Translating variable area fan nozzle providing an upstream bypass flow exit

Patent metadata

Field	Value
Publication number	US-9759087-B2
Application number	US-201313770455-A
Country	US
Kind code	B2
Filing date	Feb 19, 2013
Priority date	Aug 8, 2007
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

First claim

What is claimed is:

1. A variable area fan nozzle assembly for a turbofan engine, the assembly comprising:
(a) a nacelle having an aft edge;
(b) a translating nozzle segment having a forward edge and a first end, the nozzle segment being movably disposed behind the aft edge, wherein an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position;
(c) a deflector disposed between the aft edge and the forward edge proximate to the first end, wherein the deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end, wherein at least a portion of the deflector is received in a void in one of the nozzle segment and the nacelle, when the nozzle segment is in the stowed position,
wherein at least a portion of the deflector overlaps a portion of the nacelle when the nozzle segment is in a fully deployed position, the overlapping portion of the deflector located between the portion of the nacelle and a centerline of the variable area fan nozzle assembly.

2. A variable area fan nozzle assembly according to claim 1 , wherein the aft edge comprises an edge of a stationary forward nacelle portion.

3. A variable area fan nozzle assembly according to claim 1 , wherein the aft edge comprises an edge of a translatable thrust reverser sleeve.

4. A variable area fan nozzle assembly according to claim 1 , wherein the deflector is affixed to the nacelle and rearwardly extends from the aft edge, and the deflector is received in a void in the nozzle segment.

5. A variable area fan nozzle assembly according to claim 1 , wherein the deflector is affixed to the nozzle segment and forwardly extends from the forward edge, and the deflector is received in a void in the nacelle.

6. 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 position, an upstream bypass flow exit is formed between the trailing edge and the leading 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 at least a portion of the deflector is received in a void in one of the at least one nozzle segment and the forward nacelle portion, when the nozzle segment is in the stowed position,
wherein at least a portion of the deflector overlaps a portion of the forward nacelle portion when the nozzle segment is in a fully deployed position, the overlapping portion of the deflector located between the portion of the forward nacelle portion and the centerline.

7. A nacelle assembly according to claim 6 , wherein the forward nacelle portion is a stationary forward cowl.

8. A nacelle assembly according to claim 6 , wherein the forward nacelle portion is a translatable thrust reverser sleeve.

9. A nacelle assembly according to claim 6 , wherein the deflector is affixed to the forward nacelle portion and rearwardly extends from the trailing edge, and the deflector is received in a void in the at least one nozzle segment.

10. A nacelle assembly according to claim 6 , wherein the deflector is affixed to the at least one nozzle segment and forwardly extends from the leading edge, and the deflector is received in a void in the forward nacelle portion.

11. A nacelle assembly according to claim 6 , wherein a gap is formed between the upstream fairing portion and the downstream fairing portion when the nozzle segment is in the one or more deployed positions, and wherein the deflector is configured to substantially block air flow that exits the nacelle assembly through the upstream bypass flow exit from passing through the gap when the nozzle segment is in the one or more deployed positions.

12. A variable area fan nozzle assembly for a turbofan engine assembly having a primary bypass flow exit for discharging engine bypass flow, the assembly comprising:
(a) a forward nacelle portion having a trailing edge;
(b) a translating nozzle segment having a leading edge and a first end;
(c) a guide mechanism for movably supporting the first end of the translating nozzle segment such that the nozzle segment is movable between a stowed position and a deployed position, wherein an upstream bypass flow exit is formed between the leading edge and the trailing edge when the nozzle segment is in the deployed position;
(d) a fairing at least partially covering the guide mechanism; and
(e) a deflector for substantially preventing air from passing through the upstream bypass flow exit in a region proximate to the fairing, at least a portion of the deflector is received in a void in one of the forward nacelle portion and the at least one nozzle segment, when the nozzle segment is in the stowed position,
wherein at least a portion of the deflector overlaps a portion of the forward nacelle portion when the nozzle segment is in a fully deployed position, the overlapping portion of the deflector located between the portion of the forward nacelle portion and a centerline of the variable area fan nozzle assembly.

13. A variable area fan nozzle assembly according to claim 12 , wherein the deflector is attached to the forward nacelle portion and rearwardly extending from the trailing edge.

14. A variable area fan nozzle assembly according to claim 12 , wherein the deflector is attached to the translating nozzle segment and forwardly extending from the leading edge.

Assignees

• Rohr Inc

Inventors

• Amkraut Daniel M
• Layland Michael John
• James Norman John

Classifications

• F05D2260/606

  Bypassing the fluid · CPC title

• F02K1/09

  by axially moving an external member, e.g. a shroud (F02K1/12 takes precedence) · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F01D25/00 Primary

  Component parts, details, or accessories, not provided for in, or of interest apart from, other groups · CPC title