Thrust reverser apparatus and method

Patent metadata

Field	Value
Publication number	US-10041443-B2
Application number	US-201514734298-A
Country	US
Kind code	B2
Filing date	Jun 9, 2015
Priority date	Jun 9, 2015
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.

First claim

What is claimed is:

1. A thrust reverser configured to be positioned in a turbofan engine nacelle extending around an engine core cowl, the nacelle defining an axially extending bypass duct about the engine core cowl for receiving a fan bypass air stream, the thrust reverser comprising:
a translating sleeve movably coupled to a fixed portion of the nacelle;
a blocker door pivotally coupled to the translating sleeve such that movement of the translating sleeve in an axially rearward direction causes the blocker door to move aft while remaining in an axial orientation with respect to the translating sleeve, and wherein an outer wall of the bypass duct is radially interposed between the blocker door and a fan bypass air stream when the blocker door is in a stowed position;
a plurality of translating cascade sets circumferentially arranged about the bypass duct and movably coupled to the fixed portion of the nacelle; and
a drag linkage pivotally coupled to the blocker door and to one of the plurality of translating cascade sets, wherein the drag linkage pivots about a first pivot joint upon deployment of the blocker door into the fan bypass airstream, the first pivot joint is fixed to the forward end of one of the plurality of translating cascade sets.

2. The thrust reverser of claim 1 , wherein a first end of the blocker door is coupled to the translating sleeve at a second pivot joint, the blocker door configured to pivot about the second pivot joint radially inward to a deployed position in which the blocker door is disposed at least partially in the fan bypass air stream.

3. The thrust reverser of claim 2 , wherein the drag linkage is coupled to the blocker door at a third pivot joint located at an intermediate location along a length of the blocker door.

4. The thrust reverser of claim 3 further comprising a blocker door brake configured to prevent rotation of the blocker door about the third pivot joint when the blocker door brake is engaged.

5. The thrust reverser of claim 2 , wherein upon deployment, angular rotation of the blocker door about the second pivot joint is directionally opposite the angular rotation of the drag linkage about the first pivot joint.

6. The thrust reverser of claim 1 , wherein each cascade set of the plurality of translating cascade sets include a plurality of forwardly-directed vanes.

7. The thrust reverser of claim 1 , wherein the drag linkage is configured to be concealed within the nacelle body when the blocker door is in the stowed position.

8. The thrust reverser of claim 1 , further comprising an actuation system coupled to the translating sleeve, the actuation system including an actuator fixed to the fixed portion of the nacelle and a plurality of hydraulic cylinders driven by the actuator.

9. The thrust reverser of claim 1 , wherein:
the blocker door is one of a pair of blocker doors, each pivotally coupled to the translating sleeve; and
a first of the pair of blocker doors is pivoted to a deployed position in which the first blocker door is disposed at least partially in the fan bypass air stream and the second of the pair of blocker doors is pivoted in a direction opposite the first blocker door.

10. The thrust reverser of claim 1 further comprising a bullnose at an aft end of the fixed portion of the nacelle, and wherein the blocker door and the drag linkage are positioned forward of the bullnose when the blocker door and the drag linkage are in the stowed position.

11. A method of deploying the thrust reverser of claim 1 for use with a turbofan engine, the method comprising:
moving the translating sleeve of the thrust reverser axially rearward, wherein movement of the translating sleeve axially rearward causes the blocker door pivotally coupled to the translating sleeve via the first pivot joint to move axially rearward while remaining in the axial orientation; and
pivoting the blocker door about the first pivot joint to cause the blocker door to pivot from the axial orientation into a deployed orientation.

12. The method of claim 11 further comprising releasing a blocker door brake to allow the blocker door to pivot about the first pivot joint.

13. The method of claim 11 , wherein:
said moving the translating sleeve comprises extending a first hydraulic cylinder to cause the translating sleeve to move axially rearward; and
said pivoting the blocker door comprising extending a second hydraulic cylinder, the second hydraulic cylinder in a telescoping arrangement with the first hydraulic cylinder.

14. The method of claim 13 , wherein said extending the second hydraulic cylinder causes the drag linkage to push on the blocker door at a second pivot joint disposed at an intermediate location between ends of the blocker door.

15. The method of claim 14 further comprising a retraction of the thrust reverser by:
a) retracting the second hydraulic cylinder to pivot the blocker door from the deployed orientation to the axial orientation,
b) engaging the blocker door brake; and
c)releasing the track lock.

16. The method of claim 15 , further comprising:
d) retracting the first hydraulic cylinder to cause the translating sleeve to move axially forward.

17. The method of claim 13 further comprising following extension of the first hydraulic cylinder, engaging a track lock and releasing a blocker door brake.

18. The method of claim 13 further comprising releasing a blocker door brake to allow the blocker door to pivot about the first pivot joint.

Assignees

• Boeing Co

Inventors

• Foutch David W

Classifications

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F02K1/763 Primary

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

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F02K1/766

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