A stator assembly for straightening an air flow, a uniflow engine, a dual flow engine and an aircraft, the assembly comprising a plurality of stator blades distributed about an axis of rotation of the stator assembly, each stator blade having a plurality of blades, a chord of the stator blade taken at the root of the stator blade does not overlap a chord of an adjacent stator blade taken at the root of the adjacent stator blade in the direction of the rotation axis, and a chord of the stator blade taken at the tip of the stator blade overlaps a chord of an adjacent stator blade taken at the tip of the adjacent stator blade in the direction of the rotation axis.

    用于对气流进行矫直的定子组件,单流式发动机,双流式发动机和飞行器,该组件包括围绕定子组件的旋转轴线分布的多个定子叶片,对于每个定子叶片,在定子叶片的根部处获取的定子叶片的弦与在相邻定子叶片的根部处获取的相邻定子叶片的弦沿着旋转轴线的方向不重叠,以及在定子叶片的顶端处获取的定子叶片的弦与在相邻定子叶片的顶端处获取的相邻定子叶片的弦沿着旋转轴线的方向重叠。


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    Titel :

    Stator assembly


    Weitere Titelangaben:

    定子组件



    Erscheinungsdatum :

    19.09.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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