FIELD: engines and pumps.
SUBSTANCE: test stand for high altitude rocket engine comprises a pressure chamber, a working fluid jet through the injection nozzle assembly and the exhaust diffuser, the axis of jet nozzles are angled with respect to the injection of the exhaust diffuser axis. Injection angle determined by the ratio, the protected invention.
EFFECT: invention improves the efficiency of cooling the most heat-stressed inlet portion of the exhaust diffuser in a supersonic flow of high-temperature combustion products when using a rocket engine on solid fuel.
3 dwg
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