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1. 发明公开

EP2061694A2 ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT 审中-公开
标题翻译：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.

2. 发明授权

EP3178739B1 ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT 有权
公开(公告)号：EP3178739B1
公开(公告)日：2019-11-06
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

3. 发明公开

EP3178739A1 ROTOR BLADE TWIST DISTRIBUTION FOR A HIGH SPEED ROTARY-WING AIRCRAFT 有权
标题翻译：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。

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