LIQUID-PROPELLANT ROCKET ENGINE FUEL FEED PLANT Russian patent published in 2016 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: claimed rocket engine comprises the gas generator with the head and turbopump unit arranged there under. Said turbopump comprises the main turbine and oxidiser and fuel pumps, and starting turbine with at least one high-pressure source including the pyro charge. Oxidiser pump outlet is communicated via pipeline equipped with oxidiser valves with gas generator head. High-pressure source has the end wall with holes, their number corresponding to that of pyro charges. Note here that at least two pyro charges are used. Said starting turbine incorporates at least two nozzle diaphragms closed by the flap. Said flap can open in turns said holes and communicate them with one of nozzle diaphragms. The pipe at the joint with the gas generator is arranged radially. Aforesaid flap is coupled with the drive. Aforesaid flap is coupled with the drive via a mechanical gearing. Two or more high-pressure sources can be used.

EFFECT: multiple in-flight engine and turbopump starting.

5 cl, 9 dwg