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CONVERGENT-DIVERGENT NOZZLE FOR A TURBOFAN ENGINE OF A SUPERSONIC AIRCRAFT AND METHOD FOR ADJUSTING THE NOZZLE THROAT SURFACE IN A NOZZLE OF A TURBOFAN ENGINE
CONVERGENT-DIVERGENT NOZZLE FOR A TURBOFAN ENGINE OF A SUPERSONIC AIRCRAFT AND METHOD FOR ADJUSTING THE NOZZLE THROAT SURFACE IN A NOZZLE OF A TURBOFAN ENGINE
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机译:超音速飞机的涡轮风扇发动机的收敛-发散喷嘴和调节涡轮风扇发动机喷嘴中的喷嘴喉面的方法
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摘要
A convergent-divergent nozzle for a turbofan engine of a supersonic aircraft, wherein the nozzle has an inner wall and forms a flow channel with a nozzle throat surface and a nozzle exit surface. A trim ring that is displaceable in the axial direction between a first position and a second position is provided, wherein the inner wall of the nozzle and the trim ring are embodied and positioned with respect to each other in such a manner that the trim ring extends at a radial distance to the inner wall in the first position, wherein a ring-shaped bypass channel is provided, extending between the trim ring and the inner wall of the nozzle, and the trim ring abuts the inner wall in the second position.
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