GB842197A - Improvements in afterburner combustion equipment of a gas turbine jet propulsion engine - Google Patents

Improvements in afterburner combustion equipment of a gas turbine jet propulsion engine

Info

Publication number
GB842197A
GB842197A GB1514458A GB1514458A GB842197A GB 842197 A GB842197 A GB 842197A GB 1514458 A GB1514458 A GB 1514458A GB 1514458 A GB1514458 A GB 1514458A GB 842197 A GB842197 A GB 842197A
Authority
GB
United Kingdom
Prior art keywords
flame
reheat
fuel
disposed
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
GB1514458A
Inventor
Milton Howard Shackelford
Arthur Mccardle Jr
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.)
General Electric Co
Original Assignee
General Electric 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
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB842197A publication Critical patent/GB842197A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

Abstract

842,197. Generating combustion products under pressure. GENERAL ELECTRIC CO. May 12, 1958, No. 15144/58. Class 51 (1). [Also in Group XXVI] In a gas-turbine jet-propulsion engine having reheat combustion equipment disposed in an annular diffuser passage 13 downstream of the turbine, reheat fuel spraying means 15 and flame-holder means 16 are provided, also a pilot burner 17 for continuous ignition comprising a flame tube open at its downstream end and having inlet ports and louvres and being disposed between the fuel spraying means and the flame-holder, the pilot burner flame tube having fuel supply and ignition means. In the engine shown, the diffusion passage 13 is formed between the casing 11, disposed within the outer casing 10, and the fairing cone 12 and the reheat equipment pilot burner 17 is supported from the outer casing 10 by means of an aerofoil strut 23 so that its flared open downstream end 25 is axially in line with the space between the two radially inner flame-holder rings 16. The flame tube is formed with forwardly-facing louvres 18 and with inlet openings 19, fuel being supplied thereto by injector 20 and ignition initiated by spark device 22. A fairing indicated by broken line 28 may be disposed around the flame tube, air under pressure being supplied to the interior thereof through the hollow strut 23 from the engine compressor. Alternatively the fairing may be extended as indicated at 30 and open at its upstream end forwardly of the reheat fuel injector 15.
GB1514458A 1958-07-23 1958-05-12 Improvements in afterburner combustion equipment of a gas turbine jet propulsion engine Expired GB842197A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH6213358A CH365910A (en) 1958-07-23 1958-07-23 Afterburner on a jet engine

Publications (1)

Publication Number Publication Date
GB842197A true GB842197A (en) 1960-07-20

Family

ID=4524103

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1514458A Expired GB842197A (en) 1958-07-23 1958-05-12 Improvements in afterburner combustion equipment of a gas turbine jet propulsion engine

Country Status (2)

Country Link
CH (1) CH365910A (en)
GB (1) GB842197A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2873168A1 (en) * 2004-07-16 2006-01-20 Snecma Moteurs Sa Jet engine for military aircraft, has afterburner with ignition injector opposite to spark plug and connected to conduit delivering fuel to injector under controlled pressure independent of supply conditions of annular fuel injection ramp
EP3748232A1 (en) * 2019-06-03 2020-12-09 Rolls-Royce plc A fuel spray nozzle arrangement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2873168A1 (en) * 2004-07-16 2006-01-20 Snecma Moteurs Sa Jet engine for military aircraft, has afterburner with ignition injector opposite to spark plug and connected to conduit delivering fuel to injector under controlled pressure independent of supply conditions of annular fuel injection ramp
EP1621817A1 (en) * 2004-07-16 2006-02-01 Snecma Moteurs Afterburner with assured ignition
EP3748232A1 (en) * 2019-06-03 2020-12-09 Rolls-Royce plc A fuel spray nozzle arrangement
US11428412B2 (en) 2019-06-03 2022-08-30 Rolls-Royce Plc Fuel spray nozzle having an aerofoil integral with a feed arm

Also Published As

Publication number Publication date
CH365910A (en) 1962-11-30

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