Variable area fan nozzle with one or more integrated blocker doors

Patent metadata

Field	Value
Publication number	US-9551298-B2
Application number	US-201313949998-A
Country	US
Kind code	B2
Filing date	Jul 24, 2013
Priority date	Jul 24, 2012
Publication date	Jan 24, 2017
Grant date	Jan 24, 2017

Abstract

A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.

First claim

What is claimed is:

1. A nacelle assembly for a turbofan engine having an engine centerline, the nacelle assembly comprising:
a forward nacelle portion having an aft edge and defining a bypass duct that extends at least partially around the engine centerline, the bypass duct being configured to transport bypass airflow of the engine;
a translatable sleeve having a forward edge that extends circumferentially at least partially around the bypass duct and that is translatable away from the aft edge of the forward nacelle portion; and
a variable area fan nozzle (VAFN) airfoil having a forward end and an aft end, wherein the VAFN airfoil is movable between (a) a stowed position, (b) a VAFN flow position, and (c) a thrust reverse position, and includes one or more blocker doors coupled to the VAFN airfoil;
wherein, in the stowed position, the VAFN airfoil is substantially adjacent the translatable sleeve and forms a substantially continuous outer surface extending from an outer surface of the forward nacelle portion, to the translatable sleeve, and to the aft end of the VAFN airfoil;
wherein, in the VAFN flow position, the VAFN airfoil is moved aft away from the translatable sleeve to create an opening between the translatable sleeve and the VAFN airfoil, such that an airflow in the bypass duct is split into a flow through the bypass duct and a flow that may exit the bypass duct through the opening, and the one or more blocker doors are disposed radially against the VAFN airfoil; and
wherein, in the thrust reverse position, the VAFN airfoil and the translatable sleeve are moved aft away from the aft edge of the forward nacelle portion to expose a cascade array comprising an opening, and the one or more blocker doors are deployed so as to move from a position adjacent an inner surface of the VAFN airfoil to a position that extends into the bypass duct, such that at least a portion of the airflow in the bypass duct is directed out the bypass duct through the cascade array.

2. The nacelle assembly of claim 1 , wherein the cascade array is configured to move independently of the VAFN airfoil.

3. The nacelle assembly of claim 2 , wherein the cascade array is configured to move simultaneously with the translatable sleeve.

4. The nacelle assembly of claim 3 , wherein the cascade array is coupled to the translatable sleeve.

5. The nacelle assembly of claim 1 , wherein the VAFN airfoil further includes a mechanism that moves the blocker doors from a position adjacent an inner surface of the VAFN airfoil to a position that extends into the bypass duct.

6. The nacelle assembly of claim 5 , wherein the VAFN airfoil mechanism comprises a drag link.

7. The nacelle assembly of claim 6 , wherein the drag link is a link having an end attached to the blocker doors and configured such that the blocker doors are moved to the position that extends into the bypass duct when the VAFN airfoil is moved.

8. The nacelle assembly of claim 5 , wherein the mechanism comprises an actuator.

9. The nacelle assembly of claim 1 , wherein the translatable sleeve further includes a mechanism that moves the blocker doors from a position adjacent an inner surface of the VAFN airfoil to a position that extends into the bypass duct.

10. The nacelle assembly of claim 9 , wherein the mechanism comprises an actuator.

11. The nacelle assembly of claim 10 , wherein the actuator is coupled to the VAFN airfoil and moves the VAFN airfoil between the stowed, VAFN flow, and thrust reverse positions.

12. The nacelle assembly of claim 1 , wherein the nacelle assembly is mounted on a pylon of an aircraft.

13. The nacelle assembly of claim 12 , wherein the translatable sleeve is mounted to the pylon.

14. The nacelle assembly of claim 1 , further including a mechanism in the forward nacelle portion that moves the blocker doors to move from a position adjacent an inner surface of the VAFN airfoil to a position that extends into the bypass duct.

15. The nacelle assembly of claim 14 , wherein the mechanism comprises an actuator.

16. The nacelle assembly of claim 1 , wherein the one or more blocker doors move with the VAFN airfoil as the VAFN airfoil moves from the stowed position to the VAFN flow position.

17. A nacelle assembly for a turbofan engine having an engine centerline, the nacelle assembly comprising:
a forward nacelle portion having an aft edge and defining a bypass duct that extends at least partially around the engine centerline, the bypass duct being configured to transport bypass airflow of the turbofan engine;
a translatable sleeve having a forward edge that extends circumferentially at least partially around the bypass duct and that is translatable away from the aft edge of the forward nacelle portion; and
a variable area fan nozzle (VAFN) airfoil that includes a forward end and an aft end, each of which extends circumferentially at least partially around the bypass duct, and that is movable between a stowed position, a VAFN flow position, and a thrust reverse position;
wherein:
when the VAFN airfoil is in the stowed position, the VAFN airfoil is located in a position substantially adjacent the aft edge of the translatable sleeve and forms a substantially continuous outer surface extending from an outer surface of the forward nacelle portion, to the translatable sleeve, and to the aft end of the VAFN airfoil,
when the VAFN airfoil is in the VAFN flow position, the VAFN airfoil is located in an aft position, away from the translatable sleeve, to create an opening between the translatable sleeve and the VAFN airfoil, such that an airflow in the bypass duct is split into a flow through the bypass duct and a flow that may exit the bypass duct through the opening, and
when the VAFN airfoil is in the thrust reverse position, the VAFN airfoil and the translatable sleeve are located in an aft position away from the aft edge of the forward nacelle portion and a cascade array is exposed, the cascade array comprising an opening in the bypass duct, and one or more blocker doors directly attached to the VAFN airfoil are deployed so as to move from a position adjacent an inner surface of the VAFN airfoil to a position that extends into the bypass duct, such that the airflow in the bypass duct is directed out the bypass duct through the cascade array; and

wherein the one or more blocker doors are configured to move with the VAFN airfoil such that the one or more blocker doors remain in the position adjacent the inner surface of the VAFN airfoil when the VAFN airfoil is in the stowed position and the VAFN airfoil is in the VAFN flow position.

18. A nacelle assembly for a turbofan engine having an engine centerline, the nacelle assembly comprising:
a forward nacelle portion having an aft edge and defining a bypass duct that extends at least partially around the engine centerline, the bypass duct being configured to transport bypass airflow of the engine;
a translatable sleeve having a forward edge that extends circumferentially at least partially around the bypass duct and that is translatable away from the aft edge of the forward nacelle portion; and
a variable area fan nozzle (VAFN) airfoil having a forward end and an aft end, wherein the VAFN airfoil is movable between (a) a stowed position, (b) a VAFN flow position, and (c) a thrust reverse position, and the VAFN airfoil includes one or more blocker doors coupled to the VAFN airfoil;
wherein, in the stowed position, the VAFN airfoil is substantially adjacent the translatable sleeve, and the translatable sleeve airfoil is substantially adjacent the forward nac

Assignees

• Rohr Inc

Inventors

• Binks Alan
• Layland Michael J
• James Norman J

Classifications

• F05D2260/57

  using servos, independent actuators, etc. · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02K1/09

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

• F02K1/766

  with blocking systems or locking devices; Arrangement of locking devices for thrust reversers · CPC title

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title