GB819463A - Improved gas turbine engine fuel system - Google Patents

Improved gas turbine engine fuel system

Info

Publication number
GB819463A
GB819463A GB3095256A GB3095256A GB819463A GB 819463 A GB819463 A GB 819463A GB 3095256 A GB3095256 A GB 3095256A GB 3095256 A GB3095256 A GB 3095256A GB 819463 A GB819463 A GB 819463A
Authority
GB
United Kingdom
Prior art keywords
valve
fuel
rotor
pump
engine
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
GB3095256A
Inventor
Robert Noel Penny
Charles Spencer King
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.)
Rover Co Ltd
Original Assignee
Rover Co 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 Rover Co Ltd filed Critical Rover Co Ltd
Priority to GB3095256A priority Critical patent/GB819463A/en
Priority to CH5150557A priority patent/CH368659A/en
Publication of GB819463A publication Critical patent/GB819463A/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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D3/00—Controlling low-pressure fuel injection, i.e. where the fuel-air mixture containing fuel thus injected will be substantially compressed by the compression stroke of the engine, by means other than controlling only an injection pump
    • F02D3/02—Controlling low-pressure fuel injection, i.e. where the fuel-air mixture containing fuel thus injected will be substantially compressed by the compression stroke of the engine, by means other than controlling only an injection pump with continuous injection or continuous flow upstream of the injection nozzle

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)

Abstract

819,463. Swash plate pumps. ROVER CO. Ltd. Oct. 9, 1957 [Oct. 11, 1956], No. 30952/56. Class 102(1). [Also in Group XXVI] In a gas turbine engine fuel system including a fuel pump and a valve which is entirely carried by and rotatable with an engine driven part, the valve includes a closure member supported solely by biassing means carried by the engine driven part and arranged to open, at a predetermined speed, by centrifugal force acting on the closure member acting against the bias. The fuel pump body, Fig. 1, comprises a barrel 11 secured between end plates 12, 13. The end plate 12 has a hub 16 which provides a long bearing for the pump rotor shaft 17. The inner end of the shaft 17 is formed as a rotor 23 provided with a circular arrangement of axial bores containing pistons 24 which are urged by springs 28 towards a cam track 27 integral with the end plate 13. Fuel from a reservoir (not shown) is supplied by a pipe 29, filter 30 and ducts 31, 32 to the interior of the pump body from which it is sucked by the pistons 24 moving outwards from the rotor. As the pistons 24 move inwards, fuel is discharged through ducts 38, 39 recess 40, duct 41, annular groove 42, ducts 45, 46, 47, 48 and pipe 50 to the burners. The rotor 23 carries a centrifugally operated valve comprising a valve body 51 and a half-ball member 53 attached to the free end of a leaf spring 55. The spring 55 is attached to the rotor by a bracket 57 and screw 58. When a predetermined speeed is reached, the valve member 53 is lifted off its seat and fuel is bypassed back to the pump inlet. A relief valve 122 may be provided to allow a burner to be shut down while the pump is running. A half-ball member 91 mounted on a pivoted lever 90 and urged to the closed position by a spring 94 is lifted off its seat by a Bourden tube when a predetermined temperature of an engine part is exceeded. In a modification the loading of the relief valve 122 is made variable by manual means to allow the speed to be controlled below the limit imposed by the centrifugally operated valve 53. In another modification, a second centrifugally operated valve is arranged in parallel with the centrifugally operated valve previously referred to. The loading of this second valve is variable by the driver so as to control the speed of the engine between the maximum and minimum valves.
GB3095256A 1956-10-11 1956-10-11 Improved gas turbine engine fuel system Expired GB819463A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB3095256A GB819463A (en) 1956-10-11 1956-10-11 Improved gas turbine engine fuel system
CH5150557A CH368659A (en) 1956-10-11 1957-10-11 Device for supplying fuel to a gas turbine unit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3095256A GB819463A (en) 1956-10-11 1956-10-11 Improved gas turbine engine fuel system

Publications (1)

Publication Number Publication Date
GB819463A true GB819463A (en) 1959-09-02

Family

ID=10315668

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3095256A Expired GB819463A (en) 1956-10-11 1956-10-11 Improved gas turbine engine fuel system

Country Status (2)

Country Link
CH (1) CH368659A (en)
GB (1) GB819463A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1177875B (en) * 1960-03-01 1964-09-10 Lucas Industries Ltd Fuel pump

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1177875B (en) * 1960-03-01 1964-09-10 Lucas Industries Ltd Fuel pump

Also Published As

Publication number Publication date
CH368659A (en) 1963-04-15

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