利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

6 条记录 (耗时 0.01 秒)

    ROTOR BLADE FOR A HIGH SPEED ROTARY-WING AIRCRAFT
    2.
    发明公开
    ROTOR BLADE FOR A HIGH SPEED ROTARY-WING AIRCRAFT 有权
    ROTORBLATTFÜREIN HOCHGESCHWINDIGKEITS-DREHFLÜGELFLUGZEUG

    公开(公告)号：EP1893483A2

    公开(公告)日：2008-03-05

    申请号：EP06849761.9

    申请日：2006-04-28

    申请人： Sikorsky Aircraft Corporation

    发明人： BAGAI, Ashish ,  MOFFITT, Robert, C. ,  BLACKWELL, Robert, H. ,  KRAUSS, Timothy, A.

    IPC分类号： B64C27/46

    CPC分类号： B64C27/10 ,  B64C27/467 ,  B64C27/82 ,  B64C2027/8236 ,  Y10S416/02 ,  Y10S416/05

    摘要： A main rotor blade exhibiting a unique planform shape in which the blade chord increases from the root end of the blade inboard region to the outer main region of the blade, where the blade chord achieves a maximum chord at a spanwise location within the main region, then decreases toward a distal tip end. The leading edge preferably is generally straight while the trailing edge is contoured to define the chord. Another characteristic feature of the rotor blade design is the location of the blade-feathering axis in which the feathering axis is located at a mid chord position over some inboard length of the rotor blade then transitions to a quarter chord location. Another characteristic feature is an airfoil distribution along the blade span that transitions from a blunt trailing edge to a sharp trailing edge airfoil suited for mid-range Mach number operation. The tip region preferably utilizes a transonic flow airfoil. Another characteristic feature of the rotor blade design is an unconventional combination of positive and negative twist gradients.

    摘要翻译： 主转子叶片具有独特的平面形状，其中叶片弦从叶片内侧区域的根部端延伸到叶片的外部主区域，其中叶片弦在主区域内的翼展方向位置处达到最大弦线， 然后朝向远端尖端减小。 前缘优选地大体上是直的，而后缘被轮廓化以限定弦。 转子叶片设计的另一个特征是叶片羽化轴线的位置，其中羽化轴线位于转子叶片的一些内侧长度的中间弦位置处，然后转变到四分之一弦的位置。 另一个特征是沿着叶片跨度的翼型分布，其从钝的后缘转变成适用于中档马赫数操作的尖锐后缘翼型。 尖端区域优选地使用跨音速流动翼型件。 转子叶片设计的另一个特征是正负扭转梯度的非常规组合。

    ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT
    4.
    发明公开
    ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT 审中-公开
    高速旋翼飞机的转子叶片扭转分布

    公开(公告)号：EP3178739A1

    公开(公告)日：2017-06-14

    申请号：EP17151338.5

    申请日：2007-08-22

    申请人： Sikorsky Aircraft Corporation

    发明人： BAGAI, Ashish ,  KREUSCHER, Lauren

    IPC分类号： B64C27/10 ,  B64C27/467

    摘要： Main rotor blades of the dual, counter-rotating, rigid coaxial rotor system exhibit a unique unconventional combination of positive and negative twist gradients in which the rotor system rotor Figure of Merit (hover efficiency) is improved by providing a dissimilar twist distribution between the lower rotor blade (20L) and the upper rotor blades (20U). This improvement is specifically a result of reduced profile drag of the lower rotor system, achieved by driving the effective operating condition of the lower rotor blades to be similar to the upper rotor blade such that the tip drag losses of the lower main rotor have been reduced considerably using a mathematically vigorous approach. While minimal induced power consumption resulted due to the dissimilar lower main rotor twist, a significant profile power benefit is realized, resulting in the improved hover efficiency with essentially no reduction in rotor forward flight performance.

    摘要翻译： 双转子，反转，刚​​性同轴转子系统的主转子叶片表现出独特的非常规正扭矩和负扭转梯度组合，其中转子系统转子品质因数（悬停效率）通过提供不同扭转分布 转子叶片（20L）和上部转子叶片（20U）。 这种改进特别是下转子系统的轮廓阻力减小的结果，其通过将下转子叶片的有效操作条件驱动为类似于上转子叶片来实现，使得下主转子的末端阻力损失已经降低 大量使用数学强有力的方法。 尽管由于不同的较低主旋翼扭转而导致最小感应功率消耗，但实现了显着的功率优势，导致悬停效率提高，而转子前向飞行性能基本没有降低。

    ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT
    6.
    发明公开
    ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT 审中-公开
    刀片的旋转分布高速旋转翼飞机

    公开(公告)号：EP2061694A2

    公开(公告)日：2009-05-27

    申请号：EP07872171.9

    申请日：2007-08-22

    申请人： Sikorsky Aircraft Corporation

    发明人： BAGAI, Ashish ,  KREUSCHER, Lauren

    IPC分类号： B63H1/20

    CPC分类号： B64C27/10 ,  B64C27/467 ,  B64C27/82 ,  B64C2027/8236 ,  Y10S416/02 ,  Y10S416/05

    摘要： Main rotor blades of the dual, counter-rotating, rigid coaxial rotor system exhibit a unique unconventional combination of positive and negative twist gradients in which the rotor system rotor Figure of Merit (hover efficiency) is improved by providing a dissimilar twist distribution between the lower rotor blade and the upper rotor blades. This improvement is specifically a result of reduced profile drag of the lower rotor system, achieved by driving the effective operating condition of the lower rotor blades to be similar to the upper rotor blade such that the tip drag losses of the lower main rotor have been reduced considerably using a mathematically vigorous approach. While minimal induced power consumption resulted due to the dissimilar lower main rotor twist, a significant profile power benefit is realized, resulting in the improved hover efficiency with essentially no reduction in rotor forward flight performance.