GB723830A - Flame stabilising device - Google Patents

Flame stabilising device

Info

Publication number
GB723830A
GB723830A GB2305652A GB2305652A GB723830A GB 723830 A GB723830 A GB 723830A GB 2305652 A GB2305652 A GB 2305652A GB 2305652 A GB2305652 A GB 2305652A GB 723830 A GB723830 A GB 723830A
Authority
GB
United Kingdom
Prior art keywords
fuel
casing
duct
swirl vanes
gas
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
GB2305652A
Inventor
Sidney Allen
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors 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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Priority to GB2305652A priority Critical patent/GB723830A/en
Priority to FR1083057D priority patent/FR1083057A/en
Priority to DEA18766A priority patent/DE948023C/en
Publication of GB723830A publication Critical patent/GB723830A/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

Abstract

723,830. Vapour burners. ARMSTRONG SIDDELEY MOTORS, Ltd. Aug. 6, 1953 [Sept. 13, 1952], No. 23056/52. Class 75 (1) [Also in Group XII] In a flame stabilizing device for use in an exhaust reheat system of a gas turbine jet propulsion engine, the supply of fuel for the stabilizing device is introduced into and near one end of a duct 19 disposed in the main gas flow and having adjacent the fuel inlet 22 an opening 24 through which a small amount of the main gas flow can enter, the opposite end 20 of the duct communicating substantially centrally with the upstream end of the stabilizer casing 14. The casing 14 is supported by radial struts 15 which are'secured to the jet pipe 13 by means of bolts 17, and in Fig. 1 the duct 19 extends radially and is in line with one of the struts 15. In a second embodiment, the duct extends co-axially upstream from the stabilizer casing and the fuel supply pipe is led radially across the jet pipe. The fuel passing through the duct 19 is vaporized and enters the casing 14 through swirl vanes 27. Gaseous fluid flowing in the jet pipe enters the casing 14 through swirl vanes 30 which impart swirl in a direction opposed to that of the vanes 27. The means for causing ignition of the fuel within the stabilizer casing so as to form the pilot flame and the means for supplying the main reheat fuel are not shown. In further embodiments, the vaporized fuel and gas issuing from the duct 19 does not pass through swirl vanes 27, but impinges on a flat baffle plate which causes turbulence and directs the mixture radially outwords. In a further embodiment, the vaporized fuel and gas issues through swirl vanes 27 but the gas stream entering the casing 14 impinges on a baffle plate which thereby causes turbulence. Specification 674,641 is referred to, and Specification 705,772 is referred to in the Provisional Specification.
GB2305652A 1952-09-13 1952-09-13 Flame stabilising device Expired GB723830A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB2305652A GB723830A (en) 1952-09-13 1952-09-13 Flame stabilising device
FR1083057D FR1083057A (en) 1952-09-13 1953-09-04 Flame stabilizer device for jet propulsion apparatus
DEA18766A DE948023C (en) 1952-09-13 1953-09-12 Flame stabilizer for jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2305652A GB723830A (en) 1952-09-13 1952-09-13 Flame stabilising device

Publications (1)

Publication Number Publication Date
GB723830A true GB723830A (en) 1955-02-09

Family

ID=10189393

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2305652A Expired GB723830A (en) 1952-09-13 1952-09-13 Flame stabilising device

Country Status (3)

Country Link
DE (1) DE948023C (en)
FR (1) FR1083057A (en)
GB (1) GB723830A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931175A (en) * 1957-01-29 1960-04-05 Bristol Aero Engines Ltd Fuel burners in ducts
US2950763A (en) * 1955-11-22 1960-08-30 Hiller Aircraft Corp Jet driven rotor
US2974488A (en) * 1956-11-27 1961-03-14 Snecma Combustion devices for continuous-flow internal combustion machines
US3793828A (en) * 1970-09-26 1974-02-26 Secr Defence Combustion system deflector plate

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1081722B (en) * 1956-11-27 1960-05-12 Snecma Combustion device for steel engines with uninterrupted flow
DE1138590B (en) * 1958-11-07 1962-10-25 United Aircraft Corp Flame holder
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
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB628366A (en) * 1947-09-01 1949-08-26 Donald Louis Mordell Improvements relating to gas turbine engines
DE851428C (en) * 1949-11-30 1952-10-06 Armstrong Siddeley Motors Ltd Fuel supply device in gas turbines

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2950763A (en) * 1955-11-22 1960-08-30 Hiller Aircraft Corp Jet driven rotor
US2974488A (en) * 1956-11-27 1961-03-14 Snecma Combustion devices for continuous-flow internal combustion machines
US2931175A (en) * 1957-01-29 1960-04-05 Bristol Aero Engines Ltd Fuel burners in ducts
US3793828A (en) * 1970-09-26 1974-02-26 Secr Defence Combustion system deflector plate

Also Published As

Publication number Publication date
DE948023C (en) 1956-08-23
FR1083057A (en) 1955-01-05

Similar Documents

Publication Publication Date Title
US2621477A (en) Combustion apparatus having valve controlled passages for preheating the fuel-air mixture
US2404335A (en) Liquid fuel burner, vaporizer, and combustion engine
US2520388A (en) Apparatus for supporting combustion in fast-moving air streams
US3299632A (en) Combustion chamber for a gas turbine engine
US3285007A (en) Fuel injector for a gas turbine engine
GB1259124A (en)
GB1284439A (en) Fuel injector for a gas turbine engine
GB1180524A (en) Gas Turbine Jet Engine of the By-Pass Type
GB691068A (en) Fuel burning means for a gaseous-fluid propulsion jet
GB1357533A (en) Combustion equipment for gas turbine engines
GB1114728A (en) Burner e.g. for a gas turbine engine combustion chamber
GB723830A (en) Flame stabilising device
GB809300A (en) Improvements relating to combustion chambers for combustion turbines, jet propulsionengines and the like
US2635564A (en) Combustion system for pulverulent fuel
US3046731A (en) Flame stabilization in jet engines
GB757332A (en) Liquid fuel combustion chambers for jet-propulsion, engines, gas turbines, or other purposes
GB751098A (en) Improvements in combustion devices particularly applicable to aircraft jet propulsion units
GB674641A (en) Fuel-burning means for a gaseous-fluid propulsion jet
GB811745A (en) Improvements relating to combustion chambers for gas-turbine or jet-propulsion devices and the method of operating the same
GB1283827A (en) Improvements in or relating to combustion apparatus
GB1242066A (en) Improvements in reheat combustion apparatus for by-pass gas turbine engines
GB667394A (en) Improvements in or relating to combustion equipment for gas-turbine engines
GB1184379A (en) Improvements in or relat ing to Combustion Devices
GB743809A (en) Ignition means for use in starting gas turbine engines
GB1305887A (en)