The invention relates to an aviation propeller (10) having a longitudinal axis (X) and comprising a hub (12) and at least two annular rows of unducted blades (18), including 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) and the downstream annular row (16) being rotatable about the longitudinal axis (X). The downstream annular row (16) includes a series of blades including a first blade (18a) and a second blade (18b), each blade extending from the hub (12) in a radial direction to define a radial direction between the hub (12) and the corresponding blade (18a; 18b), characterized in that the radial dimension of the first blade (18a) is greater than the radial dimension of the second blade (18b).

    本发明涉及航空推进器(10),其具有纵轴(X),并且包括轮毂(12),以及无涵道叶片(18)的至少两个环形行,所述至少两个环形行包括沿着所述纵轴(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)能够围绕所述纵轴(X)旋转,所述下游环形行(16)包括一系列叶片,包含第一叶片(18a)和第二叶片(18b),每个叶片在径向方向上从所述轮毂(12)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,其特征在于,所述第一叶片(18a)的径向尺寸大于所述第二叶片(18b)的径向尺寸。


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    Titel :

    Aviation propeller


    Weitere Titelangaben:

    航空推进器



    Erscheinungsdatum :

    2024-03-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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