公开(公告)号：US4077741A

公开(公告)日：1978-03-07

申请号：US687640

申请日：1976-05-18

申请人： Martin Vincent Lowson ,  David Leonard Hawkings ,  Geoffrey Malcolm Byham ,  Frederick John Perry

发明人： Martin Vincent Lowson ,  David Leonard Hawkings ,  Geoffrey Malcolm Byham ,  Frederick John Perry

IPC分类号： B64C27/46

CPC分类号： B64C27/463

摘要： A helicopter rotor blade includes a rearwardly swept tip portion having a leading edge of aerofoil profile located forward of the leading edge of a central portion of the blade, and blended with a sharp tip edge of higher sweep magnitude than the leading edge and extending rearwardly to an extreme tip of the blade. A rearwardly swept trailing edge extends from a junction with the trailing edge of the central portion to the extreme tip so that the tip portion has a chord dimension greater than that of the central portion of the blade.In operation, the rotor blade utilizes a stable vortex dominated flow field created over the tip portion to provide operational advantages in respect of both a retreating and an advancing blade.

摘要翻译： 直升机转子叶片包括向后扫掠的尖端部分，其具有位于叶片的中心部分的前缘前方的翼型轮廓的前缘，并且与前缘相比具有更高扫掠幅度的锋利尖端边缘并且向后延伸到 叶片的尖端。 向后扫掠的后缘从与中心部分的后缘的接合点延伸到最前端，使得尖端部分的弦的尺寸大于叶片的中心部分的弦长。

公开(公告)号：US5992793A

公开(公告)日：1999-11-30

申请号：US779120

申请日：1997-01-06

申请人： Frederick John Perry ,  Robert John Harrison ,  Alan Brocklehurst

发明人： Frederick John Perry ,  Robert John Harrison ,  Alan Brocklehurst

IPC分类号： B64C27/46 ,  B64C3/14

CPC分类号： B64C27/463

摘要： An aerofoil comprises a leading edge and a trailing edge which define a mean chord length, and the aerofoil having an inner or root end adapted for attachment to an aircraft, and an outer end which includes a tip which is adapted in use to divide the airflow into two generally equal vortices one being an inner vortex and the other being an outer vortex the inner vortex being arranged to trail from an outer edge of a forward region of the tip and pass over a rear region of the tip.

摘要翻译： 机翼包括限定平均弦长的前缘和后缘，并且翼型件具有适于附接到飞行器的内端或根端，以及包括尖端的外端，所述端部适于使用气流 分成两个大致相等的涡流，一个是内部涡流，另一个是外部涡流，内部涡流设置成从尖端的前部区域的外边缘延伸并越过尖端的后部区域。

公开(公告)号：US5927948A

公开(公告)日：1999-07-27

申请号：US839177

申请日：1997-04-23

申请人： Frederick John Perry ,  Alan Brocklehurst ,  Robert John Harrison

发明人： Frederick John Perry ,  Alan Brocklehurst ,  Robert John Harrison

IPC分类号： B64C11/18 ,  B64C27/46 ,  B64C27/467 ,  B64C11/16

CPC分类号： B64C27/463

摘要： A propeller (10a) comprising a plurality of propeller blades (9a) each having a root end (11a) attached to the central propeller disc or hub (12a), an intermediate portion (13a) extending from the root end (11a) and having a generally aerofoil cross section extending chordwise between a leading edge (14a) and a trailing edge (15a), and the blade (9a) having a tip (19) at an end of the intermediate portion (13a) remote from the root end (11a), the tip (19) having a leading edge portion (20) extending forwardly from a junction (21) with the leading edge (14a) of the intermediate portion (13a) thus to provide a discontinuity or notch (25) in the leading edge (14a) of the blade (9a) at the junction (21).

摘要翻译： 包括多个螺旋桨叶片（9a）的螺旋桨（10a），每个螺旋桨叶片（9a）各自具有附接到中心推进盘或轮毂（12a）的根部端部（11a），从根部端部（11a）延伸的中间部分（13a） 在前缘（14a）和后缘（15a）之间弦向延伸的大致翼型横截面，并且叶片（9a）在远离根端的中间部分（13a）的端部具有尖端（19） 11a），具有从中间部分（13a）的前缘（14a）向前延伸的前缘部分（20）的尖端（19）由此在中间部分（13a）的前缘（14a）处提供不连续或凹口（25） 在连接处（21）处的叶片（9a）的前缘（14a）。