Patent ID: 9347397
Filing Date: 2016-05-24
CPC Classification: F02K,F05D

Claim Text:
1. A nacelle assembly for a gas turbine engine comprising: a core defining an engine central longitudinal axis; an inner-fixed structure radially outward of the core and having a core cowl that extends from the inner-fixed structure to a trailing edge; a thrust reverser spaced radially outward of the inner-fixed structure to define a fan flow path; a vent having a core cowl internal surface formed as part of the core cowl and a vent inner surface spaced radially inward of the core cowl internal surface to define a vent flow path; and a reflex member extending from the trailing edge to impede mixing of the fan flow path and the vent flow path, wherein the reflex member includes a curved portion that is formed as part of a radially outer surface of the reflex member.