GB761182A - Improvements in or relating to gas turbine engines and more particularly jet turbine engines - Google Patents

Improvements in or relating to gas turbine engines and more particularly jet turbine engines

Info

Publication number
GB761182A
GB761182A GB20343/54A GB2034354A GB761182A GB 761182 A GB761182 A GB 761182A GB 20343/54 A GB20343/54 A GB 20343/54A GB 2034354 A GB2034354 A GB 2034354A GB 761182 A GB761182 A GB 761182A
Authority
GB
United Kingdom
Prior art keywords
compressor
auxiliary
air
turbine
supplied
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
GB20343/54A
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB761182A publication Critical patent/GB761182A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/236—Fuel delivery systems comprising two or more pumps
    • F02C7/2365—Fuel delivery systems comprising two or more pumps comprising an air supply system for the atomisation of fuel
    • 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
    • F23R3/24—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants of the fluid-screen type

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

761,182. Gas turbine Jet-propulsion plant. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. July 12, 1954 [July 15, 1953], No. 20343/54. Class 110 (3). [Also in Group XII] In a gas turbine engine, the combustion equipment is provided with flame stabilizing means constituted by a gaseous screen formed by a jet or jets of gas, for example air, issuing transversely to the flow of combustion gases through the equipment. The air supply for the screen is from an auxiliary compressor which supplies the air at a pressure greater than that supplied by the main engine compressor. The engine shown comprises an air compressor 1, turbine 5 and combustion equipment 3, the stabilizing screen being formed by jets of air issuing transversely through apertures 8, 8a in the hollow ring members 7, 7a. Fuel is supplied in an upstream direction through nozzle 4. Air is tapped from the main compressor discharge at 13 and is further compressed in the auxiliary centrifugal compressor 11 and passes by way of pipes 10 to the hollow ring members 7, 7a. Additional fuel may be supplied through an injector 4a into the air delivered by the auxiliary compressor. The auxiliary compressor is driven by a turbine 14 supplied with combustion gases tapped from the discharge of the combustion equipment 3, the exhaust from the turbine 14 passing through an auxiliary propulsion nozzle 17. The auxiliary compressor may alternatively be driven by the main turbine 5 by means of suitable gearing or it could be mounted on the main turbine-compressor shaft. The auxiliary turbine 14 may be supplied with gases from auxiliary combustion equipment supplied with air from the main compressor 1. Specifications 751,013, 751,098 and 761,167, [all in Group XII], are referred to.
GB20343/54A 1953-07-15 1954-07-12 Improvements in or relating to gas turbine engines and more particularly jet turbine engines Expired GB761182A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR761182X 1953-07-15

Publications (1)

Publication Number Publication Date
GB761182A true GB761182A (en) 1956-11-14

Family

ID=9172137

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20343/54A Expired GB761182A (en) 1953-07-15 1954-07-12 Improvements in or relating to gas turbine engines and more particularly jet turbine engines

Country Status (1)

Country Link
GB (1) GB761182A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4543785A (en) * 1982-07-07 1985-10-01 Hugh Patrick Turbo-ram-jet engine
GB2157371A (en) * 1984-02-10 1985-10-23 Hugh Patrick Combined turbo-jet and ram-jet engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4543785A (en) * 1982-07-07 1985-10-01 Hugh Patrick Turbo-ram-jet engine
GB2157371A (en) * 1984-02-10 1985-10-23 Hugh Patrick Combined turbo-jet and ram-jet engine

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