Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.


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    Title :

    ENTRÉE D'AIR D'UNE NACELLE D'UNE TURBOMACHINE D'AÉRONEF


    Additional title:

    AIR INLET OF A NACELLE OF AN AIRCRAFT JET ENGINE
    LUFTEINLASS EINER GONDEL EINER FLUGZEUG STRAHLTRIEBWERKEN



    Publication date :

    2024-05-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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    Entrée d’air d’une nacelle d’une turbomachine d’aéronef

    LONCLE ALEXIS YVES-MARIE / VALLEROY LAURENT GEORGES | European Patent Office | 2021

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    NACELLE D'AERONEF COMPRENANT UNE ENTREE D'AIR

    ROUYRE FRANÇOIS | European Patent Office | 2017

    Free access