基于多分辨率SPH-FEM耦合方法的鸟撞问题数值模拟  

Numerical simulation of bird strike based on multi-resolution SPH-FEM coupling method

作　　者：马明瑞 陈福振 严红[1,2] 刘凡 MA Mingrui;CHEN Fuzhen;YAN Hong;LIU Fan(School of Power and Energy,Northwestern Polytechnical University,Xi’an710129,China;Yangtze River Delta Research Institute of NPU,Northwestern Polytechnical University,Taicang215400,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]西北工业大学太仓长三角研究院,太仓215400

出　　处：《航空学报》2024年第21期245-265,共21页Acta Aeronautica et Astronautica Sinica

基　　金：陕西省重点研发计划(2022SF-151);太仓市科技计划(TC2022JC10)。

摘　　要：本文针对航空发动机风扇叶片鸟撞问题的数值模拟方法研究,提出了一种考虑有限单元自适应生成的多分辨率SPH-FEM耦合方法。首先,新方法通过在FEM单元内部插值点处设置一组背景粒子,克服了传统SPH-FEM耦合方法在耦合界面处对模型离散尺度的一致性要求;其次,新方法在传统有限元算法的基础上加入单元自适应生成算法和无反射边界条件,将计算过程中对模型所有单元的求解转变为对关键区域的部分单元进行求解,降低了计算成本。文章应用所建立的新耦合方法开展了多结构鸟体撞击航空发动机风扇叶片的数值模拟研究,分析了撞击的动态响应,揭示了叶片受鸟撞过程的损伤机理,对航空发动机风扇叶片抗鸟撞设计和提高飞行安全性具有重要意义。To study the problem of bird strike on aero-engine fan blades,this paper proposes a multi-resolution SPHFEM coupling method considering adaptive generation of finite elements.Firstly,by setting a group of background particles at the interpolation points inside the FEM elements,the new method overcame the problem of consistency requirement of model discrete scale at the coupling interface in the traditional SPH-FEM coupling method.Secondly,by adding an element adaptive generation algorithm and applying the non-reflecting boundary condition,the new method changed the calculation range from all elements to elements at critical areas,reducing computational costs.Using this new coupling method,this study conducted numerical simulations of bird strikes on areo-engine fan blades,analyzed the dynamic response during the impact process,and revealed the damage mechanisms of fan blades under the condition of bird strikes.It is of important significance for the design of bird strike resistance for aero-engine fan blades and the improvement of flight safety.

关 键 词：航空发动机 风扇叶片 SPH-FEM 鸟撞 飞行安全 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程] O347[理学—固体力学] O316[理学—力学]