Patent ID: 9103298
Filing Date: 2015-08-11
Classification: F02C,F02K,F05D,Y02T

Abstract:
1. A nacelle for a turbofan engine having an engine centerline, the nacelle comprising: a forward assembly that defines a bypass duct extending circumferentially at least partially around the engine centerline, the bypass duct being configured to transport bypass airflow of the engine, the forward assembly having an aft edge that extends circumferentially at least partially around the bypass duct; a variable area fan nozzle (VAFN) disposed behind the forward assembly and movable relative to the forward assembly between a stowed position and a deployed position, an upstream bypass flow exit for the bypass duct being defined between the forward assembly and the VAFN when the VAFN is in the deployed position, an outer surface of the VAFN providing an aerodynamic boundary for bypass airflow exited through the bypass flow exit; and a seal attached to the forward assembly, the seal including an inner wall and a plurality of webs attached to the inner wall and extending transversely there-from, each of the webs extending circumferentially at least partially around the bypass duct, the inner wall defining an exposed inner surface that extends circumferentially at least partially around the bypass duct, the inner surface providing a substantially smooth aerodynamic boundary for bypass airflow exited through the bypass flow exit when the VAFN is in the deployed position, at least a portion of the inner surface interfacing with the VAFN outer surface when the VAFN is in the stowed position, at least one of the plurality of webs deformable into a non-planar configuration when the VAFN is in the stowed position.