LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2002 - IPC

FIELD: space craft. SUBSTANCE: proposed liquid-propellant rocket engine is designed for use in cryogenic stages, launch vehicle stages and as spacecraft cruise engines. It has combustion chamber with regenerative cooling passage and components delivery pumps (fuel and oxidizer) with turbine on one shaft into which condenser is fitted. Outlet of condenser coolant line is connected with inlet of combustion chamber and with inlet of combustion chamber regenerative cooling passage. Outlet of condenser heat carrier line is connected with inlet of one of components pumps. Outlet of pump of this component is connected with input of condenser coolant line. Second input of condenser is connected with turbine outlet. Outlet of pump of other component is connected with combustion chamber inlet. EFFECT: enlarged sphere of application and increased efficiency of liquid-propellant rocket engine. 1 dwg