The invention relates to an aviation propulsion device comprising a central engine (3), upstream and downstream series of blades (9, 6), blades (90, 60) of at least one of these series adapted to be rotationally driven by a turbine about a central longitudinal axis (X), and a nacelle (5) enclosing said central engine. At least some of the two series of blades are variable pitch blades. At least one of the blades (90) of the first series of blades (9) has a rear edge with saw teeth (93) and/or at least one of the blades (60) of the second series of blades (6) has a front edge with saw teeth (63).

    本发明涉及航空推进装置,其包括中心发动机(3)、上游系列和下游系列的叶片(9、6)、这些系列中的至少一者的适于由涡轮围绕中心纵向轴线(X)旋转驱动的叶片(90、60),以及围封所述中心发动机的短舱(5)。所述两个系列的叶片中的至少一些是可变俯仰叶片。所述第一系列的叶片(9)的叶片(90)中的至少一个带有具有锯齿(93)的后边缘,和/或所述第二系列的叶片(6)的叶片(60)中的至少一个带有具有锯齿(63)的前边缘。


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    Titel :

    PROPULSION DEVICE FOR AN AIRCRAFT


    Weitere Titelangaben:

    用于飞行器的推进装置


    Beteiligte:

    Erscheinungsdatum :

    15.03.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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