Rotor hub bearing system

Patent metadata

Field	Value
Publication number	US-9896198-B2
Application number	US-201514805159-A
Country	US
Kind code	B2
Filing date	Jul 21, 2015
Priority date	Nov 15, 2011
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

The bearing system is configured for treating and reacting dynamic loading within a rotor hub of rotorcraft. The bearing system includes an outer member having a plurality of alternating outer elastomeric layers and shim layers. The outer member has an inboard surface configured for bonding to an inboard bearing support, and the outer member has an outboard surface configured for bonding to an outboard bearing support. The bearing system has an inner member bonded to an interior surface of the outer member. The inner member can include a rigid inner core, as well as a plurality of elastomeric layers and shim layers configured to react torsional movements of the rotor blade.

First claim

The invention claimed is:

1. A bearing system for an aircraft, the system comprising:
an outer member having a plurality of alternating outer elastomeric layers and shim layers, wherein the outer member has an inboard surface configured for bonding to an inboard bearing support, and wherein the outer member has an outboard surface configured for bonding to an outboard bearing support;
an inner member bonded to an interior surface of the outer member, the inner member comprising:
a rigid inner core;
a first journal bearing member having alternating inner member elastomeric layers and inner member shim layers, the journal member being cylindrically shaped; and
a flat bearing member having alternating inner member elastomeric layers and inner member shim layers, the flat bearing member being oriented vertically through the rigid inner core;
wherein the first journal bearing member and the first flat bearing are configured to provide torsional compliance.

2. The system according to claim 1 , wherein the flat bearing member is centered on a vertical centerline of the rigid inner core.

3. The system according to claim 1 , wherein the first journal bearing member is offset from a vertical centerline of the rigid inner core.

4. The system according to claim 1 , wherein the first journal bearing member is configured to be nearly rigid in response to a flapping motion of the rotor blade.

5. The system according to claim 1 , wherein the flat bearing member is configured to be nearly rigid in response to a lead/lag motion of the rotor blade.

6. The system according to claim 1 , wherein the flat bearing member and first journal bearing member are bonded in the rigid inner core.

7. The system according to claim 1 , wherein outboard bearing support is coupled to a rotor yoke in a rotor hub, the rotor yoke having a flapping flexure for partially treating flapping movements of the rotor blade.

8. The system according to claim 1 , wherein the inboard bearing support is coupled to a rotor grip, the rotor grip configured for securing the rotor blade.

9. The system according to claim 1 , the inner member further comprising:
a second journal bearing member also having alternating inner member elastomeric layers and inner member shim layers.

10. The system according to claim 9 , the inner member further comprising:
a rigid spindle portion configured to transfer shear loads to the first journal bearing member and the second journal bearing member.

Assignees

• Davis Hunter
• Stamps Frank B
• Textron Innovations Inc

Inventors

• Davis Hunter
• Stamps Frank B

Classifications

• F03D1/0658

  Arrangements for fixing wind-engaging parts to a hub · CPC title

• B64C27/32 Primary

  Rotors · CPC title

• B64C27/35 Primary

  having elastomeric joints · CPC title

• Y02E10/72

  Wind turbines with rotation axis in wind direction · CPC title