A blade de-icing system is described herein comprising said blade (10) to be de-iced, having a body (13) extending between a leading edge (11) and a trailing edge (135), said leading edge (11) ending at an apex (16); said system comprising a de-icer component (14) having a recess (141) formed therein and being positioned on said leading edge (11)of said bled e (10) so that said de-icer component (14) covers and extends avvay from said apex (16) and so that said recess (141) is positioned at said apex (16) of said leading edge (11); and an anti-erosion strip (12) provided in said recess (141) of said de-icer component (14); wherein said anti-erosion strip (12) and said recess (141) are sized and shaped such that said anti-erosion strip (12) fits within said recess (141) so that outer surface of said anti-erosion strip is flush with the outer surface of said de-icer component (14). A method of manufacturing the same is also described herein.


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    Titel :

    IMPROVEMENT DEICER AERODYNAMIC INTEGRATION


    Weitere Titelangaben:

    INTEGRATION AERODYNAMIQUE AMELIOREE DE DEGIVREUR


    Beteiligte:

    Erscheinungsdatum :

    2021-09-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / F03D Windkraftmaschinen , WIND MOTORS



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