Volume 36 Issue 3
Mar.  2021
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TANG Xu, ZHANG Yukun, CHEN Yong. Prediction of composite fan blade high cycle fatigue weak-link point location[J]. Journal of Aerospace Power, 2021, 36(3): 498-508. doi: 10.13224/j.cnki.jasp.2021.03.006
Citation: TANG Xu, ZHANG Yukun, CHEN Yong. Prediction of composite fan blade high cycle fatigue weak-link point location[J]. Journal of Aerospace Power, 2021, 36(3): 498-508. doi: 10.13224/j.cnki.jasp.2021.03.006
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Prediction of composite fan blade high cycle fatigue weak-link point location

doi: 10.13224/j.cnki.jasp.2021.03.006
  • 1.

    School of Mechanical Engineering,Shanghai Jiao Tong University, Shanghai 200240,China

  • 2.

    Engineering Research Center of Gas Turbine and Civil Aero Engine,Ministry of Education,Shanghai Jiao Tong University,Shanghai 200240,China

  • Received Date: 2020-07-07
  • Publish Date: 2021-03-28
    Abstract
  • A method for predicting the high cycle fatigue weak-link point location of composite fan blade was proposed. Using the layup information file, a full-scale fan blade finite element model was established by normal extruding shell elements in ACP (ANSYS composite pre-post). Based on ANSYS-Workbench and Tecplot application program interface, the developed post-processing program completed the layup blade finite element data extracts and database creation. According to the composite material CLD (constant life diagram) model, the weak-link point index was applied to predict the location of blade high cycle fatigue failure. Case results showed that the blade failure location height did not exceed 40% of the entire blade height. First failure stress of 1st bending mode，1st torsion mode and 2nd torsion mode was layer normal stress, while 2nd bending mode, 3rd bending mode and stripe mode failures first occurred in layer shear stress. The layer normal stress weak-link point of blade bending mode was located in chord middle; the torsional mode vibration stress amplitude points were all structural plys, and S3 weak-link point was near the trailing edge. Compressive average stress could cause high cycle fatigue blade failure, and the area with a smaller static stress value could become a weak-link point.

     

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