外物冲击损伤对航空发动机风扇叶片影响研究  

Study on the Influence of Foreign Object Impact Damage on Aircraft Engine Fan Blades

作　　者：孙乐 张卓 张锴[1] 郑百林[1] 史同承 张刚 高德水 SUN Le;ZHANG Zhuo;ZHANG Kai;ZHENG Bailin;SHI Tongchen;ZHANG Gang;GAO Deshui(School of Aerospace Engineering and Applied Mechanics,Tongji University,Shanghai 200092,China;Design and Development Center,China National Aero Engine Corporation,Shanghai 201100,China;Chengdu Delivery Center,Beijing Aircraft Maintenance Engineering Co.,Chengdu 610201,Sichuan,China)

机构地区：[1]同济大学航空航天与力学学院,上海200092 [2]中国航发商用航空发动机有限责任公司设计研发中心,上海201100 [3]北京飞机维修工程有限公司成都交付中心,四川成都610201

出　　处：《力学季刊》2024年第1期99-109,共11页Chinese Quarterly of Mechanics

基　　金：上海市教育委员会联合创新计划项目(AR963)。

摘　　要：为研究外来物对航空发动机风扇叶片造成的损伤特征差异,以6 mm、10 mm、14 mm尺寸的304钢球作为冲击物,某型号退役航空发动机叶片作为靶板,通过轻气炮系统开展不同冲击位置处的外物损伤试验,并基于率相关本构模型构建了有限元模型,将基于仿真模型冲击响应后的FOD (Foreign Object Damage)损伤区域与试验损伤区域进行对比,两者在尺寸以及形状等方面取得了较高的一致性.之后利用构建的模型研究了冲击位置、角度以及小球尺寸对冲击响应过程中速度变化趋势的影响.结果表明,叶片不同位置处的抗冲击能力有很大区别,且小球尺寸对损伤区域具有决定性影响;此外还发现损伤模式不同时,小球剩余速度的变化趋势也不相同.In order to study the different damage characteristics of the aero-engine fan blades caused by the impact of foreign objects,a finite element model was constructed based on the rate-dependent constitutive model and impact tests were carried out through a light air cannon system to evaluate the damage caused by the foreign objects at different impact positions,using the 304 steel balls of 6 mm,10 mm and 14 mm sizes as the bullets and a retired aero-engine blade as the target plate.The FOD damage area based on the impact response of the simulation model was compared with the experimental damage area,and high consistency was achieved between the two results in terms of the area size and shape.After that,the effects of impact position,angle and bullet size on the velocity change trend during the impact response were investigated using the constructed model.The results show that the impact resistance of the blade differs greatly at different positions and the bullet size plays a decisive role on the damage area.In addition,the change trend of the remaining velocity of the bullet is different when the damage pattern is different.

关 键 词：轻气炮试验 损伤模式 FOD 冲击载荷仿真 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]