A fretting fatigue total life prediction method for dovetail attachment

被引：0
|
作者：
Xu K. [1 ]
Li W. [1 ]
Huang Y. [2 ]
Yu Q. [3 ]
Ma G. [3 ]
Hu W. [1 ]
机构：
[1] Aero Engine Academy of China, Beijing
[2] School of Aeronautic Science and Engineering, Beihang University, Beijing
[3] AVIC Manufacturing Technology Institute, Beijing
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2020年 / 46卷 / 10期
基金：
中国国家自然科学基金;
关键词：
Aero-engine; Dovetail attachment; Fretting damage; Fretting fatigue; Life prediction;
D O I：
10.13700/j.bh.1001-5965.2019.0471
中图分类号：
学科分类号：
摘要：
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. © 2020, Editorial Board of JBUAA. All right reserved.
引用
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页码：1890 / 1898
页数：8
相关论文
共 20 条
  • [1] WATERHOUSE R B., Fretting fatigue, (1981)
  • [2] NOWELL D, DINI D, HILLS D A., Recent developments in the understanding of fretting fatigue, Engineering Fracture Mechanics, 73, 2, pp. 207-222, (2006)
  • [3] YU S R, WANG J L, LI S X, Et al., Study on the initiation and propagation of fretting fatigue crack on the Ti-6Al-4V alloy dovetail joint, China Mechanical Engineering, 26, 24, pp. 3386-3390, (2015)
  • [4] GOLDEN P J, NICHOLAS T., The effect of angle on dovetail fretting experiments in Ti-6Al-4V, Fatigue & Fracture of Engineering Materials & Structures, 28, 12, pp. 1169-1175, (2005)
  • [5] GOLDEN P J., Development of a dovetail fretting fatigue fixture for turbine engine materials, International Journal of Fatigue, 31, 4, pp. 620-628, (2009)
  • [6] GOLDEN P J, CALCATERRA J R., A fracture mechanics life prediction methodology applied to dovetail fretting, Tribology International, 39, 10, pp. 1172-1180, (2006)
  • [7] SHI L, WEI D S, WANG Y R, Et al., An investigation of fretting fatigue in a circular arc dovetail assembly, International Journal of Fatigue, 82, 2, pp. 226-237, (2016)
  • [8] MANGARDICH D, ABRARI F, FAWAZ Z., A fracture mechanics based approach for the fretting fatigue of aircraft engine fan dovetail attachments, International Journal of Fatigue, 129, 12, (2019)
  • [9] WEI D S, WANG Y R., Analysis of fretting fatigue life of dovetail assemblies based on fracture mechanics method, Engineering Failure Analysis, 25, pp. 144-155, (2012)
  • [10] WEI D S, SHI L, WANG Y R., Cyclic plastic behavior of dovetail under fretting load, Engineering Failure Analysis, 55, pp. 100-114, (2015)
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