FIELD: engines and pumps.
SUBSTANCE: proposed liquid-propellant rocket engine comprises combustion chamber, gas generator, turbine, fuel pump, oxidiser pump, fuel and oxidiser pipelines communicating pumps outlets with gas generator and combustion chamber, starting tank for fuel component to be displaced therefrom on starting the engine. In compliance with this invention, working space of said starting tank is tightly divided by piston or flexible membrane into two parts, one being communicated with fuel pipeline and another communicates with oxidiszer pipeline.
EFFECT: simplified design, higher reliability and stability of engine starting.
1 dwg
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