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Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades

机译:直升机旋翼,飞机机翼,螺旋桨和涡轮叶片的减振降噪扰流板

摘要

A spoiler attached to helicopter main rotor blades, tail rotor blades, propellers, aircraft wings, and machined into turbine blades, that reduces vibration and silences their operation. Also, when added to a substantial part of the trailing edges of its rotor blades, the spoiler eliminates the repetitive pop-pop sound common to current helicopter flight. Preferably, the spoiler is made from durable resilient materials that bend with resistance for high speed oscillation and it is secured on the top or bottom side, or both, of the trailing edge of a blade or wing. Further, the free edge of the spoiler exhibits a non-repeating pattern of feather-like projections that collectively break up vortex formation so that the next wing or blade traveling through the same location has clean air/fluid in which to move. In addition to noise reduction, the spoiler increases blade efficiency and wing lift.
机译:扰流板安装在直升机主旋翼叶片,尾旋翼叶片,螺旋桨,飞机机翼上,并加工成涡轮叶片,可减少振动并使其运转静音。同样,当扰流板被添加到其旋翼桨叶的大部分后缘时,它消除了当前直升机飞行中常见的重复的砰砰声。优选地,扰流板由耐弯曲的耐用弹性材料制成,以抵抗高速振荡,并且将其固定在叶片或机翼的后缘的顶侧或底侧或两者上。进一步地,扰流板的自由边缘表现出羽毛状突起的非重复图案,该羽毛状突起共同破坏涡流形成,从而使穿过相同位置的下一个机翼或叶片具有在其中移动的清洁空气/流体。除了降低噪音外,扰流板还提高了叶片效率和机翼升力。

著录项

  • 公开/公告号US7413408B1

    专利类型

  • 公开/公告日2008-08-19

    原文格式PDF

  • 申请/专利权人 SAMUEL B TAFOYA;

    申请/专利号US20070709613

  • 发明设计人 SAMUEL B TAFOYA;

    申请日2007-02-22

  • 分类号B64C11/18;B64C11;

  • 国家 US

  • 入库时间 2022-08-21 20:12:14

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