FIELD: rocketry.
SUBSTANCE: invention relates to liquid-propellant rocket engines operating on cryogenic oxidizer and hydrocarbon fuel. Proposed rocket engine contains combustion chamber with regenerative cooling duct, turbopump set with oxidizer and fuel pumps, fuel outlet main lines are connected through corresponding fuel valve with combustion chamber, and oxidizer outlet main line is connected through oxidizer valve with gas generator installed over main turbine. Turbopump set is furnished additionally with fuel pump whose inlet is connected with fuel pump, and outlet, with high-pressure pipeline in which high-pressure valve is installed, flow meter is connected with gas generator, and starting turbine is included into turbopump set.
EFFECT: simplified pneumohydraulic system of engine, improved reliability, reduced mass and dimensions of engine, improved operating characteristics of engine.
5 cl, 1 dwg
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