A pitch change mechanism for an aircraft engine includes a unison ring, a plurality of crankshafts coupled to the unison ring and configured to receive a plurality of blades, an inner shaft coupled to the plurality of crankshafts and the unison ring, and an actuator cylinder and an actuator piston. The actuator cylinder is coupled to the inner shaft and is configured to move relative to the actuator piston along a longitudinal axis of the pitch change mechanism. Movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around a longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.
Pitch change mechanism for an aircraft engine
2025-02-18
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Aircraft gas turbine engine blade pitch change mechanism
European Patent Office | 2021
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