GB763449A - Improvements relating to gas turbine engine fuel systems - Google Patents

Improvements relating to gas turbine engine fuel systems

Info

Publication number
GB763449A
GB763449A GB2501753A GB2501753A GB763449A GB 763449 A GB763449 A GB 763449A GB 2501753 A GB2501753 A GB 2501753A GB 2501753 A GB2501753 A GB 2501753A GB 763449 A GB763449 A GB 763449A
Authority
GB
United Kingdom
Prior art keywords
fuel
pump
heat exchanger
passed
excess
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
GB2501753A
Inventor
Frederick William Walto Morley
Henry Cook
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB2501753A priority Critical patent/GB763449A/en
Publication of GB763449A publication Critical patent/GB763449A/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
    • F02C7/224—Heating fuel before feeding to the burner

Landscapes

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

Abstract

763,449. Gas-turbine plant. ROLLS-ROYCE, Ltd. July 29, 1954 [Sept. 9, 1953], No. 25017/53. Class 110 (3). [Also in Group XXXIV] A gas-turbine fuel system comprising a fuel pump system adapted under some conditions at least to deliver a quantity of fuel in excess of engine requirements and a by-pass to convey the excess fuel directly or indirectly to the inlet side of the fuel pump system has a heat exchanger, through which the engine lubricating oil is passed, connected to the delivery side of the fuel pump system so that the whole or part of the excess fuel passes through it. In the arrangement shown, Fig. 1, fuel from a tank 13 is supplied by a booster pump 14 to a main engine driven positive displacement fuel pump 10 which discharges through a control valve 16 to the gas turbine. The fuel pressure upstream of the valve 16 is maintained by a relief valve 20 and the excess fuel not required by the engine is by-passed back to the tank through ducting 17. A heat exchanger 18 in which lubricating oil is cooled is connected in the delivery pipe 15 of the pump 10 upstream of the ducting 17 so that the full delivery of the pump 10 passes through the heat exchanger. In a modification the heat exchanger 18 is connected in the ducting 17. In another modification, Fig. 3, which comprises a fuel system as described in Specification 763,448, an additional fuel pump 11, driven by an air turbine 21 is provided. This system is arranged so that in the low-speed range the output of the pump 11 is by-passed and in the high-speed range the output of the pump 10 is by-passed. The heat exchanger 18 is arranged in the by-pass ducting 17. In a modification of this arrangement only the fuel from the pump 10 is by-passed through the heat exchanger 18, the excess fuel from the pump 11 being by-passed through a duct 17A direct to downstream of the heat exchanger. An additional duct 17B with an orifice 22 may also be provided to ensure a fuel flow through the heat exchanger.
GB2501753A 1953-09-09 1953-09-09 Improvements relating to gas turbine engine fuel systems Expired GB763449A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2501753A GB763449A (en) 1953-09-09 1953-09-09 Improvements relating to gas turbine engine fuel systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2501753A GB763449A (en) 1953-09-09 1953-09-09 Improvements relating to gas turbine engine fuel systems

Publications (1)

Publication Number Publication Date
GB763449A true GB763449A (en) 1956-12-12

Family

ID=10220869

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2501753A Expired GB763449A (en) 1953-09-09 1953-09-09 Improvements relating to gas turbine engine fuel systems

Country Status (1)

Country Link
GB (1) GB763449A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000180A (en) * 1957-04-04 1961-09-19 Napier & Son Ltd Engines for high speed aircraft or missiles
US3095706A (en) * 1958-09-08 1963-07-02 Gen Motors Corp Gas turbine fuel nozzle cooling
DE2631748A1 (en) * 1975-07-17 1977-02-03 Gen Electric OIL COOLING SYSTEM FOR A GAS TURBINE ENGINE
US4354345A (en) * 1980-04-29 1982-10-19 United Technologies Corporation Fuel heating system for gas turbine engine
GB2260577A (en) * 1991-10-16 1993-04-21 Rolls Royce Plc Gas turbine engine starting
US5272870A (en) * 1991-09-25 1993-12-28 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Cooling arrangement for jet engines
EP1769208A2 (en) * 2004-06-30 2007-04-04 Argo-Tech Corporation Improved heat exchanger performance

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000180A (en) * 1957-04-04 1961-09-19 Napier & Son Ltd Engines for high speed aircraft or missiles
US3095706A (en) * 1958-09-08 1963-07-02 Gen Motors Corp Gas turbine fuel nozzle cooling
DE2631748A1 (en) * 1975-07-17 1977-02-03 Gen Electric OIL COOLING SYSTEM FOR A GAS TURBINE ENGINE
FR2318314A1 (en) * 1975-07-17 1977-02-11 Gen Electric FUEL SUPPLY AND CONTROL SYSTEM
US4354345A (en) * 1980-04-29 1982-10-19 United Technologies Corporation Fuel heating system for gas turbine engine
US5272870A (en) * 1991-09-25 1993-12-28 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Cooling arrangement for jet engines
GB2260577A (en) * 1991-10-16 1993-04-21 Rolls Royce Plc Gas turbine engine starting
US5253470A (en) * 1991-10-16 1993-10-19 Rolls-Royce Plc Gas turbine engine starting
GB2260577B (en) * 1991-10-16 1994-10-05 Rolls Royce Plc Gas turbine engine starting
EP1769208A2 (en) * 2004-06-30 2007-04-04 Argo-Tech Corporation Improved heat exchanger performance
EP1769208A4 (en) * 2004-06-30 2010-12-29 Argo Tech Corp Improved heat exchanger performance
US7983541B2 (en) 2004-06-30 2011-07-19 Eaton Industrial Corporation Heat exchanger performance

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