某级压气机叶盘系统失谐振动关键因素研究
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摘要
基于某级压气机叶片盘扇区,建立考虑非线性榫接触叶片盘有限元模型,应用提出的自由界面子结构-固定界面预应力模态综合超单元近似分析方法,并基于提出的围绕实验与有限元分析拟合出线性表达式的失谐参数识别方法,探究失谐关键因素对于叶盘系统振动的影响.结果表明,非线性榫接触不可忽略,提出的超单元法精度达到3.07%,满足要求.同时也表明,叶片平均频率、叶盘刚度比与频率转向对于失谐叶盘系统振动幅值、共振频率及应变能等参数均有一定影响.
Based on the blade disk basic sector of certain stage compressor,blade disk finite element model considering non-linear tenon contact was established,free-interface substructure-fixed interface prestressed modal synthesis super element approximate analysis method was proposed,meanwhile,mistuned parameters recognition method of linear expression was fitted based on the blade static-frequency test and dichotomy combined with finite element analysis,exploring the effects of mistuning key factors on blade disk vibration.Results show that the non-linear tenon contact cannot be neglected,and the accuracy of super element method is 3.07%,so the proposed method meets the requirement.In addition,blades mean frequency,disk stiffness ratio and frequency veering have an effect on mistuned bladed disks vibration amplitude,resonance frequency and strain energy and other parameters.
Based on the blade disk basic sector of certain stage compressor,blade disk finite element model considering non-linear tenon contact was established,free-interface substructure-fixed interface prestressed modal synthesis super element approximate analysis method was proposed,meanwhile,mistuned parameters recognition method of linear expression was fitted based on the blade static-frequency test and dichotomy combined with finite element analysis,exploring the effects of mistuning key factors on blade disk vibration.Results show that the non-linear tenon contact cannot be neglected,and the accuracy of super element method is 3.07%,so the proposed method meets the requirement.In addition,blades mean frequency,disk stiffness ratio and frequency veering have an effect on mistuned bladed disks vibration amplitude,resonance frequency and strain energy and other parameters.
引文
[1]Ewins D J,Imregun M.Vibration modes of packeted bladed disks[J].Journal of Vibration,Acoustics,Stress and Reliability in Design,1984,106(2):175-180.
[2]Wei S T,Pierre C.Localization phenomena in mistuned assemblies with cyclic symmetry:Part 2forced vibrations[J].Journal of Vibration,Acoustics,Stress and Reliability in Design,1988,110(4):439-449.
[3]Pierrre C,Murthy D V.Aeroelastic modal characteristics of mistuned blade assemblies:mode localization and loss of eigenstructure[J].AIAA Journal,1992,30(10):2483-2496.
[4]Ottarsson G,Pierre C.A Transfer matrix approach to free vibration localization in mistuned bladed assemblies[J].Journal of Sound and Vibration,1996,197(5):589-618.
[5]Petrov E P,Ewins D J.Analysis of the worst mistuning patterns in bladed disk assemblies[J].Journal of Turbomachinery,2003,125(4):623-631.
[6]Petrov E P,Sanliturk K Y,Ewins D.J.A new method for dynamic analysis of mistuned bladed disks based on exact relationship between tuned and mistuned systems[J].Journal of Engineering for Gas Turbines and Power,2002,122(3):586-597.
[7]Petrov E P,Sayma A I.Forced response variation of aerodynamically and structurally mistuned turbo-machinery rotors[R].ASME Paper GT2006-90948,2006.
[8]Sever I A,Petrov E P,Ewins D J.Experimental and numerical investigation of rotating bladed disk forced response using underplatform friction dampers[J].Journal of Engineering for Gas Turbines and Power,2008,130(4):042503.1-042503.11.
[9]Nikolic M,Petrov E P,Ewins D J.Robust strategies for forced response reduction of bladed disks based on large mistuning concept[J].Journal of Engineering for Gas Turbines and Power,2008,130(2):022501.1-022501.11.
[10]Petrov E P.Reduction of forced response levels for bladed discs by mistuning:overview of the phenomenon[R].ASME Paper GT2010-23299,2010.
[11]Petrov E P.A method for forced response analysis of mistuned bladed disks with aerodynamic effects included[J].Journal of Engineering for Gas Turbines and Power,2010,132(6):062502.1-062502.10.
[12]Castanier M P,Pierre C.Modeling and analysis of mistuned bladed disk vibration:status and emerging directions[J].Journal of Propulsion and Power,2006,22(2):384-396.
[13]廖海涛,王建军,李其汉.随机失谐叶盘结构失谐特性分析[J].航空动力学报,2010,25(1):160-168.LIAO Haitao,WANG Jianjun,LI Qihan.Mistuning characteristics analysis of mistuned bladed disk assemblies[J].Journal of Aerospace Power,2010,25(1):160-168.(in Chinese)
[14]白斌,白广忱,童晓晨,等.整体叶盘结构失谐振动的国内外研究状况[J].航空动力学报,2014,29(1):91-103.BAI Bin,BAI Guangchen,TONG Xiaochen,et al.Research on vibration problem of integral mistuned balded disk assemblies at home and abroad[J].Journal of Aerospace Power,2014,29(1):91-103.(in Chinese)
[15]王红建,贺尔铭,余仕侠.具有干摩擦散乱失谐的叶盘受迫响应特性[J].航空动力学报,2006,21(4):711-715.WANG Hongjian,HE Erming,YU Shixia.Forced response characteristics of bladed disks with disordered dry friction[J].Journal of Aerospace Power,2006,21(4):711-715.(in Chinese)
[16]袁惠群,张亮.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.YUAN Huiqun,ZHANG Liang.Optimization of mistuning blades arrangement for vibration absorption in an aero-engine based on artificial ant colony algorithm[J].Journal of Vibration and Shock,2012,31(11):169-172.(in Chinese)
[17]袁惠群,杨少明.基于蚁群算法和模态局部化参数的失谐叶盘减振研究[J].东北大学学报(自然科学版),2010,31(11):1611-1614.YUAN Huiqun,YANG Shaoming.Vibration reduction of mistuned blade disc by ant colony algorithm and modal localization parameter[J].Journal of Northeastern University(Natural Science),2010,31(11):1611-1614.(in Chinese)
[18]袁惠群,张亮.航空发动机转子失谐叶片减振安装优化分析[J].振动、测试与诊断,2011,31(5):647-651.YUAN Huiqun,ZHANG Liang.Optimization analysis on mistuning blades of vibration absorption in aero-engine[J].Journal of Vibration,Measurement and Diagnosis,2011,31(5):647-651.(in Chinese)
[2]Wei S T,Pierre C.Localization phenomena in mistuned assemblies with cyclic symmetry:Part 2forced vibrations[J].Journal of Vibration,Acoustics,Stress and Reliability in Design,1988,110(4):439-449.
[3]Pierrre C,Murthy D V.Aeroelastic modal characteristics of mistuned blade assemblies:mode localization and loss of eigenstructure[J].AIAA Journal,1992,30(10):2483-2496.
[4]Ottarsson G,Pierre C.A Transfer matrix approach to free vibration localization in mistuned bladed assemblies[J].Journal of Sound and Vibration,1996,197(5):589-618.
[5]Petrov E P,Ewins D J.Analysis of the worst mistuning patterns in bladed disk assemblies[J].Journal of Turbomachinery,2003,125(4):623-631.
[6]Petrov E P,Sanliturk K Y,Ewins D.J.A new method for dynamic analysis of mistuned bladed disks based on exact relationship between tuned and mistuned systems[J].Journal of Engineering for Gas Turbines and Power,2002,122(3):586-597.
[7]Petrov E P,Sayma A I.Forced response variation of aerodynamically and structurally mistuned turbo-machinery rotors[R].ASME Paper GT2006-90948,2006.
[8]Sever I A,Petrov E P,Ewins D J.Experimental and numerical investigation of rotating bladed disk forced response using underplatform friction dampers[J].Journal of Engineering for Gas Turbines and Power,2008,130(4):042503.1-042503.11.
[9]Nikolic M,Petrov E P,Ewins D J.Robust strategies for forced response reduction of bladed disks based on large mistuning concept[J].Journal of Engineering for Gas Turbines and Power,2008,130(2):022501.1-022501.11.
[10]Petrov E P.Reduction of forced response levels for bladed discs by mistuning:overview of the phenomenon[R].ASME Paper GT2010-23299,2010.
[11]Petrov E P.A method for forced response analysis of mistuned bladed disks with aerodynamic effects included[J].Journal of Engineering for Gas Turbines and Power,2010,132(6):062502.1-062502.10.
[12]Castanier M P,Pierre C.Modeling and analysis of mistuned bladed disk vibration:status and emerging directions[J].Journal of Propulsion and Power,2006,22(2):384-396.
[13]廖海涛,王建军,李其汉.随机失谐叶盘结构失谐特性分析[J].航空动力学报,2010,25(1):160-168.LIAO Haitao,WANG Jianjun,LI Qihan.Mistuning characteristics analysis of mistuned bladed disk assemblies[J].Journal of Aerospace Power,2010,25(1):160-168.(in Chinese)
[14]白斌,白广忱,童晓晨,等.整体叶盘结构失谐振动的国内外研究状况[J].航空动力学报,2014,29(1):91-103.BAI Bin,BAI Guangchen,TONG Xiaochen,et al.Research on vibration problem of integral mistuned balded disk assemblies at home and abroad[J].Journal of Aerospace Power,2014,29(1):91-103.(in Chinese)
[15]王红建,贺尔铭,余仕侠.具有干摩擦散乱失谐的叶盘受迫响应特性[J].航空动力学报,2006,21(4):711-715.WANG Hongjian,HE Erming,YU Shixia.Forced response characteristics of bladed disks with disordered dry friction[J].Journal of Aerospace Power,2006,21(4):711-715.(in Chinese)
[16]袁惠群,张亮.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.YUAN Huiqun,ZHANG Liang.Optimization of mistuning blades arrangement for vibration absorption in an aero-engine based on artificial ant colony algorithm[J].Journal of Vibration and Shock,2012,31(11):169-172.(in Chinese)
[17]袁惠群,杨少明.基于蚁群算法和模态局部化参数的失谐叶盘减振研究[J].东北大学学报(自然科学版),2010,31(11):1611-1614.YUAN Huiqun,YANG Shaoming.Vibration reduction of mistuned blade disc by ant colony algorithm and modal localization parameter[J].Journal of Northeastern University(Natural Science),2010,31(11):1611-1614.(in Chinese)
[18]袁惠群,张亮.航空发动机转子失谐叶片减振安装优化分析[J].振动、测试与诊断,2011,31(5):647-651.YUAN Huiqun,ZHANG Liang.Optimization analysis on mistuning blades of vibration absorption in aero-engine[J].Journal of Vibration,Measurement and Diagnosis,2011,31(5):647-651.(in Chinese)