航空发动机

金峰1 ，刘璐璐 1 ，朱信颖 1 ，罗刚2 ，赵振华 2 ，陈伟1.钛合金包边复合材料风扇叶片的鸟撞数值仿真[J].航空发动机,2024,50(4):107-113

钛合金包边复合材料风扇叶片的鸟撞数值仿真

Numerical Simulation on Bird Impact of Composite Fan Blade with Titanium Leading Edge

DOI：

英文关键词:omposite materials fan blade titanium leading edge bird impact numerical simulation aeroengine

基金项目:国家级研究项目、中央高校基本科研业务费专项资金（NC2022001）资助

作者	单位
金峰1 ，刘璐璐 1 ，朱信颖 1 ，罗刚2 ，赵振华 2 ，陈伟1	1.南京航空航天大学能源与动力学院， 2.机械结构力学及控制国家重点实验室：南京210016

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中文摘要:

为降低鸟体撞击航空发动机中带钛合金包边树脂基复合材料风扇叶片的试验成本，开展了数值仿真研究，为钛合金包边在航空发动机风扇叶片上的应用提供参考和依据。对风扇叶片进行简化，采用ABAQUS有限元软件构建了鸟撞带钛合金包边和不带钛合金包边的风扇叶片模型，其中，钛合金包边和复合材料叶片之间用粘结界面单元进行粘接，研究了不同鸟体冲击角度和速度下2种风扇叶片的损伤。结果表明：在鸟体冲击速度相同时，随着冲击角度的增大，风扇叶片的损伤增大且能量吸收率提高，在冲击角度也相同时，带钛合金包边的风扇叶片损伤更小且能量吸收率更高；在鸟体冲击角度相同时，随着冲击速度的加快，风扇叶片的损伤增大且能量吸收率提高；在鸟体冲击下，粘结界面单元最终发生拉伸破坏，在低速度冲击下还会发生剪切损伤。

英文摘要:

To reduce the test cost of bird strikes on aeroengine fan blades made of resin-based composite materials with titanium lead? ing edge， a numerical simulation study was conducted to provide a reference and basis for applications of titanium leading edge on fan blades. The fan blades were simplified， and bird impact models with and without titanium leading edges were constructed using ABAQUS finite element software. The titanium leading edges and composite material blades were bonded using adhesive interface elements， and the damages to the two types of fan blades under different bird impact angles and speeds were studied. The results showed that， at the same bird impact speed， the damage to the fan blades increases and the energy absorption rate improves with the increase of impact angle. When the impact angle is also the same， the fan blades with titanium leading edges have less damage and higher energy absorption rates. Similarly， at the same bird impact angle， the increase of impact speed leads to more damage to the fan blades and higher energy absorption rates. Under bird impact， the adhesive interface elements undergo tensile failure， and shear damage can also occur under low-speed impact.

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