LIQUID-PROPELLANT ROCKET ENGINE WITH AFTERBURNING Russian patent published in 2003 - IPC

FIELD: rocket engines. SUBSTANCE: proposed liquid-propellant rocket engine with afterburning contains combustion chamber, oxidizing gas generator, coaxial main pumps of propellant and oxidizer of turbopump set, additional pump to deliver propellant to gas generator. Drive of additional pump includes step-up gear, ratio 1.5-2.5. Said step-up gear is mechanically connected to shaft of propellant main pump from side of propellant delivery into main pump, and inner space of step-up gear communicates with inner spaces of main pump from propellant inlet side. Invention makes it possible to create liquid-propellant rocket engine with additional propellant pump with optimum characteristics, i.e. optimum speed, efficiency and mass, which, in its turn, leads to reduction of consumed power, temperature of oxidizing gas at output to turbine and mass of entire turbopump set. EFFECT: improved operation, reduced power consumption. 1 dwg