A rotor blade for an aircraft includes an airfoil skin, an active element, and an actuator configured to operate the active element. A heat pipe is configured to promote heat transfer from the actuator to the airfoil skin. The heat pipe has a slope gradient such that a centrifugal force generated during rotation of the rotor blade promotes travel of a condensed working fluid within the heat pipe to move from a condenser end of the heat pipe toward an evaporator end of the heat pipe.


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    Titel :

    SYSTEM FOR HEAT DISSIPATION FROM AN INTERNAL ACTUATOR IN A ROTOR BLADE


    Weitere Titelangaben:

    SYSTEME DE DISSIPATION DE CHALEUR D'UN ACTUATEUR INTERNE D'UNE PALE DE ROTOR


    Beteiligte:
    SCHANK TROY C (Autor:in) / MCGLAUN MONTE A (Autor:in)

    Erscheinungsdatum :

    22.03.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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