Method and device for supplying a space propulsion engine with liquid cryogenic propellants
US8720184B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Apr 14, 2008 |
| Grant date | May 13, 2014 |
| Priority date | — |
| Expiry date | Sep 4, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/87153
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Disclosed are a method and device for supplying a combustion chamber of a space propulsion engine with cryogenic liquid fuel and oxidizer propellants. The propellants are mixed at constant pressure to produce a propellant mixture, with the propellants being mixed at a location upstream of an orifice of a propellant injector. The propellant mixture is fed to an enclosure of the propellant injector, and from the propellant injector enclosure, the propellant mixture is injected into the combustion chamber. The flow rate of the propellant mixture from the propellant injector enclosure into the combustion chamber is varied by adjustment of the propellant injector, with the injection of the propellant mixture from the propellant injector enclosure into the combustion chamber being at constant pressure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.