LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises turbo pump including, in its turn, turbine, oxidiser and propellant pumps, extra fuel pump and combustion chamber with cylindrical part with oxidiser and propellant nozzles and nozzle with the propellant main header. It differs from known designs in that said turbo pump unit and combustion chamber are aligned. Note also that turbine is arranged inside combustion chamber cylindrical part and composed of two zones and comprises propellant extra nozzles at its cylindrical part below the turbine. Oxidiser pump outlet is communicated via pipeline incorporating oxidiser valves with combustion chamber. Mid header can be arranged at combustion chamber cylindrical part mid part. Intermediate header is arranged below mid header with propellant extra nozzles extending therein.

EFFECT: higher specific characteristics and reliability and lower launching costs.

4 cl, 4 dwg