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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    Title :

    DEICING NOSE OF AN AXIAL TURBINE ENGINE COMPRESSOR


    Additional title:

    BUSE DE DEGLACAGE D'UN COMPRESSEUR DE TURBINE AXIALE


    Contributors:

    Publication date :

    2018-04-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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