Fan blade retention and variable pitch system
AssigneeRotating Composite Technologies, LLC
InventorsJohn A. Violette, Eric Stephen Loos
Life of this patent
Estimating the term…
Abstract
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.
Claims20
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.
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.
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.
Dependencies are inferred from the claim text.