TURBO-PUMP UNIT OF ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: in a turbopump unit containing a turbine and oxidiser and fuel pumps installed coaxially to it and each containing one centrifugal impeller and a screw, external and internal shafts, a turbine wheel is installed on the internal shaft. The oxidiser pump is two-stage; both stages are of centrifugal screw type, and between the screw and the impeller of the second stage of the pump there installed is a hydraulic turbine fixed on the external shaft that passes inside the centrifugal impeller of the first stage and is connected to the screw of the first stage of the pump; the screw has external bandage ring rigidly attached to the centrifugal impeller of the second stage of the first pump; the first impeller of the pump is connected to the internal shaft through a magnetic coupling, between oxidiser and fuel pumps there is a reduction gear, in the housing of which an additional fuel pump is installed; internal shafts of oxidiser and fuel pumps are connected to a spring; the shaft of the additional fuel pump is connected to the internal shaft of the fuel pump through the reduction gear.

EFFECT: improvement of cavitation properties of pumps with minimum weight of a turbopump unit and unloading of axial forces of internal and external shafts.

3 cl, 7 dwg