FIELD: engine building.
SUBSTANCE: invention relates to a liquid propellant rocket engine. Liquid propellant propulsion system with auxiliary electric power comprises preignition chamber (11) for formation of gaseous combustion products of fuel and oxidant; main combustion chamber (10) for combustion of gas mixture from combustible and gaseous combustion products, which are released from preignition chamber (11), turbo pump (20), including turbine (21), rotated by a flow of gaseous combustion products, and first pump (22) and second pump (23), driven by turbine rotation, wherein turbo pump (20) supplies fuel from fuel tank (30) to preignition chamber (11) and supplies oxidizer from oxidizer tank (40) to preignition chamber (11) and main combustion chamber (10), electric motor (25) for rotation of turbine (21) to preignition chamber (11) and main combustion chamber (10) and coupling for connection of electric motor (25) and turbine (21) and opening of this connection between electric motor (25) and turbine (21).
EFFECT: invention provides reduced consumption of rocket fuel during preliminary cooling.
7 cl, 4 dwg
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