一种航空发动机整机振动模型支承刚度的辨识方法  

A support stiffness identification method for whole aero-engine vibration model

作　　者：屈美娇 陈果 QU Mei-jiao;CHEN Guo(College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学民航学院

出　　处：《振动工程学报》2019年第3期490-500,共11页Journal of Vibration Engineering

基　　金：国家自然科学基金面上项目(51675263);江苏省研究生培养创新工程项目(KYLX16_0387);南京航空航天大学博士学位论文创新创优基金资助项目(BCXJ17-10);航空发动机及燃气轮机重大专项基础研究项目(2017IV0080045)

摘　　要：提出了一种航空发动机整机振动模型支承刚度识别的方法。首先,建立航空发动机整机动力学模型,将支承刚度和安装节刚度视为待优化的连接刚度,然后通过有限元仿真计算,得到在不同连接刚度下各阶整机固有频率。以支持向量机构造从各支承刚度到各阶固有频率的回归函数。接下来,采用遗传算法进行目标优化,以整机真实固有频率(可通过模态试验获取)为基础,建立遗传算法适应度函数,利用实数编码,最终识别得到整机各处连接刚度。以带机匣的航空发动机转子试验器为算例进行方法验证,根据整机模态试验结果,进行了支承刚度和安装节刚度识别,结果表明了该方法的有效性。A method for aircraft engine vibration model support stiffness identification is proposed.Firstly,the dynamic model of the whole aero-engine is established,and the support and mounting stiffness parameters are taken as the connection stiffness parameters to be optimized.Secondly,the natural frequencies under different connection stiffness parameters are obtained through the finite element simulation,and the regression function from the stiffness to the natural frequency is constructed by the method of support vector machines.Then,the genetic algorithm is applied to the multi-objective optimization.Based on the real natural frequencies of the whole machine(which can be obtained by modal test),a fitness function of multi-objective optimization of genetic algorithm is established,and the real number encoding is used to finally accomplish the connection stiffness parameter identification.An aero-engine rotor tester with casing is taken as an example to verify the method.The support and mounting stiffness parameters of the whole tester are identified based on the results of the modal test,and the results show the effectiveness of the proposed method.

关 键 词：航空发动机 整机振动 模型修正 连接刚度 刚度辨识 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]