LIQUID-PROPELLANT ENGINE WORKING ON CRYOGENIC COMPONENTS OF PROPELLANT WITH CLOSED LOOP OF DRIVE OF TURBINE OF TURBO-PUMP UNIT Russian patent published in 2002 - IPC

FIELD: liquid-propellant rocket engines. SUBSTANCE: liquid- propellant engine includes chamber with regenerative cooling passage, turbo-pump unit with oxidizer and fuel pumps whose outlet mains are connected with injector assembly of chamber and loop of drive of turbo-pump unit turbine which includes regenerative cooling passage of chamber, turbine and fuel pump connected in succession. Fitted at fuel pump outlet is controllable flow rate divider whose one outlet is connected with injector assembly of chamber and other outlet is connected with regenerative cooling passage of chamber; fuel pump is multi-stage in construction; outlet branch pipe of turbine of turbo-pump unit is connected with stage of fuel pump where pressure is not below critical level when cavitation arises. Turbine outlet of turbo-pump unit is connected with inlet of second stage of fuel pump through flow regulator. EFFECT: enhanced reliability of engine; reduced mass and cost. 10 cl, 9 dwg