GB887829A - Improvements relating to flame tubes for combustion systems - Google Patents

Improvements relating to flame tubes for combustion systems

Info

Publication number
GB887829A
GB887829A GB37442/59A GB3744259A GB887829A GB 887829 A GB887829 A GB 887829A GB 37442/59 A GB37442/59 A GB 37442/59A GB 3744259 A GB3744259 A GB 3744259A GB 887829 A GB887829 A GB 887829A
Authority
GB
United Kingdom
Prior art keywords
wall
sleeve
disposed
end cap
flame tube
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
GB37442/59A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB887829A publication Critical patent/GB887829A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)

Abstract

887,829. Generating combustion products under pressure. UNITED AIRCRAFT CORPORATION. Nov. 4, 1959 [March 31, 1959], No. 37442/59. Class 51 (1). A flame tube for a combustion system, for example of a gas-turbine engine, comprises an outer wall in the form of a sleeve, an annular end cap at the upstream end of the outer wall and a plurality of fuel nozzles disposed in the end cap concentric with the outer wall, the end cap having a central opening for admission of air into the flame tube and swirl-producing means disposed in the path of air admitted through the opening. The flame tube shown comprises an outer wall 2, an annular end cap 6 having a central opening and a ring of openings 10 in which are disposed fuel nozzles 8, and an inner sleeve 4 extending from the central opening. A ring of swirl vanes 24 is disposed at the downstream end of the sleeve 4, the vanes being disposed between an outer ring 26 and an inner dome-shaped fairing member 28. A central air inlet passage 14 is provided within the sleeve 4 and an annular combustion space 12 is provided between the outer wall 2 and the inner sleeve 4. The wall 2 and the sleeve 4 are formed of short frusto-conical rings which overlap one another and have air inlet openings 22 therein. The transition piece 16 is of cylindrical form at its upstream end 18 where it engages the outer wall 2, and is of segmental form at its downstream end 20 from which the combustion gases discharge to the turbine nozzle.
GB37442/59A 1959-03-31 1959-11-04 Improvements relating to flame tubes for combustion systems Expired GB887829A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US803175A US2951339A (en) 1959-03-31 1959-03-31 Combustion chamber swirler

Publications (1)

Publication Number Publication Date
GB887829A true GB887829A (en) 1962-01-24

Family

ID=25185787

Family Applications (1)

Application Number Title Priority Date Filing Date
GB37442/59A Expired GB887829A (en) 1959-03-31 1959-11-04 Improvements relating to flame tubes for combustion systems

Country Status (4)

Country Link
US (1) US2951339A (en)
DE (1) DE1118535B (en)
FR (1) FR1238089A (en)
GB (1) GB887829A (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3099134A (en) * 1959-12-24 1963-07-30 Havilland Engine Co Ltd Combustion chambers
DE2538134C2 (en) * 1974-08-27 1984-11-08 Mitsubishi Jukogyo K.K., Tokio/Tokyo Oil burner
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
US3991562A (en) * 1975-07-21 1976-11-16 United Technologies Corporation Combustion chamber assembly having removable center liner
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5253478A (en) * 1991-12-30 1993-10-19 General Electric Company Flame holding diverging centerbody cup construction for a dry low NOx combustor
US6430919B1 (en) * 2000-03-02 2002-08-13 Direct Propulsion Devices, Inc. Shaped charged engine
US7574865B2 (en) * 2004-11-18 2009-08-18 Siemens Energy, Inc. Combustor flow sleeve with optimized cooling and airflow distribution

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2175866A (en) * 1934-04-16 1939-10-10 Philip S Arnold Fuel burner
GB670092A (en) * 1949-01-03 1952-04-16 Rolls Royce Improvements relating to combustion equipment for gas-turbine engines
US2676460A (en) * 1950-03-23 1954-04-27 United Aircraft Corp Burner construction of the can-an-nular type having means for distributing airflow to each can
GB800512A (en) * 1955-01-03 1958-08-27 Lucas Industries Ltd Liquid fuel combustion chambers
US2813397A (en) * 1957-01-02 1957-11-19 United Aircraft Corp Thermal expansion means for combustion chambers

Also Published As

Publication number Publication date
DE1118535B (en) 1961-11-30
US2951339A (en) 1960-09-06
FR1238089A (en) 1960-08-05

Similar Documents

Publication Publication Date Title
US2520388A (en) Apparatus for supporting combustion in fast-moving air streams
US2475911A (en) Combustion apparatus
GB1427146A (en) Combustion apparatus for gas turbine engines
GB1328623A (en) Fuel spray nozzle
GB911759A (en) Improvements in fluid fuel combustion apparatus
GB894470A (en) Improvements in flame tubes for burning liquid fuel in an air stream
GB840054A (en) A device for generating power gases for driving power plants such as turbines
US2632299A (en) Precombustion chamber
GB1180929A (en) Combustion Apparatus, for example for Gas Turbines.
GB884756A (en) Primary air intake device for the combustion chamber of a gas-turbine unit
GB887829A (en) Improvements relating to flame tubes for combustion systems
US2982099A (en) Fuel injection arrangement in combustion equipment for gas turbine engines
GB812201A (en) Improvements in combustion equipment for continuous-flow internal combustion engines
GB757332A (en) Liquid fuel combustion chambers for jet-propulsion, engines, gas turbines, or other purposes
GB751013A (en) Improvements in combustion devices particularly applicable to aircraft jet propulsion units
GB824306A (en) Improvements in or relating to combustion equipment of gas-turbine engines
GB918778A (en) Improvements in or relating to gas-turbine engines
GB704468A (en) Improvements in or relating to combustion chambers for liquid, gaseous or pulverisedsolid fuels
GB736823A (en) Engine combustion chambers
US2882843A (en) Combustion apparatus
GB1196168A (en) Combustion Assemblies for Gas-Turbine Engines
GB710353A (en) Improvements in or relating to combustion equipment for gas-turbine engines
GB719301A (en) Improvements relating to gas turbine engines
GB906865A (en) Improvements in or relating to combustion equipment
GB791753A (en) Improvements in or relating to flame tubes for use in combustion systems of gas turbine engines