| 叶片力亏损与端壁边界层流动关联的数值研究 |
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| 引用本文： | 吴虎,陈辅群,刘松龄.叶片力亏损与端壁边界层流动关联的数值研究[J].航空学报,1992,13(7):431-435. |
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| 作者姓名： | 吴虎 陈辅群 刘松龄 |
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| 作者单位： | 西北工业大学发动机系，西北工业大学发动机系，西北工业大学发动机系 西安 710072，西安 710072，西安 710072 |
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| 摘 要： | 通过理论分析提出一种考虑叶片端部间隙影响的叶片力亏损模型,并对三种轴流压气机叶栅的端壁边界层及叶片力亏损进行了数值计算。计算结果与实验结果比较表明吻合程度较好,说明提出的叶片力亏损模型具有可行性和通用性。数值分析也表明端壁边界层流动与叶片力亏损存在着紧密的关联:端壁边界层的偏转程度对切向叶片力亏损有明显影响;边界层轴向动量增长率对轴向叶片力亏损起主要作用。
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| 关 键 词： | 轴流压气机 叶栅 端壁边界层 叶片力亏损 |
NUMERICAL STUDY OF THE RELATIONSHIP BETWEEN ENDWALL BOUNDARY LAYER FLOW AND ITS BLADE FORCE DEFECT |
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| Wu Hu,Chen Fu-qun,Liu Song-ling.NUMERICAL STUDY OF THE RELATIONSHIP BETWEEN ENDWALL BOUNDARY LAYER FLOW AND ITS BLADE FORCE DEFECT[J].Acta Aeronautica et Astronautica Sinica,1992,13(7):431-435. |
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| Authors: | Wu Hu Chen Fu-qun Liu Song-ling |
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| Institution: | Department of Power, Northwestern Pol ytechnical University, Xi'an, 710072 |
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| Abstract: | A new model is presented for calculating the end-wall boundary layer and its blade force defect inside the axial compressor cascade, based on theoretical analysis. The model can consider the influence of tip clearence. The predictions for three different loaded compressor cascades agree well with experimental results. It is found that the development of end-wall boundary layer has a severe influence on the blade force defect from the results of numerical calculations. The calculated results of three different cascades show that the skewed degree of end-wall boundary layer is related to the transverse blade force defect and the relationship between the changed ratio of axial momentum thickness of end-wall boundary layer and axial blade force defect is rather close. |
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| Keywords: | axial compressor cascade end-wall boundary layer blade force defect |
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