TURBOPUMP UNIT Russian patent published in 2016 - IPC F04D13/00 F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: invention can be used in turbopump units of liquid-propellant rocket engines incorporated with multiple-shot rockets. Invention aims at increasing the turbopump bearing serviceability at multiple burns of liquid-propellant engine by decreasing the bearing heating. For this, claimed turbopump unit comprises housing 1, rotor with rotary pump 2, turbine 3, bearing support 4, low-pressure pump intake pump 5, high-pressure pump outlet 6, high-pressure chamber 7, pipe 8, check valve 9 and jet 10. At engine shutdown, the pressure downstream of the pump drops to zero. Note here that check valve 9 closes to force the liquid component from high-pressure chamber 7 via jet 10 by fuel component vapour pressure into bearing support to cool down the bearings.

EFFECT: decreased heating of bearings, higher reliability of multiple burns.

1 dwg