GB876186A - High output power plant, for example, rocket engines - Google Patents
High output power plant, for example, rocket enginesInfo
- Publication number
- GB876186A GB876186A GB32887/58A GB3288758A GB876186A GB 876186 A GB876186 A GB 876186A GB 32887/58 A GB32887/58 A GB 32887/58A GB 3288758 A GB3288758 A GB 3288758A GB 876186 A GB876186 A GB 876186A
- Authority
- GB
- United Kingdom
- Prior art keywords
- supplied
- hydrogen
- liquid
- duct
- turbine
- 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
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
Abstract
876,186. Generating combustion products under pressure. UNITED AIRCRAFT CORPORATION. Oct. 15, 1958 [Oct. 29, 1957], No. 32887/58. Class 51 (1). [Also in Group XXVI] A power plant, for example a rocket engine, comprises a combustion chamber having a discharge nozzle through which combustion gases are delivered, liquid fuel being delivered by a pump and then heated, being thereby gasified, a portion of the gasified fuel being supplied as working fluid to a turbine which drives the liquid fuel pump, the remainder of the gasified fuel being delivered directly to the combustion chamber to which an oxidizer is also supplied. The invention is shown applied to a rocket motor which comprises a combustion section 10 and a propulsion nozzle 30, the combustion section comprising an outer casing 12 and an inner flame tube 14 having inlet openings 16, 24, 28. Gaseous hydrogen is supplied to the space between the flame tube and outer casing through nozzles 18, 20, hydrogen entering the flame tube through the openings 16, 24, and 28 that entering through opening 28 forming a cooling, layer on the surface of the propulsion nozzle. Liquid oxygen is supplied through injectors 22 into the flame tube. Liquid oxygen and liquid hydrogen are stored in containers 34, 36 respectively, and liquid hydrogen is supplied through duct 38 to pump 40, thence through a heat exchanger formed by a plurality of tubes 42 surrounding the propulsion nozzle, the liquid hydrogen being thereby gasified. A part of the gaseous hydrogen passes through duct 50 to the injector 18, while the remainder flows through duct 52 to turbine 54. The hydrogen exhausting from the turbine passes through duct 58 to injector 20. Liquid oxygen from the container 34 is supplied by pump 56 to the injectors 22. The pumps 40 and 56 are driven by the turbine 54. For starting, the propulsion nozzle may be supplied with an inner core 60 having an electric heating coil 62; also, at starting, the pumps 40 and 56 are driven by an electric motor 68.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US876186XA | 1957-10-29 | 1957-10-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB876186A true GB876186A (en) | 1961-08-30 |
Family
ID=22206252
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB32887/58A Expired GB876186A (en) | 1957-10-29 | 1958-10-15 | High output power plant, for example, rocket engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB876186A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2921979A1 (en) * | 2007-10-08 | 2009-04-10 | Astrium Sas Soc Par Actions Si | DEVICE AND METHOD FOR PUMP MOTORIZATION FOR INTERNAL COMBUSTION ENGINE FUSE ENGINE |
| FR2991391A1 (en) * | 2012-05-30 | 2013-12-06 | Snecma | Feeding device for feeding cryogenic propellant e.g. liquid oxygen, into propellant chamber of rocket engine, has tank containing cryogenic propellant, and electric pump connected within tank for pumping propellant through feeding circuit |
| CN109357287A (en) * | 2018-11-21 | 2019-02-19 | 贵州智慧能源科技有限公司 | Segmented rocket engine combustion chamber and power drive unit |
| US10669943B2 (en) | 2011-02-17 | 2020-06-02 | Rolls-Royce Plc | Fuel pumping arrangement for an aircraft engine |
| CN112555056A (en) * | 2020-12-02 | 2021-03-26 | 西安航天动力研究所 | Afterburning circulating liquid engine core system thermal test device and parameter coordination method |
-
1958
- 1958-10-15 GB GB32887/58A patent/GB876186A/en not_active Expired
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2921979A1 (en) * | 2007-10-08 | 2009-04-10 | Astrium Sas Soc Par Actions Si | DEVICE AND METHOD FOR PUMP MOTORIZATION FOR INTERNAL COMBUSTION ENGINE FUSE ENGINE |
| WO2009047250A3 (en) * | 2007-10-08 | 2009-06-25 | Astrium Sas | Method and device enabling a rocket engine pump to be driven by an internal combustion engine |
| US8430361B2 (en) | 2007-10-08 | 2013-04-30 | Astrium Sas | Method and device enabling a rocket engine pump to be driven by an internal combustion engine |
| US10669943B2 (en) | 2011-02-17 | 2020-06-02 | Rolls-Royce Plc | Fuel pumping arrangement for an aircraft engine |
| FR2991391A1 (en) * | 2012-05-30 | 2013-12-06 | Snecma | Feeding device for feeding cryogenic propellant e.g. liquid oxygen, into propellant chamber of rocket engine, has tank containing cryogenic propellant, and electric pump connected within tank for pumping propellant through feeding circuit |
| CN109357287A (en) * | 2018-11-21 | 2019-02-19 | 贵州智慧能源科技有限公司 | Segmented rocket engine combustion chamber and power drive unit |
| CN112555056A (en) * | 2020-12-02 | 2021-03-26 | 西安航天动力研究所 | Afterburning circulating liquid engine core system thermal test device and parameter coordination method |
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