FIELD: engines and pumps.
SUBSTANCE: hypersonic engine comprises combustion chamber. Fuel downstream of fuel pump is heated to temperature higher than self-ignition temperature before feed to combustion chamber. Fuel is heated in heat exchanger arranged in combustion chamber walls or directly in said chamber. This engine comprises two stages, two combustion chambers and one shared jet nozzle. Second stage features profile of circular ramjet wherein second stage compressor is located ahead of combustion chamber. First stage diffuser makes the centre body of circular inlet device for second stage and can displace in lengthwise direction for adjustment of inlet device.
EFFECT: continuous ramjet operation, prevention of blowout.
7 cl, 1 dwg
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