GB894470A - Improvements in flame tubes for burning liquid fuel in an air stream - Google Patents

Improvements in flame tubes for burning liquid fuel in an air stream

Info

Publication number
GB894470A
GB894470A GB3328360A GB3328360A GB894470A GB 894470 A GB894470 A GB 894470A GB 3328360 A GB3328360 A GB 3328360A GB 3328360 A GB3328360 A GB 3328360A GB 894470 A GB894470 A GB 894470A
Authority
GB
United Kingdom
Prior art keywords
ring
air
adjacent
dome
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
GB3328360A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation Co
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 US843565A priority Critical patent/US3064424A/en
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB894470A publication Critical patent/GB894470A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air
    • F23R3/12Air inlet arrangements for primary air inducing a vortex
    • F23R3/14Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/06Arrangement of apertures along the flame tube
    • F23R3/08Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

Abstract

894,470. Generating combustion products under pressure. GENERAL MOTORS CORPORATION. Sept. 28, 1960 [Sept. 30, 1959], No. 33283/60. Class 51 (1). In combustion equipment for burning liquid fuel in an air-stream, for example in a gas turbine engine, and comprising a flame tube disposed within an outer air casing, the flame tube comprises an end dome and a cylindrical section body of equal diameter disposed coaxially with their adjacent edges separated by a gap, an annular strip having axial corrugations and air admission holes being disposed within the flame tube so as to bridge the gap between the dome and adjacent body. The flame tube 10 shown is one of a plurality disposed within the annular air passage 14 formed between the outer and inner air casing walls 12, 15 and comprises an end dome 23, four frusto-conical sections 38, 39, 41, 42, a cylindrical section 43 and an outlet section 17, the cross-section of which changes from circular at its upstream end to a sector of an annulus at its downstream end. The cylindrical portion 30 of the end dome 23 is separated from the upstream end of the adjacent frustoconical section 38 by a gap 51 and a corrugated ring member 50 spans the gap, being secured within the flame tube to the adjacent parts by spot welding. The ring member 50 is formed with air admission holes 52 and a ring 54 is secured to the inner surfaces of the corrugations of the ring member 50, the ring being subsequently divided by a number of axial slots 55 so as to form a plurality of ring portions. An air swirler device 33 is mounted at the centre of the end dome 23 and comprises an inner ring 35, an outer ring 34 and a number of helically disposed vanes 36 therebetween. The tip 29 of the fuel injector 19 is received within the inner ring of the air swirler. The adjacent ends of the frusto-conical sections 38 and 39, 39 and 41, 41 and 42 are secured together by means of corrugated rings 45 which form inlets for cooling air. The downstream ends of the sections 38, 39, 41 are divided at 46 so as to eliminate stresses due to differential expansion, and air inlet openings 58, 59, 61 are formed in the sections. A ferrule 26 is mounted in the tube section 38 to receive an igniter or a support member and adjacent flame tubes are interconnected by means of pipes engaging with the connectors 27. Reference has been directed by the Comptroller to Specification 687,954.
GB3328360A 1959-09-30 1960-09-28 Improvements in flame tubes for burning liquid fuel in an air stream Expired GB894470A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US843565A US3064424A (en) 1959-09-30 1959-09-30 Flame tube

Publications (1)

Publication Number Publication Date
GB894470A true GB894470A (en) 1962-04-26

Family

ID=25290391

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3328360A Expired GB894470A (en) 1959-09-30 1960-09-28 Improvements in flame tubes for burning liquid fuel in an air stream

Country Status (2)

Country Link
US (1) US3064424A (en)
GB (1) GB894470A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1284157B (en) * 1963-12-04 1968-11-28 Rolls Royce Combustion device for gas turbine engines
US3589127A (en) * 1969-02-04 1971-06-29 Gen Electric Combustion apparatus
US4198815A (en) * 1975-12-24 1980-04-22 General Electric Company Central injection fuel carburetor
EP0093572A1 (en) * 1982-04-28 1983-11-09 The BOC Group, Inc. Air-fuel mixing device
EP0371090A1 (en) * 1987-12-28 1990-06-06 Sundstrand Corporation Gas turbine with forced vortex fuel injection

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1040390A (en) * 1965-07-12 1966-08-24 Rolls Royce Gas turbine engine
GB1136543A (en) * 1966-02-21 1968-12-11 Rolls Royce Liquid fuel combustion apparatus for gas turbine engines
GB1180929A (en) * 1966-04-28 1970-02-11 English Electric Co Ltd Combustion Apparatus, for example for Gas Turbines.
GB1240009A (en) * 1968-07-27 1971-07-21 Leyland Gas Turbines Ltd Flame tube
DE2018641C2 (en) * 1970-04-18 1972-05-10 Motoren Turbinen Union REVERSE COMBUSTION CHAMBER FOR GAS TURBINE ENGINES
GB1357533A (en) * 1970-09-11 1974-06-26 Lucas Industries Ltd Combustion equipment for gas turbine engines
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
US4244178A (en) * 1978-03-20 1981-01-13 General Motors Corporation Porous laminated combustor structure
US4180972A (en) * 1978-06-08 1980-01-01 General Motors Corporation Combustor support structure
US4312186A (en) * 1979-10-17 1982-01-26 General Motors Corporation Shingled laminated porous material
US4361010A (en) * 1980-04-02 1982-11-30 United Technologies Corporation Combustor liner construction
US4527397A (en) * 1981-03-27 1985-07-09 Westinghouse Electric Corp. Turbine combustor having enhanced wall cooling for longer combustor life at high combustor outlet gas temperatures
US4475344A (en) * 1982-02-16 1984-10-09 Westinghouse Electric Corp. Low smoke combustor for land based combustion turbines
DE4228816C2 (en) * 1992-08-29 1998-08-06 Mtu Muenchen Gmbh Burners for gas turbine engines
US6994096B2 (en) * 2003-01-30 2006-02-07 Philip Morris Usa Inc. Flow distributor of an electrically heated cigarette smoking system
US9447970B2 (en) * 2011-05-12 2016-09-20 General Electric Company Combustor casing for combustion dynamics mitigation

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2603064A (en) * 1946-12-12 1952-07-15 Chrysler Corp Combustion chamber with multiple conical sections providing multiple air paths for gas turbines
US2537033A (en) * 1947-07-18 1951-01-09 Westinghouse Electric Corp Gas turbine combustion chamber construction
US2657531A (en) * 1948-01-22 1953-11-03 Gen Electric Wall cooling arrangement for combustion devices
US2555965A (en) * 1950-03-24 1951-06-05 Gen Electric End cap for fluid fuel combustors
US2651912A (en) * 1950-10-31 1953-09-15 Gen Electric Combustor and cooling means therefor
US2768497A (en) * 1951-02-03 1956-10-30 Gen Motors Corp Combustion chamber with swirler
DE1060667B (en) * 1955-10-15 1959-07-02 Stroemungsmasch Anst Combustion device for gas turbines

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1284157B (en) * 1963-12-04 1968-11-28 Rolls Royce Combustion device for gas turbine engines
US3589127A (en) * 1969-02-04 1971-06-29 Gen Electric Combustion apparatus
US4198815A (en) * 1975-12-24 1980-04-22 General Electric Company Central injection fuel carburetor
EP0093572A1 (en) * 1982-04-28 1983-11-09 The BOC Group, Inc. Air-fuel mixing device
EP0371090A1 (en) * 1987-12-28 1990-06-06 Sundstrand Corporation Gas turbine with forced vortex fuel injection
EP0371090A4 (en) * 1987-12-28 1991-06-12 Sundstrand Corporation Gas turbine with forced vortex fuel injection

Also Published As

Publication number Publication date
US3064424A (en) 1962-11-20

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