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A simple unified critical plane damage parameter for high-temperature LCF life prediction of a Ni-based DS superalloy

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Abstract

A simple unified critical plane damage parameter (i.e., the modified resolved shear strain range ∆γ mod) based on a slip mechanism-related critical plane concept was proposed in this paper, integrating life prediction of low cycle fatigue (LCF) behavior affected by anisotropy, load ratio and stress concentration into one framework, where the critical plane is determined as the slip plane on which the damage parameter is the maximum during the cycle. For notched specimens, this procedure was specially carried out at the fatigue initiation sites located on the notch surface, which were well predicted by the distribution of Von-Mises stress range ∆σ Mises. The applications of this damage parameter in a directionally solidified superalloy at high temperatures showed that the LCF lives resulting from complicated loading conditions (i.e., variable material orientation, temperature, loading ratio and notch feature) were well simulated consistently, and the predicted fatigue life is within a scatter band of ±3.

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Acknowledgements

The research was supported by National Natural Science Foundation of China (No. NSFC 51275023) and the Innovation Foundation of BUAA for Ph.D. Graduates (No. YWF-14-YJSY-49).

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Authors and Affiliations

  1. School of Energy and Power Engineering, Beihang University, Beijing, 100191, China

    Jia Huang, Xiaoguang Yang, Duoqi Shi & Xiaoan Hu

  2. Beijing Institute of Aeronautical Materials, Beijing, 100095, China

    Huichen Yu

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  1. Jia Huang
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  2. Xiaoguang Yang
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  3. Duoqi Shi
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  4. Huichen Yu
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  5. Xiaoan Hu
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Correspondence to Duoqi Shi.

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Huang, J., Yang, X., Shi, D. et al. A simple unified critical plane damage parameter for high-temperature LCF life prediction of a Ni-based DS superalloy. J Mater Sci 49, 7625–7638 (2014). https://doi.org/10.1007/s10853-014-8418-6

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  • DOI: https://doi.org/10.1007/s10853-014-8418-6

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