A blade de-icing system for a blade to be de-iced that has a body extending between a leading edge and a trailing edge, said leading edge ending at an apex. The system includes a de-icer component having a recess formed therein and being positioned on said leading edge of said blade so that said de-icer component covers and extends away from said apex and so that said recess is positioned at said apex of said leading edge; and an anti-erosion strip provided in said recess of said de-icer component; wherein said anti-erosion strip and said recess are sized and shaped such that said anti-erosion strip fits within said recess so that outer surface of said anti-erosion strip is flush with the outer surface of said de-icer component. A method of manufacturing the same is also described herein.


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    Title :

    DEICER AERODYNAMIC INTEGRATION


    Contributors:

    Publication date :

    2021-09-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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