FR2406075A1 - COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS - Google Patents

COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS

Info

Publication number
FR2406075A1
FR2406075A1 FR7730487A FR7730487A FR2406075A1 FR 2406075 A1 FR2406075 A1 FR 2406075A1 FR 7730487 A FR7730487 A FR 7730487A FR 7730487 A FR7730487 A FR 7730487A FR 2406075 A1 FR2406075 A1 FR 2406075A1
Authority
FR
France
Prior art keywords
channel
perforations
frustoconical
combustion apparatus
downstream
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
FR7730487A
Other languages
French (fr)
Other versions
FR2406075B1 (en
Inventor
Jacques Emile Jules Caruel
Marc Francois Bernard Buisson
Simone Coutor
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 FR7730487A priority Critical patent/FR2406075A1/en
Priority to GB7840058A priority patent/GB2009859B/en
Priority to DE2844349A priority patent/DE2844349C2/en
Publication of FR2406075A1 publication Critical patent/FR2406075A1/en
Application granted granted Critical
Publication of FR2406075B1 publication Critical patent/FR2406075B1/fr
Granted legal-status Critical Current

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
    • F23R3/02—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
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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
    • 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)
  • Extrusion Moulding Of Plastics Or The Like (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

La présente invention concerne un appareil de combustion pour moteurs à turbine à gaz. Cet appareil de combustion est formé d'un canal 2 disposé dans un carter 1. La paroi du canal 2 est formée d'une succession d'ondulations annulaires comprenant chacune une première partie tronconique 4, divergeant vers l'aval, et une seconde partie tronconique 5, convergeant vers l'aval, raccordée à la précédente, dont la longueur projetée sur l'axe de la chambre est supérieure à celle de la première partie. La première partie 4 comporte un grand nombre de perforations 6, de faibles dimensions, régulièrement réparties destinées à l'introduction d'air de refroidissement. Le canal 2 peut être réalisé par roulage d'une tôle, les perforations étant effectuées par bombardement électronique, les ondulations étant imprimées enfin par un procédé du type à la molette L'invention s'applique notamment à la réalisation des canaux de rechauffe pour turboréacteurs.The present invention relates to a combustion apparatus for gas turbine engines. This combustion device is formed of a channel 2 disposed in a casing 1. The wall of the channel 2 is formed of a succession of annular undulations each comprising a first frustoconical part 4, diverging downstream, and a second part. frustoconical 5, converging downstream, connected to the previous one, the length projected onto the axis of the chamber is greater than that of the first part. The first part 4 comprises a large number of perforations 6, of small dimensions, regularly distributed for the introduction of cooling air. Channel 2 can be produced by rolling a sheet, the perforations being effected by electronic bombardment, the corrugations finally being printed by a method of the roller type. The invention applies in particular to the production of heating channels for turbojets. .

FR7730487A 1977-10-11 1977-10-11 COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS Granted FR2406075A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR7730487A FR2406075A1 (en) 1977-10-11 1977-10-11 COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS
GB7840058A GB2009859B (en) 1977-10-11 1978-10-10 Combustion apparatus
DE2844349A DE2844349C2 (en) 1977-10-11 1978-10-11 Post-combustion duct for a jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7730487A FR2406075A1 (en) 1977-10-11 1977-10-11 COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS

Publications (2)

Publication Number Publication Date
FR2406075A1 true FR2406075A1 (en) 1979-05-11
FR2406075B1 FR2406075B1 (en) 1980-04-04

Family

ID=9196335

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7730487A Granted FR2406075A1 (en) 1977-10-11 1977-10-11 COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS

Country Status (3)

Country Link
DE (1) DE2844349C2 (en)
FR (1) FR2406075A1 (en)
GB (1) GB2009859B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3117515C2 (en) * 1980-05-07 1983-11-10 Brown, Boveri & Cie Ag, 6800 Mannheim Overflow housing
US4878283A (en) * 1987-08-31 1989-11-07 United Technologies Corporation Augmentor liner construction
DE19528406A1 (en) * 1995-08-02 1997-02-06 Bmw Rolls Royce Gmbh Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension
JP2018054210A (en) * 2016-09-28 2018-04-05 株式会社Ihi Liner for combustor
CN112984559A (en) * 2021-03-19 2021-06-18 中国联合重型燃气轮机技术有限公司 Flame tube, combustion chamber, and gas turbine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2525206A (en) * 1944-12-13 1950-10-10 Lucas Ltd Joseph Multiple truncated conical element combustion chamber
FR1135017A (en) * 1955-10-28 1957-04-23 Snecma Improvement in the combustion chambers of continuous flow internal combustion machines
GB818634A (en) * 1955-09-29 1959-08-19 Birmingham Small Arms Co Ltd Improvements in or relating to combustion chambers for gas turbines
FR2123386A1 (en) * 1971-01-25 1972-09-08 United Kingdom Government
US3712062A (en) * 1968-04-17 1973-01-23 Gen Electric Cooled augmentor liner

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1171207B (en) * 1960-04-01 1964-05-27 United Aircraft Corp Can burner for a gas turbine combustion chamber

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2525206A (en) * 1944-12-13 1950-10-10 Lucas Ltd Joseph Multiple truncated conical element combustion chamber
GB818634A (en) * 1955-09-29 1959-08-19 Birmingham Small Arms Co Ltd Improvements in or relating to combustion chambers for gas turbines
FR1135017A (en) * 1955-10-28 1957-04-23 Snecma Improvement in the combustion chambers of continuous flow internal combustion machines
US3712062A (en) * 1968-04-17 1973-01-23 Gen Electric Cooled augmentor liner
FR2123386A1 (en) * 1971-01-25 1972-09-08 United Kingdom Government

Also Published As

Publication number Publication date
DE2844349A1 (en) 1979-04-12
GB2009859A (en) 1979-06-20
FR2406075B1 (en) 1980-04-04
DE2844349C2 (en) 1986-07-17
GB2009859B (en) 1982-04-07

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Legal Events

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ST Notification of lapse