作者：张亮1, 李欣1, 袁惠群2
作者单位：1. 辽宁工业大学机械工程与自动化学院, 辽宁 锦州 121001;
2. 东北大学机械工程与自动化学院, 辽宁 沈阳 110819
关键词：模态测试;有限元法;失谐叶片;参数识别;弹性模量
摘要：
针对现有叶片失谐参数选择及识别方法存在的不足,提出一种基于模态测试与有限元法相结合的叶片失谐参数识别方法。以某压气机一级叶片为研究对象,通过模态测试获得叶片一阶弯曲固有频率。对叶片弹性模量引入扰动参数,采用弹性模量改变模拟叶片失谐。基于有限元法识别出与叶片模态测试一阶弯曲固有频率对应的失谐扰动参数与失谐弹性模量,采用拟合计算获得各叶片失谐参数。结果表明:叶片失谐弹性模量与一阶弯曲无量纲固有频率测试值之间为近似线性关系;该方法识别速度较快且准确度高,可广泛应用于航空发动机、燃气轮机、汽轮机叶片的失谐参数识别。
Mistuning parameter identification of blades based on modal testing and finite element method
ZHANG Liang1, LI Xin1, YUAN Huiqun2
1. Faculty of Mechanical Engineering and Automation, Liaoning University of Technology, Jinzhou 121001, China;
2. School of Mechanical Engineering and Automation, Northeastern University, Shenyang 110819, China
Abstract: To solve the deficiency in selection and identification of mistuning parameters at present, a new way has been proposed to identify the mistuning parameters based on both modal testing and finite element method. During the experiment, compressor blades were taken as research objects. The natural frequency for first-order bending of the blades was measured using the modal testing. Perturbation parameters were introduced to elastic modulus while the later were changed to stimulate the mistuning blades. The elastic modulus and perturbation parameters corresponding to the natural frequency described above were identified based on modal testing data. Ultimately, the mistuning parameters of all the blades were obtained via fitting calculation. The results show that the mistuning elastic modulus presents an approximate linear relationship with the natural frequency for dimensionless first-order bending. This method is fast and accurate and can be widely used to identify the mistuning parameters of aero-engine, gas turbine, steam turbine blades.
Keywords: modal testing;finite element method;mistuning blades;parameter identification;elastic modulus
2015, 41(11): 16-19 收稿日期: 2015-02-10;收到修改稿日期: 2015-04-13
基金项目: 国家自然科学基金项目(51275081);辽宁省教育厅科学研究一般项目(L2014246);辽宁工业大学教师科研启动基金(X201202)
作者简介: 张亮(1983-),男,副教授,博士,研究方向为机械振动、转子动力学。
参考文献
[1] 张亮,袁惠群,韩清凯,等. 基于微动滑移摩擦模型的失谐叶盘系统振动分析[J]. 振动工程学报,2012,25(3):289-293.
[2] 姚建尧,王建军,李其汉. 失谐叶盘结构鲁棒性能分析[J].航空动力学报,2010,25(7):1634-1639.
[3] 袁惠群,张亮,韩清凯,等. 基于蚁群算法的航空发动机失谐叶片减振排布优化分析[J]. 振动与冲击,2012,31(11):169-172.
[4] 王建军,于长波,李其汉. 错频叶盘结构振动模态局部化特性分析[J]. 航空动力学报,2009,24(4):788-792.
[5] 秦飞,陈立明. 失调叶片-轮盘系统耦合振动分析[J]. 北京工业大学学报,2007,33(2):126-128.
[6] Kim N E, Griffin J H. System identification in high modal density regions of bladed disks[C]//The 8th National Turbine Engine High Cycle Fatique Conference Monterey USA,2003.
[7] Feiner D M, Griffin J H. Mistuning identification of bladed disks using a fundamental mistuning model-Part I:Theory[J]. Journal of Turbomachinery,2004,126(1):150-158.
[8] Bladh R, Castanier M P, Pierre C. Reduced order modeling and vibration analysis of mistuned bladed disk assemblies with shrouds[J]. ASME J Eng Gas Turbines Power,1999(121):515-522.
[9] Mignolet M P, Rivas-Guerra A J, Delor J P. Identification of mistuning characteristics of bladed disks from free response data-Part I[J]. Journal of Engineering for Gas Turbines and Power,1999,123(2):395-403.
[10] 王帅,王建军,李其汉. 一种基于模态缩减技术的整体叶盘结构失谐设别方法[J]. 航空动力学报,2009,24(3):662-669.
[11] 张亮. 航空发动机叶片轮盘系统振动特性及多场耦合力学特性研究[D]. 沈阳:东北大学,2013.
[12] 中国航空材料手册[M]. 北京:中国标准出版社,2002:72-91.
