An aircraft blade assembly, including: a blade extending from a blade root to an opposite tip; and a heat exchanger disposed on at least a portion of a leading edge of the blade, the heat exchanger including: a first arcuate panel shaped to conform to the leading edge of the blade; and a second arcuate panel mated with the first arcuate panel; wherein at least one of the first and second arcuate panels includes a channel formed thereon to form a fluid passage between the first and second arcuate panels.


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    Title :

    Aircraft propeller blade radiator


    Contributors:

    Publication date :

    2024-06-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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