A rear assembly for a turbojet engine nacelle includes at least one composite wall separating a cold portion from a hot portion comprising an element to be cooled, the composite wall having first and second skins which extend facing the cold portion and the hot portion respectively, and which are separated from one another by a middle assembly having cells delimited by internal walls. The first skin includes a plurality of through-openings connecting the cold portion and the cells, the internal walls having through-openings connecting the cells to one another, and the second skin having a through-opening which has its mouth facing the element to be cooled.


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    Title :

    ENSEMBLE ARRIÈRE POUR NACELLE DE TURBORÉACTEUR


    Additional title:

    REAR ASSEMBLY FOR A TURBOJET ENGINE NACELLE
    HINTERE ANORDNUNG FÜR EINE TURBOSTRAHL-TRIEBWERKSGONDEL


    Contributors:

    Publication date :

    2024-08-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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