摘要
采用商业软件FLUEN6.2对NREL风力机就8 m/s^15 m/s风速范围进行了数值计算,对由于旋转导致叶片升力增大现象进行了分析,并将计算结果与NASA风洞试验结果进行了对比.计算结果表明风速<10 m/s时,叶片上的压力分布与试验结果吻合较好,只有r/R=0.47段有较大偏差,当风速>10 m/s时,二者的偏差也随之增大,但差别不是很大,除叶片根部区域以及偶尔在r/R=0.47区域二者存在差别外二者吻合较好.从计算得到的流线图可以看出,在叶片吸力面上有较大的分离和横向流动区域,可以证实由于旋转效应,在r/R=0.30和r/R=0.47的2个区域存在升力增大和失速延迟现象.
This paper focuses on the augmented lift phenomenon as a result of blade rotation. In the investigations the commercial software FLUENT6.2 was used. The calculations are compared with the measurement results of the NASA Ames wind tunnel experiment at wind speeds between 8m/s and 15m/s . The computations show good agreement for the pressure distributions for almost all five segments at wind speeds below 10m/s,only large deviations occur at segment r/R=0. 47. Beyond 10m/s deviations with the experiment increase, but still,apart from the inboard r/R=0. 30 segment and occasionally the r/R=0. 47 location, the results are surprisingly good. Large separated areas and cross flows dominate the flow on the suction side as can be distracted from the calculated streamlines. For the rotation effects, the presence of augmented lift and stall delay can be confirmed for the span sections at r/R=0.30 and r/R=0.47
出处
《甘肃科学学报》
2009年第1期105-109,共5页
Journal of Gansu Sciences
基金
国家重点基础研究发展计划(973计划)(2007CB714602)
关键词
旋转效应
风力机
叶片
升力增大
失速延迟
rotation effects
wind turbine
blade
augmented lift
stall delay
