The nacelle (10) comprises a tubular casing, open at its opposite axial ends, with an inner wall (12) and an outer wall (14) which are connected to each other at the front end along a leading edge (16) and at the rear end along a trailing edge (18) and which enclose, together with the leading edge (16) and the trailing edge (18), a cavity (20). In order to prevent the formation of ice at least in the zone of the leading edge (16) of the nacelle (10), a separating member (22) made of porous material is arranged inside the cavity (20) so as to divide the cavity (20) into an inner cavity (20a), between the inner wall (12) and the porous separating member (22), and an outer cavity (20b), between the outer wall (14) and the porous separating member (22), and so as to put the inner cavity (20a) in fluid communication with the outer cavity (20b) only in a front zone (20c) of the cavity (20) in contact with the leading edge (16), and a two-phase fluid is contained in the cavity (20).


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    Titel :

    NACELLE FOR AN AIRCRAFT ENGINE WITH DE-ICING SYSTEM USING A TWO-PHASE FLUID


    Weitere Titelangaben:

    GONDEL FÜR EIN FLUGZEUGTRIEBWERK MIT ENTEISUNGSSYSTEM MIT EINER ZWEIPHASIGEN FLÜSSIGKEIT
    NACELLE POUR UN MOTEUR D'AÉRONEF AVEC SYSTÈME DE DÉGIVRAGE UTILISANT UN FLUIDE À DEUX PHASES


    Beteiligte:

    Erscheinungsdatum :

    2018-12-19


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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