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.


    Access

    Download


    Export, share and cite



    Title :

    De-Icing Splitter for an Axial Turbine Engine Compressor


    Contributors:

    Publication date :

    2017-02-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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



    De-icing splitter for an axial turbine engine compressor

    BOUILLON DAVID / COLLIN CLÉMENT / TERLINDEN GUILLAUME | European Patent Office | 2018

    Free access

    Splitter nose with plasma de-icing for axial turbine engine compressor

    HERBAUT GHISLAIN / BOUILLON DAVID | European Patent Office | 2019

    Free access

    De-icing device for a splitter nose of an axial turbine engine compressor

    OGGERO QUENTIN | European Patent Office | 2018

    Free access

    Device for de-icing a splitter nose of an aviation turbine engine

    LOURIT DAMIEN DANIEL SYLVAIN / MARLIN FRANÇOIS MARIE PAUL | European Patent Office | 2019

    Free access

    DEVICE FOR DE-ICING A SPLITTER NOSE OF AN AVIATION TURBINE ENGINE

    LOURIT DAMIEN DANIEL SYLVAIN / MARLIN FRANÇOIS MARIE PAUL | European Patent Office | 2017

    Free access