The invention relates to a turbojet engine nacelle component (23) cooling assembly (30), said assembly (30) comprising at least one composite wall (20) separating a cold zone (8) and a hot zone (16) containing said component (23), said assembly (30) comprising at least one opening (31) made in said composite wall (20) and a thermally conductive interface element (33) positioned on the composite wall (20) in such a way as to obstruct said opening or openings (31), said element (33) being intended to be associated with said component (23). The invention also relates to a nacelle comprising a component (23) that is intended to be cooled, and to such a cooling assembly (30).


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    Title :

    ENSEMBLE DE REFROIDISSEMENT POUR UN COMPOSANT D'UNE NACELLE POUR TURBOREACTEUR


    Contributors:

    Publication date :

    2016-09-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

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



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