GB752880A - Internal-combustion-turbine jet propulsion engine fuel systems - Google Patents
Internal-combustion-turbine jet propulsion engine fuel systemsInfo
- Publication number
- GB752880A GB752880A GB2228353A GB2228353A GB752880A GB 752880 A GB752880 A GB 752880A GB 2228353 A GB2228353 A GB 2228353A GB 2228353 A GB2228353 A GB 2228353A GB 752880 A GB752880 A GB 752880A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pipe
- turbine
- fuel
- pump
- supplied
- 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
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
752,880. Gas turbine jet propulsion plant. ROLLS-ROYCE, Ltd. Aug. 12, 1954 [Aug. 12, 1953], No. 22283/53. Class 110(3) In a gas turbine jet propulsion plant having a main and a reheat combustion system, the combustion systems are fed with fuel by separate pumps driven by air turbines which are arranged in series and supplied with air from the compressor of the gas turbine plant. The gas turbine jet propulsion engine 10 has an axial flow compressor 12, main combustion equipment 13, turbine 14, jet pipe 15 and reheat combustion equipment 16. Fuel is supplied to the main injectors 13a from a tank 17 by a booster pump 18 and a main fuel pump 20 which discharges through a control device 22 and a shut off cock 23. The pump 20 is driven by a turbine 26 supplied with air from the compressor 12 through a pipe 24. The exhaust of the turbine 26 passes to a valve 41 by which it may be passed either to a pipe 44 which leads to the exhaust of the turbine 14 or to the pipe 39 which leads to a second turbine 37 which drives a reheat fuel pump 33. The pump 33 is supplied with fuel from a tank 30 by a booster pump 31 and discharges through a control valve 35 and shut off cock 36 to reheat fuel injectors 16a. The pipe 44 may discharge to atmosphere as shown at 45. The turbine 37 exhausts through pipe 47 and nozzles 49 which project into holes 50 in a casing forming a cooling jacket 51 around the jet pipe. The nozzles 49 induce a flow of cooling air through the jacket 51 as described and claimed in Specification 724,004. The pipe 47 may exhaust to atmosphere. Specification 743,859 also is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2228353A GB752880A (en) | 1953-08-12 | 1953-08-12 | Internal-combustion-turbine jet propulsion engine fuel systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2228353A GB752880A (en) | 1953-08-12 | 1953-08-12 | Internal-combustion-turbine jet propulsion engine fuel systems |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB752880A true GB752880A (en) | 1956-07-18 |
Family
ID=10176870
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2228353A Expired GB752880A (en) | 1953-08-12 | 1953-08-12 | Internal-combustion-turbine jet propulsion engine fuel systems |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB752880A (en) |
-
1953
- 1953-08-12 GB GB2228353A patent/GB752880A/en not_active Expired
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