Reflex annular vent nozzle
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United States of America Patent
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May 24, 2016
Grant Date -
Feb 6, 2014
app pub date -
Aug 2, 2012
filing date -
Aug 2, 2012
priority date (Note) -
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Abstract
A gas turbine engine includes a core defining an engine central longitudinal axis. An inner-fixed structure is radially outward of the core. A core cowl extends from the inner-fixed structure to a trailing edge. A thrust reverser is spaced radially outward of the core cowl to define a fan flow path. A vent has a core cowl inner surface formed as part of the core cowl and a vent inner surface that is spaced radially inward of the core cowl inner surface to define a vent flow path. A reflex member extends from a trailing edge of the core nacelle to impede mixing of the fan flow path and the vent flow path.
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