The invention discloses a helicopter rotor blade capable of inhibiting a blade tip vortex. The helicopter rotor blade comprises a blade body and at least one plasma jet generator, the paddle body is provided with a front edge, a rear edge and a paddle tip end face located between the front edge and the rear edge, and the plasma jet generator is buried in the paddle body and sprays plasma jet through a jet hole corresponding to the plasma jet generator and provided with an opening in the paddle tip end face. By adopting the helicopter rotor blade, the blade tip vortex can be effectively inhibited, and the blade-vortex noise is reduced. Furthermore, by means of bionics, the end face of the paddle tip is constructed to be in a wave shape, the jet flow holes are formed in the top ends of the wave crests, and therefore paddle tip vortexes are more effectively restrained through active and passive ways, and paddle-vortex interference noise is more remarkably reduced.

    本申请公开了一种能够抑制桨尖涡的直升机旋翼桨叶,其包括桨叶本体和至少一个等离子体射流发生器;桨叶本体设有前缘、后缘及位于前缘与后缘间的桨尖端面,等离子体射流发生器埋设于桨叶本体内,其通过与其对应的开口于桨尖端面的射流孔喷射等离子体射流。采用上述技术方案,能够有效抑制桨尖涡,降低桨‑涡噪声。进一步,还利用仿生学,将桨尖端面构造为波浪形,将射流孔的位置开设于波峰顶端,从而通过主‑被动两种途径更有效地抑制桨尖涡,更显著地降低桨‑涡干扰噪声。


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    Titel :

    Helicopter rotor blade capable of inhibiting tip vortex


    Weitere Titelangaben:

    一种能够抑制桨尖涡的直升机旋翼桨叶


    Beteiligte:
    LIN QI (Autor:in) / CHEN CHEN (Autor:in) / ZHANG TAO (Autor:in) / LIU RUBING (Autor:in)

    Erscheinungsdatum :

    04.06.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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