An aeroplane turbojet low-pressure compressor vane includes a leading edge, a trailing edge, a surface, and an extrados surface which extend from the leading edge to the trailing edge. To combat the presence and the formation of ice, the vane is provided with an electric de-icing device with a thermistor. The thermistor forms a heating electrical track suitable for de-icing the vane. The present application also proposes a method for producing a turbine engine vane.


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    Title :

    AUBE DE TURBOMACHINE, COMPRESSEUR,TURBOMACHINE ET PROCÉDÉ DE RÉALISATION ASSOCIÉ


    Additional title:

    TURBOMACHINE BLADE, CORRESPONDING COMPRESSOR, TURBOMACHINE AND PRODUCTION METHOD
    SCHAUFEL EINER STRÖMUNGSMASCHINE, ZUGEHÖRIGE VERDICHTER, STRÖMUNGSMASCHINE UND HERSTELLUNGSVERFAHREN


    Contributors:

    Publication date :

    2021-09-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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