LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/00 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises onboard computer, electric power source, oxidiser turbo pump unit 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 gas generator. In differs from known designs in that it incorporates two turbo pump units, that is, oxidiser turbo pump unit and propellant turbo pump unit. Gas generators are integrated with turbo pump units. Oxidiser turbo pump unit comprises oxidiser pump and extra oxidiser pump while propellant turbo pump unit comprises propellant pump. Turbo pump units and combustion chamber may be arranged in one plane in symmetry about combustion chamber lengthwise axis while their lengthwise axes are parallel with the latter. Shaft of said turbo pump units run in opposite directions. Said turbo pump units may feature equal weight. Combustion chamber is provided with bearing ring whereto one or two pairs of thrust vector control wires are connected. 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, 5 dwg