Patent ID: 8662417

Claim:
A nacelle assembly for a gas turbine engine comprising: a nacelle defined about an axis and defining a boundary of a fan bypass flow path; and a fan variable area nozzle including a plurality of inserts movably mounted to said nacelle, each of said plurality of inserts located at a circumferential position about said nacelle, wherein said plurality of inserts are each independently moveable into the fan bypass flow path relative to said nacelle to selectively vary a fan nozzle exit area, wherein said plurality of inserts arranged in a stowed position define at least a portion of a radial inner boundary of the fan bypass flow path, wherein said plurality of inserts are moveable axially aft to reach a deployed position, wherein said plurality of inserts are axially forward of the aft end of the fan nozzle exit area, wherein said plurality of inserts in a deployed position bifurcate said fan bypass flow path into a radially inner flow path and a radially outer flow path.