A blade (1) of a rotor (100) for a rotary-wing aircraft equipped with an outer covering (2) extending along the span of the said blade (1). This outer covering (2) is provided with an extrados skin (2′) and with an intrados skin (2″) defining a cavity (8). The said blade (1) also includes structural means extending into the said cavity (8) and connecting the said blade (1) to a hub (110) of the said rotor (100). The said cavity (8) is filled with a filling material that includes at least one partition parallel to a chord of the said blade (1) [and] at least two independent blocks of filling material filling the said cavity (8), thereby allowing the reduction of the torsional rigidity along the span of the said blade (1).


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    Titel :

    BLADE WITH REDUCED TORSIONAL RIGIDITY, AND ROTOR EQUIPPED WITH SUCH A BLADE


    Beteiligte:

    Erscheinungsdatum :

    22.10.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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