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

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	Experimental study of rotor blades vibration and noise in multistage high pressure compressor and their relevance
其他题名	Experimental study of rotor blades vibration and noise in multistage high pressure compressor and their relevance
	Fengtong ZHAO 1; Xiaodong JING 1; Mingsui YANG 3; Deyou WANG 2; Yundong SHA 2; Xiaochi LUAN 2
	2020
发表期刊	Chinese Journal of Aeronautics
ISSN	1000-9361
卷号	33 期号:3 页码:870-878
摘要	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. Keywords: Acoustic resonance, Blades vibration, Characteristic frequency, Multistage compressor, Source identification
关键词	Motor vehicles. Aeronautics. Astronautics TL1-4050
收录类别	CSCD
语种	英语
资助项目	[National Natural Science Foundation of China] ; [Aeronautical Science Foundation of China]
CSCD记录号	CSCD:6693914
引用统计	被引频次：14[CSCD] [CSCD记录]
文献类型	期刊论文
条目标识符	http://ir.imr.ac.cn/handle/321006/87167
专题	中国科学院金属研究所
作者单位	1.School of Energy and Power Engineering,Beihang University 2.Liaoning Province Key Laboratory of Advanced Measurement And Test Technology of Aviation Propulsion Systems,Shenyang Aerospace University 3.中国科学院金属研究所
推荐引用方式 GB/T 7714	Fengtong ZHAO,Xiaodong JING,Mingsui YANG,et al. Experimental study of rotor blades vibration and noise in multistage high pressure compressor and their relevance[J]. Chinese Journal of Aeronautics,2020,33(3):870-878.
APA	Fengtong ZHAO,Xiaodong JING,Mingsui YANG,Deyou WANG,Yundong SHA,&Xiaochi LUAN.(2020).Experimental study of rotor blades vibration and noise in multistage high pressure compressor and their relevance.Chinese Journal of Aeronautics,33(3),870-878.
MLA	Fengtong ZHAO,et al."Experimental study of rotor blades vibration and noise in multistage high pressure compressor and their relevance".Chinese Journal of Aeronautics 33.3(2020):870-878.