A de-icing splitter nose of an axial turbine engine, specifically, a de-icing splitter nose of a turbo-jet engine compressor includes an annular row of vanes, each of which has a radially extending leading edge, and a de-icing system based on hot-air injection. The injection is pulsed, i.e. discontinuous. The system includes an annular row of injection orifices for injecting de-icing fluid onto the vanes in respective injection directions. Each injection orifice is associated with a vane such that the injection directions thereof are substantially parallel to the leading edge of the related vane, enabling said vane to be de-iced.


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    Titel :

    DEICING NOSE OF AN AXIAL TURBINE ENGINE COMPRESSOR


    Weitere Titelangaben:

    BUSE DE DEGLACAGE D'UN COMPRESSEUR DE TURBINE AXIALE


    Beteiligte:

    Erscheinungsdatum :

    21.04.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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