叶片安装角对叶盘结构受迫响应特性的影响  

Effect of blade stagger angle on forced response of bladed disk assemblies

作　　者：兰海强[1] 臧朝平[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2012年第11期2547-2552,共6页Journal of Aerospace Power

基　　金：江苏省高校优势学科建设工程(PADA);教育部博士点基金(20093218110008);国家自然科学基金(51175244)

摘　　要：利用简化的叶盘结构有限元模型和基于极值原理的改进Monte Carlo模拟技术,详细分析了叶片安装角失谐对叶盘结构受迫响应特性的影响.分别对6种不同安装角误差的叶盘结构的受迫响应进行了数值计算,得到了各自对应的响应放大因子概率密度曲线,通过曲线比较,分析了叶片安装角误差对叶盘结构受迫响应特性的影响规律.研究表明:安装角误差虽对叶盘结构的固有频率影响较小,但对叶片受迫响应影响是很大的,并且受迫响应幅值放大因子随安装角失谐程度增加而增加.Using simplified finite element model and the accelerated Monte Carlo simula- tion based on extremum principle, the forced response characteristics of bladed disks with stagger angle mistuning were investigated in detail. Six different variations of stagger angle error were simulated and corresponding probability density functions of response magnifica- tion factors were calculated separately. By comparing different curves, effect regularity of bladed stagger angle on the forced response of bladed disk assemblies was explored. Results indicate that stagger angle mistuning has small effect natural frequencies, but has a great effect on the blade response. The forced response would increase when stagger angle mis- tuning strength increases.

关 键 词：安装角 叶盘结构 失谐 MONTE CARLO模拟 受迫响应 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]