FIELD: engine building.
SUBSTANCE: invention relates to liquid-propellant rocket engines. Rocket engine comprises a copper alloy combustion chamber, a copper-free welded-in transition ring welded to the copper alloy combustion chamber, and nozzle head welded to copper-free welded-in adapter ring. Engine can be manufactured by forming a combustion chamber from a copper alloy using additive manufacturing, copper-free welded-in adapter ring is welded to combustion chamber from copper alloy and nozzle head welded-in copper-free adapter ring is welded to it.
EFFECT: invention provides easier separation and reconnection of injector head and combustion chamber by means of adapter ring, as well as elimination of mixing of compositions during welding, from which the combustion chamber and nozzle head are made.
16 cl, 6 dwg
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