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.


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    Title :

    HELICE POUR TURBOMACHINE D'AERONEF COMPRENANT DES MOYENS DE SECOURS DE CALAGE EN INCIDENCE DE PALE


    Contributors:

    Publication date :

    2018-04-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES






    PALE POUR UNE HELICE DE TURBOMACHINE, NOTAMMENT A SOUFFLANTE NON CARENEE, HELICE ET TURBOMACHINE COMPRENANT UNE TELLE PALE

    VION LAURENCE FRANCINE / FERNANDO RASIKA / JODET NORMAN BRUNO ANDRÉ | European Patent Office | 2018

    Free access

    PALE POUR UNE HELICE DE TURBOMACHINE, NOTAMMENT A SOUFFLANTE NON CARENEE, HELICE ET TURBOMACHINE COMPRENANT UNE TELLE PALE

    VION LAURENCE FRANCINE / FERNANDO RASIKA / JODET NORMAN BRUNO ANDRÉ | European Patent Office | 2015

    Free access