FIELD: aircraft engineering.
SUBSTANCE: proposed jet engine installation contains supersonic rocket nozzle and means to provide burning inside ring zone of supersonic divergent part. Supersonic rocket nozzle is formed by convergent part, neck and supersonic divergent part. Burning inside ring zone of supersonic divergent part is provided by injection and combustion of liquid rocket propellant in ring zone to increase thrust. Means by means of which burning inside ring zone is provided consists of great number of nozzles arranged in places distributed along circumference of supersonic divergent part. Nozzles provide injection of liquid propellant and liquid oxidizer over circumference in direction one into another into ring zone.
EFFECT: provision of high specific impulse at high altitude without reduction of thrust at sea level.
2 cl, 2 dwg
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