LIQUID-PROPELLANT ROCKET ENGINE TURBOPUMP UNIT Russian patent published in 2014 - IPC F04D13/04 F04D29/58 

FIELD: engines and pumps.

SUBSTANCE: set of inventions relates to turbopump units of liquid-propellant rocket engines and nuclear rocket engines. Turbopump unit comprises pump 1, turbine 2, shaft 3 running in ball bearings 4, wheel 6 of turbine 2 and impeller 6 fitted on shaft 3, housing 8, separation chamber 9 with shaft seals 11 on the side of pump chamber and chamber ahead of turbine wheel 6. Separation chamber 9 is connected via channel 12 and external discharge pipeline 13 with engine main line wherein pressure is lower than that inside turbine 2. External pipeline 13 can be connected with gas circuit downstream of turbine 2, with line feeding fluid to pump 1 and lined feeding fluid into engine. Separation chamber 9 can be communicated with gas circuit downstream of turbine via channel or channels in shaft 3 and turbine wheel 6.

EFFECT: higher reliability and efficiency.

5 cl, 2 dwg