某发动机一级压气机叶片抗鸟撞数值模拟

基于PAM．CRASH显式碰撞分析软件，建立了鸟撞发动机一级压气机叶片全尺寸有限元计算模型。计算分析了真实工况下鸟撞发动机叶片不同部位时鸟体及叶片的变形过程和动态响应。计算结果表明，鸟体被叶片切碎的大小及叶片变形程度与鸟体撞击叶片部位有关，鸟体撞击叶片根部时鸟体大部分从叶盘下通过，叶梢位移较小而叶根等效应力较大，导致叶片从根部发生断裂的可能性较大；撞击中部时，整个鸟体被叶片切碎后沿着叶片缝隙穿过，叶梢位移和叶根等效应力处于中等水平，对叶片损害不大；撞击梢部时，叶根等效应力很小，但叶梢位移很大，相临叶片发生撞击可能使发动机无法正常工作。

Numerical simulation of bird striking on blades of an engine primary compressor

Based on the explicit impact analysis software PAM-CRASH, the full scale finite element calculation model of bird striking on blades of an engine primary compressor was established. The process of deformation and dynamic response of the bird and blades were calculated when the bird impacting on different site of the engine compressor under the normal working condition of the engine. The calculating results indicated that the scale size of disintegrated bird by blades and the deformation stage were related with the site of blade that was impacted by bird. When the bird impacting on root site of the blade, most of the bird bodies passed through the underneath disc of the compressor and only just a few was disintegrated by blades, the displacement on tip site of blades is inferior but the stresses on root site of blades is major, so it is easier that the blade break on the root. All of the＇bird body was disintegrated and passed through the gap of blades as the bird impacting on middle site of the blade, the displacement on the tip of blades and thestresses on root site of blades are medium and the damage of the blade is lightness. While the bird impacting with the tip site of the blade, the stresses on root site of blades is very small but the displacement on tip of blades is great, this may lead to the impacting between two adjacent blades and the engine can＇t work normally.