Frequency spectrum of unsteady pressure on rotor blade with rotor-stator interaction

被引：0
|
作者：
Zhang X.-B. [1 ,2 ]
Wang Y.-R. [1 ,2 ]
Huang Z.-S. [1 ,2 ]
Wang X.-P. [1 ,2 ]
机构：
[1] School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing
[2] Collaborative Innovation Center for Advanced Aero-Engine, Beijing
来源：
| 1695年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 31期
关键词：
Compressor; Frequency spectrum characteristics; Higher order dominant frequency; Rotor-stator interaction; Unsteady pressure;
D O I：
10.13224/j.cnki.jasp.2016.07.019
中图分类号：
学科分类号：
摘要：
The unsteady pressure on compressor rotor blade surface due to rotor-stator interaction was simulated by use of multi-channel model and phase lagged method based on single-channel model. The unsteady pressure on rotor blade surface in both time domain and frequency domain was analysed, and its higher order dominant frequencies were studied. The results show that the results of phase lagged method agree well with those of multi-channel method, the unsteady pressure peak frequencies of rotor blade are the BPF (blade passing frequency) and its harmonics, and the unsteady pressure amplitude of 2BPF is approximately 2 times of 1BPF above the middle position of blade height, this can be attributed to the wake transportation and shock oscillation. The results can provide a reference for investigating thoroughly the causes of high cycle fatigue failure of blade due to its vibration. © 2016, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1695 / 1703
页数：8
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