The invention relates to an aviation turbine engine fan module including a de-icing system (10) for de-icing an inlet cone (1) and comprising a sheath (30) placed inside an inside space defined upstream by the inlet cone, said sheath comprising a first duct (38) having at least one hot air admission orifice (42), said first duct being configured to convey hot air from a bearing enclosure (22) of the engine towards a wall of the inlet cone in order to heat it from the inside, the sheath further comprising a second duct (40) having at least one outlet situated downstream from the admission orifice of the first duct, said second duct being configured to discharge air from the first duct towards the downstream end of the engine. The invention also provides a method of de-icing a turbine engine inlet cone.


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    Title :

    SYSTEME ET PROCEDE DE DEGIVRAGE D'UN CONE D'ENTREE DE TURBOMACHINE



    Publication date :

    2018-07-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    MODULE DE SOUFFLANTE DE TURBOMACHINE COMPRENANT UN SYSTÈME DE DÉGIVRAGE D'UN CÔNE D'ENTRÉE DE TURBOMACHINE ET PROCÉDÉ DE DÉGIVRAGE

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    TURBOMACHINE COMPRENANT UN SYSTEME DE DEGIVRAGE DU CONE AMONT, ET PROCEDE ASSOCIE

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