A pitch mechanism for an aircraft engine includes a coordination ring, a plurality of crankshafts coupled to the coordination ring and configured to receive a plurality of blades, an inner shaft coupled to the plurality of crankshafts and the coordination ring, and actuator cylinders and actuator pistons. An actuator cylinder is coupled to the inner shaft and configured to move relative to the actuator piston along a longitudinal axis of the pitch mechanism. Movement of the actuator cylinder relative to the actuator piston is translated into rotation of each of the plurality of crankshafts about a longitudinal axis of each of the plurality of crankshafts to vary a pitch of the plurality of vanes.
一种用于飞行器发动机的变距机构,包括协调环、联接至协调环并配置为接收多个叶片的多个曲轴、联接至多个曲轴和协调环的内轴、以及致动器气缸和致动器活塞。致动器气缸联接至内轴并且配置为沿变距机构的纵向轴线相对于致动器活塞移动。致动器气缸相对于致动器活塞的移动被转换为多个曲轴中的每一个围绕多个曲轴中的每一个的纵向轴线的旋转,以改变多个叶片的节距。
Pitch changing mechanism for aircraft engine
用于飞行器发动机的变距机构
2025-01-10
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Aircraft gas turbine engine blade pitch change mechanism
European Patent Office | 2021
|