FIELD: engines and pumps.
SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines running on three components, i.e. cryogenic oxidiser, hydrocarbon fuel and cryogenic fuel (fluid hydrogen). Turbopump unit (TPU) intended for three-component liquid propellant rocket engine comprises turbine, gas generator, oxidiser pump, first fuel pump and extra pump of first fuel. In differs from know designs in that it incorporates second fuel pump and extra pump of second fuel mounted between oxidiser and first fuel pumps.
EFFECT: higher reliability thanks to TPU shaft stress relief.
2 cl, 2 dwg
