GB670247A - Improvements in or relating to combustion apparatus - Google Patents

Improvements in or relating to combustion apparatus

Info

Publication number
GB670247A
GB670247A GB21731/48A GB2173148A GB670247A GB 670247 A GB670247 A GB 670247A GB 21731/48 A GB21731/48 A GB 21731/48A GB 2173148 A GB2173148 A GB 2173148A GB 670247 A GB670247 A GB 670247A
Authority
GB
United Kingdom
Prior art keywords
fuel
tube
baffles
distributed over
nozzles
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
GB21731/48A
Inventor
Alexander Pearse Johnstone
Ronald Thomas Max Forman
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
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Publication of GB670247A publication Critical patent/GB670247A/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
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

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)

Abstract

670,247. Gas turbine plant. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Feb. 2, 1949. [Aug. 17, 1948; Jan. 4, 1949] Nos. 21731/48 and 226/49. Divided out of 665,446. Class 110(iii). [Also in Group XII] The reheat combustion chamber of a gas turbine jet propulsion engine has means for injecting fuel without ignition into the exhast gases at a plurality of points distributed over a transverse section of the exhaust pipe, means to form a stabilized combustion zone similarly distributed over the section of the exhaust duct downstream of the fuel injection zone and means to control the lateral spread of the fuel between the fuel injecting and the stabilizing means. The exhaust gases from a turbine 1, Fig. 1 are reheated in passing to the propulsion nozzle 7. The reheating apparatus comprises a group of fuel injection nozzles 9 distributed over the cross-section of the duct and a plurality of flame stabilizing baffles 10 similarly distributed in a region downstream of the nozzles 9. The nozzles 9 inject fuel upstream into a tubular member 12, Fig. 2, which controls the lateral spread of fuel at the baffles 10. Normally, it is not desired to allow fuel to leave the upstream end of the tube 12, but at high fuel flows it is difficult to prevent it. In this case, the flow of this fuel may be controlled by flaring the end of the tube outwardly as at 13 or each tube may be provided with a sheath 14, Fig. 2 or the whole system of tubes a sheath 15, Fig. 1. In a modification, a rectangular baffle plate which partially blocks off the upstream end of the tube 12 may be provided. In another modification only some of the jets 9 are provided with tubes 12, the remaining jets discharging freely into the gas stream. Preferably, each fuel jet 9 has a stabilizing baffle 10 and each baffle houses an ignition device. The first Provisional Specification also describes the proposal to connect the control of the reheat fuel with that of the nozzle area. The ignition means in the baffles 10 may be operated successively as the nozzle area is increased. Specification 665,446 is referred to. Specifications 606,176 and 659,800, [both in Group XXVI], also are referred to in the Provisional Specifications.
GB21731/48A 1948-02-19 1948-08-17 Improvements in or relating to combustion apparatus Expired GB670247A (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB275239X 1948-02-19
US7504249A 1949-02-07 1949-02-07
US220605A US2705868A (en) 1948-02-19 1951-04-12 Combustion apparatus
US220610A US2705869A (en) 1948-02-19 1951-04-12 Combustion apparatus

Publications (1)

Publication Number Publication Date
GB670247A true GB670247A (en) 1952-04-16

Family

ID=32303577

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21731/48A Expired GB670247A (en) 1948-02-19 1948-08-17 Improvements in or relating to combustion apparatus

Country Status (4)

Country Link
US (2) US2705869A (en)
CH (1) CH275239A (en)
FR (1) FR981045A (en)
GB (1) GB670247A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4453384A (en) * 1981-02-21 1984-06-12 Rolls-Royce Limited Fuel burners and combustion equipment for use in gas turbine engines

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2651178A (en) * 1951-01-18 1953-09-08 A V Roe Canada Ltd Combination injector and stabilizer for gas turbine afterburners
US2780062A (en) * 1951-04-03 1957-02-05 Curtiss Wright Corp Jet engine burner construction
US2780915A (en) * 1951-12-05 1957-02-12 Solar Aircraft Co Fuel distribution system for jet engine and afterburner
US2712221A (en) * 1952-04-22 1955-07-05 Westinghouse Electric Corp Gas turbine afterburner apparatus
US2840990A (en) * 1952-07-17 1958-07-01 John P Longwell Multistage fuel injection for ram-jet combustor
US2835109A (en) * 1952-07-17 1958-05-20 John P Longwell Igniter for ram-jet
US2780916A (en) * 1952-08-22 1957-02-12 Continental Aviat & Engineerin Pilot burner for jet engines
US2931174A (en) * 1952-12-20 1960-04-05 Armstrong Siddeley Motors Ltd Vaporizer for liquid fuel
NL187782B (en) * 1953-06-27 Sony Corp VIDEO SIGNAL DISPLAY SYSTEM AND VIDEO SIGNAL RECORDING DEVICE.
US2861424A (en) * 1954-04-09 1958-11-25 Douglas Aircraft Co Inc Fuel supply means for combustion apparatus
US2986359A (en) * 1956-06-15 1961-05-30 Tino Ovid Airplane lifting device
DE1276414B (en) * 1956-07-13 1968-08-29 Snecma Incinerator
US3085401A (en) * 1959-01-22 1963-04-16 Rolls Royce Reheat combustion equipment of gas-turbine engines
DE1132765B (en) * 1959-12-14 1962-07-05 Gen Electric Combustion device for a gas flow to a jet engine combustion chamber, in particular to an afterburner
US3162238A (en) * 1961-10-09 1964-12-22 Preway Inc Gas burner utilizing air above atmospheric pressure
GB1390031A (en) * 1971-08-21 1975-04-09 Rolls Royce Reheat system for a gas turbine engine
FR2588920B1 (en) * 1985-10-23 1987-12-04 Snecma POSTCOMBUSTION TURBOREACTOR WITH INDIVIDUAL RADIAL POSTCOMBUSTION INJECTORS
US4751815A (en) * 1986-08-29 1988-06-21 United Technologies Corporation Liquid fuel spraybar
US5000004A (en) * 1988-08-16 1991-03-19 Kabushiki Kaisha Toshiba Gas turbine combustor
US4967562A (en) * 1988-12-12 1990-11-06 Sundstrand Corporation Turbine engine with high efficiency fuel atomization
US20210231143A1 (en) * 2019-05-20 2021-07-29 Jonathan Jan Device and method for augmenting gas flow

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2385833A (en) * 1943-01-27 1945-10-02 Kevork K Nahigyan Fuel vaporizer for jet propulsion units
NL67339C (en) * 1944-11-28
FR920910A (en) * 1945-02-01 1947-04-22 Power Jets Res & Dev Ltd Improvements made to combustion devices, more especially to those in which gas streams circulate at high speed
US2583651A (en) * 1945-08-14 1952-01-29 Jr Arthur Fredrick Horning Airplane power plant with direct cooling of exhaust valves
US2566373A (en) * 1946-01-10 1951-09-04 Edward M Redding Fuel control system for turbojet engines
US2557020A (en) * 1946-04-26 1951-06-12 Standard Oil Dev Co Use of sulfur in the suppression of carburizing in gas turbine and jet propulsion engines
US2506611A (en) * 1948-03-02 1950-05-09 Westinghouse Electric Corp Fuel control for aviation gas turbine power plants
US2508420A (en) * 1948-09-21 1950-05-23 Westinghouse Electric Corp Combustion apparatus

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4453384A (en) * 1981-02-21 1984-06-12 Rolls-Royce Limited Fuel burners and combustion equipment for use in gas turbine engines

Also Published As

Publication number Publication date
FR981045A (en) 1951-05-21
CH275239A (en) 1951-05-15
US2705869A (en) 1955-04-12
US2705868A (en) 1955-04-12

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