There is disclosed an inertial particle separator communicating with an engine inlet. The inertial particle separator has: a main duct body; a bypass duct; and a splitter defined by an intersection of the main duct and the bypass duct. The main duct and the bypass duct having particular geometric characteristics. A method of separating particles via inertia in an aircraft engine inlet is also provided.


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    Titel :

    GAS TURBINE ENGINE WITH INERTIAL PARTICLE SEPARATOR


    Beteiligte:
    MARRANO ROBERTO (Autor:in) / BISSON FRANCOIS (Autor:in)

    Erscheinungsdatum :

    31.10.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B01D SEPARATION , Trennen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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