带气膜孔的失谐整体叶盘的模态研究

Modal Analysis of Mistuned Bladed Disk Assemblies with Film Holes

在保证精度的条件下,为了提高航空发动机的计算效率与模拟的准确性,对经典混合界面子结构模态综合法(HISCMSM)进行改进,采用改进的HISCMSM建立了带气膜孔的失谐整体叶盘的有限元模型(FEM)并对其进行了模态分析,与高保真有限元模型方法(Finite element model method,FEMM)相比,相对误差≤0.79%,比整体高保真FEMM和经典的HICMSM计算效率分别提高31.01%～55.78%,0.89%～5.45%,研究中考虑了气膜孔的影响,发现气膜孔使得叶盘的模态频率降低,其中气膜孔的大小使得模态频率先减小后增大再减小,气膜孔的排列及角度的改变对叶盘模态频率的影响不大,而气膜孔数对其影响较大。为叶盘结构的设计提供了一定指导意义,为下一步的动力响应研究奠定了基础。

Under the guaranteeing the computational accuracy,to ensure the simulation is more in line with the real practical results and increase the calculation efficiency,the classical hybrid interface substructure component modal synthesis method(HISCMSM)is improved.The finite element model(FEM)of the mistuned bladed disk assemblies(MBDA)with film holes is built by this methodology and the modal is analyzed.Comparing with the high fidelity integral structure finite element model method(FEMM),the modal deviation is not more than 0.79%,but the computational time is shortened by 31.01%~55.78%,the computational efficiency is higher by 0.89%~5.45% than that via classical HICMSM.So the computational efficiency and the computational accuracy of this method are both superior to the classical HICMSM.The effect of the film holes on the modal is investigated,comparing with the solid MBDA,the modal is declined.Firstly the modal frequencies decrease after an increase with the increasing of size,and they almost do not alter with the arrangement and the angle changing,but they are impacted by the number of the film holes.The above investigations lay the foundation for the further study on the dynamic response of the MBDA and have a certain guiding significance for the design of the BDA.