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1. 发明授权

US06190132B1 Rotor blade for rotorcraft 有权
标题翻译：旋翼飞轮转子叶片
公开(公告)号：US06190132B1
公开(公告)日：2001-02-20
申请号：US09404824
申请日：1999-09-24
申请人： Eiichi Yamakawa , Atsushi Murashige , Tomoka Tsujiuchi
发明人： Eiichi Yamakawa , Atsushi Murashige , Tomoka Tsujiuchi
IPC分类号： B64C2746
CPC分类号： B64C27/46 , B64C27/463 , B64C27/467 , Y10S416/02
摘要： A blade root portion of a rotor blade is attached to a rotor head for rotating. A center portion linearly elongates from the blade root portion. A blade tip portion outward elongates from the center portion and has a shape which is defined by a leading edge, a side edge and a trailing edge, and has a predetermined aerofoil. In the leading edge of the blade tip portion, a swept-back angle &lgr;(r) at a distance r from the rotation center of a rotor satisfies relational expression (1) of a rotor blade length R of a rotorcraft, a maximum flight Mach number M∞ which is a flight limit speed of the rotorcraft, a blade tip Mach number MTIP which is a tip speed during hovering, and a drag divergence Mach number Mdd which is determined from the aerofoil of the blade tip portion. According to this configuration, it is possible to provide a rotor blade for a rotorcraft in which the performance in high-speed flying is improved, the high-speed impulsive noise can be reduced, and a high control performance is attained.
摘要翻译：转子叶片的叶片根部附接到转子头部用于旋转。中心部分从叶片根部线性延伸。叶片尖端部分从中心部分向外延伸并且具有由前缘，侧边缘和后缘限定的形状，并且具有预定的机翼。在叶片尖端部分的前缘中，与转子旋转中心距离r的扫掠角lambd（r）满足旋翼飞机转子叶片长度R的关系式（1），最大飞行马赫数数字Minfin是旋翼航空器的飞行极限速度，作为悬停期间的尖端速度的叶片尖端马赫数MTIP，以及从叶片尖端部分的翼面确定的牵引发散马赫数Mdd。根据该结构，能够提供用于旋转飞行器的转子叶片，其中提高了高速飞行的性能，可以降低高速冲击噪声，并且实现了高的控制性能。

2. 发明授权

US06231308B1 Rotor blade for rotary wing aircraft 失效
标题翻译：转翼飞机转子叶片
公开(公告)号：US06231308B1
公开(公告)日：2001-05-15
申请号：US08925526
申请日：1997-09-08
申请人： Natsuki Kondo , Tomoka Tsujiuchi , Eiichi Yamakawa
发明人： Natsuki Kondo , Tomoka Tsujiuchi , Eiichi Yamakawa
IPC分类号： B63H126
CPC分类号： B64C27/463
摘要： The root end is attached to the rotor head for rotationally driving. The central portion has aerodynamic characteristics depending on the leading and trailing edges and which extend linearly from the root end in parallel to each other, and the chord dimension therebetween. A planform shape of the blade tip portion is defined by the first leading edge which extends forwardly as the distance from the outboard end of the leading edge of the central portion outwardly increases, the second leading edge and the side edge which are rearwardly swept as the distance from the outboard end of the first leading edge toward outboard side outwardly increases, the first trailing edge which is curved forwardly as the distance from an outboard end of the trailing edge of the central portion outwardly increases, and the second trailing edge which is swept rearwardly as the distance from the outboard end point of the first trailing edge outwardly increases. This configuration makes it possible to eliminate the delocalization in the supersonic region and greatly reduce high-speed impulsive noises.
摘要翻译：根端连接到转子头部用于旋转驱动。中心部分具有取决于前缘和后缘的空气动力特性，并且其从根端彼此平行地延伸，并且其之间的弦尺寸。叶片尖端部分的平面形状由当从中心部分的前缘的外侧端部的距离向外增加时向前延伸的第一前缘限定，第二前缘和侧边缘被向后扫掠，从第一前缘的外侧端向外侧的距离向外增大，当与中心部分的后缘的外侧端部的距离向外增加时，第一后缘向前弯曲，并且第二后缘被扫过随着距离第一后缘的外侧端点的距离向外增加，向后延伸。该结构能够消除超音速区域的离域化，大大降低高速脉冲噪声。

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