Nozzle for an aircraft turboprop engine with an unducted fan
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United States of America Patent
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Oct 30, 2018
Grant Date -
Feb 4, 2016
app pub date -
Oct 13, 2015
filing date -
Apr 15, 2013
priority date (Note) -
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Abstract
The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
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