LIQUID ROCKET ENGINE Russian patent published in 2021 - IPC F02K9/48 

FIELD: engine building.

SUBSTANCE: invention relates to rocket and space equipment and can be used in the structure of a liquid rocket engine with a turbine pump fuel supply system, made according to the configuration without afterburning, with a radiation-cooled tip of the nozzle of the chamber. A liquid rocket engine made according to the configuration without afterburning, including a turbine pump unit (TPU) 3, a gas generator 4, a gas duct 5 of the exhaust line of the TPU 3 turbine, a combustion chamber 1 with a radiation-cooled tip (RCT) of the nozzle 2, cooled by the exhaust gas of the turbine, the input of the cooling line whereof is communicated via the collector 6 with the gas duct 5, and the output with an annular supersonic nozzle 8 made around the RCT 2, built into the gas duct 5 before the collector of the cooling line 6 of the RCT is a centrifugal separator 9 in the form of a vortex chamber with a tangential input 10 and two outputs 11, 12, wherein one of the outputs with collection of gas from the central area of the vortex chamber is directed along the direction of thrust of the engine to the collector 6 of the cooling line of the RCT, and the other with collection from the periphery of the vortex chamber is directed against the direction of thrust of the engine to the nozzle for discharge 13 of the separated solid phase.

EFFECT: invention provides an increase in the reliability and efficiency of cooling the RCT of the engine.

1 cl, 2 dwg