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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United States of America Patent
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Aug 11, 2020
Grant Date -
Aug 30, 2018
app pub date -
Feb 21, 2018
filing date -
Feb 27, 2017
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Abstract
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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