Low shear modulus transition shim for elastomeric bearing bonding in torsional applications

• US 9,879,722 B2
• Filed: 03/11/2013
• Issued: 01/30/2018
• Est. Priority Date: 03/11/2013
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Jarrett, Chad Lewis, Stamps, Frank Bradley, Sottiaux, Daniel P.
• Primary Examiner(s): Laurenzi, Mark
• Assistant Examiner(s): France, Mickey
• Application Number:
  US13/793,683
• Publication Number:
  US 20140255191A1
• Time in Patent Office: 1,786 Days
• Field of Search: 384125, 384276, 384297, 384626, 384909, 384912, 3849071
• CPC Class Codes: B64C 27/33 having flexing arms
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: F16C 27/02 Sliding-contact bearings
• CPC Class Codes: F16C 33/04 Brasses; Bushes; Linings
• CPC Class Codes: F16F 1/3842 Method of assembly, production or treatment; Mounting thereof supports for pipes, cables or protective tubing F16L3/00

Abstract

A bearing assembly comprises a bearing, a shim disposed within the bearing, and a component disposed within the shim. The shim comprises a first material, the component comprises a second material, and the first material has an elastic modulus value that is lower than an elastic modulus value of the second material. An apparatus comprises an elastomeric bearing, a fiberglass shim, and a steel spindle that is connected to the elastomeric bearing through the shim. A method for reducing strain in an adhesive layer that connects a bearing to a component comprises selecting a shim material having an elastic modulus value that is less than an elastic modulus value of the component and providing instructions to connect the component to the shim by placing the adhesive layer between an outer surface of the component and an inner surface of the shim.

Claims

1. A bearing assembly comprising:

a bearing comprising alternating rigid and elastomeric layers;

a shim fitted within the bearing, the shim comprising fiberglass;

a metal rotor blade spindle disposed within the shim; and

an adhesive layer that adheres the shim to the metal rotor blade spindle,

wherein the shim comprises a first material and the metal rotor blade spindle a second material,

wherein the first material has an elastic modulus value that is lower than an elastic modulus value of the second material, and the shim is configured to absorb at least a portion of a torsional strain between the metal rotor blade spindle and the bearing that reduces torsional strain on the adhesive layer.

2. The bearing assembly of claim 1, wherein the metal comprises steel.

3. The bearing assembly of claim 1, wherein the bearing comprises an elastomeric bearing.

4. The bearing assembly of claim 1, further comprising an adhesive layer disposed between the shim and the bearing.

5. The bearing assembly of claim 1, wherein the bearing comprises a helicopter rotor shear bearing.

6. The bearing assembly of claim 1, wherein the metal rotor blade spindle comprises a spindle of a rotor grip.

7. An apparatus comprising:

an elastomeric bearing comprising alternating rigid and elastomeric layers;

a fiberglass shim disposed within the elastomeric bearing, wherein the fiberglass shim comprises a first material and a steel rotor blade spindle comprises a second material and is fitted with the fiberglass shim a second material, wherein the first material has an elastic modulus value that is lower than an elastic modulus value of the second material, and the fiberglass shim is configured to absorb at least a portion of a torsional strain between the steel rotor blade spindle and the elastomeric bearing that reduces torsional strain on an adhesive layer between the fiberglass shim and the steel rotor blade spindle;

wherein the steel rotor blade spindle is connected to the elastomeric bearing through the fiberglass shim; and

the adhesive layer adheres the fiberglass shim to the steel rotor blade spindle.

8. The apparatus of claim 7, further comprising a pitch horn that is attached to one end of the steel rotor blade spindle and that is configured to rotate the steel rotor blade spindle within the elastomeric bearing.

9. The apparatus of claim 7, wherein the elastomeric bearing comprises alternating elastic and rigid layers.

10. The apparatus of claim 7, wherein the elastomeric bearing comprises a rotor shear bearing.

11. The apparatus of claim 7, wherein the steel spindle is a steel rotor blade spindle of a rotor grip that is configured to rotate a rotor blade, wherein the rotor grip and the rotor blade are components of a rotor assembly, wherein the apparatus further comprises an engine, a drive shaft, a transmission, a mast, and a fuselage, wherein power from the engine is transferred to the rotor assembly through the drive shaft, the transmission, and the mast, and wherein the fuselage houses and supports at least a portion of the engine, the drive shaft, the transmission, and the mast.

12. A method for reducing strain in an adhesive layer that connects a bearing to a metal rotor blade spindle, the method comprising:

selecting a shim material, wherein the shim material is fiberglass, having an elastic modulus value that is less than an elastic modulus value of the metal rotor blade spindle, wherein the shim comprises a first material and the metal rotor blade spindle is fitted with the shim a second material, wherein the first material has an elastic modulus value that is lower than an elastic modulus value of the second material, and the shim is configured to absorb at least a portion of a torsional strain between the metal rotor blade spindle and the bearing that reduces torsional strain on the adhesive layer; and

adhering the shim to the metal rotor blade spindle with the adhesive layer between an outer surface of the metal rotor blade spindle and an inner surface of the shim.

13. The method of claim 12, wherein connecting the metal rotor blade spindle to the shim comprises bonding the metal rotor blade spindle to the shim using fiberglass strands or carbon fibers.

14. The method of claim 12, wherein connecting the metal rotor blade spindle to the shim comprises removing gas bubbles from the adhesive layer using a vacuum.

15. The method of claim 12, comprising disposing the shim within the bearing before the metal rotor blade spindle is connected to the shim.

16. The method of claim 12, further comprising selecting a shape of the shim.

17. The method of claim 16, wherein selecting the shape of the shim comprises selecting a shim having an annular cylinder shape.

18. The method of claim 16, wherein selecting the shape of the shim comprises selecting a shim having an annular tapered shape.