Pivot thrust reverser with multi-point actuation

Patent metadata

Field	Value
Publication number	US-9581108-B2
Application number	US-201414184376-A
Country	US
Kind code	B2
Filing date	Feb 19, 2014
Priority date	Feb 22, 2013
Publication date	Feb 28, 2017
Grant date	Feb 28, 2017

Abstract

One embodiment includes a pivot thrust reverser with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

First claim

The invention claimed is:

1. A pivot thrust reverser for use in a gas turbine engine assembly, the pivot thrust reverser comprising:
a first pivot door with an upper linkage and a lower linkage;
a second pivot door spaced from the first pivot door with an upper linkage and a lower linkage;
a first actuator located on a first side of an attachment location to drive the upper linkage of the first pivot door;
a second actuator located on a second side of the attachment location to drive the upper linkage of the second pivot door; and
a third actuator located substantially radially opposite the attachment location to drive both the lower linkage of the first pivot door and the lower linkage of the second pivot door, wherein the first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator, and wherein the second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

2. The pivot thrust reverser of claim 1 , wherein the first actuator, the second actuator and the third actuator are all located between a surface of a bypass duct and an outer surface of a nacelle.

3. The pivot thrust reverser of claim 2 , wherein the first actuator, the second actuator, and the third actuator are circumferentially spaced apart.

4. The pivot thrust reverser of claim 2 , wherein the first pivot door and the second pivot door each form both a portion of the surface of the bypass duct and a portion of the outer surface of the nacelle when in the stowed position.

5. The pivot thrust reverser of claim 1 , wherein the first pivot door and the second pivot door are pivoted from the stowed position to the deployed position on respective pivot points that are each spatially fixed relative to the gas turbine engine assembly.

6. The pivot thrust reverser of claim 1 , wherein in the deployed position the first pivot door and the second pivot door each circumferentially surround an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.

7. The pivot thrust reverser of claim 1 , wherein the second pivot door is spaced approximately 180° from the first pivot door relative to an axis of the gas turbine engine assembly.

8. The pivot thrust reverser of claim 1 , further comprising a first cutout on the first pivot door.

9. The pivot thrust reverser of claim 8 , further comprising a second cutout on the second pivot door.

10. The pivot thrust reverser of claim 9 , wherein the first cutout on the first pivot door and the second cutout on the second pivot door are both arc-shaped.

11. The pivot thrust reverser of claim 1 , wherein the first pivot door and the second pivot door are each located substantially at an aft portion of a nacelle, and wherein the nacelle contains one opening at the aft portion where the first pivot door is located when in the stowed position and opens into when in the deployed position and a second opening at the aft portion where the second pivot door is located when in the stowed position and opens into when in the deployed position.

12. A method for use in a gas turbine engine assembly, the method comprising:
pivoting a first pivot door with an upper linkage and a lower linkage from a stowed position to a deployed position by a first actuator and a third actuator with the first actuator driving the upper linkage connected to the first pivot door and the third actuator driving the lower linkage connected to the first pivot door; and
pivoting a second pivot door with an upper linkage and a lower linkage spaced from the first pivot door from the stowed position to the deployed position by a second actuator and the third actuator with the second actuator driving the upper linkage connected to the second pivot door and the third actuator driving the lower linkage connected to the second pivot door.

13. The method of claim 12 , further comprising:
circumferentially surrounding an inner surface of a bypass duct with the first pivot door and the second pivot door when the first pivot door and the second pivot door are in the deployed position; and
redirecting a fan bypass stream during engine operation when the first pivot door and the second pivot door are in the deployed position.

14. The method of claim 13 , further comprising maintaining both a core stream and a nacelle ventilation stream to flow in the same manner as when the first pivot door and the second pivot door are in the stowed position.

15. The method of claim 13 , wherein the first pivot door and the second pivot door are pivoted on respective pivot points each spatially fixed relative to the gas turbine engine assembly.

16. The method of claim 15 , further comprising locating the first pivot door and the second pivot door to form both a portion of a surface of a bypass duct and a portion of an outer surface of a nacelle when in a stowed position.

17. The method of claim 16 , further comprising locating the first actuator, the second actuator, and the third actuator between the surface of the bypass duct and the outer surface of the nacelle.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M

Classifications

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• F02K1/64

  Reversing fan flow · CPC title

• F02K1/763 Primary

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

• Y10T29/49229

  Prime mover or fluid pump making · CPC title