A helicopter engine air intake including an anti-icing grid that provides a large bypass flow in event of icing. The air intake includes air intake lips and an anti-icing grid mounted on outer ends of the air intake lips, being interposed in the air flow penetrating into the air intake, at least one air intake lip being formed by a thin metal sheet.


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    Titel :

    Helicopter engine air intake with increased bypass flow


    Beteiligte:
    JACTAT PAUL-ETIENNE (Autor:in) / BULOT NICOLAS (Autor:in) / LEBRUSQ PASCAL (Autor:in) / VERGEZ THIERRY (Autor:in)

    Erscheinungsdatum :

    11.09.2018


    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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