FIELD: rocket engine engineering.
SUBSTANCE: method comprises making cooled lining of the combustion chamber, at least two conformal sections of the inner load-bearing member made of the nozzle throat, and at least two conformal sections of the outer load-bearing member made of nozzle throat. The outer surface of the lining is then provided with a number of passages for flowing coolant. The outer surface of the cooled lining made of the sections is provided with the inner load-bearing member . The closed outer surface of the inner load-bearing member is provided with the outer load-bearing member to define assembled member bearing the lining. The assembled member is provided with inlet and outlet ring collectors of the cooling system to define assembled structure. The structure is then subjected to the hot quasi-static pressing.
EFFECT: reduced weight and cost of manufacturing.
2 cl, 7 dwg
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