An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.


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    Titel :

    INERTIAL PARTICLE SEPARATOR FOR AIRCRAFT ENGINE


    Weitere Titelangaben:

    TRÄGHEITSPARTIKELABSCHEIDER FÜR FLUGZEUGTRIEBWERK
    SÉPARATEUR DE PARTICULES À INERTIE POUR MOTEUR D'AÉRONEF


    Beteiligte:
    YAN GUORONG (Autor:in) / CUNNINGHAM MARK (Autor:in)

    Erscheinungsdatum :

    2023-02-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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