Numerical simulation of the non-uniform flow in a full-annulus multi-stage axial compressor with the harmonic balance method
Numerical simulation of the non-uniform flow in a full-annulus multi-stage axial compressor with the harmonic balance method
复制标题
全环隙多级轴流压气机非均匀流动谐波平衡法数值模拟
DOI：
10.1177/1687814019897213
复制
发表时间：
2020-03
影响因子：
2.1
通讯作者：
Franco Magagnato
中科院分区：
文献类型：
--
作者：
Sun Haiou;Wang Meng;Wang Zhongyi;Wang Song;Franco Magagnato
为了提高对现代先进轴流压气机非定常流场的认识，采用谐波平衡法对全环空多级轴流压气机进行了非定常流场仿真。由于叶轮机械内部流动具有自然周期性，采用谐波平衡法可以降低计算成本。为了验证谐波平衡法的准确性，首先将数值结果与实验结果进行了比较。结果表明，谐波平衡法得到的多级轴流压气机内部流场和运行特性与实验结果吻合，相对误差在3%范围内。通过对轴向压气机内部流场的分析可以发现，相邻叶片排间隙内的气流由轴对称逐渐变为非轴对称，然后在下游叶片进口前又恢复到几乎完全轴对称分布，只有轻微的非轴对称分布，可以忽略不计。此外，随着流动的发展，这种轻微的非轴对称分布会不断累积，最终在后期形成明显的周向非均匀流场，这可能是传统的单通道数值方法在多级轴向压气机模拟中会产生一定误差的原因。
To improve the understanding of unsteady flow in modern advanced axial compressor, unsteady simulations on full-annulus multi-stage axial compressor are carried out with the harmonic balance method. Since the internal flow in turbomachinery is naturally periodic, the harmonic balance method can be used to reduce the computational cost. In order to verify the accuracy of the harmonic balance method, the numerical results are first compared with the experimental results. The results show that the internal flow field and the operating characteristics of the multi-stage axial compressor obtained by the harmonic balance method coincide with the experimental results with the relative error in the range of 3%. Through the analysis of the internal flow field of the axial compressor, it can be found that the airflow in the clearance of adjacent blade rows gradually changes from axisymmetric to non-axisymmetric and then returns to almost completely axisymmetric distribution before the downstream blade inlet, with only a slight non-axisymmetric distribution, which can be ignored. Moreover, the slight non-axisymmetric distribution will continue to accumulate with the development of the flow and, finally, form a distinct circumferential non-uniform flow field in latter stages, which may be the reason why the traditional single-passage numerical method will cause certain errors in multi-stage axial compressor simulations.
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DOI：
10.1016/j.jcp.2008.02.028
发表时间：
2008-01
期刊：
J. Comput. Phys.
影响因子：
--
作者：
K. Ekici;K. Hall;E. Dowell
通讯作者：
K. Ekici;K. Hall;E. Dowell
影响因子：
1.9
作者：
K. Ekici;K. Hall;R. Kielb
通讯作者：
K. Ekici;K. Hall;R. Kielb
影响因子：
10
作者：
Jeffrey P. Thomas;E. Dowell;K. Hall;C. Denegri
通讯作者：
Jeffrey P. Thomas;E. Dowell;K. Hall;C. Denegri
影响因子：
1.7
作者：
Li He;T. Chen;R. Wells;Y. S. Li;W. Ning
通讯作者：
Li He;T. Chen;R. Wells;Y. S. Li;W. Ning
影响因子：
2.5
作者：
F. Sicot;A. Gomar;G. Dufour;A. Dugeai
通讯作者：
F. Sicot;A. Gomar;G. Dufour;A. Dugeai