Patent ID: 8997497
Filing Date: 2015-04-07
Classification: B64D,F02K,F05D

Abstract:
1. A nacelle assembly for a gas turbine engine comprising: a core nacelle defined about an engine centerline axis of rotation; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; a variable area nozzle in communication with said fan bypass flow path, said variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section includes a leading edge region that defines a concave external contour that extends away from the engine centerline axis and said first fan nacelle section includes a trailing edge region that defines a convex internal contour that extends towards the engine centerline axis; and a flexible surface mounted to at least one of an inner surface at said convex internal contour and an outer surface at said concave external contour.