Patent ID: 9617871
Date: 2017-04-11
CPC Classifications: B64D,F01D,F02K

Claim:
1. A nacelle assembly apparatus for a turbofan engine, the apparatus comprising: a nacelle wall defining a bypass duct that extends at least partially around a centerline of a turbofan engine, the bypass duct being configured to transport bypass airflow of the engine, the nacelle wall having an aft end recess within a thickness of the nacelle wall; and an arcuate variable area fan nozzle (VAFN) section having a front region, a center region, and a trailing edge, the VAFN section being movable between (a) a fully forward position and (b) a fully aft position, the front region of the VAFN section configured to be at least partially supported within the recess of the nacelle wall at all positions between and including the fully forward and fully aft positions, and the center region configured within the recess of the nacelle wall where the VAFN section is in the fully forward position; wherein the VAFN section is configured to bear against and be at least partially supported by an internal lip of the recess, and the VAFN section is radially outboard of the internal lip.