Rotor assembly

Patent metadata

Field	Value
Publication number	US-11459088-B2
Application number	US-201916590322-A
Country	US
Kind code	B2
Filing date	Oct 1, 2019
Priority date	Oct 1, 2019
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

A rotor assembly configured to increase the stiffness of a rotor mast. The rotor assembly includes the rotor mast, a rotor hub, a mast nut, a mast bearing, and a cuff disposed between the mast nut and the mast bearing. The cuff is captured and compressed between the mast nut and the inner race of the mast bearing along an uninterrupted load path that extends between the mast nut and the mast bearing.

First claim

What is claimed is:

1. A rotor assembly, comprising:
a rotor mast configured to be driven in rotation about a mast axis;
a rotor hub coupled to the rotor mast for common rotation therewith;
a plurality of rotor blades extending from the rotor hub;
a mast bearing including an inner race, an outer race, and a plurality of roller elements therebetween, the inner race being coupled to the rotor mast for common rotation therewith;
a cuff surrounding the rotor mast, the cuff being positioned axially between the rotor hub and the mast bearing; and
a mast nut configured to apply a compressive force to the cuff and the inner race of the mast bearing.

2. The rotor assembly of claim 1 , wherein the rotor mast includes a shoulder adjacent the mast bearing.

3. The rotor assembly of claim 2 , further comprising:
a mast adapter, wherein the mast adapter couples the rotor hub to the rotor mast for common rotation therewith, the mast adapter being configured to be subject to the compressive force applied by the mast nut.

4. The rotor assembly of claim 3 , further comprising:
a first conical ring positioned between the mast nut and the mast adapter.

5. The rotor assembly of claim 4 , further comprising:
a second conical ring positioned between the mast adapter and the cuff.

6. The rotor assembly of claim 1 , further comprising:
an adapter bearing coupled to the cuff; and
a fan disk coupled to the adapter bearing.

7. A rotor assembly, comprising:
a rotor mast configured to be driven in rotation about a mast axis;
a rotor hub coupled to the rotor mast for common rotation therewith;
a plurality of rotor blades extending from the rotor hub;
a mast bearing coupled to the rotor mast;
a mast nut coupled to the rotor mast; and
a component disposed axially between the mast nut and the mast bearing, the component being configured to resist flexion of the rotor mast.

8. The rotor assembly of claim 7 , wherein the mast nut is configured to apply a compressive force through the component.

9. The rotor assembly of claim 7 , wherein the mast nut is disposed within the rotor hub.

10. The rotor assembly of claim 7 , wherein the component comprises an accessory adapter, comprising:
a cuff coupled for common rotation with the rotor mast.

11. The rotor assembly of claim 10 , wherein the accessory adapter further comprises:
an accessory bearing coupled to the cuff; and
a fan disk coupled to the accessory bearing.

12. The rotor assembly of claim 7 , wherein the component comprises a plurality of components, including:
a mast adapter, wherein the mast adapter couples the rotor hub to the rotor mast for common rotation therewith; and
a cuff coupled for common rotation with the rotor mast.

13. The rotor assembly of claim 12 , wherein the plurality of components further comprises:
a first conical ring positioned between the mast nut and the mast adapter; and
a second conical ring positioned between the cuff and the mast adapter.

14. The rotor assembly of claim 13 , further comprising:
an accessory bearing coupled to the cuff; and
a fan disk coupled to the accessory bearing.

15. An aircraft, comprising:
a fuselage;
a motor configured to produce rotational energy; and
a rotor assembly, comprising:
a rotor mast configured to be driven in rotation about a mast axis by the rotational energy produced by the motor;
a rotor hub coupled to the rotor mast for common rotation therewith;
a plurality of rotor blades extending from the rotor hub;
a mast bearing coupled to the rotor mast;
a mast nut coupled to the rotor mast; and
a component disposed axially between the rotor hub and the mast bearing, the component being configured to resist flexion of the rotor mast.

16. The aircraft of claim 15 , further comprising:
a duct surrounding the plurality of rotor blades.

17. The aircraft of claim 16 , wherein the duct and the rotor assembly are configured to rotate relative to the fuselage.

18. The aircraft of claim 15 , wherein the component comprises an accessory adapter, comprising:
a cuff coupled for common rotation with the rotor mast.

19. The aircraft of claim 18 , wherein the accessory adapter further comprises:
an accessory bearing coupled to the cuff; and
a fan disk coupled to the accessory bearing.

20. The aircraft of claim 18 , wherein the component comprises a plurality of components including:
a mast adapter, wherein the mast adapter couples the rotor hub to the rotor mast for common rotation therewith;
a first conical ring positioned between the mast nut and the mast adapter; and
a second conical ring positioned between the cuff and the mast adapter.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Thompson George Matthew
• Speller Charles Hubert
• Knoll Jonathan

Classifications

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• B64C27/28

  with forward-propulsion propellers pivotable to act as lifting rotors · CPC title

• B64C11/46

  Arrangements of, or constructional features peculiar to, multiple propellers {(B64C11/306 takes precedence)} · CPC title

• B64C11/02

  Hub construction · CPC title