LOW-THRUST LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2018 - IPC F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: liquid rocket engine of low thrust (LRELT) contains a chamber 1, a mixing head with an inner bottom 2, an axial centrifugal nozzle 3, a peripheral belt of the jet nozzles 4, the annular conical deflector 5 between them, wherein the centrifugal nozzle slice 6 is recessed from the outlet edge 7 of the deflector surface forming surface toward the peripheral belt of the jet nozzles 4, a cavity of the combustion chamber 8 above the outer surface 9 of the deflector and a cavity 10 under the inner surface 11 of the deflector and an inner bottom of the mixing head are communicated by channels 12, which are offset from the nozzle holes by half a step (α/2). With this design, the nozzles 4 do not experience perturbations when the engine is running.

EFFECT: increase of power characteristics of the engine, reliable cooling of the combustion chamber and the mixing head.

5 dwg