Corrosion resistant bearing material

Patent metadata

Field	Value
Publication number	US-10012265-B2
Application number	US-201514728402-A
Country	US
Kind code	B2
Filing date	Jun 2, 2015
Priority date	Dec 6, 2007
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

In one aspect, the present invention resides in an edge flap arrangement for an aircraft wing that has a main flap element and an actuator for moving the main flap element relative to the wing, a linkage arrangement that supports the main flap element from the aircraft wing for movement relative to the wing, the linkage arrangement including a drop link and a hinge point. The fixed strut and the drop link are pivotally connected by the hinge point. The hinge point includes a bearing. The bearing is an hourglass bearing assembly that has an inner raceway outer raceway. The outer raceway is positioned around the inner raceway. A plurality of rollers is disposed between the inner raceway and the outer raceway. The plurality of rollers, the outer raceway and/or the inner raceway are manufactured from CREN and/or CRES.

First claim

What is claimed is:

1. An edge flap arrangement for an aircraft wing, the arrangement comprising:
a main flap element and an actuator for moving the main flap element relative to the wing;
a linkage arrangement supporting the main flap element from the aircraft wing for movement relative to the wing, the linkage arrangement including a fixed strut secured to the aircraft wing and a drop link secured to the main flap, the fixed strut and the drop link being pivotally connected by a hinge point;
the hinge point comprising at least a first hourglass bearing assembly, the first hourglass bearing assembly comprising:
an inner raceway defining a radially outwardly facing convex surface having an inner raceway radius of curvature Ri;
an outer raceway defining a radially inward facing convex inner surface having an outer raceway radius of curvature Ro, the outer raceway being positioned around the inner raceway; and
a plurality of rollers disposed between the inner raceway and the outer raceway, each of the plurality of first rollers having an hourglass shape and being in rolling engagement with the inner raceway and the outer raceway.

2. The edge flap arrangement of claim 1 , further comprising:
at least a second hourglass bearing assembly installed in the actuator for moving the main flap element relative to the aircraft wing, the at least one second hourglass bearing assembly comprising:
an inner raceway defining a radially outwardly facing convex surface having an inner raceway radius of curvature Ri;
an outer raceway defining a radially inward facing convex inner surface having an outer raceway radius of curvature Ro, the outer raceway being positioned around the inner raceway; and
a plurality of second rollers disposed between the inner raceway and the outer raceway, each of the plurality of rollers having an hourglass shape and being in rolling engagement with the inner raceway and the outer raceway.

3. The edge flap arrangement of claim 1 wherein the hinge point comprises a plurality of first bearings.

4. The edge flap arrangement of claim 2 wherein the actuator comprises a plurality of second bearings.

5. The edge flap arrangement of claim 1 , wherein each of the plurality of rollers comprises CRES.

6. The edge flap arrangement of claim 5 , wherein each of the plurality of rollers comprises 440C stainless steel.

7. The edge flap arrangement of claim 1 , wherein the inner raceway comprises CRES.

8. The edge flap arrangement of claim 7 , wherein the inner raceway comprises 440C stainless steel.

9. The edge flap arrangement of claim 1 , wherein the outer raceway comprises CRES.

10. The edge flap arrangement of claim 9 , wherein the outer raceway comprises 440C stainless steel.

11. The edge flap arrangement of claim 1 configured for use with other than Boeing® aircraft.

12. The edge flap arrangement of claim 1 configured for use with an Airbus A-350 aircraft.

13. The edge flap arrangement of claim 2 , wherein each of the plurality of first and second rollers comprises CREN.

14. The edge flap arrangement of claim 2 , wherein each of the plurality of first and second rollers comprises AMS 5925.

15. The edge flap arrangement of claim 2 , wherein each of the plurality of first and second rollers comprises AMS 5920.

16. The edge flap arrangement of claim 1 , wherein the inner raceway comprises CREN.

17. The edge flap arrangement of claim 1 , wherein the inner raceway comprises AMS 5925.

18. The edge flap arrangement of claim 1 , wherein the inner raceway comprises AMS 5920.

19. The edge flap arrangement of claim 1 , wherein the outer raceway comprises CREN.

20. The edge flap arrangement of claim 1 , wherein the outer raceway comprises AMS 5925.

21. The edge flap arrangement of claim 1 , wherein the outer raceway comprises AMS 5920.

22. The edge flap arrangement of claim 2 , wherein each of the plurality of first and second rollers comprises 422 stainless steel.

23. The edge flap arrangement of claim 1 , wherein the inner raceway comprises 422 stainless steel.

24. The edge flap arrangement of claim 1 , wherein the outer raceway comprises 422 stainless steel.

Assignees

• Roller Bearing Co America Inc

Inventors

• Habibvand Alex
• Gyuricsko Frederick S
• Phoenix Jay
• Fredericksen Arnold E
• Cowles Jr John H

Classifications

• F16C11/0614

  the female part of the joint being open on two sides · CPC title

• F16C33/62

  Selection of substances · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• B64C9/16

  at the rear of the wing · CPC title