LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises onboard computer, electric power source, oxidiser turbo pump including main turbine, pumps and starting turbine, propellant gas generator, external compressed air bottle connected via high-pressure pipeline and external valve, fast-release connector, check valve and onboard pipeline to starting turbine, and igniters on combustion chamber and oxidiser gas generator. In compliance with this invention it additionally comprises propellant turbo pump unit with second main turbine, propellant pump and second booster turbine, and propellant gas generator integrated with propellant gas generator. Second booster turbine is connected via pipeline including starting valve with main turbine outlet. Oxidiser turbo pump unit comprises oxidiser pump and extra oxidiser pump. Oxidiser gas generator may be arranged between main turbine and oxidiser pump. Propellant gas generator may be arranged above second main turbine. Propellant gas generator sidewall allows regenerative cooling and comprises inner and outer spaced apart shells.

EFFECT: improved specific characteristics, higher reliability, multifold starting.

17 cl, 6 dwg