13th International Conference on Fracture June 16–21, 2013, Beijing, China -8- 26.7 81.01 30.4 81.50 34.1 82.66 37.8 82.95 Therefore, based on experimental and numerical investigations, a new criterion for withdrawal from service of this type of turbine component to assure the structural integrity of this aeroengine is established by the industrial corporation, that is, if the overhaul period is 300hours and 500hours, the critical crack size are 23.5mm and 17mm respectively. And considering twice overhaul period, we can obtain critical crack size 14.5mm for 300hour-overhaul period and 7.7mm for 500hour-overhaul period. 4. Conclusions This paper studied the crack growth life of a full scale turbine component at elevated temperature under HLCCF loading through experimental and numerical methods. The experimental system achieves HLCCF loading of the full scale turbine component, and a special design of the blade clamp successfully simulates the stress field of the turbine blade. A new reliable crack growth life assessment strategy for turbine component is developed based on experimental and numerical investigations under HLCCF loading. In summary, this paper provides a new way to establish a lifetime criterion for withdrawal from service of turbine components. Acknowledgements This work is supported by Aviation Science Fund of China (2011ZB51015) and Doctoral Fund of Ministry of Education of China (20111102120011). The writers are grateful. References [1]R.Q. Wang, C.D. Cho, J.X. Nie. Combined fatigue life test and extrapolation of turbine disk mortise at elevated temperature. Journal of Engineering for Gas Turbine and Power, Transactions of the ASME, 127 (2005) 863-868. [2]N.X. Hou, Z.X. Wen, Q.M. Yu, et al. Application of a combined high and low cycle fatigue life model on life prediction of SC blade. International Journal of Fatigue, 31(2009) 616-619. [3]C. Schweizer, T. Seifert, B. Nieweg, et al. Mechanisms and modeling of fatigue crack growth under combined low and high cycle fatigue loading. International Journal of Fatigue, 33(2011) 194-202. [4]D.Y. Hu, R.Q. Wang, G. C. Hou, Combined Fatigue Experiments on Full Scale Turbine Components", Aircraft Engineering and Aerospace Technology, 2013, 85(2013) (on line). [5]S.A. Meguid, P.S. Kanth, A. Czekanski. Finite element analysis of fir-tree region in turbine discs. Finite Elements in Analysis and Design, 35(2000) 305-317. [6]A. Pineau, S.D. Antolovich. High temperature fatigue of nickel-base superalloys-a review with special emphasis on deformation models and oxidation. Engineering Failure Analysis, 16(2009) 2668-2697. [7]P. J. Golden, T. Nicholas. The effect of angle on dovetail fretting experiments in Ti-6Al-4V. Fatigue & Fracture of Engineering Materials & Structures, 28(2005) 1169-1175. [8]S. Issler, E. Roos. Numerical and experimental investigations into life assessment of blade-disc connections of gas turbines. Nuclear Engineering and Design, 226(2003) 155-164. [9]R.Q. Wang, J.X. Nie. A new experimental method to study combined fatigue of actual turbine disk mortise teeth at elevated temperature. Journal of Engineering for Gas Turbines and Power, Transaction of the ASME, 119(1997) 969-972.
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