摘要
外物损伤严重影响航空发动机风扇/压气机叶片的使用寿命,其冲击参数对残余应力分布的影响是重要的研究方向。为探究冲击参数对模拟叶片损伤的影响,根据空气炮试验系统对模拟叶片的冲击情况,使用有限元方法对TC4钛合金模拟叶片进行了外物损伤数值模拟;分析了不同冲击参数下模拟叶片的残余应力分布;得到了冲击角度、冲击速度以及冲击小球直径对模拟叶片损伤的影响规律。通过将数值模拟结果与空气炮试验结果进行对比,发现损伤深度的最大误差为30.2%,表明了本文模拟方法的有效性。研究结果可为压气机叶片结构损伤容限设计提供依据。
For aero-engine fan/compressor blades, the inhalation of hard foreign objects will cause local impact damage and large residual stress on blades, which will seriously affect the service life of blades. In order to explore the influence of impact parameters on the simulated blade damages, according to the results of the air cannon tests, the numerical simulations of FOD were performed on the TC4 titanium alloy simulated blades. The residual stress distributions of the simulated blades under different impact parameters were analyzed, and the influence laws of impact angle, velocity and ball diameter on simulated blade damages were obtained. Compared with the test results, the maximum error of the simulated notch depth is 30.2%,which shows the effectiveness of the numerical simulation method and can provide a basis for the damage tolerance design of the compressor blade.
作者
张克瑶
杨雅丽
孙阳
黄永芳
陈立杰
ZHANG Ke-yao;YANG Ya-li;SUN Yang;HUANG Yong-fang;CHEN Li-jie(School of Aerospace Engineering,Xiamen University,Xiamen 361005,China)
出处
《燃气涡轮试验与研究》
2022年第2期41-46,共6页
Gas Turbine Experiment and Research
基金
国家自然科学基金(51475396)
航空发动机高空模拟技术重点实验室基金(SYS2015006)。
关键词
航空发动机
外物损伤
模拟叶片
有限元方法
残余应力
数值模拟
aero-engine
foreign object damage
simulated blade
finite element method
residual stress
numerical simulation
