Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses

Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses
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轴流式压缩机和涡轮机的边界层开发：第 4 部分（共 4 部分）—计算和分析

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发表时间：
1997
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影响因子：
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通讯作者：
Hyoun
Hyoun
中科院分区：
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文献类型：
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作者：
D. Halstead;D. Wisler;T. Okiishi;G. Walker;H. Hodson;Hyoun

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这是四部分论文的第四部分。它从第 16.0 节开始，总结了对综合实验和计算分析的描述，这些实验和计算分析得出了多级涡轮机械中翼型表面边界层发展的详细图片。在本文中，提出了使用几种现代边界层代码进行的计算预测。稳定代码和非稳定代码都被评估。将结果与边界层测量的时间平均和非稳态积分参数进行比较。进行评估是为了提供使用预测代码来定位转变和预测损失的指导。然后提出计算分析的结论。
This is Part Four of a four-part paper. It begins with Section 16.0 and concludes the description of the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this paper, the computational predictions made using several modern boundary layer codes are presented. Both steady codes and an unsteady code were evaluated. The results are compared with time-averaged and unsteady integral parameters measured for the boundary layers. Assessments are made to provide guidance in using the predictive codes to locate transition and predict loss. Conclusions from the computational analyses are then presented.