CRYOGENIC PROPELLANT ROCKET ENGINE Russian patent published in 1997 - IPC

FIELD: rocketry and space engineering; liquid-propellant rocket engines using cryogenic oxidizer and hydrocarbon fuel. SUBSTANCE: liquid-propellant rocket engine includes combustion chamber with nozzle, cryogenic oxidizer and fuel turbo-pumps provided with drive turbines and gas generator equipped with cooling jacket connected to oxidizer service line. Outlet of gas generator is connected with inlet of turbine of fuel turbo-pump and outlet of gas generator cooling jacket is connected with inlet of second turbine of oxidizer turbo-pump whose outlet is connected with inlet of oxidizer turbo-pump through heat exchanger mounted in oxidizer service line. Cryogenic oxidizer admitted to gas generator cooling jacket is gasified due to heat exchange with generator gas and is used as working medium for drive of oxidizer turbo-pump. EFFECT: enhanced efficiency of cooling of generator gas; avoidance of increased thermal action of gas on turbine blades; reduced amount of burnt fuel. 2 dwg