GB744178A - Improvements relating to combustion equipment of gas-turbine engines - Google Patents

Improvements relating to combustion equipment of gas-turbine engines

Info

Publication number
GB744178A
GB744178A GB845553A GB845553A GB744178A GB 744178 A GB744178 A GB 744178A GB 845553 A GB845553 A GB 845553A GB 845553 A GB845553 A GB 845553A GB 744178 A GB744178 A GB 744178A
Authority
GB
United Kingdom
Prior art keywords
casing
baffle
annular
open
cylindrical
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
GB845553A
Inventor
Francis Murray Johnson
Vernon Wallace Greenhough
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 GB845553A priority Critical patent/GB744178A/en
Publication of GB744178A publication Critical patent/GB744178A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

744,178. Generating combustion products under pressure. ROLLS-ROYCE, Ltd. March 12, 1954 [March 26, 1953], No. 8455/53. Class 51 (1). In a gas turbine engine, exhaust reheat combustion comprises fuel injecting means 21 and downstream thereof stabilizing means comprising a baffle element disposed in a tubular or annular casing, the upstream end of the latter being apertured to permit fuel and gas mixture to enter and flow between the baffle element and the wall of the casing, the wall of the casing extending downstream of the baffle element and being open to the gas stream at its downstream end. In Fig. 3 the baffle 23 is conical with the apex upstream and is mounted in a tubular casing having a conical portion 24, open at its apex 25 and a cylindrical portion 27 open at the downstream end. The baffle 25 is either open or closed at its downstream end. A transverse annular plate may be disposed between the baffle and the tubular casing, the plate being perforated for the passage of air-fuel mixture. In Fig. 6 an annular angle-section baffle 123 is disposed within an annular angle-section casing 124 having a slot opening 125 at its upstream end. Cylindrical walls 127 extend from the casing 124 and perforated rings 128 support the baffle within the casing 124, 127. In Fig. 7 the conical baffle 23 has a cylindrical extension 31, the downstream end of which is flanged, 32, to engage the cylindrical casing portion 27, the parts being secured by split pins 33. The cylindrical extension 31 is perforated at 34 for entry of fuel-gas mixture. A similar construction is used in the case of an annular baffle in an annular outer casing. The equipment is either for reheating exhaust gases in a jet propulsion engine or for reheating gases between turbines in a multi-stage gas turbine engine.
GB845553A 1953-03-26 1953-03-26 Improvements relating to combustion equipment of gas-turbine engines Expired GB744178A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB845553A GB744178A (en) 1953-03-26 1953-03-26 Improvements relating to combustion equipment of gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB845553A GB744178A (en) 1953-03-26 1953-03-26 Improvements relating to combustion equipment of gas-turbine engines

Publications (1)

Publication Number Publication Date
GB744178A true GB744178A (en) 1956-02-01

Family

ID=9852819

Family Applications (1)

Application Number Title Priority Date Filing Date
GB845553A Expired GB744178A (en) 1953-03-26 1953-03-26 Improvements relating to combustion equipment of gas-turbine engines

Country Status (1)

Country Link
GB (1) GB744178A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948117A (en) * 1956-10-01 1960-08-09 Gen Electric Afterburner flameholder
EP0224429A2 (en) * 1985-11-25 1987-06-03 United Technologies Corporation Gas turbine engine augmentor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948117A (en) * 1956-10-01 1960-08-09 Gen Electric Afterburner flameholder
EP0224429A2 (en) * 1985-11-25 1987-06-03 United Technologies Corporation Gas turbine engine augmentor
EP0224429A3 (en) * 1985-11-25 1988-09-14 United Technologies Corporation Gas turbine engine augmentor

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