Liquid fuel rocket engine with a closed flow cycle
US6470670B2 · kind B2 · utility
14Cited by
2References
9Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 1, 2000 |
| Grant date | Oct 29, 2002 |
| Priority date | — |
| Expiry date | Dec 26, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/48
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A liquid fuel rocket engine with a closed direct auxiliary flow cycle has a combustion chamber connected to each liquid fuel source through a respective main liquid fuel supply line. A turbo pump is provided in each main fuel supply line. The turbo pump is driven by a gas generator which is connected to a first bypass fuel supply line for supplying fuel to the gas generator. An exhaust gas duct (8, 9, 10) leads from the gas generator into at least one main fuel supply line for feeding gas generator exhaust gas into the main fuel supply line upstream of the turbo pump.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.