GB853108A - Combustion system - Google Patents

Combustion system

Info

Publication number
GB853108A
GB853108A GB9210/57A GB921057A GB853108A GB 853108 A GB853108 A GB 853108A GB 9210/57 A GB9210/57 A GB 9210/57A GB 921057 A GB921057 A GB 921057A GB 853108 A GB853108 A GB 853108A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
flame tube
turbine
disc
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
GB9210/57A
Inventor
Rhys Price Probert
Peter Martin
Edward Langford Hartley
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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
Priority to US3126705D priority Critical patent/US3126705A/en
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB9210/57A priority patent/GB853108A/en
Priority to GB9313/56A priority patent/GB853110A/en
Publication of GB853108A publication Critical patent/GB853108A/en
Priority to US142799A priority patent/US3182453A/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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/236—Fuel delivery systems comprising two or more pumps
    • F02C7/2365—Fuel delivery systems comprising two or more pumps comprising an air supply system for the atomisation of fuel
    • 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
    • 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

Abstract

853,108. Liquid fuel burners. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. March 20, 1957 [March 26, 1956], No. 9210/57. Divided out of 853,110. Class 75(1). [Also in Groups XII and XXVI] In a gas turbine, the liquid fuel is applied to the surface of a rotating disc from which it is thrown off centrifugally as a liquid sheet, into the high velocity air stream from the compressor. The fuel is thus atomised and mixed with the air in the flame tube. A secondary air stream from the compressor passes between the flame tube and the turbine outer casing and part mixes with the combustion gases in the turbine and part flows back towards the flame tube inlet by a passage in the flame tube inner wall which is cooled thereby. The fuel spraying disc is slightly coned inwardly to cause the fuel to adhere by centrigufal force. As shown, the turbine 10, 12 is supplied from the flame tube 31 which receives air from the compressor 6, 8 driven by 10, 12 through shaft 14. The fuel is led into 31 from hollow shaft 23 through ports 45, 47, to the downstream surface of the disc 24. The latter rotates with 14 and the ports are dimensioned so that the fuel is thrown from the disc periphery as a sheet into the airstream at 36. Turbulence is increased by the paddles 51. The air flow from 6, 8 is divided by the flame tube outer wall 32 into two annular streams, one through duct 35 and the other into 31. The inlet to 31 is divided by fingers 36, which may be shaped to meter the air-flow. The outlet from 31 is a number of channels 56 formed by corrugations spaced apart circumferentially in 32 to provide alternating passages which discharge streams of hot gas and air. The inner wall 33 of 31 is cooled by air pumped by fan 61 from 56 through holes 62, into passage 60. Specifications 723,015 and 853,109 also are referred to.
GB9210/57A 1956-03-26 1956-03-26 Combustion system Expired GB853108A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US3126705D US3126705A (en) 1956-03-26 Combustion system
GB9210/57A GB853108A (en) 1956-03-26 1956-03-26 Combustion system
GB9313/56A GB853110A (en) 1956-03-26 1956-03-26 Combustion system
US142799A US3182453A (en) 1956-03-26 1961-10-04 Combustion system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9210/57A GB853108A (en) 1956-03-26 1956-03-26 Combustion system

Publications (1)

Publication Number Publication Date
GB853108A true GB853108A (en) 1960-11-02

Family

ID=9867542

Family Applications (2)

Application Number Title Priority Date Filing Date
GB9313/56A Expired GB853110A (en) 1956-03-26 1956-03-26 Combustion system
GB9210/57A Expired GB853108A (en) 1956-03-26 1956-03-26 Combustion system

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB9313/56A Expired GB853110A (en) 1956-03-26 1956-03-26 Combustion system

Country Status (2)

Country Link
US (1) US3126705A (en)
GB (2) GB853110A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199541B (en) * 1961-12-04 1965-08-26 Jan Jerie Dr Ing Propellant gas collector for the stator of gas turbines
FR2438166A1 (en) * 1978-10-02 1980-04-30 Gen Electric IMPROVED GAS TURBINE ENGINE
EP0178242A1 (en) * 1984-10-11 1986-04-16 United Technologies Corporation Cooling scheme for combustor vane interface
US4733538A (en) * 1978-10-02 1988-03-29 General Electric Company Combustion selective temperature dilution
US4769996A (en) * 1987-01-27 1988-09-13 Teledyne Industries, Inc. Fuel transfer system for multiple concentric shaft gas turbine engines

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US762048A (en) * 1903-07-16 1904-06-07 Henry Berg Fuel-burner.
CH114844A (en) * 1924-10-23 1926-07-01 Sulzer Ag Oil burner with rotating atomizer.
US1996336A (en) * 1931-01-08 1935-04-02 Firm Junkers & Co G M B H Burner for liquid fuel
US2086377A (en) * 1931-09-23 1937-07-06 Bryan Steam Corp Oil burner
US2249878A (en) * 1939-01-21 1941-07-22 Charles T Asbury Oil burner
US2284141A (en) * 1940-07-25 1942-05-26 Advance Aluminum Castings Corp Suction fan unit
US2595505A (en) * 1946-04-20 1952-05-06 Continental Aviat & Engineerin Coaxial combustion products generator, turbine, and compressor
US2720750A (en) * 1947-11-04 1955-10-18 Helmut R Schelp Revolving fuel injection system for jet engines and gas turbines
US2657531A (en) * 1948-01-22 1953-11-03 Gen Electric Wall cooling arrangement for combustion devices
US2547959A (en) * 1948-01-27 1951-04-10 Westinghouse Electric Corp Centrifugal fuel feeding system for annular combustion chambers
US2694291A (en) * 1948-02-07 1954-11-16 Henning C Rosengart Rotor and combustion chamber arrangement for gas turbines
US2536600A (en) * 1948-02-07 1951-01-02 Daniel And Florence Guggenheim Rotating, feeding, and cooling means for combustion chambers
US2568921A (en) * 1948-04-27 1951-09-25 Westinghouse Electric Corp Combustion chamber with rotating fuel nozzles
US2659196A (en) * 1949-08-09 1953-11-17 United Aircraft Corp Centrifugal fuel supply means for jet engine afterburners
BE507258A (en) * 1950-12-02
US2801519A (en) * 1951-02-17 1957-08-06 Garrett Corp Gas turbine motor scroll structure
US2602292A (en) * 1951-03-31 1952-07-08 Gen Electric Fuel-air mixing device
US2929209A (en) * 1953-09-15 1960-03-22 Phillips Petroleum Co Combustion of fuel on the surface of a rotating disc

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1199541B (en) * 1961-12-04 1965-08-26 Jan Jerie Dr Ing Propellant gas collector for the stator of gas turbines
FR2438166A1 (en) * 1978-10-02 1980-04-30 Gen Electric IMPROVED GAS TURBINE ENGINE
US4733538A (en) * 1978-10-02 1988-03-29 General Electric Company Combustion selective temperature dilution
EP0178242A1 (en) * 1984-10-11 1986-04-16 United Technologies Corporation Cooling scheme for combustor vane interface
US4769996A (en) * 1987-01-27 1988-09-13 Teledyne Industries, Inc. Fuel transfer system for multiple concentric shaft gas turbine engines

Also Published As

Publication number Publication date
US3126705A (en) 1964-03-31
GB853110A (en) 1960-11-02

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