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Thermal barrier coating life prediction method for a turbine blade[J]. Journal of Aerospace Power, 2018, 33(1): 48-53. doi: 10.13224/j.cnki.jasp.2018.01.006
Citation: Thermal barrier coating life prediction method for a turbine blade[J]. Journal of Aerospace Power, 2018, 33(1): 48-53. doi: 10.13224/j.cnki.jasp.2018.01.006
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Thermal barrier coating life prediction method for a turbine blade

doi: 10.13224/j.cnki.jasp.2018.01.006
  • Received Date: 2016-11-16
  • Publish Date: 2018-01-28
    Abstract
  • Based on the stresslife model developed by NASA and integrated in CoatLife software, the life prediction method of the thermal barrier coating on a turbine blade was investigated. Through the introduction of the oxidation mass gain in the life model, the oxidation dynamic was considered， and the high temperature oxidation effect can be introduced in the life model. Because the fatigue strength coefficient was the function of service time and geometric radius, the arbitrary geometry in real structures and the time dependent deterioration effect could be covered. The calculation results showed that the cycle life and the time life of the coating decreased with the increase of the maximum temperature or fatigue strength coefficient. Based on the design temperature field, the life of a turbine blade coating was predicted. The results showed that the spalling life the coating at the half height of the leading edge was about 336h when the cyclic time was 1h, and this agreed well with the real coating life between 300h and 400h.

     

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