Rotor assembly apparatus

Patent metadata

Field	Value
Publication number	US-10875637-B2
Application number	US-201815976582-A
Country	US
Kind code	B2
Filing date	May 10, 2018
Priority date	Dec 15, 2014
Publication date	Dec 29, 2020
Grant date	Dec 29, 2020

Abstract

Rotor assembly apparatus are disclosed. An example rotor assembly includes a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly. A first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts. Each of the second shafts to provide torque to a respective blade coupled to the rotor assembly.

First claim

What is claimed is:

1. A rotor assembly, comprising:
a swashplate responsive to at least one of a collective control or a cyclic control;
a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the swashplate; and
a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly;
a plurality of carriers, each carrier coupled to a respective one of the second shafts;
a first stage planetary gear system disposed in each of the carriers;
a second stage planetary gear system disposed in each of the carriers; and
an output shaft coupled to each of the second stage planetary gear systems to provide the torque to respective ones of the blades.

2. A rotor assembly, comprising:
a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly;
a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly;
a plurality of carriers, each carrier coupled to a respective one of the second shafts
a first stage planetary gear system disposed in each of the carriers;
a second stage planetary gear system disposed in each of the carriers;
an output shaft coupled to each of the second stage planetary gear systems to provide the torque to respective ones of the blades; and
pitch shafts, a sun gear of the first stage planetary gear systems being coupled to respective ones of the pitch shafts.

3. The rotor assembly as defined in claim 1 , wherein the first gear assembly comprises a bull gear and pinion gears, each of the second shafts extending from respective ones of the pinion gears.

4. The rotor assembly as defined in claim 3 , wherein the bull gear is coupled to the first shaft via a diaphragm coupling.

5. The rotor assembly as defined in claim 3 , wherein the bull gear assembly comprises first teeth angled relative to the first axis, and each of the pinion gears comprises second teeth angled relative to the first axis.

6. The rotor assembly as defined in claim 1 , wherein the first axis is different than each of a plurality of second axes corresponding to respective ones of the second shafts.

7. The rotor assembly as defined in claim 1 , wherein the torque is applied to a torsion shaft of the respective blades to cause the respective blades to twist.

8. A rotor assembly, comprising:
a swashplate responsive to at least one of a collective control or a cyclic control;
a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the swashplate; and
a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly;
a carrier coupled to each one of the second shafts, each one of the second shafts extending through a pitch shaft of a rotor assembly, each one of the second shafts providing a first amount of torque to the carrier;
a first stage planetary gear system disposed in the carrier, the carrier to drive rotation of the first stage planetary gear system;
a second stage planetary gear system disposed in the carrier, the first stage planetary gear system to drive rotation of the second stage planetary gear system; and
an output of the second stage planetary gear system to provide a second amount of torque to a blade.

9. A rotor assembly, comprising:
a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly;
a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly;
a carrier coupled to each one of the second shafts, each one of the second shafts extending through a pitch shaft of a rotor assembly, each one of the second shafts providing a first amount of torque to the carrier;
a first stage planetary gear system disposed in the carrier, the carrier to drive rotation of the first stage planetary gear system, the first stage planetary gear system including a first stage sun gear, the first stage sun gear being fixed to the pitch shaft;
a second stage planetary gear system disposed in the carrier, the first stage planetary gear system to drive rotation of the second stage planetary gear system; and
an output of the second stage planetary gear system to provide a second amount of torque to a blade.

10. The rotor assembly as defined in claim 9 , wherein first stage planet gears mesh with the first stage sun gear, and each of the first stage planet gears is mounted to a planet shaft.

11. The rotor assembly as defined in claim 10 , wherein the second stage planetary gear system includes a second stage sun gear, the output of the second stage planetary gear system including the second stage sun gear.

12. The rotor assembly as defined in claim 11 , wherein second stage planet gears mesh with the second stage sun gear, and each of the second stage planet gears is mounted to a respective one of the planet shafts.

13. The rotor assembly as defined in claim 1 , wherein the first axis is perpendicular to second axes of the second shafts.

14. The rotor assembly as defined in claim 1 , wherein the first gear assembly includes a first angled gear concentric with the first shaft and second angled gears, each of the second angled gears to mesh with the first angled gear.

15. A rotor assembly, comprising:
a swashplate responsive to at least one of a collective control or a cyclic control;
a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the swashplate; and
a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly, wherein the first gear assembly includes a first angled gear concentric with the first shaft and second angled gears, each of the second angled gears to mesh with the first angled gear; and
a second gear assembly to receive one of second torques from one of the second shafts,
the second gear assembly including:
a first planetary gear system driven by a respective one of the second shafts; and
a second planetary gear system driven by the first planetary gear system, the second planetary gear system including a sun gear coupled to an output shaft.

16. The rotor assembly as defined in claim 15 , wherein the output shaft is to twist the rotor blade.

17. The rotor assembly as defined in claim 15 , wherein the second gear assembly includes a planet carrier to house the first planetary gear system and the second planetary gear system.

Assignees

• Boeing Co

Inventors

• Podgurski Daniel M

Classifications

• F01D7/00

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title

• F05D2260/72

  by turning around an axis parallel to the rotor centre line · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C27/37 Primary

  having articulated joints · CPC title

• B64C2027/7222

  using airfoil deformation · CPC title