Fan blade retention and variable pitch system
A system for providing variable pitch to a rotor blade of an aircraft engine includes a rotatable hub; at least one blade mounted on the rotatable hub; a gear mechanism operably connected to the rotatable hub; a timing ring rotatably and operably connected to the gear mechanism; and a pitch arm operably connecting the timing ring and the at least one blade mounted on the rotatable hub. In the operation of the system, the gear mechanism facilitates the rotation of the timing ring to vary the pitch of the at least one blade mounted on the rotatable hub.
1. A system for providing variable pitch to a rotor blade of an aircraft engine, the system comprising:
a rotatable hub;
at least one blade mounted on the rotatable hub;
a gear mechanism operably connected to the rotatable hub;
a timing ring rotatably and operably connected to the gear mechanism; and
a pitch arm operably connecting the timing ring and the at least one blade mounted on the rotatable hub;
wherein operation of the gear mechanism rotates the timing ring to vary the pitch of the at least one blade mounted on the rotatable hub.
2. The system of claim 1 , further comprising flexible tennons connecting the at least one blade to the rotatable hub.
3. The system of claim 2 , wherein the flexible tennons are fabricated from a carbon fiber material.
4. The system of claim 2 , wherein the flexible tennons are fabricated from fibrous polyamide.
5. The system of claim 2 , wherein the flexible tennons are fabricated from fibrous glass.
6. The system of claim 2 , wherein the flexible tennons are fabricated from fibrous materials in a resinous matrix system.
7. The system of claim 1 , further comprising a pin, the at least one blade being connected to the pin, and the pin being connected to the rotatable hub.
8. The system of claim 1 , wherein the at least one blade includes blade tennons depending therefrom, the blade tennons being connected to support tennons extending from the rotatable hub, the blade tennons and the support tennons being connected to a pin.
9. The system of claim 1 , wherein the at least one blade is rotatably mounted on a post extending from the rotatable hub.
10. The system of claim 1 , wherein the gear mechanism comprises a gear frame mounted to a forward face of the rotatable hub, and a segmented gear operably mounted to the gear frame.
11. The system of claim 10 , further comprising a drive mechanism operably connected to the segmented gear.
12. The system of claim 11 , wherein the operable connection of the drive motor to the segmented gear comprises an arrangement of worms and worm gears, the operation of which cause the rotation of the segmented gear and the timing ring.
13. A system for retaining a fan blade of an aircraft and providing variable pitch to the fan blade, the system comprising:
a rotatable hub;
at least one fan blade mounted on the rotatable hub;
a gear mechanism operably connected to the rotatable hub;
a drive mechanism connected to and in operable communication with the gear mechanism;
a timing ring rotatably and operably connected to the gear mechanism; and
a pitch arm operably connecting the timing ring and the at least one fan blade mounted on the rotatable hub;
wherein operation of the drive motor rotates the timing ring via the gear mechanism to vary the pitch of the at least one fan blade mounted on the rotatable hub.
14. The system of claim 13 , wherein the gear mechanism comprises,
a gear frame mounted to the rotatable hub;
a segmented gear rotatably mounted to the gear frame; and
a bearing located between a forward-facing surface of the gear frame and a rearward-facing surface of the segmented gear;
wherein the drive motor is mounted to the gear frame; and
wherein the segmented gear is rotatable on the bearing by the drive motor.
15. The system of claim 13 , wherein the drive motor includes a first worm, a worm gear is in operable communication with the first worm, and the worm gear is in operable communication with a second worm located on the gear mechanism, the operation of the drive motor causing the rotation of the gear mechanism and the timing ring.
16. The system of claim 13 , further comprising a pin connecting a root portion of the fan blade to the rotatable hub.
17. The system of claim 16 , further comprising blade tennons extending from the root portion of the fan blade and connecting to the pin and support tennons connected to the rotatable hub and the pin.
18. The system of claim 13 , wherein the pitch arm is operably connected to the timing ring and to a pin to which the at least one fan blade is attached.
19. The system of claim 13 , wherein the pitch arm is operably connected to the timing ring and to a cradle to which the at least one fan blade is attached.
20. A system for providing variable pitch to a rotor blade of an aircraft engine, the system comprising:
a rotatable hub;
at least one blade mounted on the rotatable hub;
a gear mechanism operably connected to the rotatable hub;
a timing ring rotatably and operably connected to the gear mechanism;
a pitch arm operably connecting the timing ring and the at least one blade mounted on the rotatable hub;
flexible tennons connecting the at least one blade to the rotatable hub; and
a pin, the at least one blade being connected to the pin, and the pin being connected to the rotatable hub;
wherein operation of the gear mechanism rotates the timing ring to vary the pitch of the at least one blade mounted on the rotatable hub.