GB858525A - Improvements relating to combustion chambers for prime movers - Google Patents

Improvements relating to combustion chambers for prime movers

Info

Publication number
GB858525A
GB858525A GB25841/58A GB2584158A GB858525A GB 858525 A GB858525 A GB 858525A GB 25841/58 A GB25841/58 A GB 25841/58A GB 2584158 A GB2584158 A GB 2584158A GB 858525 A GB858525 A GB 858525A
Authority
GB
United Kingdom
Prior art keywords
insert
flame tube
air
secured
opening
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
GB25841/58A
Inventor
Roy Edward Godfrey
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries Ltd
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 Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB25841/58A priority Critical patent/GB858525A/en
Publication of GB858525A publication Critical patent/GB858525A/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
    • 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)
  • Gas Burners (AREA)

Abstract

858,525. Generating combustion products under pressure. LUCAS (INDUSTRIES) Ltd., J. Aug. 11, 1959 [Aug. 12, 1958], No. 25841/58. Class 51 (1). In an air jacketed type of combustion chamber for use in jet propulsion engines and other internal combustion engines in which the flame tube c is formed with openings b for the admission of secondary and dilution air, an insert a is associated with each opening. Each insert is made from a small sheet metal plate shaped so that a part of its periphery is received within the associated air inlet opening and so that the remaining part forms with the inner surface of the flame tube wall a narrow gap through which a limited flow of air can enter the flame tube in a direction parallel to the wall. A hole is formed in the insert having a lip around its periphery for the admission of a radial inflow of air. The upstream part of the insert is of semi-circular form and is received within the opening b being secured thereto by means of lugs d which lie adjacent the outer surface of the flame tube and are secured thereto by welding. The downstream portion e of the insert is shaped to extend beneath the wall of the flame tube forming therewith a narrow space f through which air flows along the inner surface of the flame tube as indicated by the arrows. The portion e of the insert is shaped so that it may be secured to the inner surface of the flame tube at g. A hole is formed in the insert concentric with the opening b in the flame tube, the hole being formed with an inwardly directed lip h to guide radially inflowing air. In a second embodiment, the upstream portion of the insert is spaced from the edge of the air inlet opening b so as to form a narrow air inlet passage m, the edge of the inlet opening b being formed with an inwardly directed lip k parallel to the lip h of the insert. The downstream portion e of the insert extends beneath the wall of the flame tube and is secured thereto as in the first embodiment. Attachment lugs d are not provided in this embodiment, the insert being secured to the edge of the inlet opening b by welding at the points o. Specification 665,155 is referred to.
GB25841/58A 1958-08-12 1958-08-12 Improvements relating to combustion chambers for prime movers Expired GB858525A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB25841/58A GB858525A (en) 1958-08-12 1958-08-12 Improvements relating to combustion chambers for prime movers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB25841/58A GB858525A (en) 1958-08-12 1958-08-12 Improvements relating to combustion chambers for prime movers

Publications (1)

Publication Number Publication Date
GB858525A true GB858525A (en) 1961-01-11

Family

ID=10234222

Family Applications (1)

Application Number Title Priority Date Filing Date
GB25841/58A Expired GB858525A (en) 1958-08-12 1958-08-12 Improvements relating to combustion chambers for prime movers

Country Status (1)

Country Link
GB (1) GB858525A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0187731A1 (en) * 1985-01-07 1986-07-16 United Technologies Corporation Combustion liner for a gas turbine engine
US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
FR2593237A1 (en) * 1986-01-17 1987-07-24 Hispano Suiza Sa MULTIFLUX TURBOREACTOR PUSH INVERTER COLD FLOW CHANNEL ASSOCIATED WITH COMBINED MEANS OF AIR TANK
US4700544A (en) * 1985-01-07 1987-10-20 United Technologies Corporation Combustors
EP0318312A1 (en) * 1987-11-27 1989-05-31 General Electric Company Aperture insert for the combustion chamber of a gas turbine
EP0363624A1 (en) * 1988-10-07 1990-04-18 Westinghouse Electric Corporation Gas turbine combustion chamber with air scoops
EP1205635A2 (en) * 2000-11-03 2002-05-15 General Electric Company Gas injector system and its fabrication
CN114135901A (en) * 2021-11-08 2022-03-04 中国航发四川燃气涡轮研究院 Ablation-proof flame tube large-hole jet sleeve
US20220412560A1 (en) * 2021-06-23 2022-12-29 General Electric Company Dilution air inlets with notched tip and slotted tail for combustor

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
EP0187731A1 (en) * 1985-01-07 1986-07-16 United Technologies Corporation Combustion liner for a gas turbine engine
US4700544A (en) * 1985-01-07 1987-10-20 United Technologies Corporation Combustors
FR2593237A1 (en) * 1986-01-17 1987-07-24 Hispano Suiza Sa MULTIFLUX TURBOREACTOR PUSH INVERTER COLD FLOW CHANNEL ASSOCIATED WITH COMBINED MEANS OF AIR TANK
EP0233798A1 (en) * 1986-01-17 1987-08-26 HISPANO-SUIZA Société anonyme dite: Cold flux channel of a multiflux turbine thrust reverser having air chute devices
US4815281A (en) * 1986-01-17 1989-03-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Air take-off for a turbojet engine cold flow duct
EP0318312A1 (en) * 1987-11-27 1989-05-31 General Electric Company Aperture insert for the combustion chamber of a gas turbine
EP0363624A1 (en) * 1988-10-07 1990-04-18 Westinghouse Electric Corporation Gas turbine combustion chamber with air scoops
EP1205635A2 (en) * 2000-11-03 2002-05-15 General Electric Company Gas injector system and its fabrication
EP1205635A3 (en) * 2000-11-03 2004-02-11 General Electric Company Gas injector system and its fabrication
US20220412560A1 (en) * 2021-06-23 2022-12-29 General Electric Company Dilution air inlets with notched tip and slotted tail for combustor
US11965653B2 (en) * 2021-06-23 2024-04-23 General Electric Company Dilution air inlets with notched tip and slotted tail for combustor
CN114135901A (en) * 2021-11-08 2022-03-04 中国航发四川燃气涡轮研究院 Ablation-proof flame tube large-hole jet sleeve

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