LOX/LIQUID HYDROGEN ENGINE Russian patent published in 1999 - IPC

FIELD: rocket manufacturing. SUBSTANCE: engine has chamber, gas generator, main and auxiliary turbopump units, oxygen and hydrogen booster pump unit. main turbopump unit has main oxygen pump, additional oxygen pump, hydrogen pump and turbine, all installed on common shaft. Auxiliary turbopump unit has hydrogen pump and turbine installed on common shaft. Main oxygen pump is connected with chamber head by pipeline. Outlet of additional pump is connected by pipelines with gas generator head and with inlet of hydraulic turbine of oxygen booster pump unit. Outlet of hydrogen pump of main turbopump unit is connected with gas generator head. Inlets and outlets of turbines of main and auxiliary units are connected by pipelines with gas generator outlet and with chamber head, respectively. Pump outlets of oxygen and hydrogen booster pump units are connected with inlet of corresponding pumps of main and auxiliary turbopump units. To increase power output of main and auxiliary units, outlet of hydrogen pump of auxiliary unit is connected with chamber head. To increase pressure in chamber using hydrogen flowing through chamber cooling duct to drive turbines, outlet of hydrogen pump of auxiliary unit is connected by pipeline with inlet of chamber cooling duct, and outlet of chamber cooling duct is connected with head of gas generator. Parallel oxygen pump is installed on shaft of auxiliary unit to improve anticavitation properties of main oxygen pump. EFFECT: enhanced energy-mass characteristics of engine unit with oxygen-hydrogen engines by increasing engine thrust. 4 cl, 3 dwg