| 轴向前倾叶片流场的数值分析 |
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| 引用本文： | 杨立军,陆亚钧.轴向前倾叶片流场的数值分析[J].航空动力学报,1995,10(2):124-126,198. |
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| 作者姓名： | 杨立军 陆亚钧 |
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| 作者单位： | 北京航空航天大学 |
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| 摘 要： | 对一种新式的风机叶片即轴向前倾叶片流场进行数值计算, 采用时间推进法计算无粘流场, 采用非正交曲线坐标系附面层积分方程求解附面层参数, 得到了一些有意义的结果。
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| 关 键 词： | 前倾叶片 附面层 数值分析 |
| 收稿时间： | 6/1/1994 12:00:00 AM |
| 修稿时间： | 1994/10/1 0:00:00 |
NUMERICAL ANALYSIS OF FLOW FIELD ABOUT SWEEP FORWARD BLADES OF COMPRESSORS OR FANS |
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| Yang Lijun and Lu Yajun.NUMERICAL ANALYSIS OF FLOW FIELD ABOUT SWEEP FORWARD BLADES OF COMPRESSORS OR FANS[J].Journal of Aerospace Power,1995,10(2):124-126,198. |
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| Authors: | Yang Lijun and Lu Yajun |
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| Institution: | 4th Dept.,Beijing University of Aeronautics and Astronautics,Beijing 100083 |
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| Abstract: | A numerical analysis of the flow field about sweep forward blades has been carried out.Time marching method is used to calculate the three dimensional inviscid flow field.Boundary layer parameters are calculated with integrated boundary layer equations in non orthogonal axises.The calculated results show that in axial compressors and fans with sweep forward blades the intensity of passage vortex,secondary flow and tip losses are decreased,the early separation from the blade surface is protected,the flow field in tip area is improved obviously.As a result,the aerodynamic efficiency of axial compressor or ventilator is enhanced. |
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| Keywords: | Sweep forward blades boundary layer Numerical analysis |
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