LPRE TURBO PUMP UNIT Russian patent published in 2010 - IPC F02K9/48 F04D9/04 

FIELD: engines and pumps.

SUBSTANCE: proposed liquid-propellant rocket engine turbo pump unit comprises turbine, 1^st, 2^nd and 3^rd impellers of radial-flow pumps of fuel oxidiser, and extra fuel pump. Note here that three-stage turbine incorporates three turbine wheels fitted on outer, intermediate and centre shafts, respectively. Note also that oxidiser and fuel radial-flow pumps incorporate augers fitted ahead of radial flow impellers. Besides outer shaft is coupled with 1^st impeller arranged closer to turbine, intermediate shaft is coupled with 1^st auger and 2^nd impeller, while inner shaft is coupled with 2^nd auger and 3^rd impeller. Fuel pump and extra fuel pump are intercommunicated by pipeline. Turbine third stage wheel and that of second stage feature smaller diametres than that of first stage turbine wheel. Lubricant bypass channel is made inside outer shaft to lube bearings wherein aforesaid shafts run. Faces of turbine wheels and radial flow impellers have annular seals to form unloading chambers.

EFFECT: improved cavitation properties of LPRE turbo pump and unloading axially all shafts.

4 cl, 1 dwg