改进的混合界面子结构模态综合法在失谐叶盘结构动态特性分析中的应用  

Application of Improved Hybrid Interface Substructural Component Modal Synthesis Method in Dynamic Characteristics Analysis of Mistuned Bladed Disk Assemblies

作　　者：白斌[1] 白广忱[1] 费成巍[1] 赵合阳[1] 童晓晨[2] 

机构地区：[1]北京航空航天大学能源与动力工程学院 [2]国家知识产权局专利局专利审查协作北京中心

出　　处：《机械工程学报》2015年第9期73-81,共9页Journal of Mechanical Engineering

基　　金：国家自然科学基金资助项目(51375032;51335003)

摘　　要：在保证精度的条件下，为了提高航空发动机动态特性分析的计算效率，针对传统混合界面子结构模态综合法（Hybrid interface substructural component modal synthesis method, HISCMSM）综合后还可能存在计算量大的问题，提出一种改进的HISCMSM。该方法将综合后的模型进一步减缩，建立了叶片＋轮盘的组合结构的参数化模型，对各个子结构建立有限元模型（Finite element model, FEM）并综合求其模态和振型。与整体结构有限元法相比，计算时间缩短23.86%～35.74%，模态偏差不大于0.49%，而传统法，其计算时间缩短14.63%～29.20%，模态偏差不超过0.57%，可见，该方法计算效率比传统法有显著提高，尤其是在高价模态求解时，计算效率提高的更加明显，同时分析了谐调与失谐叶盘结构模态位移、模态应力和模态应变能的分布，发现叶盘结构失谐后其对称性被破坏，出现了局部化现象，且随着失谐幅值的增大，振动逐渐向少数叶片集中，局部化现象越来越明显，为下一步的动态响应以及概率分析奠定了基础。In order to improve the computational efficiency of the dynamic characteristics analysis in the aeroengine with the computational accuracy, an improved hybrid interface substructural component modal synthesis method （HISCMSM） is proposed due to the problem of the large amount of calculation via the traditional HISCMSM when the substructures are assembled. The comprehensive model is further reduced by this method. The assembled structural parametric model of blades and disks is built by this method to establish each substructural finite element model （FEM） and the natural frequency and modal shape are obtalned. Compared with the overall structure FEM, the computational time and the modal deviation are respectively shortened by 23.86%-35.74%, 14.63%-29.20%and 0%-0.49%, 0%-0.57%via the improved method and the traditional method. So the improved method is much more efficient than the traditional method, especially in the high order modal solution which is much clear, meanwhile, modal displacement, modal stress and modal straln energy of the tuned and mistuned bladed disk assemblies are investigated, the symmetry of the tuned bladed disk assemblies is damaged and the localization phenomenon is observed which reinforces with the mistuned amplitude increasing. Gradually, the vibration is localized in a few blades and the phenomenon is getting more and more obvious, which can settle the foundation of the further research on dynamic response and the probability analysis of the mistuned bladed disk assemblies.

关 键 词：混合界面子结构模态综合法 航空发动机 失谐叶盘结构 有限元模型 计算效率 计算精度 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]