Numerical simulation of effect of circumferential non-uniform tip clearance on rotating instability in a rotor

被引：2

作者：

Jiang, Chao ^{[1
]}

Wang, Zhikuan ^{[1
]}

Le, Guigao ^{[2
]}

Hu, Jun ^{[3
]}

机构：

[1] Beijing System Design Institute of Electro-Mechanic Engineering, The Fourth Academy, China Aerospace Science and Industry Corporation Limited, Beijing

[2] School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing

[3] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 12期

关键词：

circumferential non-uniform tip clearance; low pressure; radial vortices; rotating instability; rotor; tip leakage flow;

D O I：

10.13224/j.cnki.jasp.20220973

中图分类号：

学科分类号：

摘要：

In order to study the flow phenomenon of rotating instability in compressors with nonuniform tip clearance，the Rotor 67 was taken as the research object，and the detailed flow field results and the characteristic lines of three kinds of eccentric rotor were calculated utilizing the three-dimensional full annulus unsteady computational fluid dynamics. The numerical calculation results showed that when the average tip clearance was constant，the eccentricity had little effect on the characteristic line of the non-stall part，but had a significant effect on the stall boundary. The disturbances in the tip region of concentric and eccentric rotors had a unified physical structure. These disturbances presented as moving low-pressure spots on the shroud，which were three-dimensional radial vortices starting from the suction surface of the blade and ending in the shroud，and had no direct relationship with the tip clearance leakage vortex. The eccentricity only changed the circumferential distribution pattern of the disturbances，and did not change the physical nature of the perturbation. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

引用

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