In order to simplify the design of an aircraft turbo engine propeller while enhancing the safety function thereof related to control of the blade angle of attack, a propeller is provided comprising a secondary rotational coupling to couple in rotation, along the radial axis of the blade, the inner radial end of the blade root with a mechanical joining member of a blade angle of attack control device, the secondary coupling being designed and configured to be active in the event of failure of the main pin.
HELICE POUR TURBOMACHINE D'AERONEF COMPRENANT DES MOYENS DE SECOURS DE CALAGE EN INCIDENCE DE PALE
2018-04-13
Patent
Electronic Resource
French
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