Volume 37 Issue 5
May  2022
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Article Navigation >  Journal of Aerospace Power  > 2022  >  37(5): 946-953
YOU Yu, XU Jian, YAN Qun, ZHANG Wei, GUO Dingwen, HUANG Taiyu. Combined fatigue life prediction and experiment verification for turbine blade[J]. Journal of Aerospace Power, 2022, 37(5): 946-953. doi: 10.13224/j.cnki.jasp.20210019
Citation: YOU Yu, XU Jian, YAN Qun, ZHANG Wei, GUO Dingwen, HUANG Taiyu. Combined fatigue life prediction and experiment verification for turbine blade[J]. Journal of Aerospace Power, 2022, 37(5): 946-953. doi: 10.13224/j.cnki.jasp.20210019
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Combined fatigue life prediction and experiment verification for turbine blade

doi: 10.13224/j.cnki.jasp.20210019

  • Laboratory of Aeronautical Acoustics and Vibration，Aircraft Strength Research Institute of China，Xi'an 710065，China

  • Received Date: 2021-01-14
  • Publish Date: 2022-05-28
    Abstract
  • In order to solve the fatigue strength problems of turbine rotor blade under the combined loads of temperature,centrifugal force and aerodynamic/acoustic,the decomposition method of a high-low cycle complex load spectrum and the full-time domain creep damage cumulative model based on the high-low cycle complex load were investigated.The combined fatigue life prediction method considering simultaneously the fatigue damage of creep,low cycle and high cycle was proposed.Meanwhile,the high-low cycle complex fatigue experiment platform was developed through application of the critical technologies,such as orthogonal loads decoupling and coordinated loading control of the complex load.Finally,taking a simulation specimen of a turbine blade as the research object,the combined fatigue life prediction and experiment verification were accomplished.Results showed that the scatter factor of experiment result of combined fatigue life was 1.01,and the deviation between the prediction result and the experiment result was less than 24%.The validity of fatigue life prediction model was verified,providing an effective technical approach to fatigue strength design and validation for aero-engine hot-end components.

     

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