THREE-COMPONENT LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2016 - IPC F02K9/46 

FIELD: engines and pumps.

SUBSTANCE: claimed rocket engine comprises the chamber, gas generator, control and adjustment units, at least one turbopump assembly with at least two pumps of two liquid propellants. Note here that the gas path downstream of at least one turbine is communicated with the chamber mixing head. In compliance with claimed invention, the pump of liquid propellant of lower density is fitted on the separate shaft. The mixer is arranged in the gas path communicating the gas generator and the turbine, downstream of the chamber cooling path, or with the turbodrive connected with outlet chamber of the pump of one of liquid propellants. Note here that the adjustment assembly is mounted at the pipe communicating the oxidizer pump outlet and the gas generator mixing head, or at the pipe communicating the manifold downstream of the chamber cooling path and gas generator mixing head, or at the pipe communicating the outlet of pipe of lower-density liquid propellant and the gas generator mixing head.

EFFECT: higher specific thrust pulse and decreased weight of liquid-propellant rocket engine.

3 dwg