LIQUID ROCKET ENGINE Russian patent published in 2009 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: liquid rocket engine includes the following, which is installed on the frame: combustion chamber with jet nozzle, turbine-driven pump made in the form of a single unit containing the main turbine, oxidant and fuel pumps, gas generator installed above the main turbine, which have regenerative cooling system. According to the invention, there installed concentrically to jet nozzle is a nozzle head piece made as to the profile as the continued part of the nozzle and having the possibility of being moved along longitudinal axis of combustion chamber by means of a drive; at that, nozzle head piece design is cooled and consists of a cooling jacket installed concentrically to nozzle head piece thus forming a gap the cavity of which is connected with flexible pipelines to fuel pump and fuel manifold. Drive consists of at least one actuator. The latter is located on the nozzle and fixed on the frame and fixed on combustion chamber. Actuator is connected to synchronisation mechanism, and nozzle head piece is installed on the guide cylinder. As actuator, there used is electric engine. As actuator, there used is hydraulic cylinder.

EFFECT: optimum rocket engine operation within a wide range of modes at various heights, simplifying pneumatic hydraulic scheme, improving reliability, increasing power.

9 cl, 6 dwg