Volume 29 Issue 9
Sep.  2014
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Article Navigation >  Journal of Aerospace Power  > 2014  >  29(9): 2104-2112
GUO Xue-lian, FAN Yu, LI Lin. Experimental test method for high-frequency modal damping of turbomachinery blades[J]. Journal of Aerospace Power, 2014, 29(9): 2104-2112. doi: 10.13224/j.cnki.jasp.2014.09.013
Citation: GUO Xue-lian, FAN Yu, LI Lin. Experimental test method for high-frequency modal damping of turbomachinery blades[J]. Journal of Aerospace Power, 2014, 29(9): 2104-2112. doi: 10.13224/j.cnki.jasp.2014.09.013
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Experimental test method for high-frequency modal damping of turbomachinery blades

doi: 10.13224/j.cnki.jasp.2014.09.013

  • 1. Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China;

  • 2. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 2013-06-08
  • Publish Date: 2014-09-28
    Abstract
  • High-frequency modal damping ratio experimental identification of turbomachinery blade was studied using NASA Rotor37 blade. The blade was tested by random acoustic excitation in order to obtain evident high frequency response. It is shown, both numerically and experimentally, that the obtained frequency-response curve at high-frequency also showed the information of the excited modes from the supporting structure. Therefore the vibration of the supporting structure was also monitored by several sensors. Then a data processing approach was proposed to distinguish the blade dominant peaks by comparing the energy transfer ratio of the blade with that of the supporting structure. After wavelet threshold denoising, the blade's modal damping ratios less than 10kHz were obtained by fitting the blade dominant peaks. Additionally, the results show that the magnitude of blade's high-frequency modal damping is less than 1% when it is produced by general metal materials, and the magnitude has a downward trend along with the frequency.

     

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