GB891826A - Improvements relating to flame-supporting devices for combustion chambers - Google Patents

Improvements relating to flame-supporting devices for combustion chambers

Info

Publication number
GB891826A
GB891826A GB22639/60A GB2263960A GB891826A GB 891826 A GB891826 A GB 891826A GB 22639/60 A GB22639/60 A GB 22639/60A GB 2263960 A GB2263960 A GB 2263960A GB 891826 A GB891826 A GB 891826A
Authority
GB
United Kingdom
Prior art keywords
ring member
air
disposed
flame
walls
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
GB22639/60A
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.)
Daimler Benz AG
Original Assignee
Daimler Benz AG
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 Daimler Benz AG filed Critical Daimler Benz AG
Publication of GB891826A publication Critical patent/GB891826A/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
    • F23R3/16—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
    • 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
    • F23R3/10—Air inlet arrangements for primary air

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)

Abstract

891,826. Generating combustion products under pressure. DAIMLER-BENZ A.G. June 28, 1960 [July 28, 1959], No. 22639/60. Class 51 (1). A combustion chamber of a gas-turbine jetpropulsion engine or of a ram-jet unit comprises an annular flame-supporting device coaxial therewith, the device comprising a middle ring member which is convex in the upstream direction and on which fuel injection nozzles are disposed, and inner and outer annular air deflecting wall members which co-operate with the side faces of the middle ring to form air passages, web members being disposed at regular intervals between the side faces of the middle ring and the inner and outer air deflecting wall members so that air is led past the middle ring in a number of individual channels. The combustion chamber shown comprises an annular flame tube having walls 11, 12, disposed within an outer air casing 13, 14. The ring member 15 supports a plurality of fuel injection nozzles 16, and inner and outer annular wall members 17 and 18 are disposed adjacent the ring member to define air entry passages. The downstream edges of the ring member 15 and of the walls 17, 18 produce flame-supporting eddies as indicated at 19, 20, 21, 22. V-section struts 25, 26 extend between the ring member and the walls, the struts being open downstream. Fuel is injected through the struts as indicated by the arrows 29, 30.
GB22639/60A 1959-07-28 1960-06-28 Improvements relating to flame-supporting devices for combustion chambers Expired GB891826A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED31172A DE1108518B (en) 1959-07-28 1959-07-28 Flame holder for combustion chambers of gas turbine engines

Publications (1)

Publication Number Publication Date
GB891826A true GB891826A (en) 1962-03-21

Family

ID=7040800

Family Applications (1)

Application Number Title Priority Date Filing Date
GB22639/60A Expired GB891826A (en) 1959-07-28 1960-06-28 Improvements relating to flame-supporting devices for combustion chambers

Country Status (3)

Country Link
US (1) US3154516A (en)
DE (1) DE1108518B (en)
GB (1) GB891826A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1926295A1 (en) * 1968-05-24 1969-12-04 Gen Electric Combustion chamber for jet engines

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1301644B (en) * 1965-11-23 1969-08-21 Daimler Benz Ag Device for ventilating injection nozzles for gas turbine engines, especially aircraft engines
US3364678A (en) * 1966-02-28 1968-01-23 Gen Electric Means for stabilizing fluid flow in diffuser-combustor systems in axial flow gas turbine engines
US4051671A (en) * 1974-10-31 1977-10-04 Brewer John A Jet engine with compressor driven by a ram air turbine
US6122916A (en) * 1998-01-02 2000-09-26 Siemens Westinghouse Power Corporation Pilot cones for dry low-NOx combustors
EA007696B1 (en) 2002-06-26 2006-12-29 Эр-Джет Энджиниринг Лтд. Orbiting combustion nozzle engine
CN112815355B (en) * 2021-01-19 2023-02-28 重庆交通大学绿色航空技术研究院 Flame stabilizing device of small turbine engine and turbine engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689457A (en) * 1949-03-15 1954-09-21 Hermann Oestrich Burner, particularly for gas turbines
GB703002A (en) * 1951-02-14 1954-01-27 Rolls Royce Improvements in or relating to gas turbines
GB780493A (en) * 1954-07-20 1957-08-07 Rolls Royce Improvements relating to combustion equipment for gas-turbine engines
GB744659A (en) * 1954-07-29 1956-02-08 Rolls Royce Improvements in or relating to combustion equipment of gas turbine engines
US2914912A (en) * 1955-10-24 1959-12-01 Gen Electric Combustion system for thermal powerplant
US2948117A (en) * 1956-10-01 1960-08-09 Gen Electric Afterburner flameholder
FR1166154A (en) * 1957-02-01 1958-11-04 Snecma Semi-vaporization burner
FR998079A (en) * 1958-08-22 1952-01-14 Snecma Device for the entry of air into the primary zone of a turbo-machine combustion chamber
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1926295A1 (en) * 1968-05-24 1969-12-04 Gen Electric Combustion chamber for jet engines

Also Published As

Publication number Publication date
US3154516A (en) 1964-10-27
DE1108518B (en) 1961-06-08

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