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Experimental study of rotor blades vibration and noise in multistage high pressure compressor and their relevance

查看参考文献22篇

文摘 Rotor blades fault of aeroengine compressor is mostly caused by mechanical and aerodynamic excitation. And the excitation factor of high intensity sound wave to rotor blades should not be ignored. Experimental researches are conducted on a multistage high pressure compressor. When high level vibration occurs on the first stage of rotor blades, the noise spectrum presents typical characteristic for discrete multi-tone in the compressor. The amplitude of blade vibration displacement and the sound pressure level of characteristic frequency noise increases and decreases simultaneously and reaches the maximum value at the same time. This frequency merely occur on a certain speed range and is locked in a specific range which presents no variation with the rotating speed. When high level vibration occurs on the first stage of rotor blades, the noise spectrum presents a sharp peak and the propagation state of the characteristic frequency is a helix structure in the compressor. It can be confirmed that acoustic resonance occurs in the multistage compressor. The acoustic resonance frequency and its side band frequencies are generated by modulation of a rotating noise source at the rotor speed which is the excitation source of the rotor blades vibration.
来源 Chinese Journal of Aeronautics ,2020,33(3):870-878 【核心库】
DOI 10.1016/j.cja.2019.02.008
关键词 Acoustic resonance ; Blades vibration ; Characteristic frequency ; Multistage compressor ; Source identification
地址

1. School of Energy and Power Engineering, Beihang University, Beijing, 100191  

2. Shenyang Aerospace University, Liaoning Province Key Laboratory of Advanced Measurement And Test Technology of Aviation Propulsion Systems, Shenyang, 110136  

3. Shenyang Engine Design and Research Institute, Aero Engine (Group) Corporation of China, Shenyang, 110015

语种 英文
文献类型 研究性论文
ISSN 1000-9361
学科 航空
基金 co-supported by the National Natural Science Foundation of China ;  中国航空科学基金
文献收藏号 CSCD:6693914

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引证文献 14 篇

1 Han Le Lock-in phenomenon of tip clearance flow and its influence on aerodynamic damping under specified vibration on an axial transonic compressor rotor Chinese Journal of Aeronautics,2022,35(3):185-201
CSCD被引 7 次

2 Zhao Fengtong Physical model for acoustic resonance in annular cavity structure Chinese Journal of Aeronautics,2020,33(12):3228-3237
CSCD被引 1 次

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