GB718427A - Improvements in continuous flow internal combustion engines, and in particular turbo-jets or turbo-props - Google Patents

Improvements in continuous flow internal combustion engines, and in particular turbo-jets or turbo-props

Info

Publication number
GB718427A
GB718427A GB15861/51A GB1586151A GB718427A GB 718427 A GB718427 A GB 718427A GB 15861/51 A GB15861/51 A GB 15861/51A GB 1586151 A GB1586151 A GB 1586151A GB 718427 A GB718427 A GB 718427A
Authority
GB
United Kingdom
Prior art keywords
fuel
valve
flow
pilot
burners
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
GB15861/51A
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.)
Office National dEtudes et de Recherches Aerospatiales ONERA
Original Assignee
Office National dEtudes et de Recherches Aerospatiales ONERA
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 Office National dEtudes et de Recherches Aerospatiales ONERA filed Critical Office National dEtudes et de Recherches Aerospatiales ONERA
Publication of GB718427A publication Critical patent/GB718427A/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
    • F02C7/228—Dividing fuel between various 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)

Abstract

718,427. Gas turbine plant. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES (O.N.E.R.A.). July 4, 1951 [July 4, 1950], No. 15861/51. Class 110(3) [Also in Group XII] A gas turbine plant having a combustion chamber including a pilot injection device and a main fuel injection device located upstream of the pilot device fed from a common fuel supply has means for varying the distribution of fuel between the two devices so that. during operation, a minimum quantity of fuel is always fed to the pilot device and has part of the flow of air deflected upstream of the main injection device and re-introduced into the flow downstream of the combustion zone. Fuel is supplied to a combustion chamber 1, Fig. 1, by means of a burner 5 and pilot burners 3 located downstream of the burners 5. The fuel supply conduits 4, 6 are controlled by a slide valve 11, Fig. 6. The valve 11 I is loaded by a spring 14 towards the left hand end of the casing 10 to which th.e fuel is supplied by a pipe 9. At low fuel flow, the valve 11 is at the left hand end of the casing 10 so that fuel is supplied through the longitudinal grooves 13 to the conduits 4 and pilot burners 3 only. As the fuel flow increases, the valve 11 moves to the right and allows fuel to flow through the conduits 6 to the burners 5. A passage 12 through the valve 11 balances the static pressures on each end of the valve. To vary the value of the fuel pressure at which this change over occurs in accordance with the air flow, a threaded plug 15 is provided to vary the loading of the spring 14. The plug 15 is rotated through gearing 16, 17 by means of a piston 18 subject to the air pressure at the compressor discharge. An annular form of combustion chamber is also described.
GB15861/51A 1950-07-04 1951-07-04 Improvements in continuous flow internal combustion engines, and in particular turbo-jets or turbo-props Expired GB718427A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR718427X 1950-07-04

Publications (1)

Publication Number Publication Date
GB718427A true GB718427A (en) 1954-11-17

Family

ID=9090573

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15861/51A Expired GB718427A (en) 1950-07-04 1951-07-04 Improvements in continuous flow internal combustion engines, and in particular turbo-jets or turbo-props

Country Status (1)

Country Link
GB (1) GB718427A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1978307A3 (en) * 2007-04-05 2010-03-24 Kawasaki Jukogyo Kabushiki Kaisha Combustor of a gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1978307A3 (en) * 2007-04-05 2010-03-24 Kawasaki Jukogyo Kabushiki Kaisha Combustor of a gas turbine engine
US8572977B2 (en) 2007-04-05 2013-11-05 Kawasaki Jukogyo Kabushiki Kaisha Combustor of a gas turbine engine

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