A de-icing and anti-icing splitter for an axial turbine engine low-pressure compressor has an external annular wall delimiting the secondary or bypass flow, and an internal annular wall; notably an external stator shroud; delimiting the primary or main stream. The upstream edge of the internal wall is fixed to the upstream annular hook of the external wall. The splitter has a series of notches which pass radially through the internal wall to allow de-icing fluid to circulate through the hook. The notches may form crescents. The splitter becomes simpler while at the same time maintaining optimal efficiency.


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    Titel :

    De-Icing Splitter for an Axial Turbine Engine Compressor


    Beteiligte:

    Erscheinungsdatum :

    2017-02-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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