FIELD: rocketry. SUBSTANCE: according to proposed method of operation of liquidpropellant rocket engine with turbopump delivery of cryogenic propellant on basis of oxygen oxidizer and fuel, recovering gas, after generation of vapor, is used directly for afterburning in chamber with remaining part of fuel. Liquid propellant rocket engine implementing proposed method employs gas generator designed for generating recovering gas being connected directly to nozzle head of chamber. EFFECT: increased efficiency of liquid-propellant rocket engine by increasing specific thrust pulse. 5 cl, 3 dwg
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