压气机动应力测试的叶-盘耦合分析方法  

A Blade-disc Coupling Analysis Method for Dynamic Stress Test of Compressor

作　　者：王斌 张奇 农斌 洪广洋 李健[2] WANG Bin;ZHANG Qi;NONG Bin;HONG Guang-yang;LI Jian(AECC South Industry Company Limited,Zhuzhou 412002,China;College of Sciences,Northeastern University,Shenyang 110004,China)

机构地区：[1]中国航发南方工业有限公司,株洲412002 [2]东北大学理学院,沈阳110004

出　　处：《科学技术与工程》2022年第27期12217-12222,共6页Science Technology and Engineering

基　　金：中国航发南方工业有限公司科研项目(K20275)。

摘　　要：为评估发动机压气机转子叶片的振动特性和工作可靠性,基于循环对称结构模态分析基本理论,建立了大叶片在轮盘装配条件下的耦合振动特性分析方法。以压气机某级为研究对象通过循环对称建立叶-盘耦合结构有限元模型,得到叶-盘系统在静态和工作转速下的模态及应力分布,并通过与实验结果的对比验证了该方法的可靠性。利用Campbell图确定了叶片的危险转速,并评估特定转速下系统频率裕度,为压气机工作叶片动应力测量提供数值仿真技术支撑。Based on the modal analysis theory of cyclic symmetric structure, the method for analyzing coupled vibration characteristics of large blades under the wheel assembly condition was established to evaluate the vibration characteristics and working reliability of the compressor rotor blades. A compressor stage was selected as the research object and the finite element model of blade-disc coupling structure was established by cyclic symmetry. The modal and stress distribution of the blade-disc system under static and working speeds were obtained. The reliability of the proposed method was verified by comparing with the experimental results. The dangerous rotational speed of the blade was determined using Campbell diagram, and the frequency margin of the system was evaluated at specific rotational speed, which provided numerical simulation technology support for the dynamic stress measurement of the compressor working blade.

关 键 词：叶-盘结构 共振分析 循环对称结构 有限元分析 动应力测试 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]