LIQUID CRYOGENIC PROPELLANT ROCKET ENGINE WITH CLOSED LOOP OF TURBINE DRIVE OF TURBOPUMP UNIT (VERSIONS) Russian patent published in 2000 - IPC

FIELD: rocketry; cryogenic liquid propellant rocket engines. SUBSTANCE: liquid-propellant engine has chamber with injector assembly and regenerative cooling line, turbopump unit with oxidizer pump (liquid oxygen) and fuel (hydrocarbon fuel) pump whose outlet mains are connected with injector assembly of chamber and closed loop of turbine drive of turbopump unit which includes circulating pump, regenerative cooling line heat exchanger-heater using gas as heat-transfer agent which are connected in series; gas is obtained in gas generator fed from outlet mains of oxidizer and fuel pumps; heat transfer agent from outlet of above-mentioned heat exchanger-heater is introduced into outlet main of oxidizer pump; turbopump unit includes also turbine, heat exchanger-condenser mounted on outlet main of oxidizer pump; outlet of heat exchanger-condenser is connected with circulating pump inlet through flow regulator. Control of engine is effected by means of component ratio regulator fitted in gas generator fuel supply main. Another version of liquid-propellant engine consists in availability of fuel pump which simultaneously performs function of circulating pump. Besides that, fuel pump outlet is connected with injector assembly of chamber and with chamber regenerative cooling line through controllable flow divider. Systems of these engines include starting systems with starting pump connected in parallel with circulating pump. Pump is connected with autonomous drive through split coupling. After starting the engine, starting pump is switched off. EFFECT: enhanced reliability of engine due to obtaining optimal characteristics in thermal factor and strength characteristics; low cost of engine due to usage of low-cost materials. 14 cl, 2 dwg