Patent ID: 9222439
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 an immediate proximity of the nozzle, but without making contact with the nozzle, to recover energy of thermal radiation emitted when the rocket engine is in operation and to heat the inert fluid, the heater device comprising a plate in a form of a portion of a conical frustum that extends exclusively around the divergent section of the nozzle over an angle σ lying in a range 30° to less than 360°.