GB870266A - Multistage high altitude engine with single combustion stack - Google Patents
Multistage high altitude engine with single combustion stackInfo
- Publication number
- GB870266A GB870266A GB2528557A GB2528557A GB870266A GB 870266 A GB870266 A GB 870266A GB 2528557 A GB2528557 A GB 2528557A GB 2528557 A GB2528557 A GB 2528557A GB 870266 A GB870266 A GB 870266A
- Authority
- GB
- United Kingdom
- Prior art keywords
- hydrogen
- heat
- turbine
- burnt
- 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
- 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
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
Abstract
870,266. Generating combustion products under pressure. GARRETT CORPORATION. Aug. 9, 1957, No. 25285/57. Class 51 (1). [Also in Group XXVI] A multistage turbine is supplied with heated hydrogen gas as a working fluid. The exhaust hydrogen from the final stage is burnt, with an oxidant, in one side of a heat-exchanger to heat the supply hydrogen to the turbine. The three turbine stages 31, 33, 37 are connected through heat-exchangers 22, 27 and are supplied with hydrogen from tank 12 through the heat-exchanger 17. The latter is heated by exhaust hydrogen from the stage 37, burnt in combustion chamber 39 with liquid oxygen from tank 41. After leaving 17 the hydrogen is cooled in heat-exchangers 22, 27 before entry to the turbine first stage 31. 22 and 27 heat the hydrogen before entry to the succeeding stages 33, 37. In the case of an aircraft engine, the combustion chamber 39 may be supplied with either oxygen or air. In addition, unburnt hydrogen leaving the heatexchanger is burnt in an after-burner in the propulsion unit nozzle. Specification 870,271 is referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2528557A GB870266A (en) | 1957-08-09 | 1957-08-09 | Multistage high altitude engine with single combustion stack |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2528557A GB870266A (en) | 1957-08-09 | 1957-08-09 | Multistage high altitude engine with single combustion stack |
Publications (1)
Publication Number | Publication Date |
---|---|
GB870266A true GB870266A (en) | 1961-06-14 |
Family
ID=10225233
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2528557A Expired GB870266A (en) | 1957-08-09 | 1957-08-09 | Multistage high altitude engine with single combustion stack |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB870266A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2636674A1 (en) * | 1988-09-16 | 1990-03-23 | Gen Electric | DEVICE AND METHOD FOR GENERATING ELECTRICITY |
-
1957
- 1957-08-09 GB GB2528557A patent/GB870266A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2636674A1 (en) * | 1988-09-16 | 1990-03-23 | Gen Electric | DEVICE AND METHOD FOR GENERATING ELECTRICITY |
GB2225059A (en) * | 1988-09-16 | 1990-05-23 | Gen Electric | Gas turbine electricity generation |
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