LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2017 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: in the liquid-propellant rocket engine combustion chamber comprising an outer steel shell and an inner shell of a copper alloy with coolant path channels placed therein with turbulizing projecting elements on the surfaces of each of the channels, the minimum distant from the longitudinal axis of the shell, according to the invention, the cooling path channels located in the thickness of the inner shell formed by additive techniques by the method of selective laser melting are made closed, and additionally, turbulizing projecting elements in the form of a triangle, the larger side thereof facing the channel entry, and the smaller one - to the channel output, are made on the surfaces of each channel, the most distant from the longitudinal axis of the shell.

EFFECT: increased efficiency of the cooling path of the LRE combustion chamber, reducing the length and the manufacturing cost of the combustion chamber inner shell.

6 dwg