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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2019, Vol. 40 ›› Issue (5): 122669-122669.doi: 10.7527/S1000-6893.2018.22669

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

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

ZHAO Fengtong1,2, JING Xiaodong1, SHA Yundong2, WANG Xiaoyu1, LUAN Xiaochi2   

  1. 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)

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

CLC Number: