An inertial particle separator (40), having: an inlet duct (42) defining an intake (48); an intermediate duct (44) extending from the inlet duct (42) to an engine inlet (12); a bypass duct (46) in fluid communication with and extending downstream from the inlet duct (42), the bypass duct (46) defining an outlet (56) communicating with the environment (E) of the aircraft engine (10), a splitter (50) defined at an intersection of a wall (46) of the bypass duct (46a) and a wall (44d) of the intermediate duct (44); a splitter vane (52) within the intermediate duct (44) and having a leading edge (52a) located upstream of the splitter (50) relative to a flow (F) circulating through the separator (40), the splitter vane (52) and the wall (44d) of the intermediate duct (44) defining a channel (60) therebetween; and a porous plate (62) extending across the channel (60) 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 :

    24.03.2021


    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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