LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 1997 - IPC

FIELD: rocketry and space engineering. SUBSTANCE: liquid-propellant rocket engine includes combustion chamber with nozzle, cryogenic oxidizer turbo-pump and hydrocarbon fuel turbo-pump with oxidizer and fuel service lines which are connected with drive turbine and gas generator for turbine made in form of cryogenic oxidizer heat exchanger-evaporator mounted on fuel service fuel line before fuel turbo-pump and connected to oxidizer service line after oxidizer turbo-pump by means of liquid line. Outlet of turbine is connected with oxidizer service line at turbo-pump inlet through heat exchanger mounted on oxidizer service line after oxidizer turbo-pump. Cryogenic oxidizer admitted to heat exchange-evaporator is gasified and preheated due to heat exchanger with high-boiling hydrocarbon fuel and is fed to turbine inlet driving the oxidizer turbo-pump and fuel turbo-pump. Oxidizer used in turbine passes through heat exchanger where it is cooled by main flow of oxidizer flowing to combustion chamber and is admitted to oxidizer service line at oxidizer turbo-pump inlet. EFFECT: enhanced efficiency. 1 dwg