GB901442A - Improvements in fuel injection system for a combustion chamber of a gas turbine engine - Google Patents

Improvements in fuel injection system for a combustion chamber of a gas turbine engine

Info

Publication number
GB901442A
GB901442A GB1739661A GB1739661A GB901442A GB 901442 A GB901442 A GB 901442A GB 1739661 A GB1739661 A GB 1739661A GB 1739661 A GB1739661 A GB 1739661A GB 901442 A GB901442 A GB 901442A
Authority
GB
United Kingdom
Prior art keywords
fuel
valve
spray bar
assemblies
spray
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
GB1739661A
Inventor
Gregory Edward Mceneny
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
Priority to GB1739661A priority Critical patent/GB901442A/en
Priority claimed from CH681761A external-priority patent/CH392154A/en
Publication of GB901442A publication Critical patent/GB901442A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F02C7/232—Fuel valves; Draining valves or systems
    • 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)
  • Fuel-Injection Apparatus (AREA)

Abstract

901,442. Jet propulsion plant. GENERAL ELECTRIC CO. May 12, 1961, No. 17396/61. Class 110 (3). A fuel injection system for a combustion chamber of a gas turbine engine comprises a plurality of spray bar assemblies disposed at circumferentially-spaced positions within the combustion chamber, the assemblies being interconnected by a manifold, valve means being provided between the manifold and each of the spray bar assemblies, each of the valve means affording parallel fuel flow paths to its associated spray bar assembly. Each fuel flow path is provided with a control-valve, the control valves being pre-set to open at different fuel flow pressures whereby one flow path is opened during relatively low fuel pressure to supply fuel to the spray bar assembly, and whereby another fuel flow path is opened during relatively higher fuel flow pressure to supply fuel to the spray bar assembly in conjunction with the fuel supplied through the first flow path. A reheat combustion system of a gas turbine jet engine is shown in Fig. 1, fuel being supplied from a tank 22 through a main fuel pump 24 to the main combustion system, and through a reheat fuel pump 26 and control valve 28 to a manifold 30 and thence to groups of spray bars 33 disposed within the reheat combustion chamber 16. A series of valve assemblies 38 is connected to the manifold 30, each of the valve assemblies having a group of spray bars 40, 42, 44, 46, 48 connected thereto, the spray bars having fuel distributing orifices 50, 52, 54, 56, 58. Each valve assembly 38 is divided by a wall 65 into a primary chamber 66 and a secondary chamber 68 and fuel passes into the chambers under the control of primary valve 70 and secondary valve 72, respectively, the valve 70 being arranged to open at a lower fuel pressure than valve 72. Fuel passes from the primary chamber 66 through a series of metering orifices 78, and from the secondary chamber 68 through a series of metering orifices 80, the orifices 78 and 80 being connected in pairs to each of the spray bars, the connection to the spray bar 42 being shown in Fig. 5.
GB1739661A 1961-05-12 1961-05-12 Improvements in fuel injection system for a combustion chamber of a gas turbine engine Expired GB901442A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1739661A GB901442A (en) 1961-05-12 1961-05-12 Improvements in fuel injection system for a combustion chamber of a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1739661A GB901442A (en) 1961-05-12 1961-05-12 Improvements in fuel injection system for a combustion chamber of a gas turbine engine
CH681761A CH392154A (en) 1961-06-12 1961-06-12 Fuel injection system

Publications (1)

Publication Number Publication Date
GB901442A true GB901442A (en) 1962-07-18

Family

ID=25700228

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1739661A Expired GB901442A (en) 1961-05-12 1961-05-12 Improvements in fuel injection system for a combustion chamber of a gas turbine engine

Country Status (1)

Country Link
GB (1) GB901442A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4992418A (en) * 1972-09-05 1974-09-03
FR2476230A1 (en) * 1980-02-19 1981-08-21 Gen Electric FUEL INJECTION SYSTEM FOR A GAS TURBINE ENGINE PUSH INCREASE
EP2189720A1 (en) * 2008-11-21 2010-05-26 Siemens Aktiengesellschaft Burner assembly

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2476230A1 (en) * 1980-02-19 1981-08-21 Gen Electric FUEL INJECTION SYSTEM FOR A GAS TURBINE ENGINE PUSH INCREASE
EP2189720A1 (en) * 2008-11-21 2010-05-26 Siemens Aktiengesellschaft Burner assembly
WO2010057709A1 (en) * 2008-11-21 2010-05-27 Siemens Aktiengesellschaft Burner arrangement

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