A rotor blade (20) for a rotary wing aircraft includes a component bay (32) located substantially enclosed in the rotor blade (20) and one or more components (30) positioned in the component bay (32). An airflow is located at the component bay (32) and an airflow outlet (38) is located at the component bay (32) radially outboard of the airflow inlet (34). The airflow inlet (34) and airflow outlet (38) allow a continuous airflow through the component bay (32) via centrifugal forces of rotation of the rotor blade (20), the continuous airflow cooling the one or more components (30) disposed at the component bay (32).


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    Titel :

    Rotor blade component cooling


    Weitere Titelangaben:

    Kühlung eines Rotorblattbauteils
    Refrodissement d'un composant d'une pale de rotor


    Beteiligte:
    SCOTT MARK W (Autor:in)

    Erscheinungsdatum :

    24.07.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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