Rotor systems and methods

Patent metadata

Field	Value
Publication number	US-10343787-B2
Application number	US-201715788039-A
Country	US
Kind code	B2
Filing date	Oct 19, 2017
Priority date	Oct 19, 2017
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A rotor system including a hub; a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface; a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears including a plurality of teeth for engaging the engagement surface of the rim; wherein the one or more outer drive gears are configured to rotate the rim such that the plurality of rotor blades rotates about the hub. Other aspects provide an aircraft rotor system and methods of operating an aircraft rotor system.

First claim

The invention claimed is:

1. A rotor system comprising:
a hub;
a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface;
a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and
one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears comprising a plurality of teeth for engaging the engagement surface of the rim;
wherein the one or more outer drive gears is configured to rotate the rim such that the plurality of rotor blades rotates about the hub.

2. The system of claim 1 , wherein each of the plurality of rotor blades has an inboard portion and an outboard portion, the inboard portion is configured to be coupled to the hub, and the outboard portion is configured to be coupled to the rim.

3. The system of claim 2 , wherein the outboard portion of each of the plurality of rotor blades comprises a blade tip that collectively define a circumference, and the rim is configured to be coupled to each blade tip such that the rim extends about the circumference.

4. The system of claim 1 , wherein each of the one or more outer drive gears can be rotated independently.

5. The system of claim 1 , wherein the engagement surface is disposed on an exterior portion of the rim.

6. The system of claim 1 , wherein the one or more outer drive gears can be rotated by at least one of an electric motor, a hydraulic motor, and a pneumatic motor.

7. The system of claim 1 , wherein the hub is only rotated by the rim.

8. The system of claim 1 , wherein the rim and the plurality of rotor blades comprise a unitary member.

9. An aircraft rotor system comprising:
a first hub having a first hub axis about which the first hub is configured to rotate;
a first plurality of rotor blades configured to extend from the first hub and rotate about the first hub axis;
wherein the first hub is configured to be rotated about the first hub axis only by the first plurality of rotor blades.

10. The system of claim 9 , further comprising a first rim configured to extend about the first hub and comprising:
a first engagement surface; and
a first interior surface configured to be coupled to at least one rotor blade of the first plurality of rotor blades.

11. The system of claim 10 , further comprising one or more outer drive gears disposed adjacent to the first engagement surface of the first rim comprising:
a plurality of teeth for engaging the first engagement surface of the first rim;
wherein the one or more outer drive gears are configured to rotate the first rim such that the first plurality of rotor blades rotates about the first hub.

12. The system of claim 11 , wherein the one or more outer drive gears are disposed at equidistant points about the first engagement surface of the first rim.

13. The system of claim 11 , wherein each of the one or more outer drive gears are configured to be rotated independently.

14. The system of claim 10 , further comprising:
a second hub having a second hub axis about which the second hub is configured to rotate;
a second plurality of rotor blades configured to extend from the second hub and rotate about the second hub axis;
a second rim configured to extend about the second hub and comprising:
a second engagement surface; and
a second interior surface configured to be coupled to at least one rotor blade of the second plurality of rotor blades; and

an outer drive gear disposed adjacent to the first engagement surface of the first rim and the second engagement surface of the second rim, the outer drive gear comprising a plurality of teeth for engaging the first engagement surface of the first rim and the second engagement surface of the second rim;
wherein the outer drive gear is configured to rotate the first rim and the second rim.

15. The system of claim 14 , wherein the first rim rotates in a first direction and the second rim rotates in a second direction such that the first direction and the second direction are different directions.

16. The system of claim 14 , wherein the outer drive gear is at least one of the following: a spiral bevel gear, a bevel gear, and a face gear.

17. A method of operating an aircraft rotor system comprising:
providing a first rotor assembly, comprising:
a first hub;
a first rim configured to rotate about the first hub, the first rim including a first interior surface and a first engagement surface; and
a first plurality of rotor blades extending from the first hub and coupled to the first interior surface of the first rim;

providing a first drive gear disposed adjacent to the first engagement surface of the first rim; and
rotating the first drive gear to impart rotation to the first rotor assembly.

18. The method of claim 17 , further comprising:
providing a second drive gear disposed adjacent to the first engagement surface of the first rim; and
rotating the second drive gear to impart rotation to the first rotor assembly.

19. The method of claim 17 , further comprising:
providing a second rotor assembly, comprising:
a second hub;
a second rim configured to rotate about the second hub, the second rim including a second interior surface and a second engagement surface; and
a second plurality of rotor blades extending from the second hub and coupled to the second interior surface of the second rim;

wherein the step of rotating the first drive gear imparts rotation to the second rotor assembly.

20. The method of claim 19 , wherein the first plurality of rotor blades and the second plurality of rotor blades rotate in different directions.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Davis Alison Ann
• Speller Charles

Classifications

• B64C2027/8209

  Electrically driven tail rotors · CPC title

• B64D35/06

  the propellers or rotors being counter-rotating · CPC title

• B64D35/00 Primary

  Transmitting power from power plants to propellers or rotors; Arrangements of transmissions · CPC title

• B64C2027/8254

  Shrouded tail rotors, e.g. "Fenestron" fans · CPC title

• B64C27/12

  Rotor drives · CPC title