考虑沙尘颗粒冲蚀损伤的航空叶片寿命预估  

Life Prediction for the Aircraft Blade with Sand Particles Erosion Damage

作　　者：游文俊 梅威威 王计真 杨强[2] 詹志新 胡伟平[1] You Wenjun;Mei Weiwei;Wang Jizhen;Yang Qiang;Zhan Zhixin;Hu Weiping(Beihang University,Beijing 100191,China;Aviation Key Laboratory of Technology and Science on Structure Impact Dynamics,Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]北京航空航天大学,北京100191 [2]中国飞机强度研究所结构冲击动力学航空科技重点实验室,陕西西安710065

出　　处：《航空科学技术》2022年第8期68-77,共10页Aeronautical Science & Technology

基　　金：航空科学基金(20200041051001)。

摘　　要：在沙漠环境下,当航空发动机叶片和直升机桨叶在高速运行时,会吸入沙尘微粒使其撞击在发动机叶片或其他部位,造成冲蚀损伤。在循环载荷的作用下,冲蚀坑处往往形成疲劳源,会对材料的疲劳特性造成很大影响。本文基于连续损伤力学理论,建立了考虑沙尘颗粒冲蚀损伤钛合金叶片的疲劳寿命预测方法。首先,基于有限元显式计算,模拟沙尘颗粒冲击钛合金叶片,分析了冲蚀坑、残余应力、残余应变以及初始塑性损伤;其次,推导了疲劳损伤模型,以及相应的损伤力学数值算法;再次,编写VUMAT子程序,采用数值解法,对含冲蚀损伤的钛合金叶片进行寿命预估,最后,深入分析了不同冲蚀情况下,钛合金叶片的疲劳损伤及疲劳寿命。计算结果表明,冲击速度越大,轴向残余应力越大,材料的损伤速率越快;冲击角度越大,冲击凹坑深度越浅,叶片的疲劳寿命越高。该研究为发动机叶片在沙尘颗粒冲蚀影响下的疲劳损伤评定提供一种可行方法。In desert environment,when the aircraft engine blade and helicopter blade are running at a high speed,the dust particles could be inhaled and then hit the aircraft engine blade or other parts,which leads to the erosion damage.Under cyclic loadings,the fatigue source often occurs around the erosion crater,thus greatly affecting the fatigue properties of materials.In this study,the approach for fatigue life prediction of titanium alloy blades with erosion damage is established based on the continuous damage mechanics.Firstly,the formulation of erosion crater by the impact of dust particle is simulated according to the explicit finite element computation.Secondly,the fatigue damage model is derived,and the corresponding damage mechanics finite element numerical solution is implemented.After that,the VUMAT subroutine is completed to predict the fatigue life of titanium alloy blades with erosion damage.Finally,the fatigue damage and fatigue life of titanium alloy blades under different erosion conditions are further analyzed.The results show that the greater the impact velocity,the greater the axial residual stress and the faster the damage rate of the material.Furthermore,the greater the impact angle,the shallower the impact pit depth,and the higher the fatigue life of the blade.This study provides a feasible method for the fatigue damage evaluation of engine blades under the influence of sand and dust particle erosion.

关 键 词：冲蚀损伤 疲劳损伤 寿命预估 发动机叶片 数值模拟 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]