An aircraft engine, has: an upstream stator having upstream stator vanes distributed about a central axis; and a downstream stator having downstream stator vanes distributed about the central axis, the downstream stator located downstream of the upstream stator, a number of the upstream stator vanes different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes; and a second vane differing from the first vane by a geometric parameter, the geometric parameter causing the second vane to have one or more of: a stiffness greater than that of the first vane, and a major portion of a leading edge of the second vane circumferentially overlapped by another one of the upstream stator vanes.


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    Titel :

    AIRCRAFT ENGINE WITH STATOR HAVING VARYING GEOMETRY


    Beteiligte:
    CAPRON ALEXANDRE (Autor:in) / ANAND KARAN (Autor:in) / YAM TAMMY (Autor:in) / AZMI ALI (Autor:in) / CLAUDE SYLVAIN (Autor:in) / BALIKE KRISHNA PRASAD (Autor:in) / MITTAL PRAKUL (Autor:in)

    Erscheinungsdatum :

    30.11.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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