FGH96高温变幅疲劳载荷试验及损伤累积模型研究  

High temperature variable amplitude fatigue loading test and damage accumulation modeling of FGH96

作　　者：姜仁杰 杨晓光[1] 黄佳[2] 程穆威 石多奇[1] JIANG Renjie;YANG Xiaoguang;HUANG Jia;CHENG Muwei;SHI Duoqi(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Research Institute of Aerospace Technology,Central South University,Changsha 410083,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中南大学航空航天技术研究院,湖南长沙410083

出　　处：《推进技术》2024年第8期207-215,共9页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅳ-0017-0085);国家自然科学基金(12172021,52205177);湖南省自然科学基金(2021JJ40741)。

摘　　要：针对涡轮盘用镍基高温合金FGH96,开展两级疲劳载荷试验以及谱载荷试验。试验载荷设计参考了涡轮盘关键点载荷及实测飞行任务谱特征。采用常见损伤累积模型对试验结果进行分析。结果显示,FGH96在低-高载荷次序下循环分数和大于1,在高-低载荷次序下循环分数和小于1,符合常见非线性疲劳损伤累积模型的预期;对于谱载荷的疲劳寿命,由Chaboche非线性疲劳损伤模型与时间分数模型组成的损伤累积模型的预测则偏保守,且具有较高的预测精度,预测结果均在2倍偏差带内。The investigated material is nickel-based alloy FGH96 used for turbine discs.Firstly,two-level fatigue loading test and spectrum loading tests were conducted.The test loads refer to the turbine disc critical point loads and the measured flight mission spectrum characteristics.Then the test results were analyzed using common damage accumulation models.The results show that FGH96 has a cyclic fraction sum greater than 1 in the low-high loading sequence and less than 1 in the high-low loading sequence,which is in accordance with the expectation of common nonlinear fatigue damage accumulation models.For the fatigue life of the spectrum load⁃ing,the prediction of the damage accumulation model consisting of the Chaboche nonlinear fatigue damage model and the time fraction model is conservative and has a high prediction accuracy,with all the predictions within the 2-fold deviation band.

关 键 词：镍基高温合金 损伤累积模型 变幅疲劳载荷 次序效应 谱载荷 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程] TG132.3[一般工业技术—材料科学与工程]