An aircraft anti-icing system (1) includes an inlet lip (14) that includes an outer shell (46) attached to a bulkhead (32). The inlet lip (14) encloses an annular housing volume (44). The system (1) further includes one or more vanes (56) extending from the bulkhead (32) into the annular housing volume (44). Each vane of the one or more vanes (56) includes a first end (28) coupled to the bulkhead (32), a free end (30) extending into the annular housing volume (44), and a vane body (67) extending therebetween. The one or more vanes (56) are positioned downstream from a nozzle (34) configured to direct a high temperature gas stream (50) into the annular housing volume (44) in a first direction (58). The one or more vanes (56) are configured to redirect the high temperature gas stream (50) through a first turn angle from the first direction (58) to a second direction (60). The second direction (60) is configured to reduce a direct impingement (52) of the high temperature gas stream (50) on an inner surface (62) of the inlet lip (14).


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    Titel :

    NOZZLE AND VANE SYSTEM FOR NACELLE ANTI-ICING


    Weitere Titelangaben:

    DÜSE UND SCHAUFEL SYSTEM ZUR TRIEBWERKSGONDELENTEISUNG
    SYSTÈME DE BUSE ET DE SOUPAPE POUR ANTIGIVRAGE DE NACELLE


    Beteiligte:

    Erscheinungsdatum :

    2017-08-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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