航空发动机整机静子建模与刚度验证  

Modeling and Validation of Stiffness Character for Whole Aeroengine Stator

作　　者：贾瑞琦[1] 曹茂国[1] 梁海涛[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2015年第6期74-80,共7页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：基于建立航空发动机整机状态的结构动力学分析有限元模型要求,对应用于静子机匣的不同有限元网格模型进行了对比分析,并将其组装成整机模型,进行了各支点的静柔度计算和对比试验。结果表明:对静子建模可分为主承力和其他机匣部件分别进行。承力机匣采用实体单元模型,有效模拟其刚度特性;传力机匣采用壳单元模型,在保证计算精度的前提下减小计算规模。通过对整机静子模型状态下轴承座静柔度计算与试验结果的对比,验证了整机静子模型刚度分布的有效性,经过质量修正后可以为整机状态结构动力学分析提供模型。Different types of Finite Element Model （FEM） mesh model for the typical aeroengine stators were studied under the requirement of state FEM for structural dynamic of whole engine. A whole engine model was established by assembling the major engine stator, and the static flexibility of fulcrums were calculated and compared. The analysis result shows that the eases can he classified into two types. For the bearing support structures, the solid element should be used for appropriate idealization of the stiffness characteristics. For other engine cases, the shell element should be used to reduce computing scale on the premise of guarantee calculation precision. The stiffness characteristics was validated by comparing numerical result to the static flexibility test which was carried out during engine design process, and the model can be used in the whole engine structural dynamic analysis after the aualitv correction.

关 键 词：静子有限元模型 静子刚度 柔度试验 模型验证 结构动力学 航空发动机 

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]