FIELD: liquid propellant rocket engines.
SUBSTANCE: liquid propellant rocket engine (LPRE) consists of a traction combustion chamber and unified autonomous systems for feeding the combustion chamber with fuel components in both the liquid and gaseous phases. Autonomy is ensured by the fact that the additive oxidizer of the reducing gas generator of the autonomous combustion chamber (CC) supply system is supplied with fuel from an autonomous displacement system for supplying the additive oxidizer, and the additive fuel is supplied to the oxidizing gas generator of the autonomous system for supplying the CS with oxidizer from an autonomous displacement system for supplying the additive fuel.
EFFECT: invention improves the efficiency of controlling the operating mode of the liquid propellant rocket engine by regulating the flow rates and pressures of the oxidizer and fuel in the compressor station by changing the operating modes of turbopump units, as well as regulating the flow rates of additive components in gas generators.
2 cl, 2 dwg
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