小失谐对整体叶盘结构动态特性的影响
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摘要
基于失谐叶盘频差提出了小失谐的概念,总结了其在实际工程叶盘中的表现形式。以扇区3自由度集中参数叶盘模型为对象,系统研究小失谐对不同模态族的模态局部化和响应幅值放大的影响。研究表明:小失谐在模态族最高节径处同样会造成严重的振动局部化现象。当失谐强度为0.001时,模态局部化因子达到17;当失谐强度为0.007时,响应幅值放大可达1.8。小失谐对叶盘结构动态特性的影响显著,在设计和使用中应予以重视。
The mistuning strength referred to as "small mistuning" was defined based on the frequency differences between the tuned and mistuned bladed disk.The existence and distribution of the small mistuning in industrial bladed disks were introduced.A lumped parameter bladed disk model with three-degree-of-freedom(3-DOF)in each sector was used as an example to investigate the effects of small mistuning on the dynamic characteristics.The results indicated that small mistuning can lead to severe vibration localization at the maximum nodal diameter.For the studied example,mistuning strength 0.001 can lead to a modal localization factor 17,and mistuning strength 0.007 can lead to a maximum amplitude amplification factor 1.8.Therefore,special attention must be paid to small mistuning during design and service stages of the bladed disk structures.
The mistuning strength referred to as "small mistuning" was defined based on the frequency differences between the tuned and mistuned bladed disk.The existence and distribution of the small mistuning in industrial bladed disks were introduced.A lumped parameter bladed disk model with three-degree-of-freedom(3-DOF)in each sector was used as an example to investigate the effects of small mistuning on the dynamic characteristics.The results indicated that small mistuning can lead to severe vibration localization at the maximum nodal diameter.For the studied example,mistuning strength 0.001 can lead to a modal localization factor 17,and mistuning strength 0.007 can lead to a maximum amplitude amplification factor 1.8.Therefore,special attention must be paid to small mistuning during design and service stages of the bladed disk structures.
引文
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[23]VISHWAKARMA V,SINHA A.Forced response statistics of a bladed rotor with geometric mistuning[J].AIAA Journal,2015,53(9):2776-2781.
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[26]王增强.航空发动机整体叶盘加工技术[J].航空制造技术,2013,42(9):40-43.WANG Zengqiang.Machining technology of aeroengine blisk[J].Aeronautical Manufacturing Technology,2013,42(9):40-43.(in Chinese)
[27]徐家文,赵建社.航空发动机整体构件特种加工新技术[M].北京:国防工业出版社,2011.
[28]陈光.航空发动机结构设计分析[M].北京:北京航空航天大学出版社,2014.
[29]BEIROW B,GIERSCH T,KüHHORN A,et al.Forced response analysis of a mistuned compressor blisk[J].Journal of Engineering for Gas Turbines and Power,2014,136(6):62507.1-62507.13.
[30]KENYON J A,GRIFFIN J H.Experimental demonstration of maximum mistuned bladed disk forced response[J].Journal of Turbomachinery,2003,125(4):673-682.
[31]BATAILLY A,AGRAPART Q,MILLECAMPS A,et al.Experimental and numerical simulation of a rotor/stator interaction event localized on a single blade within an industrial high-pressure compressor[J].Journal of Sound and Vibration,2016,375:308-331.
[32]CHOI Y S,FLEETER S.Aerodynamic damping effects on the resonant response of mistuned IBRs[R].:AIAA Aerospace Sciences Meeting and Exhibit,2013.
[2]李其汉,王延荣.航空发动机结构强度设计问题[M].上海:上海交通大学出版社,2014.
[3]王建军,李其汉,朱梓根.失谐叶片一轮盘结构系统振动局部化问题的研究进展[J].力学进展,2000,30(4):517-528.WANG Jianjun,LI Qihan,ZHU Zigen.Vibratory localization of mistuned bladed disk assemblies:a review[J].Advances in Mechanics,2000,30(4):517-528.(in Chinese)
[4]王建军,李其汉.航空发动机失谐叶盘振动减缩模型与应用[M].北京:国防工业出版社,2009.
[5]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.
[6]臧朝平,兰海强.失谐叶盘结构振动问题研究新进展[J].航空工程进展,2011(2):133-142.ZANG Chaoping,LAN Haiqiang.Advances in research vibration problem of mistuned blisk assemblies[J].Advances in Aeronautical Science and Engineering,2011,(2):133-142.(in Chinese)
[7]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 bladed disk assemblies at home and abroad[J].Journal of Aerospace Power,2014,29(1):91-103.(in Chinese)
[8]姚建尧,高阳,王建军.航空发动机失谐叶盘动态特性研究进展[J].航空制造技术,2016,516(21):76-85.YAO Jianyao,GAO Yang,WANG Jianjun.A review of dynamic characteristics of mistuned bladed disks[J].Aeronautical Manufacturing Technology,2016,516(21):76-85.(in Chinese)
[9]CASTANIER M P,PIERRE C.Using intentional mistuning in the design of turbomachinery rotors[J].AIAA Journal,2002,40(10):2077-2086.
[10]王建军,姚建尧,李其汉.刚度随机失谐叶盘结构概率模态特性分析[J].航空动力学报,2008,23(2):256-262.WANG Jianjun,YAO Jianyao,LI Qihan.Probability characteristics of vibratory mode of bladed disk assemblies with random stiffness mistuning[J].Journal of Aerospace Power,2008,23(2):256-262.(in Chinese)
[11]BLADH R,PIERRE C,CASTANIER M P.Dynamic response predictions for a mistuned industrial turbomachinery rotor using reduced-order modeling[J].Journal of Engineering for Gas Turbines and Power,2002,124(4):311-324.
[12]王建军,于长波,姚建尧,等.失谐叶盘振动模态局部化定量描述方法[J].推进技术,2009,30(4):457-461.WANG Jianjun,YU Changbo,YAO Jianyao,et al.Vibratory mode localization factors of mistuned bladed disk assemblies[J].Journal of Propulsion Technology,2009,30(4):457-461.(in Chinese)
[13]于长波,王建军,李其汉.失谐叶盘结构的概率响应局部化特性[J].航空动力学报,2010(9):2006-2012.YU Changbo,WANG Jianjun,LI Qihan.Probability characteristics for response localization of mistuned bladed disk assemblies[J].Journal of Aerospace Power,2010(9):2006-2012.(in Chinese)
[14]CAPIEZ-LERNOUT E,SOIZE C.Nonparametric modeling of random uncertainties for dynamic response of mistuned balded disks[J].Journal of Engineering for Gas Turbines and Power,2004,126(7):610-618.
[15]CAPIEZ-LERNOUT E,SOIZE C,LOMBARD J P,et al.Blade manufacturing tolerances definition for a mistuned industrial bladed disk[J].Journal of Engineering for Gas Turbines and Power,2005,127(3):621-628.
[16]LIM S H,BLADH R,CASTANIER M P,et al.Compact,generalized component mode mistuning representation for modeling bladed disk vibration[J].AIAA Journal,2007,45(9):2285-2298.
[17]CHOI B K,LENTZ J,RIVAS-GUERRA A J,et al.Optimization of intentional mistuning patterns for the reduction of the forced response effects of unintentional mistuning:formulation and assessment[J].Journal of Engineering for Gas Turbines and Power,2003,125(1):131-140.
[18]YAO Jianyao,WANG Jianjun,LI Qihan.Robustness analysis of mistuned bladed disk using the upper bound of structured singular value[J].Journal of Engineering for Gas Turbines and Power,2009,131(3):32501.1-32501.7.
[19]YAO Jianyao,WANG Jianjun,LI Qihan.Improved modal localization and excitation factors for understanding mistuned bladed disk response[J].Journal of Propulsion and Power,2011,27(1):50-60.
[20]KASZYNSKI A A,BECK J A,BROWN J M.Uncertainties of an automated optical 3D geometry measurement,modeling,and analysis process for mistuned integrally bladed rotor reverse engineering[J].Journal of Engineering for Gas Turbines and Power,2013,135(10):102504.1-102504.8.
[21]VISHWAKARMA V,SINHA A,BHARTIYA Y,et al.Modified modal domain analysis of a bladed rotor using coordinate measurement machine data on geometric mistuning[J].Journal of Engineering for Gas Turbines and Power,2015,137(4):42502.1-42502.8.
[22]BHARTIYA Y,SINHA A.Geometric mistuning identification of integrally bladed rotors using modified modal domain analysis[J].Journal of Engineering for Gas Turbines and Power,2014,136(12):122504.1-122504.8.
[23]VISHWAKARMA V,SINHA A.Forced response statistics of a bladed rotor with geometric mistuning[J].AIAA Journal,2015,53(9):2776-2781.
[24]BECK J A,BROWN J M,KASZYNSKI A A,et al.Geometric mistuning reduced-order models for integrally bladed rotors with mistuned disk--blade boundaries[J].Journal of Turbomachinery,2015,137(7):71001.1-71001.11.
[25]BECK J A,BROWN J M,KASZYNSKI A A,et al.Mistuned response prediction of dual flow-path integrally bladed rotors with geometric mistuning[J].Journal of Engineering for Gas Turbines and Power,2015,137(6):62501.1-62501.9.
[26]王增强.航空发动机整体叶盘加工技术[J].航空制造技术,2013,42(9):40-43.WANG Zengqiang.Machining technology of aeroengine blisk[J].Aeronautical Manufacturing Technology,2013,42(9):40-43.(in Chinese)
[27]徐家文,赵建社.航空发动机整体构件特种加工新技术[M].北京:国防工业出版社,2011.
[28]陈光.航空发动机结构设计分析[M].北京:北京航空航天大学出版社,2014.
[29]BEIROW B,GIERSCH T,KüHHORN A,et al.Forced response analysis of a mistuned compressor blisk[J].Journal of Engineering for Gas Turbines and Power,2014,136(6):62507.1-62507.13.
[30]KENYON J A,GRIFFIN J H.Experimental demonstration of maximum mistuned bladed disk forced response[J].Journal of Turbomachinery,2003,125(4):673-682.
[31]BATAILLY A,AGRAPART Q,MILLECAMPS A,et al.Experimental and numerical simulation of a rotor/stator interaction event localized on a single blade within an industrial high-pressure compressor[J].Journal of Sound and Vibration,2016,375:308-331.
[32]CHOI Y S,FLEETER S.Aerodynamic damping effects on the resonant response of mistuned IBRs[R].:AIAA Aerospace Sciences Meeting and Exhibit,2013.