Patent ID: 8505307
Filing Date: 2013-08-13
Classification: F02K,F05D,Y10T

Abstract:
1. A nacelle assembly for a turbofan aircraft engine having an engine centerline, the nacelle comprising: a stationary forward nacelle portion having an outer fairing and a trailing edge; a translatable variable area fan nozzle comprising two or more nozzle segments, each nozzle segment having first and second opposed ends and a leading edge that outwardly and rearwardly slopes at a first angle with respect to the engine centerline, the fan nozzle being selectively movable between a stowed position and one or more deployed positions, wherein in the deployed position, an upstream bypass flow exit is formed between the trailing edge and the leading edge; and a split beavertail fairing comprising an upstream fairing portion on the outer fairing and a downstream fairing portion on at least one end of at least one nozzle segment; wherein when the at least one 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 outer fairing and the at least one nozzle segment; and wherein when the at least one nozzle segment is in the deployed position, the upstream fairing portion and the downstream fairing portion define a substantially rearwardly extending elongated gap therebetween, the elongated gap being inclined with respect to the engine centerline at a second angle.