Co-rotating stacked rotor disks for improved hover performance
The system of the present application represents a rotor hub for a rotorcraft and a rotorcraft incorporating the rotor hub. The rotor hub is represented as having multiple rotor disk assemblies, each rotor disk assembly rotating in the same direction about the same mast axis of rotation. In the preferred embodiment, each rotor disk assembly has three rotor blades. The upper rotor disc assembly and the lower rotor disk assembly are separated by approximately 2.5% of the rotor disk diameter, at least to take advantage of “wake contraction”.
1. A rotor hub for a rotorcraft, comprising:
an upper rotor disk assembly having a plurality of upper rotor blades;
a lower rotor disk assembly having a plurality of lower rotor blades;
wherein the upper rotor disk assembly and the lower rotor disk assembly are configured to rotate in a same direction and about a same axis of rotation;
wherein the upper rotor disk assembly and the lower rotor disk assembly are spaced apart a distance to permit the lower rotor disk assembly to take air in that is outside of a contracted wake caused by the upper rotor disk assembly, so as to increase the effective diameter or area of lower rotor disk assembly.
2. The rotor hub according to claim 1 , wherein the upper rotor disk assembly and the lower rotor disk assembly are spaced apart along the axis of rotation so as to introduce clean air to the lower rotor disk assembly.
3. The rotor hub according to claim 1 , wherein the upper rotor disk assembly and the lower rotor disk assembly are configured to rotate in a counter clockwise direction about the axis of rotation.
4. The rotor hub according to claim 1 , wherein the upper rotor disk assembly and the lower rotor disk assembly are configured to rotate in a clockwise direction about the axis of rotation.
5. The rotor hub according to claim 1 , wherein the upper rotor disk assembly and the lower rotor disk assembly are attached to a rotor mast.
6. The rotor hub according to claim 2 , wherein the introduction of clean air to the lower rotor disk assembly increases an effective rotor disk area of the lower rotor disk assembly, thereby increasing performance of the rotor hub.
7. The rotor hub according to claim 2 , wherein the upper rotor disk assembly and the lower rotor disk assembly are spaced apart along the axis of rotation by approximately 2.5% of a diameter of the upper rotor disk assembly.
8. The rotor hub according to claim 2 , wherein the upper rotor disk assembly is clocked by 30° relative to the lower rotor disk assembly.
9. The rotor hub according to claim 1 , wherein the plurality of upper rotor blades are equally spaced about the axis of rotation.
10. The rotor hub according to claim 1 , wherein the plurality of lower rotor blades are equally spaced about the axis of rotation.
11. The rotor hub according to claim 1 , wherein the plurality of upper rotor blades includes three upper rotor blades.
12. The rotor hub according to claim 1 , wherein the plurality of lower rotor blades includes three lower rotor blades.
13. A rotorcraft, comprising:
a fuselage;
a tail member carried by the fuselage;
a landing gear coupled to the fuselage;
an anti-torque device operably associated with the tail member;
a rotor hub operably associated with the fuselage, the rotor hub comprising:
an upper rotor disk assembly having a plurality of upper rotor blades;
a lower rotor disk assembly having a plurality of lower rotor blades;
wherein the upper rotor disk assembly and the lower rotor disk assembly are configured to rotate in a single direction and about a single axis of rotation;
wherein the upper rotor disk assembly and the lower rotor disk assembly are spaced apart a distance to permit the lower rotor disk assembly to take air in that is outside of a contracted wake caused by the upper rotor disk assembly, so as to increase the effective diameter or area of lower rotor disk assembly.
14. The rotorcraft according to claim 13 , wherein the upper rotor disk assembly and the lower rotor disk assembly are spaced apart along the axis of rotation so as to take advantage of wake contraction, thereby increasing an effective diameter of the lower rotor disk assembly.
15. The rotorcraft according to claim 13 , wherein the lower rotor disk assembly is clocked by 30° to the upper rotor disk assembly.
16. The rotorcraft according to claim 13 , wherein the rotor hub rotates in a counterclockwise direction.
17. The rotorcraft according to claim 13 , wherein the plurality of upper rotor blades includes three upper rotor blades and the plurality of lower rotor blades is includes three lower rotor blades.