COOLING SYSTEM OF COMBUSTION CHAMBER OF LIQUID- PROPELLANT ROCKET ENGINE Russian patent published in 2003 - IPC

FIELD: rocket engines. SUBSTANCE: proposed cooling system of combustion chamber of liquid propellant rocket engine with regenerative cooling duct contains intercoolant cylinder with valve and heat exchanger-cooler. Output of combustion chamber regenerative cooling duct is connected with input of heat exchanger-cooler through turbine by heat carrier line. Output of heat exchanger-cooler communicates through heat carrier line by means of valve with intercoolant cylinder. Input and output of heat exchanger-cooler are connected, respectively, with coolant delivery and discharge main line by means of coolant line. Output of pump is connected with input of combustion chamber regenerative cooling duct. EFFECT: improved efficiency and enlarged operating capabilities of liquid propellant rocket engine. 1 dwg