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GB830007A - Fuel control for gas turbine engine - Google Patents

Fuel control for gas turbine engine

Info

Publication number
GB830007A
GB830007A GB34358/56A GB3435856A GB830007A GB 830007 A GB830007 A GB 830007A GB 34358/56 A GB34358/56 A GB 34358/56A GB 3435856 A GB3435856 A GB 3435856A GB 830007 A GB830007 A GB 830007A
Authority
GB
United Kingdom
Prior art keywords
valve
piston
pump
leak
fuel
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
GB34358/56A
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.)
Bendix Aviation Corp
Original Assignee
Bendix Aviation 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 Bendix Aviation Corp filed Critical Bendix Aviation Corp
Publication of GB830007A publication Critical patent/GB830007A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/10Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners

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

830,007. Gas-turbine jet-propulsion plant. BENDIX AVIATION CORPORATION. Nov. 9, 1956 [Dec. 15, 1955], No. 34358/56. Class 110 (3). [Also in Group XXIX] Control apparatus for gas-turbine engines with afterburner fuel control means 44 comprises a fluid-operated device 109 controlling fuel supply through the control means 44, and two devices controlling fluid supply to the device 109, one 65 being manually actuated and the other 79 being actuated in response to engine speed to permit fluid flow for a range of speeds above a predetermined value. A pump 36 supplies fuel through a main fuel control 34 to the main burners 26 and also up to a piston valve 64 and past a pressure regulator 126 to a cylinder 122 having a leak-off valve 120. A manual throttle lever 54 for the control 34 opens the valve 64 through a cam 56 allowing the pump discharge pressure to pass to a normally closed piston valve 79. On the engine speed reaching a predetermined minimum value set by an adjustment 140, an engine speed sensitive flyweight 112 acts through lever 116 to close the leak-off valve 120 whereby the piston 129 spring connected to the leak-off valve, moves upwards and through its cam 134 closes a leak-off valve 96 whereby the pump discharge pressure builds up beneath a piston 80. As the piston moves up, direct pump pressure is suddenly applied via passage 86 and opens the piston valve 79 to allow pump discharge pressure to pass to the left-hand side of a piston 103 which moves to open the valve 107 allowing fuel to pass through a pump 48 and fuel control 44 to after burners 50. The piston valve 79 is hydraulically locked in its raised position regardless of subsequent engine speed changes. When the lever 54 is moved to allow the valve 65 to close, pump discharge pressure is cut-off at 76 and 86 and spring 82 moves the piston valve 79 downwards to close line 98 and connect both sides of the piston 103 to pump intake pressure via pipe 110 so that spring 105 closes valve 107.
GB34358/56A 1955-12-15 1956-11-09 Fuel control for gas turbine engine Expired GB830007A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US830007XA 1955-12-15 1955-12-15

Publications (1)

Publication Number Publication Date
GB830007A true GB830007A (en) 1960-03-09

Family

ID=22174809

Family Applications (1)

Application Number Title Priority Date Filing Date
GB34358/56A Expired GB830007A (en) 1955-12-15 1956-11-09 Fuel control for gas turbine engine

Country Status (1)

Country Link
GB (1) GB830007A (en)

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