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.