A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2≤J/D≤0.6 where D is the hydraulic diameter of an injection orifice.


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    Title :

    Device for deicing a splitter nose and inlet guide vanes of an aviation turbine engine



    Publication date :

    2020-08-11


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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