Fu Xi, Zhang Lina, Yang Wenzhao, Yin Zhaoming, Zhou Jiakang, Wang Hongwei
School of Machinery and Automation, Weifang University, Weifang 261061, China.
Department of Mechanical Engineering, Hebei University of Water Resources and Electric Engineering, Changzhou 061001, China.
Materials (Basel). 2025 Jul 17;18(14):3354. doi: 10.3390/ma18143354.
The Ti-6Al-4V alloy is a typical α + β type titanium alloy and is widely used in the manufacture of aero-engine fans, compressor discs and blades. The working life of modern aero-engine components is usually required to reach more than 10 cycles, which makes the infinite life design based on the traditional fatigue limit unsafe. In this study, through symmetrical loading high-cycle fatigue tests on Ti-6Al-4V titanium alloy, a nonlinear cumulative damage life prediction model was established. Further very-high-cycle fatigue tests of titanium alloys were carried out. The variation law of plastic strain energy in the evolution process of very-high-cycle fatigue damage of titanium alloy materials was described by introducing the internal stress parameter. A prediction model for the very-high-cycle fatigue life of titanium alloys was established, and the sensitivity analysis of model parameters was carried out. The results show that the established high-cycle/very-high-cycle fatigue models can fit the test data well. Moreover, based on the optimized model parameters through sensitivity analysis, the average error of the prediction results has decreased from 59% to 38%. The research aims to provide a model or method for predicting the engineering life of titanium alloys in the high-cycle/very-high-cycle range.
Ti-6Al-4V合金是一种典型的α+β型钛合金，广泛应用于航空发动机风扇、压气机盘和叶片的制造。现代航空发动机部件的工作寿命通常要求达到10次以上循环，这使得基于传统疲劳极限的无限寿命设计不安全。在本研究中，通过对Ti-6Al-4V钛合金进行对称加载高周疲劳试验，建立了非线性累积损伤寿命预测模型。进一步开展了钛合金的超高周疲劳试验。通过引入内应力参数，描述了钛合金材料超高周疲劳损伤演化过程中塑性应变能的变化规律。建立了钛合金超高周疲劳寿命预测模型，并进行了模型参数的敏感性分析。结果表明，所建立的高周/超高周疲劳模型能很好地拟合试验数据。此外，基于通过敏感性分析优化后的模型参数，预测结果的平均误差从59%降至38%。该研究旨在提供一种预测钛合金在高周/超高周范围内工程寿命的模型或方法。
