FIELD: engines and pumps.
SUBSTANCE: hypersonic turbo ejector engine comprises inlet device, compressor, main combustion chamber, turbine gas ejector, afterburner and outlet device. Ejector high-pressure channel communicates, on one side, with compressor via main combustion chamber, and, on its opposite side, it communicates with turbine via mixing chamber. Ejector low-pressure channel communicates, on one side, with atmosphere via main combustion chamber, and, on its opposite side, it communicates with turbine via mixing chamber. Has ejector low-pressure channel accommodates steam-air ejector with its high-pressure channel making a continuation of high-pressure channel of air-to-air heat exchanger arranged at engine compressor outlet.
EFFECT: higher thrust and reduced fuel consumption for entire range of altitudes and speeds.
4 dwg
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