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GB1084916A - Fuel injection device - Google Patents

Fuel injection device

Info

Publication number
GB1084916A
GB1084916A GB3642964A GB3642964A GB1084916A GB 1084916 A GB1084916 A GB 1084916A GB 3642964 A GB3642964 A GB 3642964A GB 3642964 A GB3642964 A GB 3642964A GB 1084916 A GB1084916 A GB 1084916A
Authority
GB
United Kingdom
Prior art keywords
fuel
casing
secured
manifold
reheat
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
GB3642964A
Inventor
John Hunter Hill
Stuart Wellington Pond
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.)
Continental Aviation and Engineering Corp
Original Assignee
Continental Aviation and Engineering Corp
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 Continental Aviation and Engineering Corp filed Critical Continental Aviation and Engineering Corp
Priority to GB3642964A priority Critical patent/GB1084916A/en
Publication of GB1084916A publication Critical patent/GB1084916A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

1,084,916. Gas turbine jet engines; reheat equipment. CONTINENTAL AVIATION & ENGINEERING CORPORATION. Sept.4, 1964, No.36429/64. Headings F1G, F1J and F1L. The invention relates to combustion equipment comprising an annular casing defining a combustion chamber and a fuel supply device which comprises an annular fuel manifold from which extend radially inwardly into the combustion chamber a plurality of straight fuel spray nozzles. The spray nozzles are removably secured to the fuel manifold. The invention is described with reference to reheat combustion equipment of a gas turbine jet engine, the reheat fuel being pyrophoric. The reheat combustion chamber is defined by a casing 14 and the annular fuel manifold 10 is disposed therearound. A plurality of fuel spray nozzles 12 are releasably secured to the manifold by locking means 13, the spray nozzles extending radially inwardly into the combustion chamber through openings in the wall of the casing 14. Each spray nozzle is formed with openings 17 and is secured to the manifold 10 by a screwed coupling 13A, 13B. A bush 20 is located within each opening 18 in the casing 14 by means of a pair of flange members 19, 21 secured to the casing by bolts 23 and the spray nozzle 12 passes through the bush with clearance to permit sliding movement therein. A troughshaped flame stabilizing member 24 is associated with each spray nozzle, being secured to the flange 19.
GB3642964A 1964-09-04 1964-09-04 Fuel injection device Expired GB1084916A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3642964A GB1084916A (en) 1964-09-04 1964-09-04 Fuel injection device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3642964A GB1084916A (en) 1964-09-04 1964-09-04 Fuel injection device

Publications (1)

Publication Number Publication Date
GB1084916A true GB1084916A (en) 1967-09-27

Family

ID=10388066

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3642964A Expired GB1084916A (en) 1964-09-04 1964-09-04 Fuel injection device

Country Status (1)

Country Link
GB (1) GB1084916A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2344241A1 (en) * 1972-09-05 1974-03-21 Gen Electric FASTENING SYSTEM FOR REINFORCEMENT FUEL INJECTION
DE2338673A1 (en) * 1963-08-07 1975-02-20 Gen Electric THRUST INCREASE SYSTEM WITH FLOW MIXING
EP1489269A2 (en) * 2003-06-18 2004-12-22 General Electric Company Methods and apparatus for injecting cleaning fluids into combustors

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2338673A1 (en) * 1963-08-07 1975-02-20 Gen Electric THRUST INCREASE SYSTEM WITH FLOW MIXING
DE2344241A1 (en) * 1972-09-05 1974-03-21 Gen Electric FASTENING SYSTEM FOR REINFORCEMENT FUEL INJECTION
JPS4992418A (en) * 1972-09-05 1974-09-03
JPS5819848B2 (en) * 1972-09-05 1983-04-20 ゼネラル エレクトリツク カンパニイ Gas turbine engine thrust boosting fuel injector mounting device
EP1489269A2 (en) * 2003-06-18 2004-12-22 General Electric Company Methods and apparatus for injecting cleaning fluids into combustors
EP1489269A3 (en) * 2003-06-18 2005-05-18 General Electric Company Methods and apparatus for injecting cleaning fluids into combustors

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