The invention relates to an aero-propeller (10) having a longitudinal axis (X) and comprising a hub (12), an upstream annular row (14) and a downstream annular row (16) spaced apart from one another along the longitudinal axis (X), the upstream annular row (14) being rotatable about the longitudinal axis (X), the downstream annular row (16) comprising a first blade (18a) and a second blade (18b), each blade extends in a radial direction to define a distance between the hub (12) and a corresponding blade (18a; 18b) in the radial direction; wherein the second blade (18b) is positioned closer to an angular position at 3 o'clock or 9 o'clock than the first blade (18b) when viewed at an angle about the longitudinal axis (X), and the radial dimension of the first blade (18a) is greater than the radial dimension of the second blade (18b).

    本发明涉及一种航空推进器(10)具有纵轴(X)并且包括轮毂(12)、沿着所述纵轴(X)彼此间隔开的上游环形行(14)和下游环形行(16),所述上游环形行(14)可围绕所述纵轴(X)旋转,所述下游环形行(16)包括第一叶片(18a)和第二叶片(18b),每个叶片在径向方向上延伸以限定所述轮毂(12)与对应叶片(18a;18b)的径向外端之间的径向尺寸;其中围绕所述纵轴(X)成角度地观察,所述第二叶片(18b)比所述第一叶片(18b)更靠近3点钟处的角位置或9点钟处的角位置定位,并且所述第一叶片(18a)的所述径向尺寸大于所述第二叶片(18b)的所述径向尺寸。


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    Titel :

    Aviation propeller


    Weitere Titelangaben:

    航空推进器



    Erscheinungsdatum :

    02.04.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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