Rocket engine with cryogenic propellants
US9222438B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 16, 2010 |
| Grant date | Dec 29, 2015 |
| Priority date | — |
| Expiry date | Feb 19, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/64
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cyrogenic-propellant rocket engine includes: at least a first tank for a first liquid propellant; a second tank for a second liquid propellant; a third tank for an inert fluid; an axisymmetrical nozzle including a combustion chamber, a device for injecting first and second liquid propellants into the combustion chamber, a nozzle throat, and a divergent section; and a heater device including at least one duct for conveying the inert fluid and arranged outside the nozzle in immediate proximity thereof, but without making contact therewith, to recover energy of thermal radiation emitted when the rocket engine is in operation and to heat the inert fluid.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.