GB670092A - Improvements relating to combustion equipment for gas-turbine engines - Google Patents

Improvements relating to combustion equipment for gas-turbine engines

Info

Publication number
GB670092A
GB670092A GB12549A GB12549A GB670092A GB 670092 A GB670092 A GB 670092A GB 12549 A GB12549 A GB 12549A GB 12549 A GB12549 A GB 12549A GB 670092 A GB670092 A GB 670092A
Authority
GB
United Kingdom
Prior art keywords
tube
tubular structure
flame tube
flame
air
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
GB12549A
Inventor
Francis Murray Johnson
John Bertram Holliday
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB12549A priority Critical patent/GB670092A/en
Publication of GB670092A publication Critical patent/GB670092A/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
    • F23R3/04—Air inlet arrangements

Abstract

670,092. Generating combustion products under pressure. ROLLS-ROYCE, Ltd. March 7, 1950 [Jan. 3, 1949], No. 125/49. Class 51 (i). In combustion equipment comprising a plurality of flame tubes 11 arranged in one or more air casings 10 a tubular structure 15a, 15b extends into each flame tube from its inlet end, thus forming with the tube an annular space in which a plurality of fuel injectors 21 are located, the tubular structure having outlet passages 16 through which compressed dilution air may flow into the flame tube downstream of the combustion zone. The tubular structure comprises either an imperforate cylindrical portion 15a and a perforated conical cap 15b, or a tapered tube the cross-section of which decreases from the inlet end to the downstream end. Holes 17 and 18 are formed in the wall of the flame tube to admit secondary and dilution air. Conical baffles 25 are provided around the fuel injection devices 21 to form stagnant zones into which fuel is delivered. The flame tube is supported within the air casing 10 by means of plug devices 13 engaging in sockets 14.
GB12549A 1949-01-03 1949-01-03 Improvements relating to combustion equipment for gas-turbine engines Expired GB670092A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB12549A GB670092A (en) 1949-01-03 1949-01-03 Improvements relating to combustion equipment for gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB12549A GB670092A (en) 1949-01-03 1949-01-03 Improvements relating to combustion equipment for gas-turbine engines

Publications (1)

Publication Number Publication Date
GB670092A true GB670092A (en) 1952-04-16

Family

ID=9698850

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12549A Expired GB670092A (en) 1949-01-03 1949-01-03 Improvements relating to combustion equipment for gas-turbine engines

Country Status (1)

Country Link
GB (1) GB670092A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1062985B (en) * 1955-12-30 1959-08-06 United Aircraft Corp Combustion chamber for turbo-jet engines
US2982098A (en) * 1953-04-22 1961-05-02 Power Jets Res & Dev Ltd Liquid fuel vaporizing combustion systems
US3000182A (en) * 1960-04-01 1961-09-19 United Aircraft Corp Can burner design
DE1118535B (en) * 1959-03-31 1961-11-30 United Aircraft Corp Flame tube for gas turbine combustion chambers
US3116606A (en) * 1958-07-21 1964-01-07 Gen Motors Corp Combustion can support
DE1164159B (en) * 1961-04-19 1964-02-27 Bristol Siddeley Engines Ltd Combustion chamber for gas turbine engines
DE1167594B (en) * 1960-04-25 1964-04-09 Rolls Royce Annular combustion chamber for gas turbine jet engines
DE1181004B (en) * 1959-03-11 1964-11-05 Rolls Royce Combustion chamber for gas turbine jet engines

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2982098A (en) * 1953-04-22 1961-05-02 Power Jets Res & Dev Ltd Liquid fuel vaporizing combustion systems
DE1062985B (en) * 1955-12-30 1959-08-06 United Aircraft Corp Combustion chamber for turbo-jet engines
US3116606A (en) * 1958-07-21 1964-01-07 Gen Motors Corp Combustion can support
DE1181004B (en) * 1959-03-11 1964-11-05 Rolls Royce Combustion chamber for gas turbine jet engines
DE1118535B (en) * 1959-03-31 1961-11-30 United Aircraft Corp Flame tube for gas turbine combustion chambers
US3000182A (en) * 1960-04-01 1961-09-19 United Aircraft Corp Can burner design
DE1167594B (en) * 1960-04-25 1964-04-09 Rolls Royce Annular combustion chamber for gas turbine jet engines
DE1164159B (en) * 1961-04-19 1964-02-27 Bristol Siddeley Engines Ltd Combustion chamber for gas turbine engines

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