薄靶板受叶片形弹体撞击的数值仿真研究  

NUMERICAL SIMULATION OF A THIN PLATE IMPACTED BY BLADE PROJECTILE

作　　者：何庆[1] 宣海军[1] 廖连芳[2] 洪伟荣[1] 吴荣仁[1] 

机构地区：[1]浙江大学化工机械研究所高速旋转机械实验室,杭州310027 [2]中国航空工业集团公司沈阳发动机设计研究所,沈阳110015

出　　处：《工程力学》2010年第4期234-239,共6页Engineering Mechanics

基　　金：航空推进技术验证计划项目(APTD-1104-03)

摘　　要：为研究航空发动机薄壁机匣包容高速飞断平板条叶片的能力,数值模拟了平板条叶片以不同偏航角和初始速度垂直撞击矩形靶板的过程。数值仿真采用Johnson-Cook本构模型和失效准则以考虑应变率、应力三轴度和温度对材料性能的影响,分析了叶片形弹体的偏航角和初始速度对弹体和靶板变形、失效模式及能量损耗过程的影响。结果表明:随着偏航角的增大,靶板的主要失效模式从绝热剪切带破坏过渡到撕裂破坏,破坏及变形区域增大,弹道极限速度提高;平板条的主要变形则为撞击头部的镦粗过渡到整体的弯曲。研究结果对于揭示机匣受断叶冲击破坏机理和改善叶片包容能力设计方法具有指导意义。To study the aeroengine containment capability of the case for high-speed released blade, numerical simulations of the blade project impact thin plate with the variation of a yaw angle and an initial velocity are done. The constitutive material model and the fracture model criterion proposed by Johnson and Cook, which takes into account the effect of strain rate, stress triaxiality and temperature on the equivalent strain, are used in the numerical simulations. The effects of a yaw angle and an initial velocity on the deformations, failure patterns and faded energy changing of the blade and the plate are analyzed. It is shown that with the increase of the yaw angle, the main failure mode of the plate changes from adiabatic shear band to tearing, the failure area and ballistic limit velocity are also increased, and the deformation pattern of the blade plate changes from head upsetting to whole bending. The results could be referenced to further understand the damage mechanism of the released blade impact on the outside case, and to improve the design method for the blade containment in turbofan engine.

关 键 词：航空发动机 断叶片撞击 数值模拟 包容能力 偏航角 

分 类 号：O347.3[理学—固体力学] V231.91[理学—力学]