Nozzle of a turbomachine provided with chevrons with a non-axisymmetric inner face
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United States of America
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Mar 15, 2022
Grant Date -
Aug 1, 2019
app pub date -
Apr 11, 2019
filing date -
Apr 11, 2019
priority date (Note) -
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status (Latency Note)
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Abstract
In a cowl for a nozzle, an internal wall has a cross-section with a determined abscissa on the axis defining a neck line on the internal wall. The cowl has, downstream of the determined abscissa, indentations in the trailing edge which delimit chevrons distributed in the circumferential direction. The internal wall of the cowl diverges radially towards the interior, in a second axial half-plane passing through the tip of a chevron, from the upstream tangent on the point of the neck line in the second axial half-plane, and the lines defining the internal wall of the cowl in any axial half-plane do not have a turning point downstream of the determined abscissa of the neck line.
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