Rocket engine propulsion system
US8572948B1 · kind B1 · utility
7Cited by
4References
11Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Oct 15, 2010 |
| Grant date | Nov 5, 2013 |
| Priority date | — |
| Expiry date | Aug 23, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/64
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket propulsion system having a liquid fuel tank and a liquid oxidizer tank, where a liquid inert gas tank supplies liquid inert gas to a liquid inert gas pump driven by a turbine of the engine to pressurize the liquid inert gas, which is passed through a heat exchanger around the nozzle to vaporize the inert gas, that is then used to pressurize the liquid oxidizer tank so that a liquid oxidizer pump is not needed, or to pressurize both the liquid oxidizer tank and the liquid fuel tank so that a liquid oxidizer pump and a liquid fuel pump are not needed in the rocket engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.