BEARING FAILURE INDICATOR

• US 20090116777A1
• Filed: 05/03/2007
• Published: 05/07/2009
• Est. Priority Date: 05/16/2006
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus UK Limited (Airbus SE)
• Inventors: Burness, Richard John Henry, Blades, Paul
• Granted Patent: US 8,087,832 B2
• Time in Patent Office: Days
• US Class Current: 384/448
• CPC Class Codes: F16C 11/045 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 Class Codes: F16C 19/38 with two or more rows of rollers
• CPC Class Codes: F16C 19/52 with devices affected by abnormal or undesired conditions
• CPC Class Codes: F16C 23/086 forming a track for rolling elements
• CPC Class Codes: G01M 13/04 Bearings

Abstract

The invention provides a bearing failure indication arrangement comprising a bearing having an inner and outer race, a first part arranged to be attached in fixed relation to either the bearing inner race or bearing outer race, a failure indicator arranged in fixed relation to both the first part and either the bearing inner race or the bearing outer race, the failure indicator constructed so that if relative movement occurs between the first part and the bearing race to which it is attached, the failure indicator responds to the relative movement thereby indicating failure of the bearing. The failure indicator is particularly adapted for use in aircraft structures and indicates full of partial bearing failure by means of movement and/or deformation of the indicator.

Claims

1. A bearing failure indication arrangement comprising:

a bearing having an inner and outer race;

a first part arranged to be attached in fixed relation to either the bearing inner race or bearing outer race;

a failure indicator arranged in fixed relation to both the first part and either the bearing inner race or the bearing outer race, the failure indicator adapted so that if relative movement occurs between the first part and the bearing race to which it is attached, the failure indicator responds to the relative movement thereby indicating failure of the bearing, wherein the failure indicator incorporates a pointer which is adapted to move, in relation to the bearing race to which it is in fixed relation, when the bearing failure indicator deforms or moves.

2. A bearing failure indication arrangement as claimed in claim 1 wherein the failure indicator responds to the relative movement by moving in relation to the first part and/or the bearing race to which the first part is attached.

3. A bearing failure indication arrangement as claimed in claim 1 wherein the failure indicator responds to the relative movement by deforming.

4. A bearing failure indication arrangement as claimed in claim 1 wherein the failure indicator is in the form of an annular ring that is adapted to engage with the bearing inner race or the bearing outer race.

5. A bearing failure indication arrangement as claimed in claim 1 wherein the failure indicator engages with the bearing inner race or the bearing outer race by means of a detent.

7. A bearing failure indication arrangement as claimed in claim 1 wherein the first part is a hinge pin that is mounted in the bearing inner race.

8. A bearing failure indication arrangement as claimed in claim 7 wherein the failure indicator is in the form of an annular ring, the inner perimeter of which is adapted to engage with an outer surface of the hinge pin.

9. A bearing failure indication arrangement as claimed in claim 5 wherein the pointer is adapted to move and/or deform if the hinge pin moves in relation to the bearing inner race.

10. A bearing failure indication arrangement as claimed in claim 1 wherein the failure indicator is fabricated from a material having properties selected so that the failure indicator responds to a specific torque being transmitted between the bearing inner and outer race.

11. A hinge incorporating at least one bearing failure indication arrangement claimed in claim 1.

12. An aircraft control surface incorporating a hinge as claimed in claim 11.

6. (canceled)