LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2015 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: liquid propellant rocket engine comprises combustion chamber, turbopump unit, drain chamber with drain pipe and cylinder with compressed gas. Note here that said drain chamber is arranged between oxidizer pump and turbine. Drain pipe is equipped with gas ejector. In compliance with this invention two drain chambers are arranged between turbine and oxidizer pump and between oxidizer pump and propellant pump. Gas ejector is connected via pipe with chamber located downstream of the turbine. Said pipe is provided with the valve and throttle.

EFFECT: decreased weight and higher reliability.

2 cl, 2 dwg