FIELD: engines and pumps.
SUBSTANCE: invention relates to rocketry, particularly to liquid-propellant rocket engines running on three components, primarily, on cryogenic oxidiser, hydrocarbon fuel and liquid hydrogen. Proposed turbopumping system comprises turbopump unit incorporating turbine, gas generator, oxidiser pump, first fuel pump and extra first fuel pump. In compliance with this invention, proposed system comprises second turbopump unit incorporating turbine, gas generator, oxidiser pump, second fuel pump and extra multi-stage second fuel pump.
EFFECT: higher reliability due to reduced axial sizes and axial loads in turbopump shaft.
2 cl, 1 dwg
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