Patent ID: 9222438
Filing Date: 2015-12-29
Classification: F02K

Abstract:
1. A cryogenic-propellant rocket engine comprising: 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 that is used to pressurize at least one of the first and second tanks; 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; a heater device including at least one duct for conveying the inert fluid and arranged outside the nozzle in immediate proximity of the nozzle, but without making contact with the nozzle, exclusively around said divergent section, to recover energy of thermal radiation emitted when the rocket engine is in operation and to heat the inert fluid; and wherein the heater device comprises a metal structure in which the inert fluid for heating flows and a fine layer that is strongly absorbent from a thermal radiation point of view deposited at least on walls that face the nozzle constituting a radiant power source.