Drag link assembly including buried drag link fitting

Patent metadata

Field	Value
Publication number	US-10612490-B2
Application number	US-201414262393-A
Country	US
Kind code	B2
Filing date	Apr 25, 2014
Priority date	Apr 25, 2014
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

A drag link assembly for use in a thrust reverser of a propulsion system is provided. The thrust reverser includes a fixed structure and a translating structure that at least partially define an annular airstream bypass duct there between. The translating structure is moveable relative to the fixed structure. The translating structure includes a blocker door disposed at least partially within the airstream bypass duct. The drag link assembly includes a drag link fitting and a drag link. The drag link fitting is fastened to the fixed structure of the thrust reverser. The drag link includes a first end portion and an opposing second end portion. The first end portion is pivotably connected to the blocker door. The second end portion is pivotably connected to the drag link fitting. The second end portion includes a curved section.

First claim

What is claimed is:

1. A thrust reverser of a gas turbine propulsion system for an aircraft, comprising:
a blocker door which pivots between a stowed position, and a deployed position in which the blocker door redirects air to generate reverse thrust;
a drag link fitting fastened to a fixed structure of the thrust reverser at least in part by a fastener, the fixed structure forming a radially inner peripheral boundary of a bypass duct within the gas turbine propulsion system; and
a drag link having a first end and a distal second end, the first end being pivotably attached to the blocker door, and the distal second end being pivotably attached to the drag link fitting at a pivot point;
wherein the distal second end of the drag link is disposed at least partially in a channel of the drag link fitting, the fastener is disposed at least partially in the channel, and the fastener is axially overlapped by and below the distal second end of the drag link; and
wherein the drag link extends straight at least substantially along a radially-extending drag link axis, and the pivot point is offset from the radially-extending drag link axis.

2. The thrust reverser of claim 1 , wherein the fastener is at least substantially covered by the drag link when the drag link is in a first pivot position relative to the drag link fitting, and the fastener is at least partially exposed when the drag link is in a second pivot position relative to the drag link fitting.

3. The thrust reverser of claim 2 , wherein the fastener is at least partially exposed to a bypass airstream flowing through the bypass duct of the thrust reverser when the drag link is in the second pivot position relative to the drag link fitting.

4. The thrust reverser of claim 1 , wherein the channel is at least substantially covered by the drag link when the drag link is in a first pivot position relative to the drag link fitting, and the channel is at least partially exposed when the drag link is in a second pivot position relative to the drag link fitting.

5. The thrust reverser of claim 4 , wherein the channel is at least partially exposed to a bypass airstream flowing through the bypass duct of the thrust reverser when the drag link is in a second pivot position relative to the drag link fitting.

6. The thrust reverser of claim 1 , wherein the pivot point is aft of the radially-extending drag link axis.

7. The thrust reverser of claim 1 , wherein the drag link has a clubfoot configuration.

8. The thrust reverser of claim 1 , wherein the distal second end of the drag link comprises a curved section.

9. The thrust reverser of claim 1 , wherein
the distal second end of the drag link is disposed laterally between and pivotally attached to first and second portions of the drag link fitting; and
the distal second end of the drag link is laterally aligned with the fastener.

10. The thrust reverser of claim 1 , further comprising a cascade, the blocker door axially overlapping the cascade relative to an axial centerline of the gas turbine propulsion system.

11. The thrust reverser of claim 1 , wherein the pivot point includes an inner fitting pin, and the inner fitting pin has axial ends abutting the drag link fitting.

12. The thrust reverser of claim 1 , wherein the blocker door is configured to pivot radially inwards, in a direction towards the fixed structure, from the stowed position to the deployed position.

13. The thrust reverser of claim 1 , wherein the drag link extends across the bypass duct when the blocker door is in the stowed position.

14. A thrust reverser of a gas turbine propulsion system for an aircraft, comprising:
a fixed structure of the thrust reverser;
a blocker door configured to pivot radially inwards, in a direction towards the fixed structure, from a stowed position to a deployed position in which the blocker door redirects air to generate reverse thrust;
a drag link fitting fastened to the fixed structure of the thrust reverser at least in part by a fastener;
a drag link having a first end and a distal second end, the first end being pivotably attached to the blocker door, and the distal second end being pivotably attached to first and second portions of the drag link fitting such that the distal second end is pivotable about a laterally extending axis; and
wherein the distal second end of the drag link is disposed at least partially in a channel of the drag link fitting and laterally between the first and the second portions of the drag link fitting, the fastener is disposed at least partially in the channel and laterally aligned, relative to the laterally extending axis, with the distal second end of the drag link, and the distal second end of the drag link axially overlaps, relative to the laterally extending axis, the fastener when the blocker door is in the stowed position.

15. The thrust reverser of claim 14 , wherein
the distal second end of the drag link is pivotably attached to the first and the second portions of the drag link fitting at a pivot point;
the drag link extends at least substantially along a radially-extending drag link axis from the first end towards the distal second end; and
the pivot point is offset from the radially-extending drag link axis.

16. The thrust reverser of claim 15 , wherein the pivot point is aft of the radially-extending drag link axis.

17. The thrust reverser of claim 15 , wherein the pivot point includes an inner fitting pin, and the inner fitting pin has axial ends abutting the drag link fitting.

18. The thrust reverser of claim 14 , wherein fixed structure forms a radially inner peripheral boundary of a bypass duct within the gas turbine propulsion system.

19. A thrust reverser of a gas turbine propulsion system for an aircraft, comprising:
a fixed structure of the thrust reverser;
a blocker door configured to pivot radially inwards, in a direction towards the fixed structure, from a stowed position to a deployed position in which the blocker door redirects air to generate reverse thrust;
a drag link fitting fastened to the fixed structure of the thrust reverser at least in part by a fastener; and
a drag link having a first end and a distal second end, the first end being pivotably attached to the blocker door, and the distal second end being pivotably attached to the drag link fitting;
wherein the distal second end of the drag link is disposed at least partially in a channel of the drag link fitting, and the fastener is disposed at least partially in the channel and below the distal second end of the drag link; and
wherein the fastener is at least substantially axially covered by the drag link when the drag link is in a first pivot position relative to the drag link fitting, and the fastener is at least partially exposed to a bypass airstream duct of the thrust reverser when the drag link is in a second pivot position relative to the drag link fitting such that the fastener is more exposed to the bypass airstream duct when the drag link is in the second pivot position rather than when the drag link is in the first pivot position.

20. The thrust reverser of claim 19 , wherein
the distal second end of the drag link is pivotably attached to first and second portions of the drag link fitting at a pivot point;
the drag link extends at least substantially along a radially-extending drag link axis from the first end towards the distal second end;
the pivot point is offset from the radially-extending drag link axis; and
the pivot point includes an inner fitting pin, and the inner fitti

Assignees

• Rohr Inc

Inventors

• Byrne Stuart J

Classifications

• F02K1/62

  by blocking the rearward discharge by means of flaps · CPC title

• F16C2360/00

  Engines or pumps · CPC title

• F16C11/045

  with at least a pair of arms pivoting relatively to at least one other arm, all arms being mounted on one pin (crank-pins F16C11/02) · CPC title

• F02K1/763 Primary

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

• F02K1/70

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