Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors
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United States of America Patent
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Oct 16, 2018
Grant Date -
Mar 23, 2017
app pub date -
Nov 30, 2016
filing date -
May 30, 2014
priority date (Note) -
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Abstract
The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.
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