An air intake module for an aircraft turbomachine extending along a longitudinal axis oriented from upstream to downstream and including an inner wall and an outer wall defining together a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, the stator member comprising an infrared wave emitting device configured to emit an infrared beam on the leading edge of at least one of the guide vanes for de-icing it.


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    Titel :

    AIR INTAKE MODULE FOR AN AIRCRAFT TURBOMACHINE AND METHOD FOR DE-ICING THEREOF


    Beteiligte:

    Erscheinungsdatum :

    26.12.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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