SOLID-PROPELLANT ROCKET ENGINE TURBOPUMP UNIT Russian patent published in 2014 - IPC F04D13/04 F04D29/66 

FIELD: engines and pumps.

SUBSTANCE: invention can be used in rocketry, turbopump units of liquid-propellant and nuclear rocket engines. Turbopump unit comprises pump 1, turbine 2 running in bearings 4 and 5, shaft 3 supporting turbine 2 wheel 6 and impeller 7, case 8, separation chamber 9 with shaft 3 seals 10 and 11, chamber 12 arranged downstream of seal 11 between separation chamber 9 and pump 1, and chamber 13 downstream of impeller 7. Seals 10 and 11 separated turbine 2 chamber from pump 1 chamber. Separation chamber 9 is connected with high-pressure chamber 13 via channel 14. Chamber 12 behind seal 11, between separation chamber 9 and pump 1, is integrated with chamber 13 downstream of impeller 7.

EFFECT: higher reliability of engine starting owing to improved cavitation properties of the pump.

6 cl, 4 dwg