LIQUID FUEL ROCKET MOTOR Russian patent published in 2014 - IPC F02K9/48 

FIELD: motors and pumps.

SUBSTANCE: liquid fuel rocket motor containing turbopump unit with the turbine installed on the shaft, oxidant and fuel pumps, and combustion chamber comprising a cylindrical part with oxidant and fuel injectors, and nozzle with the main fuel manifold and regenerative cooling system, according to the invention turbopump unit and combustion chamber are installed coaxially, the combustion chamber is designed as two-zonal and contains the first annular zone with ring-type spray unit and upper fuel manifold and the second zone with the central spray unit comprising additional fuel injectors, and the turbine is installed between the first and second zones of the combustion chamber. The oxidant pump output is connected with the combustion chamber through the pipeline with the oxidant valve. The fuel pump output is connected through pipelines with the main and upper fuel manifolds. The turbine is designed comprising the nozzle device, impeller and straightener blades with a cavity inside, central spraying unit is designed hollow and its cavity is connected with axial openings through a cavity inside straightener blades with the gap of regenerative cooling nozzle and the second zone of the combustion chamber.

EFFECT: better LFRM specific characteristics and higher reliability.

5 cl, 2 dwg