叶盘结构受迫振动响应特性和主动失谐技术实验研究  

A Successful Experimental Investigation on the Forced Response of Random and Intentional Mistuning Bladed Disks

作　　者：赵志彬[1] 贺尔铭[1] 陈熠[1] 张钊[1] 王红建[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《西北工业大学学报》2011年第6期892-897,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50775181);西北工业大学基础研究基金(JC20110237)资助

摘　　要：文章开展了失谐叶盘结构受迫振动响应特性及叶片主动失谐技术的实验研究。基于12叶片谐调叶盘结构的叶尖质量调节方法,分别实现了两组典型的叶片随机失谐形式和两组典型的叶片主动失谐形式,在叶片根部施加行波激振力,对随机失谐叶盘结构的受迫响应振动局部化进行了实验研究,并初步验证了叶片主动失谐技术对随机失谐的抑制能力;总结了失谐对叶盘结构受迫振动响应特性的影响规律,实验结果与有限元仿真结果吻合较好。Aim. The introduction of the full paper reviews a number of relevant papers in the open literature and then proposes the experimental investigation mentioned in the title, which we believe is successful and which is fully explained in sections 1 through 3. Their core consists of： The results of an experimental investigation on the effects of random blade mistuning on the forced response of bladed disks and intentional blade mistuning are repor- ted. By adding small blocks with different weights to the blade tips of a stationary, nominally periodic, 12-bladed disk, four typical mistuning bladed disks are presented for finite element simulations and experiments： two random blade mistuning specimens and two intentional blade mistuning specimens. All specimens are subjected to engine order excitation. The primary aim of this experiment is to demonstrate the occurrence of vibration localization in forced response due to random blade mistuning, and to verify two intentional blade mistuning specimens for the reduetion of blade amplitudes in forced response. ＂ The experimental results, presented in Figs. 4 through 8, and their analysis show preliminarily that they agree exceptionally well with the simulation results of finite element analysis, thus indicating that our experimental invesgation is indeed successful.

关 键 词：叶盘结构 随机失谐 振动局部化 振幅放大因子 主动失谐 

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]