TURBO-PUMP UNIT OF THREE-COMPONENT ROCKET ENGINE Russian patent published in 2011 - IPC F02K9/48 F04D1/04 

FIELD: engines and pumps.

SUBSTANCE: turbo-pump unit of three-component rocket engine includes turbine, as well as the first, the second and the third centrifugal impellers of centrifugal pumps. Turbine is three-staged and has three impellers: the first, the second and the third one, which are installed on outer, intermediate and inner shafts respectively. Centrifugal pumps are provided with screws installed in front of centrifugal wheels. Outer shaft is connected to the first centrifugal impeller which is located closer to the turbine. Intermediate shaft is connected to the first screw and the second centrifugal impeller. Inner shaft is connected to the second screw and the third centrifugal impeller and through magnetic coupling to the third screw. Automatic frequency control of screw rotation can be arranged in front of the third screw. Bypass channel of pumped lubrication product for bearings on which shafts are installed can be provided inside outer shaft. On edges of impellers of turbines and centrifugal impellers there can be provided annular seals forming discharge cavities.

EFFECT: improving cavitation properties of pump included in turbo-pump unit and providing unloading of axial forces from all shafts.

4 cl, 2 dwg