压气机内部噪声特征与转子叶片声固耦合机理分析

doi:10.7527/S1000-6893.2018.22669

流体力学与飞行力学

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压气机内部噪声特征与转子叶片声固耦合机理分析

赵奉同^1,2, 景晓东¹, 沙云东², 王晓宇¹, 栾孝驰²

1. 北京航空航天大学能源与动力工程学院, 北京 100083;
2. 沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室, 沈阳 110136

收稿日期:2018-09-12 修回日期:2018-10-23 出版日期:2019-05-15 发布日期:2018-11-14
通讯作者: 景晓东 E-mail:jingxd@buaa.edu.cn
基金资助:
国家自然科学基金（51676008）

Analysis of noise characteristics and acoustic structure coupling mechanism of rotor blades in compressor

ZHAO Fengtong^1,2, JING Xiaodong¹, SHA Yundong², WANG Xiaoyu¹, LUAN Xiaochi²

1. School of Energy and Power Engineering, Beihang University, Beijing 100083, China;
2. Liaoning Province Key Laboratory of Advanced Measurement and Test Technology of Aviation Propulsion Systems, Shenyang Aerospace University, Shenyang 110136, China

Received:2018-09-12 Revised:2018-10-23 Online:2019-05-15 Published:2018-11-14
Supported by:
National Natural Science Foundation of China (51676008)

摘要/Abstract

摘要： 航空发动机压气机转子叶片故障多由机械激励和气动激励造成，而高强声波对转子叶片的激振因素不容忽视。通过开展某型涡扇发动机压气机内部噪声测试试验，研究压气机转子叶片振动机理及其与噪声信号的对应关系。阐述了压气机内部旋转不稳定性非定常压力波作用机制，提出了基于刚性壁声波导管技术的导出式噪声测量方法，完成了某型涡扇发动机压气机内部噪声信号测试，对噪声信号进行了频谱分析和声传播特性分析。研究结果表明，某型涡扇发动机压气机内部噪声信号频谱呈现高峰值纯音分量1 402 Hz，并且该纯音分量与转子叶片通过频率呈现特定的频率组合关系。该纯音分量的噪声源在压气机内部沿发动机顺航向方向从后向前传播。利用旋转不稳定性理论，将声源频率在不同坐标系下进行转换，当噪声源周向模态数为13时，该纯音分量可调制出与高压一级转子叶片一阶振动频率相对应的激振频率。

关键词: 压气机, 转子叶片, 特征频率, 旋转不稳定性, 声固耦合

Abstract: The rotor blade fault of aero-engine compressor is mostly caused by mechanical and aerodynamic excitations. The excitation factors of high intensity sound waves to rotor blades should not be ignored. Based on the noise testing in a turbofan engine compressor, the vibration mechanism of compressor rotor blades and its corresponding relation with noise signal have been investigated. The mechanism of rotating instability unsteady pressure wave in the compressor is expounded. A noise measurement method which based on rigid wall acoustic waveguide is proposed. The internal noise signal testing of the turbofan engine compressor is completed. And the noise signal spectrum and acoustic propagation characteristics are analyzed. The results show that, the internal noise signal spectrum of the turbofan engine compressor presents a peak pure tone component of 1 402 Hz. And this tone component has a specific combination of frequencies with rotor blades. The propagation direction of this tone component noise source is from the back to the front in the airflow direction in the compressor. The noise source frequency is transformed in different coordinate systems based on the rotating instability theory. When the circumferential mode number of the noise source is thirteen, this tone component can modulate the excitation frequency corresponding to the first order vibration frequency of the first stage rotor blades of the high compressor.

Key words: compressor, rotor blade, characteristic frequency, rotating instability, acoustic structure coupling

中图分类号:

V232.4

赵奉同, 景晓东, 沙云东, 王晓宇, 栾孝驰. 压气机内部噪声特征与转子叶片声固耦合机理分析[J]. 航空学报, 2019, 40(5): 122669-122669.

ZHAO Fengtong, JING Xiaodong, SHA Yundong, WANG Xiaoyu, LUAN Xiaochi. Analysis of noise characteristics and acoustic structure coupling mechanism of rotor blades in compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(5): 122669-122669.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

压气机内部噪声特征与转子叶片声固耦合机理分析

Analysis of noise characteristics and acoustic structure coupling mechanism of rotor blades in compressor

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