LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2014 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises turbo pump unit including turbine, oxidiser and propellant pumps, extra propellant pump, all being fitted on turbine shaft, and combustion chamber. Combustion chamber has cylindrical part with oxidiser and fuel nozzles and nozzle with propellant main manifold. Turbo pump unit and combustion chamber are aligned. Double-area combustion chamber comprises first circular area with circular nozzle unit and second area with central nozzle unit incorporating extra fuel nozzles while turbine being arranged inside combustion first area. Oxidiser pump outlet is communicated via pipeline equipped with oxidiser valves with combustion chamber. Central hollow nozzle unit communicates via axial bore extending inside turbo pump unit shaft with extra fuel pump inlet.

EFFECT: decreased transverse size and weight.

3 cl, 2 dwg