2696502B1 (fr) * 1992-10-07 1994-11-04 Snecma Dispositif de post-combustion pour turbo réacteur double flux.
FR2866675B1 (fr) * 2004-02-24 2008-05-16 Snecma Moteurs Procede d'amelioration des performances d'allumage de dispositif de post-combustion pour turboreacteur double flux et dispositif de post-combustion a performance d'allumage amelioree
FR2873168B1 (fr) * 2004-07-16 2008-10-31 Snecma Moteurs Sa Turboreacteur comprenant une chambre de post-combustion a allumage securise
FR2873408B1 (fr) * 2004-07-23 2008-10-17 Snecma Moteurs Sa Turboreacteur avec un ecran de protection de la rampe de carburant d'un anneau bruleur, l'anneau bruleur et l'ecran de protection
FR2899280B1 (fr) * 2006-03-30 2012-08-31 Snecma Dispositif de montage d'une paroi de separation de flux dans une chambre de post-combustion d'un turboreacteur
US7581398B2 (en) * 2006-06-29 2009-09-01 General Electric Company Purged flameholder fuel shield

Also Published As

Publication number Publication date
US8490402B2 (en) 2013-07-23
FR2942640A1 (fr) 2010-09-03
US20100218505A1 (en) 2010-09-02

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