LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2000 - IPC

FIELD: rocketry and space engineering; cryogenic stages of launch vehicles; spacecraft. SUBSTANCE: engine includes combustion chamber with nozzle, evaporator, component supply pump, gas generator and turbine. Engine is also provided with condenser whose inlet is connected with pump outlet. Evaporator outlet is connected with turbine inlet by cooling agent line and turbine outlet is connected with condenser inlet by heat-transfer agent line. Condenser inlet of heat-transfer agent line is connected with inlet of respective pump. Evaporator inlet of heat-transfer agent line is connected with gas generator outlet. Gas generator is supplied by component supply pumps. Evaporator outlet of heat-transfer line is connected with combustion chamber inlet. During operation of engine, higher pressure may be built in its chamber and consumption of component for forming cooling curtain may be reduced. EFFECT: enhanced efficiency of engine; extended field of application. 1 dwg