复杂载荷作用下压气机叶片疲劳寿命数值分析  

Numerical Analyses on Fatigue Life for Compressor Blades under Complex Loads

作　　者：张俊红[1] 刘萌[1] 付曦[1] 寇海军 林建生[1] 

机构地区：[1]天津大学内燃机燃烧学国家重点实验室,天津300072

出　　处：《中国机械工程》2017年第12期1442-1448,1467,共8页China Mechanical Engineering

基　　金：高等学校博士学科点专项科研基金资助项目(20130032130005);天津市科技支撑计划资助重点项目(13ZCZDGX00200)

摘　　要：为提高叶片服役寿命,在计算叶片应力分布并预测其在复杂载荷作用下的疲劳寿命后,基于逆向工程建立了三种不同精度的叶片模型;考虑离心和气动载荷作用,求解压气机叶片复合载荷作用下的应力分布规律;通过叶片模拟件疲劳试验,确定TC4钛合金疲劳极限,拟合寿命模型参数;利用非线性连续损伤力学模型预测叶片在典型工况下的疲劳寿命。结果表明:不同模型的应力及寿命计算值存在一定差异,开展叶片数值分析时,需考虑计算模型还原叶片几何特征的精度对计算结果的影响。In order to improve service life of blades, three blade models were built based on re- verse engineering to calculate stress distribution and fatigue life of blades under complex loadings. Considering the influence of centrifugal loads and aerodynamic loads, stress distributions of compres- sor blades were solved under complex loads. Moreover, the fatigue limit and life prediction model pa- rameters were defined through the fatigue tests, and the fatigue life of compressor blades under the typical working conditions were predicted by nonlinear continuous damage model. Comparing the differences of stress values and fatigue life among three models, results show that the restoration de- gree of blade geometrical features for the calculation model must be considered when numerical calculations were carried out for blades with complex torsional characteristics.

关 键 词：航空发动机 压气机叶片 逆向建模 复杂载荷 疲劳寿命 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]