Vortex Trajectory Prediction and Mode Analysis of Compressor Stall with Strong Non-uniformity
Vortex Trajectory Prediction and Mode Analysis of Compressor Stall with Strong Non-uniformity
复制标题
强非均匀压气机失速涡轨迹预测与模态分析
DOI：
10.1016/j.ast.2020.106031
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发表时间：
2020-10
影响因子：
5.6
通讯作者：
Mi Zhou
中科院分区：
文献类型：
--
作者：
Li Fu;Chenxing Hu;Ce Yang;Wenrui Bao;Mi Zhou
鉴于涡轮增压压气机对了解临界条件下的流动结构和改进流动控制技术提出了更高的要求，进一步了解与尖端泄漏流动相关的尖峰失速起始的非定常行为是至关重要的。本文采用雷诺平均N-S技术，对离心式压气机的全环非定常流动进行了数值模拟，并进行了实验验证。采用多判据原理确定了叶轮内的钉型失速。然后，对数值数据进行动态模式分解，捕捉并显示绝对坐标和相对坐标下的主要流动结构。重建了相干扰动的时间和空间发展。最后，基于模式分解的结果，提出了一种修正的非对称流动旋涡轨迹预测模型，该模型可以确定尖峰失速起始的周向位置。结果表明，在绝对坐标系和相对坐标系下，DMD方法均能捕捉到与失速起始相关的低频扰动，扰动频率分别为0.44RF和0.5RF。在绝对坐标下，失速起始可分解为三种失速模式：平均流中的静止失速单元、与BPF相关的某一区域内的传播失速单元和起始处的振荡失速单元，失速频率为0.44Rf。考虑到流动重构，叶轮内的流动不稳定是相对静止的失速起始阶段，没有明显的相移，失速扰动发生在120∘周向位置。失速起始的具体位置受叶片前缘的影响，利用涡迹预测模型可以较准确地预测失速起始位置。
Given the heightened requirements of understanding the flow structure under critical condition and improving flow control technique for the turbocharger compressor, further insight into the unsteady behaviors of spike-stall inception associated with tip leakage flow was vital. In this work, an unsteady full annular simulation of a centrifugal compressor coupled with experimental validations was carried out by using the Reynolds averaged Navier–Stokes technique. A spike-type stall in the impeller was determined with multiple criterion principles. Then, a dynamic mode decomposition procedure was applied to the numerical data to capture and visualize the dominant flow structure in both absolute and relative coordinate. The temporal and spatial development of coherent perturbations was reconstructed. Finally, based on the results of mode decomposition, a modified prediction model of vortex trajectory concerning the asymmetrical flow, which can determine the circumferential location of spike-stall inception, was put forward. The results indicate that the low-frequency perturbation associated with stall inception can be captured by the DMD approach under both absolute and relative frames with the perturbation frequencies of 0.44 RF and 0.5 RF, respectively. Under absolute coordinate, the stall inception can be decomposed into three patterns: stationary stall cell in the mean flow, propagated stall cell in a certain region associated with BPF and oscillated stall cell in the origin place with the stall frequency of 0.44 RF. Considering the flow reconstruction, the flow instability in the impeller is relatively stationary stall inception without a significant phase shift and the stall perturbation occurs at 120∘ circumferential location. The specific location of stall inception is influenced by the blade leading edge, which can be predicted by the prediction model of the vortex trajectory accurately.
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影响因子：
1.7
作者：
S. Kang;C. Hirsch
通讯作者：
S. Kang;C. Hirsch
DOI：
10.1016/j.ijheatfluidflow.2018.09.013
发表时间：
2018-12
影响因子：
2.6
作者：
Xiaojian Yang;Xiaocheng Zhu;Chenxing Hu;Z. Du
通讯作者：
Xiaojian Yang;Xiaocheng Zhu;Chenxing Hu;Z. Du
影响因子：
1.2
作者：
N. Buffaz;I. Trébinjac
通讯作者：
N. Buffaz;I. Trébinjac
DOI：
10.1115/1.4034239
发表时间：
2016-06
影响因子：
1.5
作者：
Enrico Munari;Mirko Morini;M. Pinelli;P. R. Spina;A. Suman
通讯作者：
Enrico Munari;Mirko Morini;M. Pinelli;P. R. Spina;A. Suman
跨音速压缩机叶尖不稳定根源的数值研究
影响因子：
1
作者：
Guangyao An;Yanhui Wu;Zhiyang Chen;Bo Wang
通讯作者：
Bo Wang