GB664758A - Improvements in or relating to accumulator devices for aircraft engine fuel systems - Google Patents
Improvements in or relating to accumulator devices for aircraft engine fuel systemsInfo
- Publication number
- GB664758A GB664758A GB373549A GB373549A GB664758A GB 664758 A GB664758 A GB 664758A GB 373549 A GB373549 A GB 373549A GB 373549 A GB373549 A GB 373549A GB 664758 A GB664758 A GB 664758A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- pressure
- accumulator
- gas
- conduit
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
Abstract
664,758. Gas turbine fuel system. ROLLSROYCE, Ltd. Feb. 10, 1950 [Feb. 10, 1949], No. 3735/49. Class 110(iii) [Also in Groups XI, XXVII, XXVIII and XXIX] An accumulator for a gas turbine engine fuel system comprises a closed chamber with a flexible diaphragm arranged to divide the chamber into two spaces, one of which is connected to the fuel supply system and the other to a source of pressure gas so that the pressure in the second space is substantially constant and is less than the fuel pressure under normal flying conditions. The accumulator shown comprises two hemispherical parts 10, 11, bolted together by flanges 12. The flanges 12 also grip a flexible diaphragm 27 which can lie against one or other of the hemispherical liners 25 mounted in and spaced from the parts 10, 11. The part 11 is connected through a T-shaped union 14 to the fuel supply line 15 and the part 10 to a point on the gas turbine compressor through a conduit 21. A pair of fixed orifices are mounted in the conduit 21 and these together with a relief valve are arranged so that the gas pressure in the part 10 does not exceed the fuel pressure under normal conditions and remains constant. When the fuel pressure falls for any reason, e.g. negative " g " conditions, the gas pressure from the conduit 21 will force fuel from the accumulator to the feed line 15. A non-return valve is provided to prevent the flow of this fuel back into the tank. The relief valve may be connected by a pipeline to the air space above the fuel in the tank so that if the flexible diaphragm is punctured or leaks no fuel is lost.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB373549A GB664758A (en) | 1949-02-10 | 1949-02-10 | Improvements in or relating to accumulator devices for aircraft engine fuel systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB373549A GB664758A (en) | 1949-02-10 | 1949-02-10 | Improvements in or relating to accumulator devices for aircraft engine fuel systems |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB664758A true GB664758A (en) | 1952-01-09 |
Family
ID=9763962
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB373549A Expired GB664758A (en) | 1949-02-10 | 1949-02-10 | Improvements in or relating to accumulator devices for aircraft engine fuel systems |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB664758A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110030116A (en) * | 2018-12-13 | 2019-07-19 | 西安航天动力研究所 | One kind can single or multiple igniting suction half membrane type ignition modules of extruding and working method and igniting agent charging method |
| CN112594094A (en) * | 2020-12-18 | 2021-04-02 | 西安航天动力研究所 | Engine starting ignition device and ignition method based on preinstalled intermediate medium |
-
1949
- 1949-02-10 GB GB373549A patent/GB664758A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110030116A (en) * | 2018-12-13 | 2019-07-19 | 西安航天动力研究所 | One kind can single or multiple igniting suction half membrane type ignition modules of extruding and working method and igniting agent charging method |
| CN110030116B (en) * | 2018-12-13 | 2021-01-12 | 西安航天动力研究所 | Semi-membrane type ignition module capable of achieving single or multiple ignition, suction and extrusion, working method and igniter filling method |
| CN112594094A (en) * | 2020-12-18 | 2021-04-02 | 西安航天动力研究所 | Engine starting ignition device and ignition method based on preinstalled intermediate medium |
| CN112594094B (en) * | 2020-12-18 | 2022-03-04 | 西安航天动力研究所 | Engine starting ignition device and ignition method based on preinstalled intermediate medium |
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