HOUSING OF LIQUID-PROPELLANT ROCKET ENGINE CHAMBER

摘要

combustion chambers of liquid-propellant rocket engines. SUBSTANCE: housing includes combustion chamber, nozzle consisting of subsonic and supersonic parts provided with external load- bearing envelopes and injector wall with finned outer surface. Regenerative cooling passage is formed between envelope and wall. This wall is made from copper or copper alloy. Injector wall is provided with metal coat which is laminated in area of nozzle exit section over its length equal to at least 0.3 of diameter of nozzle exit section. First layer of coat is nickel coat having thickness of from 50 mkm to 1000 mkm and second layer is chromium coat having thickness of from 10 mkm to 500 mkm. EFFECT: enhanced thermal resistance of injector wall of engine combustion chamber for oxygen-kerosene rocket propellant. 3 cl, 5 dwg