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Title: Numerical Simulation on Unsteady Flow Mechanism of a 1.5-Stage Axial Transonic Compressor
题目：1.5级轴流跨音压气机非定常流动机理的数值研究
Authors: PENG Shuxuan, ZHANG Xiaoyu, WANG Wentao, ZHANG Hongwu, LI Xinlong
作者：彭姝璇，张小玉，王文涛，张宏武，李鑫龙
单位：中科南京未来能源系统研究院高效低碳燃气轮机数字化中心，中国科学院工程热物理研究所先进燃气轮机实验室，中国科学院先进能源动力重点实验室，中国科学院轻型动力创新研究院，国科学院大学，比亚迪汽车工业有限公司
Journal of Thermal Science, 2024, 33(5): 1851-1866.
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Numerical Simulation on Unsteady Flow Mechanism of a 1.5-Stage Axial Transonic Compressor.pdf
摘要
Abstract: In this paper, a numerical simulation method is used to calculate a 1.5-stage axial transonic compressor to explore its unsteady flow mechanism. The performance curve is compared with the experimental data to verify the calculation method with a high numerical accuracy, which shows that the unsteady calculation has good reliability. According to the analysis of the data from the monitoring points under the near-stall condition, the unsteady disturbances originate from the tip region of blade and perform the strongest at the blade pressure surface with a broadband characteristic. Further analysis is conducted by combining with the characteristics of the transient flow field at the tip of blade. The results show that the unsteady pressure fluctuations are caused by the migration of the new vortex cores. These new vortex cores are generated by the breakdown of leakage vortex in the downstream, which is induced by the leakage vortex and shock wave interference. Moreover, the relationship between the unsteady flow characteristics and the working conditions is also studied. The leakage vortex intensity and the shock wave strength gradually increase with the decrease of flow rate. When the combination of the leakage vortex intensity and shock wave strength reaches the first threshold, a single frequency of unsteady disturbances appears at the blade tip. When the combination of the leakage vortex intensity and shock wave strength reaches the second threshold, the frequency of unsteady disturbances changes to a broadband.
摘要：本文针对1.5级轴流跨音压气机开展非定常数值模拟，以探究非定常扰动产生机制。首先利用试验测量数据对数值仿真结果进行了校核，在数值与试验结果一致性较好的前提下对压气机非定常流动机理进行深入分析。通过设置虚拟探针对近失速工况流场进行监测，确定非定常扰动源于动叶叶顶区域，且叶片压力面扰动最强，其频率呈宽频特性。结合叶顶瞬态流场特征分析，发现泄漏涡与激波干涉使得泄漏涡破碎，其产生的新涡核在流场中迁移诱发了非定常压力扰动。进一步分析压气机节流过程中泄漏涡与激波的相互作用，发现泄漏涡强度与激波强度随流量的减小而逐渐增大，当两者组合到达第一阈值，叶顶出现了单一的扰动频率；当两者组合到达第二阈值，叶顶扰动频率向宽频转变。
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引用格式
PENG Shuxuan, ZHANG Xiaoyu, WANG Wentao, ZHANG Hongwu, LI Xinlong, Numerical Simulation on Unsteady Flow Mechanism of a 1.5-Stage Axial Transonic Compressor, Journal of Thermal Science, 2024, 33(5): 1851-1866.
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