Fatigue failure analysis of titanium alloy TC17 for aircraft engine

被引：0

作者：

Wang J. ^{[1
]}

Gao S. ^{[2
]}

Yang Y. ^{[1
]}

Du F. ^{[1
]}

Yu J. ^{[1
]}

Wang J. ^{[1
]}

机构：

[1] Dalian Maritime University, Marine Engineering College, Dalian

[2] Dalian Scientific Test and Control Technology Institute, Dalian

来源：

Wang, Jinlong (wjl19890806@dlmu.edu.cn) | 1600年 / Editorial Board of Journal of Harbin Engineering卷 / 42期

关键词：

Fatigue strength; Fatigue test; Fracture analysis; Life prediction; Stress intensity factor; Surface failure; Surface roughness; Titanium alloy TC17;

D O I：

10.11990/jheu.202003037

中图分类号：

学科分类号：

摘要：

A suitable fatigue life prediction model is established for titanium alloy TC17 to study its fatigue failure mechanism. Ultrasonic fatigue tests of titanium alloy TC17 with different stress amplitudes are performed, and the surface morphologies of specimens are quantitatively measured by a profilometer, from which the fatigue limit of TC17 is obtained to be 615 MPa. The stress-life (S-N) curve of titanium alloy TC17 under ultra-high frequency loading is proposed using the classical two-parameter model (Basquin model) and the fatigue test results of titanium alloy TC17. The fracture morphologies of specimens are observed using scanning electron microscopy, and the influences of surface roughness on the HCF and VHCF failure mechanisms of titanium alloy TC17 and degradation of fatigue performance are analyzed. The results indicate that surface roughness is the main cause of fatigue failure of titanium alloy TC17. This work has positive significance for the maintenance and life prediction of titanium alloy TC17 parts. © 2021, Editorial Department of Journal of HEU. All right reserved.

引用

页码：1203 / 1208

页数：5

共 14 条

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