OUTBOARD CENTRIFUGAL FORCE BEARING WITH INBOARD BLADE FOLD AXIS IN A FOLDING ROTOR BLADE ASSEMBLY

• US 20190185153A1
• Filed: 12/18/2017
• Published: 06/20/2019
• Est. Priority Date: 12/18/2017
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: PAULSON, Jared Mark, Baldwin, Tyler Wayne, Cravener, Kyle Thomas
• Granted Patent: US 10,640,205 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 27/48 Root attachment to rotor head
• CPC Class Codes: B64C 27/50 Blades foldable to facilitate stowage of aircraft
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft

Abstract

A rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard CF bearing and the yoke tip. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Claims

1. A folding rotor blade assembly for a tiltrotor aircraft, comprising:

a drive mast connected to a hub spring assembly;

a yoke connected to the hub spring assembly;

an inboard bearing assembly connected to the yoke proximate the hub spring assembly;

an outboard bearing assembly, including an outboard centrifugal force (“

CF”

) bearing, connected to the yoke;

a grip connected to the inboard bearing assembly; and

a rotor blade connected to the grip at a pivotal connection positioned inboard of the CF bearing.

2. The folding rotor blade assembly of claim 1, wherein the outboard bearing assembly further comprises an outboard shear bearing.

3. The folding rotor blade assembly of claim 1, wherein the inboard bearing assembly further comprises an inboard shear bearing.

4. The folding rotor blade assembly of claim 1, wherein the outboard bearing assembly further comprises:

an outboard beam connected to the rotor blade and connected to the outboard CF bearing; and

a spindle connected to the outboard CF bearing and connected to the yoke opposite the hub spring assembly.

5. The folding rotor blade assembly of claim 1, wherein the inboard bearing assembly further comprises:

a clamp plate connected to the yoke and connected to an inboard shear bearing; and

an inboard beam connected to the grip and connected to the inboard shear bearing.

6. The folding rotor blade assembly of claim 1, further comprising a pair of axially aligned blade fold bolts at the pivotal connection providing a pivot axis of the rotor blade relative to the grip.

7. The folding rotor blade assembly of claim 1, wherein the rotor blade is connected to the grip at a releasable connection with axially aligned releasable pins.

8. The folding rotor blade assembly of claim 7, wherein upon engagement of the releasable pins with the rotor blade and the grip, the rotor blade is locked with respect to the grip in an unfolded position.

9. The folding rotor blade assembly of claim 7, wherein upon release of the releasable pins from engagement with the rotor blade and the grip, the rotor blade may be rotated around the pivotal connection to a folded position.

10. The folding rotor blade assembly of claim 1, wherein the rotor blade further comprises a first blade tang and a second blade tang connected to interior surfaces of the grip at the pivotal connection.

11. A folding rotor blade assembly, comprising:

a yoke connected to a hub spring assembly;

an inboard clamp mounted to the yoke proximate the hub spring assembly and connected to an inboard shear bearing;

an inboard beam, housing the inboard shear bearing, connected to a grip;

a spindle connected to the yoke and connected to an outboard centrifugal force (“

CF”

) bearing;

an outboard beam, housing the outboard CF bearing, connected to a rotor blade; and

the rotor blade connected to the grip at a pivotal connection positioned inboard of the outboard CF bearing.

12. The folding rotor blade assembly of claim 11, further comprising a pair of axially aligned blade fold bolts at the pivotal connection providing a pivot axis of the rotor blade relative to the grip.

13. The folding rotor blade assembly of claim 12, wherein the rotor blade is connected to the grip at a releasable connection with axially aligned releasable pins.

14. The folding rotor blade assembly of claim 13, wherein upon engagement of the releasable pins with the rotor blade and the grip, the rotor blade is locked with respect to the grip in an unfolded position.

15. The folding rotor blade assembly of claim 13, wherein upon release of the releasable pins from engagement with the rotor blade and the grip, the rotor blade may be rotated around the pivotal connection to a folded position.

16. The folding rotor blade assembly of claim 13, wherein the rotor blade further comprises a first blade tang and a second blade tang connected to interior surfaces of the grip at the pivotal connection.

17. A method comprising:

pitching a rotor blade of a rotor blade assembly comprising an inboard bearing connected to a yoke and a grip, an outboard bearing connected to the yoke and the rotor blade, the rotor blade connected to the grip at a lockable connection with releasable pins and at a pivotable connection with axially aligned blade bolts providing a pivot axis inboard of the outboard bearing;

releasing the releasable pins at the lockable connection; and

rotating the rotor blade about the pivot axis.

18. The method of claim 17, wherein the outboard bearing further comprises an outboard centrifugal force bearing and a shear bearing.

19. The method of claim 18, wherein the rotor blade assembly is connected to a nacelle pivotally mounted to a wing.

20. The method of claim 19, wherein the rotor blade assembly is mounted to a wing and the wing is mounted to a fuselage.