LIQUID-PROPELLANT ENGINE (VERSIONS) Russian patent published in 2013 - IPC F42B15/00 B64G1/40 F02K9/00 

FIELD: engines and pumps.

SUBSTANCE: liquid-propellant engine includes a combustion chamber, a gas generator and a turbopump unit with a turbine and pumps. The gas generator and the turbopump unit are installed above the combustion chamber in series one above another along its axis. The gas generator and the turbopump unit are made as one whole unit. As per the first version, the liquid-propellant engine includes the following in downward direction: a gas generator, a turbine, an oxidiser pump, a fuel pump, a multiplier and an additional fuel pump, and the turbine outlet is connected to the combustion chamber via a gas line. As per the second version, the liquid-propellant engine includes the following in downward direction: an additional fuel pump, a multiplier, a fuel pump, a gas generator and a turbine, and the turbine outlet is connected immediately to the combustion chamber.

EFFECT: increasing the rocket movement speed, improving its weight characteristics and increasing the flight range.

2 cl, 7 dwg