CAJ | 학술논문

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。
재보증정도적조건하，위료제고항공발동궤동태특성분석적계산효솔，침대전통혼합계면자결구모태종합법(Hybrid interface substructural component modal synthesis method, HISCMSM)종합후환가능존재계산량대적문제，제출일충개진적HISCMSM。해방법장종합후적모형진일보감축，건립료협편+륜반적조합결구적삼수화모형，대각개자결구건립유한원모형(Finite element model, FEM)병종합구기모태화진형。여정체결구유한원법상비，계산시간축단23.86%～35.74%，모태편차불대우0.49%，이전통법，기계산시간축단14.63%～29.20%，모태편차불초과0.57%，가견，해방법계산효솔비전통법유현저제고，우기시재고개모태구해시，계산효솔제고적경가명현，동시분석료해조여실해협반결구모태위이、모태응력화모태응변능적분포，발현협반결구실해후기대칭성피파배，출현료국부화현상，차수착실해폭치적증대，진동축점향소수협편집중，국부화현상월래월명현，위하일보적동태향응이급개솔분석전정료기출。
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.