FIELD: engines and pumps.
SUBSTANCE: turbojet comprises housing accommodating air intake, axial-flow compressor, combustion chamber, turbine vanes and afterburner. Afterburner inner surface is coated by heat-isolation coating with reflection factor at working temperature smaller than unity. Turbine rear support cowl is shaped to direct circular or truncated cone with vertex angle exceeding 90 degrees. Jet nozzle has throat with radius smaller than that of the circle circumscribed by turbine vane ends. Turbojet may be provided with jet nozzle that has the throat with radius equal to or smaller than turbine rear support cowl base. For protection of turbojet its vanes are irradiated simultaneously by microwave-band radio waves and radio waves reflected from rear support cowl via said nozzle and rear support cowl. Note here that radio waves are irradiated outward via het nozzle with decreased amplitude after multiple reflections from heat-protection coating as well as those reflected from turbine vanes.
EFFECT: decreased probability of hitting.
8 cl, 4 dwg
