GB1138679A - Wall element for combustion chambers - Google Patents

Wall element for combustion chambers

Info

Publication number
GB1138679A
GB1138679A GB55081/67A GB5508167A GB1138679A GB 1138679 A GB1138679 A GB 1138679A GB 55081/67 A GB55081/67 A GB 55081/67A GB 5508167 A GB5508167 A GB 5508167A GB 1138679 A GB1138679 A GB 1138679A
Authority
GB
United Kingdom
Prior art keywords
passage
cooling air
passages
oval
dec
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.)
Expired
Application number
GB55081/67A
Inventor
Jacques Emile Jules Caruel
Armand Jean-Baptiste Lacroix
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB1138679A publication Critical patent/GB1138679A/en
Expired 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
    • 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

1,138,679. Gas turbine or like combustion chambers. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec.4, 1967 [Dec. 8, 1966], No.55081/67. Heading F1L. A wall element inter-connecting tubular sections of a combustion chamber, such as a ram jet or gas turbine engine flame tube or reheat chamber, comprises relatively thin upstream and downstream portions 11, 13 respectively, and a thickened portion 12 having axially extending cooling air passages 16 therethrough of increasing flow area in the downstream direction. As viewed in Fig. 2, the cross-section of each passage 16 is generally triangular, while the section on line V-V is trapezoidal, Fig. 5 (not shown), rectangular, oval or semi-oval. Additional radial passages 28, 29 connect each passage 16 with the wall exterior and reduce flow instability of the cooling air in passage 16. The diverging form of the passages 16 reduces the velocity at which the cooling air enters the flame tube interior.
GB55081/67A 1966-12-08 1967-12-04 Wall element for combustion chambers Expired GB1138679A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR86716A FR1520428A (en) 1966-12-08 1966-12-08 Wall element of a combustion chamber

Publications (1)

Publication Number Publication Date
GB1138679A true GB1138679A (en) 1969-01-01

Family

ID=8622177

Family Applications (1)

Application Number Title Priority Date Filing Date
GB55081/67A Expired GB1138679A (en) 1966-12-08 1967-12-04 Wall element for combustion chambers

Country Status (4)

Country Link
US (1) US3447318A (en)
DE (1) DE1601663B2 (en)
FR (1) FR1520428A (en)
GB (1) GB1138679A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5213015A (en) * 1975-07-16 1977-02-01 Rolls Royce Laminated material

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
FR2093115A5 (en) * 1970-06-02 1972-01-28 Snecma
GB2118710B (en) * 1981-12-31 1985-05-22 Secr Defence Improvements in or relating to combustion chamber wall cooling
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
US4664597A (en) * 1985-12-23 1987-05-12 United Technologies Corporation Coolant passages with full coverage film cooling slot
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
US4726735A (en) * 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4773593A (en) * 1987-05-04 1988-09-27 United Technologies Corporation Coolable thin metal sheet
GB2221979B (en) * 1988-08-17 1992-03-25 Rolls Royce Plc A combustion chamber for a gas turbine engine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2573694A (en) * 1946-07-30 1951-11-06 Westinghouse Electric Corp Combustion chamber with stepped wall construction
US2658337A (en) * 1947-12-23 1953-11-10 Lucas Ltd Joseph Combustion chamber for prime movers
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5213015A (en) * 1975-07-16 1977-02-01 Rolls Royce Laminated material
JPS5761974B2 (en) * 1975-07-16 1982-12-27 Rolls Royce 1971 Ltd

Also Published As

Publication number Publication date
US3447318A (en) 1969-06-03
DE1601663B2 (en) 1975-05-07
FR1520428A (en) 1968-04-12
DE1601663A1 (en) 1972-02-10

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