FIELD: engines and pumps.
SUBSTANCE: this invention comprises the stage of compression in compressors, heat feed in combustion chamber and the stage of expansion at turbines and jet nozzle. Said expansion at high-pressure turbine blades is executed in supersonic flow and density inversion in said flow is used for organisation of coherent radiation. Proposed engine comprises the compressor low-pressure stage, high-pressure stage, combustion chamber, high-pressure turbine, low-pressure turbine and jet nozzle. Additionally, two barrel-shape resonators, inner and outer, with semi-transparent element in outer resonator, obturator and birotating wheel of active blading. High-pressure turbine working blades are composed of the series of Laval nozzles and two barrel-like resonators arranged there behind while obturator and birotating wheel of active blading are arranged downstream of gas flow.
EFFECT: expanded operating performances due to its application as gas-dynamic laser.
2 cl, 1 dwg
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