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US 8,505,307 B2Granted
Translating variable area fan nozzle with split beavertail fairings
AssigneeRohr, Inc.
InventorShunshen Richard Wang
Life of this patent
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Abstract
A nacelle assembly includes a first portion having an outer fairing and a trailing edge, and a translatable variable area fan nozzle. The fan nozzle includes two or more nozzle segments, each nozzle segment having first and second opposed ends and a leading edge. The nozzle segments are selectively movable between a stowed position and one or more deployed positions. In the deployed position, an upstream bypass flow exit is formed between the trailing edge and the leading edge. The nacelle assembly further includes a guide mechanism for guiding the nozzle segments between the stowed position and the deployed position. A split beavertail failing shields the guide mechanism against air flow when the nozzle segments are in the stowed position.
Claims21
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.
4 more elements
A nacelle assembly comprising:
- a first 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 a circumferential end and a leading edge, 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 the upstream fairing portion comprises a first surface and the downstream fairing portion includes a second surface, wherein the first surface is substantially parallel to the second surface, wherein when the at least one nozzle segment is in the stowed position the first surface and the second surface are adjacent to one another in overlapped relation, and wherein the first surface and the second surface form a substantially rearwardly extending gap therebetween when the at least one nozzle segment is in the deployed position.
4 more elements
A nacelle assembly comprising:
- a first 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, the nozzle segments 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;
- means for guiding the nozzle segments between the stowed position and the deployed position;
- and
- means for shielding the means for guiding against air flow when the nozzle segments are in the deployed position;
- wherein the means for shielding comprises a split beavertail fairing including an upstream fairing portion on the first portion and a downstream fairing portion on at least one end of the 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 first portion 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 form a substantially rearwardly extending gap therebetween, wherein the substantially rearwardly extending gap is inclined with respect to a longitudinal centerline of the nacelle at a first angle.
3 more elements
The nacelle assembly for a turbofan aircraft engine having a centerline, the nacelle comprising:
- a stationary forward nacelle portion;
- a thrust reverser comprising a translatable sleeve having an outer fairing and a trailing edge, the translatable sleeve being movably disposed aft of the stationary forward nacelle portion;
- 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.
5 more elements
Dependencies are inferred from the claim text.