| Citation: | XU Kening, LI Wen, HUANG Yong, et al. A fretting fatigue total life prediction method for dovetail attachment[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(10): 1890-1898. doi: 10.13700/j.bh.1001-5965.2019.0471(in Chinese)
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Fatigue life of aero-engine dovetail attachment can be significantly reduced by fretting damage. Taking Ti-6Al-4V alloy aero-engine blade dovetail attachment as an example, a fretting fatigue total life prediction method for complex structure is proposed. A fatigue damage parameter was defined as an Equivalent Stress Parameter (ESP) based on modified Manson-McKnight method and multiaxial fatigue theory. Crack initiation position and nucleation life were evaluated by ESP and multiaxial stresses obtained from Finite Element Analysis (FEA). A numerical simulation method of fretting fatigue crack growth is proposed based on linear elastic fracture mechanics and maximum hoop stress criterion. From the simulated crack growth results, the function relationship between fretting fatigue propagation life and crack length was established, and the fretting fatigue propagation life was determined by the crack length at failure. The results show that the crack growth trajectory predicted by the simulation correlates well with that in a tested Ti-6Al-4V dovetail component-both have a crack kink angle of 18°. The estimated fretting fatigue total life (nucleation + propagation) of a dovetail under different fretting conditions by using the proposed numerical method matches well with test results, as the predicted total life is within 2 times of error range. Maximum tensile load has significant influence on crack nucleation and propagation life, and under the same stress ratio, the fretting fatigue total life of the Ti-6Al-4V dovetail attachment reduces one order of magnitude as the maximum tensile load increases from 18 kN to 24 kN.
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