GB852290A - Engine liquid fuel supply system - Google Patents
Engine liquid fuel supply systemInfo
- Publication number
- GB852290A GB852290A GB3043/57A GB304357A GB852290A GB 852290 A GB852290 A GB 852290A GB 3043/57 A GB3043/57 A GB 3043/57A GB 304357 A GB304357 A GB 304357A GB 852290 A GB852290 A GB 852290A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- pump
- injectors
- pressure
- line
- 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
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
-
- 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
- F02C7/236—Fuel delivery systems comprising two or more pumps
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Safety Valves (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
852,290. Gas turbine engines. ROLLSROYCE Ltd. Jan. 28, 1958 [Jan. 28, 1957], No. 3043/57. Class 110 (3). A fuel system for a continuous combustion gas turbine engine comprises primary and secondary fuel injectors, a main pump with control means metering the total fuel delivery to the injectors, through a main fuel line, branch fuel lines leading from the main fuel line to the primary and secondary fuel injectors respectively and a pressurizing arrangement, including a pump mechanically driven from the engine, in the branch line leading to the primary injector or injectors to ensure adequate pressure for atomization at all total fuel flows. Fuel is supplied to the combustion equipment 41 from a tank 9 by a fuel pump 10. The fuel is heated in an oil cooler 13 and then passed to the control and metering mechanism 14. The fuel pump may be driven by the engine or by an air turbine 8. The fuel dividing system comprises branch lines 17a, 17b leading to a manifold 46 for the primary fuel injectors 15 and to a manifold 47,for the secondary injectors 16. The branch line 17a contains an auxiliary engine-driven pump 18. A relief valve 22 in a by-pass 21 limits the delivery pressure of the pump 18. A fuel recirculating by-pass conduit 23 is also provided around the pump 18. The branch line 17b has a non-return valve 24 and a shut-off cock 25 which is coupled with a shut-off cock 19 in the line 17a. At low fuel flows the suction effect of pump 18 prevents the pressure in the pipe 12 from exceeding that necessary to open the valve 24 so that the whole of the fuel is delivered to the primary injectors 15. As the fuel flow increases, the delivery pressure of the pump 18 increases until the relief valve 22 opens. Any further increase in total fuel flow increases the pressure in the pipe 12 so that the valve 24 opens and allows fuel to flow to the secondary injectors 16. Under some conditions of operation, e.g. at high altitude, the total engine fuel requirements may be so low that cavitation will tend to occur in the pump 18. When cavitation tends to occur there is no flow in branch line 17b so that combustion chamber pressure acts on one side of the land 28a and displaces the piston valve 28 to the right against the action of the inlet pressure of the pump 18 plus the load of the spring 32 (or less the load of the spring when the spring is in chamber 29) until the chamber 30 opens the conduit 23. The pressures in the chambers 30, 31 are balanced by a passage 34. A filter may be incorporated in the line 17a.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3043/57A GB852290A (en) | 1957-01-28 | 1957-01-28 | Engine liquid fuel supply system |
US711036A US3056259A (en) | 1957-01-28 | 1958-01-24 | Engine liquid fuel supply system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3043/57A GB852290A (en) | 1957-01-28 | 1957-01-28 | Engine liquid fuel supply system |
Publications (1)
Publication Number | Publication Date |
---|---|
GB852290A true GB852290A (en) | 1960-10-26 |
Family
ID=9750881
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3043/57A Expired GB852290A (en) | 1957-01-28 | 1957-01-28 | Engine liquid fuel supply system |
Country Status (2)
Country | Link |
---|---|
US (1) | US3056259A (en) |
GB (1) | GB852290A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3147712A (en) * | 1960-09-02 | 1964-09-08 | Gen Motors Corp | Fuel pumping system for gas turbines |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3233651A (en) * | 1962-05-28 | 1966-02-08 | Holley Carburetor Co | Fluid metering system |
US3182596A (en) * | 1963-05-31 | 1965-05-11 | Borg Warner | Hydraulic systems and pumps |
US3398526A (en) * | 1966-07-21 | 1968-08-27 | Turbine Products Inc | Gas turbine and fuel delivery means therefor |
GB1299351A (en) * | 1969-01-31 | 1972-12-13 | Plessey Co Ltd | Improvements in or relating to axial-flow impeller pumps, particularly for volatile liquids |
US3946551A (en) * | 1974-01-17 | 1976-03-30 | United Technologies Corporation | Pumping and metering system |
US4208871A (en) * | 1977-08-29 | 1980-06-24 | The Garrett Corporation | Fuel control system |
US4280323A (en) * | 1978-05-25 | 1981-07-28 | Westinghouse Electric Corp. | Gas turbine fuel control having fuel viscosity compensation to provide improved ignition reliability |
US5036657A (en) * | 1987-06-25 | 1991-08-06 | General Electric Company | Dual manifold fuel system |
US4903478A (en) * | 1987-06-25 | 1990-02-27 | General Electric Company | Dual manifold fuel system |
DE19825335A1 (en) * | 1998-06-05 | 1999-12-09 | Abb Patent Gmbh | Procedure for operation of gas turbine |
GB0023727D0 (en) * | 2000-09-27 | 2000-11-08 | Lucas Industries Ltd | Control system |
US7197879B2 (en) * | 2004-04-29 | 2007-04-03 | Honeywell International, Inc. | Multiple electric fuel metering systems for gas turbine applications |
GB201102772D0 (en) * | 2011-02-17 | 2011-03-30 | Rolls Royce Goodrich Engine Control Systems Ltd | Pumping arrangement |
BR112015024588A2 (en) * | 2013-04-14 | 2017-07-18 | Gen Electric | engine overspeed protection systems |
EP4100688A4 (en) * | 2020-02-05 | 2023-07-19 | Turbogen Ltd. | Boosting cchp gas turbine system |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2669838A (en) * | 1946-09-13 | 1954-02-23 | Niles Bement Pond Co | Fluid pump control apparatus for internal-combustion turbine engines |
US2609662A (en) * | 1947-07-25 | 1952-09-09 | Chrysler Corp | Controlled dashpot for fuel metering devices |
US2678657A (en) * | 1948-04-08 | 1954-05-18 | Curtiss Wright Corp | Liquid fuel distributing apparatus |
US2643514A (en) * | 1948-08-23 | 1953-06-30 | Rolls Royce | Fuel system for gas-turbine engines with means to maintain the fuel supply within desired limits during transient operating conditions |
US2683418A (en) * | 1948-09-10 | 1954-07-13 | Bendix Aviat Corp | Pump |
US2708826A (en) * | 1949-03-30 | 1955-05-24 | United Aircraft Corp | Fuel control for gas turbine |
US2725932A (en) * | 1949-11-08 | 1955-12-06 | Rolls Royce | Fuel system for gas-turbine engines and the like |
US2813394A (en) * | 1950-03-06 | 1957-11-19 | Rolls Royce | Pump arrangements for gas-turbine engine fuel systems |
US2757961A (en) * | 1950-09-07 | 1956-08-07 | Chrysler Corp | Regulated fuel system |
US2836230A (en) * | 1953-01-07 | 1958-05-27 | Gen Electric | Emergency fuel pumping system |
GB743859A (en) * | 1953-02-27 | 1956-01-25 | Rolls Royce | Improvements in or relating to fuel systems for gas-turbine engines |
GB765339A (en) * | 1953-07-28 | 1957-01-09 | Lucas Industries Ltd | Liquid fuel supply systems for prime movers |
US2812715A (en) * | 1954-06-23 | 1957-11-12 | Westinghouse Electric Corp | Fuel system |
-
1957
- 1957-01-28 GB GB3043/57A patent/GB852290A/en not_active Expired
-
1958
- 1958-01-24 US US711036A patent/US3056259A/en not_active Expired - Lifetime
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3147712A (en) * | 1960-09-02 | 1964-09-08 | Gen Motors Corp | Fuel pumping system for gas turbines |
Also Published As
Publication number | Publication date |
---|---|
US3056259A (en) | 1962-10-02 |
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