Patent ID: 8402765
Filing Date: 2013-03-26
Classification: F02K,F05D,Y10T

Abstract:
1. A nacelle assembly for a turbofan aircraft engine having a centerline, the nacelle comprising: (a) a forward nacelle portion having an outer fairing and a trailing edge; (b) a translatable variable area fan nozzle comprising at least one nozzle segment, the nozzle segment having a leading edge and a first end and being selectively movable between a stowed position and one or more deployed positions, wherein in the deployed positions, an upstream bypass flow exit is formed between the trailing edge and the leading edge and in at least the stowed position, the nozzle segment overlaps with the forward nacelle trailing edge; (c) a split beavertail fairing comprising an upstream fairing portion on the outer fairing of the forward nacelle portion and a downstream fairing portion on the first end of at least one nozzle segment, wherein when the nozzle segment is in the stowed position, the upstream fairing portion and the downstream fairing portion combine to form a substantially continuous outer surface extending between the forward nacelle portion and the at least one nozzle segment; and (d) a deflector located proximate to the first end of the at least one nozzle segment and adjacent the split beavertail fairing, wherein the deflector is configured to substantially block air flow that exits the nacelle assembly through the upstream bypass flow exit from contacting the split beavertail fairing when the nozzle segment is in the deployed position; wherein the deflector is affixed to the nacelle and rearwardly extends from the trailing edge; wherein at least a portion of the deflector overlaps a portion of the nozzle segment when the nozzle segment is in a fully deployed position of said one or more deployed positions.