A blade retention system includes a rotor hub including a plurality of radial arms, and a blade retention yoke associated with the rotor hub and one of the plurality of radial arms. The blade retention yoke is rotatable relative to the rotor hub and the radial arm. A tension torsion device connects the radial arm to the blade retention yoke to restrict radial movement of the blade retention yoke relative to the radial arm.
BLADE RETENTION SYSTEM FOR RIGID ROTOR
2019-09-12
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Rotor blade retention system for a gas turbine engine
Europäisches Patentamt | 2022
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