压气机转子错频叶盘结构振动响应分析  

Vibration Response Analysis on Mistuned Bladed Disk Assembly of Compressor Rotors

作　　者：徐可宁 王延荣[2] 刘金龙 

机构地区：[1]中航空天发动机研究院有限公司,北京100028 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《燃气涡轮试验与研究》2013年第3期6-11,5,共7页Gas Turbine Experiment and Research

摘　　要：利用三维叶轮机械气动弹性分析软件AEAS,对某压气机转子错频叶盘结构进行了振动响应分析,比较了各计算参数、错频量对数值仿真精度和效率的影响。结果表明,谐响应分析和瞬态响应分析,可得到错频叶盘结构各叶片的瞬态位移或动应力响应,进而获得各叶片的位移放大因子。通过研究错频对叶盘结构振动响应的影响,可指导错频叶盘的结构设计,并为降低由失谐导致的航空发动机叶盘结构高循环疲劳失效提供依据。The vibration response analysis has been performed for a mistuned bladed disk assembly using an aeroelastic analysis software AEAS, and the influence of different computational parameters and mistun?ing magnitude on the numerical simulation efficiency and accuracy were compared. The calculation results indicated that the transient displacement or dynamic stress response of mistuned bladed disk assembly can be obtained with harmonic response analysis and transient response analysis, and then the displacement am?plification factor of each blade can be calculated. The research on the influence of mistuning can be used to guide the design of mistuned bladed disk assembly, thus to minimize the risk of HCF failures caused by mis?tuning.

关 键 词：航空发动机 压气机转子 错频叶盘 谐响应 强迫振动响应 有限单元法 

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]