GB735913A - Improvements in or relating to gas-turbine engine fuel systems - Google Patents
Improvements in or relating to gas-turbine engine fuel systemsInfo
- Publication number
- GB735913A GB735913A GB8977/53A GB897753A GB735913A GB 735913 A GB735913 A GB 735913A GB 8977/53 A GB8977/53 A GB 8977/53A GB 897753 A GB897753 A GB 897753A GB 735913 A GB735913 A GB 735913A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- pump
- engine
- tank
- deliver
- 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
- F02C7/236—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)
- Fuel-Injection Apparatus (AREA)
Abstract
735,913. Centrifugal pumps ; gas turbines. ROLLS-ROYCE, Ltd. May 14, 1953 [March 31, 1953 ; May 20, 1952], Nos. 8977/53 and 11457/53. Divided out of 735,874. Classes 110 (1) and 110 (3). In a gas turbine installation, having a fuel system comprising a centrifugal pump designed to deliver a quantity of fuel greater than that required in the combustion equipment has a conduit to bleed fuel from the delivery of the pump and to deliver it to a heat exchanger where it is cooled and restricting means in the conduit so that part of the fuel discharged by the pump is delivered to the combustion equipment and part to the heat exchanger. In the arrangement shown, fuel is supplied to the combustion equipment 11 by an engine-driven pump 19 through a pipe line 17, throttle 18 and injectors 15. To prevent boiling of the fuel after it has passed through the throttle 18 due to the excessive heating of the fuel as the result of the reduction of the quantity of fuel delivered by the pump at high altitudes, the pump 19 is arranged to deliver a quantity of fuel greater than the maximum amount required by the engine and the excess fuel is returned to the fuel tank 121 by a pipe line 127 having a fixed area restrictor 128. The fuel tank is cooled and in the arrangement shown, the walls of the tank form the surface of the aircraft wing. In a modification, a cooler is arranged in the pipe line 127 between the restrictor 128 and the tank 121. In a further modification the restrictor 128 is replaced by an hydraulic motor which may be arranged to drive a booster pump 122 or a fuel pressure pump of an auxiliary fuel system. The auxiliary fuel system may supply fuel to the exhaust pipe of a jet propulsion engine or to a reheat combustion chamber arranged between two turbines of a compound gas turbine engine. The conduit 127 may be connected to the discharge volute of the pump 19 and discharge into a low pressure pipe-line upstream of the centrifugal pump 19.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB320507X | 1952-05-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB735913A true GB735913A (en) | 1955-08-31 |
Family
ID=10332391
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8977/53A Expired GB735913A (en) | 1952-05-20 | 1953-03-31 | Improvements in or relating to gas-turbine engine fuel systems |
Country Status (3)
| Country | Link |
|---|---|
| CH (1) | CH320507A (en) |
| FR (1) | FR1080810A (en) |
| GB (1) | GB735913A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10316689B2 (en) | 2016-08-22 | 2019-06-11 | Rolls-Royce Corporation | Gas turbine engine health monitoring system with shaft-twist sensors |
| WO2019215228A1 (en) * | 2018-05-08 | 2019-11-14 | Eaton Intelligent Power Limited | A fuel boost pump assembly for an aircraft |
-
1953
- 1953-03-31 GB GB8977/53A patent/GB735913A/en not_active Expired
- 1953-05-19 FR FR1080810D patent/FR1080810A/en not_active Expired
- 1953-05-20 CH CH320507D patent/CH320507A/en unknown
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10316689B2 (en) | 2016-08-22 | 2019-06-11 | Rolls-Royce Corporation | Gas turbine engine health monitoring system with shaft-twist sensors |
| WO2019215228A1 (en) * | 2018-05-08 | 2019-11-14 | Eaton Intelligent Power Limited | A fuel boost pump assembly for an aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| FR1080810A (en) | 1954-12-14 |
| CH320507A (en) | 1957-03-31 |
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