GB861601A - Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller - Google Patents

Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller

Info

Publication number
GB861601A
GB861601A GB2370657A GB2370657A GB861601A GB 861601 A GB861601 A GB 861601A GB 2370657 A GB2370657 A GB 2370657A GB 2370657 A GB2370657 A GB 2370657A GB 861601 A GB861601 A GB 861601A
Authority
GB
United Kingdom
Prior art keywords
valve
diaphragm
engine speed
fuel
controlled
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
GB2370657A
Inventor
John Skellern
Ronald Albert Gilbert
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB2370657A priority Critical patent/GB861601A/en
Priority to DEN15402A priority patent/DE1129343B/en
Publication of GB861601A publication Critical patent/GB861601A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/305—Blade pitch-changing mechanisms characterised by being influenced by other control systems, e.g. 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/30—Control of fuel supply characterised by variable fuel pump output

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Reciprocating Pumps (AREA)
  • High-Pressure Fuel Injection Pump Control (AREA)

Abstract

861,601. Fluid-pressure servomotor-control systems. NAPIER & SON Ltd., D. July 25, 1958 [July 26, 1957], No. 23706/57. Class 135. [Also in Group XXVI] A control system for aircraft power plant comprising a gas turbine coupled to a propeller or helicopter rotor includes a swashplate fuel pump 13, the output of which is controlled in accordance with engine speed, and is passed through a metering valve 43 controlled by a servo mechanism 56, 57, also in accordance with engine speed, whereby the valve has a unique setting for each engine speed. Fuel pump 13 is of the type in which inclination of the swashplate is adjusted by a piston 18 working in a cylinder whose ends are interconnected through an orifice 23 and controlled by a leak-off valve 34 operated by a diaphragm 30 subjected through a port 25 in the pump casing 15 to a pressure proportional to engine speed, the diaphragm also being subjected to the loading of a spring 36, which can be varied by a pilotoperated lever 38 to vary the datum engine speed setting. The longitudinal position of sleeve 43, which is formed with a tapered port 44 furnishing the variable area fuel metering orifice, is adjusted by a power piston 57 controlled by a pilot valve 56 connected to an operating diaphragm 52 subjected to the pressures on the two sides of diaphragm 30. Piston 57 acts upon a valve loading spring 55, and is connected to sleeve 43 by a link 62. The latter is also connected by a link 82 to a lever 81 controlling a fuel dump valve 79, controlling the connection of the fuel supply line to a dump line 76 or the burner line 80. By operating lever 81 the pilot may open the fuel metering orifice to exceed its minimum setting, for engine starting. The pressure drop across metering valve 43 is communicated through pipes 70, 71 to the opposite sides of a diaphragm 73 controlling a bleed valve 75 connected to chamber 20 of the pump governor, to limit the pump output if the pressure drop exceeds a predetermined value;
GB2370657A 1957-07-26 1957-07-26 Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller Expired GB861601A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB2370657A GB861601A (en) 1957-07-26 1957-07-26 Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller
DEN15402A DE1129343B (en) 1957-07-26 1958-07-26 Fuel control device for an aircraft gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2370657A GB861601A (en) 1957-07-26 1957-07-26 Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller

Publications (1)

Publication Number Publication Date
GB861601A true GB861601A (en) 1961-02-22

Family

ID=10199970

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2370657A Expired GB861601A (en) 1957-07-26 1957-07-26 Control mechanism for aircraft power plants comprising a gas turbine engine driving a propeller

Country Status (2)

Country Link
DE (1) DE1129343B (en)
GB (1) GB861601A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3326686A (en) * 1963-05-31 1967-06-20 Gen Aniline & Film Corp Light-sensitive two-component diazotype materials adapted for heat development
DE1270890B (en) * 1961-03-02 1968-06-20 Bendix Corp Fuel control system for gas turbine systems
DE1281753B (en) * 1961-03-30 1968-10-31 Bendix Corp Fuel control system for internal combustion engines, in particular gas turbine systems

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1201615B (en) * 1962-10-27 1965-09-23 Bmw Triebwerkbau Ges M B H Device for controlling the drive unit for a jet helicopter
DE102008013849A1 (en) 2008-03-12 2009-09-17 Weber-Hydraulik Gmbh Control device and its use

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE841665C (en) * 1946-10-25 1952-06-19 Lucas Ltd Joseph Conveyor device for liquid fuel, especially for gas turbines and jet engines
DE830735C (en) * 1949-08-22 1952-02-07 Lucas Ltd Joseph Hydraulic speed controller for power machines
DE907369C (en) * 1950-12-13 1954-03-25 Lucas Ltd Joseph Device for controlling the supply of fuel to an internal combustion engine
DE942955C (en) * 1952-10-16 1956-05-09 Lucas Industries Ltd Device for regulating the fuel supply into the combustion chamber of jet engines, gas turbines or the like.

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1270890B (en) * 1961-03-02 1968-06-20 Bendix Corp Fuel control system for gas turbine systems
DE1281753B (en) * 1961-03-30 1968-10-31 Bendix Corp Fuel control system for internal combustion engines, in particular gas turbine systems
US3326686A (en) * 1963-05-31 1967-06-20 Gen Aniline & Film Corp Light-sensitive two-component diazotype materials adapted for heat development

Also Published As

Publication number Publication date
DE1129343B (en) 1962-05-10

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