GB713422A - Improvements relating to combustion equipment for gas turbine engines - Google Patents

Improvements relating to combustion equipment for gas turbine engines

Info

Publication number
GB713422A
GB713422A GB779450A GB779450A GB713422A GB 713422 A GB713422 A GB 713422A GB 779450 A GB779450 A GB 779450A GB 779450 A GB779450 A GB 779450A GB 713422 A GB713422 A GB 713422A
Authority
GB
United Kingdom
Prior art keywords
duct
wall
flame tube
diameter
combustion chamber
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
GB779450A
Inventor
Francis Murray Johnson
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 GB779450A priority Critical patent/GB713422A/en
Publication of GB713422A publication Critical patent/GB713422A/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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

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

713,422. Generating combustion products under pressure. ROLLS-ROYCE, Ltd. June 4, 1951 [March 28, 1950], No. 7794/50. Class 51 (1) In an air jacketed type of combustion chamber for a gas turbine engine, primary air is introduced into the flame tube through a duct at the upstream end thereof, the duct terminating within the flame tube, being of cylindrical or frusto-conical form, lying on the axis of the flame tube and including swirl vanes. The duct is so dimensioned that the ratio of the length L thereof on the downstream side of the swirl vanes to the diameter of the duct is greater than unity. The diameter of the duct is defined as the internal diameter of the wall of a full cylindrical duct, the internal diameter of the outer wall of an annular duct, the mean diameter of the wall of a converging or diverging duct or the mean diameter of the outer wall of a converging or diverging annular duct. The combustion chamber has a fuel injector 11 which lies on the axis of the flame tube, the injector being surrounded by the tubular portion 8a of the flame tube wall 8 so as to constitute an annular duct 15 in which the swirl vanes 16 are mounted. The wall 7 of the flame tube is supported on a seating 20 formed on a conical duct part 21 which is supported within the combustion chamber casing by aerofoil section supports 12. The body of the fuel atomizing injector is mounted on an extension 12a of the supports 12 through which extend fuel passages 13, 14. The wall members 7, 8 may be perforated to allow a small air-flow therethrough to reduce the tendency of carbon formation. Specification 686,383 is referred to.
GB779450A 1950-03-28 1950-03-28 Improvements relating to combustion equipment for gas turbine engines Expired GB713422A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB779450A GB713422A (en) 1950-03-28 1950-03-28 Improvements relating to combustion equipment for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB779450A GB713422A (en) 1950-03-28 1950-03-28 Improvements relating to combustion equipment for gas turbine engines

Publications (1)

Publication Number Publication Date
GB713422A true GB713422A (en) 1954-08-11

Family

ID=9839863

Family Applications (1)

Application Number Title Priority Date Filing Date
GB779450A Expired GB713422A (en) 1950-03-28 1950-03-28 Improvements relating to combustion equipment for gas turbine engines

Country Status (1)

Country Link
GB (1) GB713422A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3049882A (en) * 1960-05-16 1962-08-21 Gen Electric Combustor construction with means for prevention of hot streaks
US5239832A (en) * 1991-12-26 1993-08-31 General Electric Company Birdstrike resistant swirler support for combustion chamber dome
GB2405691A (en) * 2003-09-08 2005-03-09 Gen Electric An air feed duct for a gas turbine combustor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3049882A (en) * 1960-05-16 1962-08-21 Gen Electric Combustor construction with means for prevention of hot streaks
US5239832A (en) * 1991-12-26 1993-08-31 General Electric Company Birdstrike resistant swirler support for combustion chamber dome
GB2405691A (en) * 2003-09-08 2005-03-09 Gen Electric An air feed duct for a gas turbine combustor
GB2405691B (en) * 2003-09-08 2007-08-15 Gen Electric Methods and apparatus for supplying feed air to turbine combustors

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