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

ZHANG Xiao-bo; WANG Yan-rong; HUANG Zhong-shan; WANG Xiang-peng

doi:10.13224/j.cnki.jasp.2016.07.019

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

更新时间：2026-07-07

- Frequency spectrum of unsteady pressure on rotor blade with rotor-stator interaction
- Vol. 31, Issue 7, Pages: 1695-1703(2016)
- 作者机构：
  
  1. 北京航空航天大学能源与动力工程学院,北京,100191
  2. 先进航空发动机协同创新中心,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2016.07.019
  CLC：
- Published：2016
- 稿件说明：
移动端阅览
张小博, 王延荣, 黄钟山, 王翔鹏. 转静干涉下转子叶片的非定常压力频谱[J]. 航空动力学报, 2016, 31(7): 1695-1703.

doi: 10.13224/j.cnki.jasp.2016.07.019
张小博, 王延荣, 黄钟山, 王翔鹏. 转静干涉下转子叶片的非定常压力频谱[J]. 航空动力学报, 2016, 31(7): 1695-1703. DOI： 10.13224/j.cnki.jasp.2016.07.019.

doi: 10.13224/j.cnki.jasp.2016.07.019 DOI：

摘要

分别采用多通道模型和相位延迟方法的单通道模型对一压气机转子叶片因转静干涉引起的表面非定常压力进行了分析.对比了转子叶片表面非定常压力的时域和频域信息，并对其高阶主导频率进行了分析.结果表明：相位延迟方法与多通道法计算结果吻合，转子叶片非定常压力的峰值频率为叶片通过频率及其倍频，叶片中部以上区域2倍叶片通过频率的非定常压力幅值约为1倍频的2倍，分析认为这是由尾迹输运和激波振荡导致的，可为深入分析叶片由振动导致高循环疲劳失效的成因提供参考.

Abstract

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.

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Related Institution

School of Aerospace Engineering，Beijing Institute of Technology

Institute for Aero Engine，Tsinghua University

Aerospace Technology Institute，China Aerodynamics Research and Development Center

Aeronautical Foundation Institute，Naval Aviation University

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