METHOD OF PRODUCING LIQUID-PROPELLANT ROCKET ENGINE CHAMBER NOZZLE CRITICAL SECTION ASSEMBLY Russian patent published in 2009 - IPC B23P15/00 

FIELD: engines and pumps.

SUBSTANCE: method of producing liquid-propellant rocket engine chamber nozzle critical section assembly comprises producing inner and outer casings. Inner casing represents a cylinder at the nozzle subcritical part and a truncated cone at the nozzle supercritical part. Outer casing represents two mating truncated cones. Inner casing outer surface is furnished with ribbed surfaces and circular grooves arranged on its end cylindrical section. The first of circular grooves houses a solder fitted into the depth smaller than that of the groove and representing band sections tightly fitting to each other. The solder representing galvanic layers is applied onto the mating surfaces of both casings. The structure thus assembled is fitted onto the mandrel to flare the inner casing cylindrical part. The cooling passage is vacuumised. The soldering is made in the furnace at the protective gas pressure.

EFFECT: higher quality of soldered nozzle critical section assembly thanks to increased density of soldered seam in nozzle subcritical part face area.

7 cl, 2 ex, 3 dwg