一种航空发动机整机振动模型支承刚度的辨识方法
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摘要
提出了一种航空发动机整机振动模型支承刚度识别的方法。首先,建立航空发动机整机动力学模型,将支承刚度和安装节刚度视为待优化的连接刚度,然后通过有限元仿真计算,得到在不同连接刚度下各阶整机固有频率。以支持向量机构造从各支承刚度到各阶固有频率的回归函数。接下来,采用遗传算法进行目标优化,以整机真实固有频率(可通过模态试验获取)为基础,建立遗传算法适应度函数,利用实数编码,最终识别得到整机各处连接刚度。以带机匣的航空发动机转子试验器为算例进行方法验证,根据整机模态试验结果,进行了支承刚度和安装节刚度识别,结果表明了该方法的有效性。
A method for aircraft engine vibration model support stiffness identification is proposed.Firstly,the dynamic model of the whole aero-engine is established,and the support and mounting stiffness parameters are taken as the connection stiffness parameters to be optimized.Secondly,the natural frequencies under different connection stiffness parameters are obtained through the finite element simulation,and the regression function from the stiffness to the natural frequency is constructed by the method of support vector machines.Then,the genetic algorithm is applied to the multi-objective optimization.Based on the real natural frequencies of the whole machine(which can be obtained by modal test),a fitness function of multi-objective optimization of genetic algorithm is established,and the real number encoding is used to finally accomplish the connection stiffness parameter identification.An aero-engine rotor tester with casing is taken as an example to verify the method.The support and mounting stiffness parameters of the whole tester are identified based on the results of the modal test,and the results show the effectiveness of the proposed method.
A method for aircraft engine vibration model support stiffness identification is proposed.Firstly,the dynamic model of the whole aero-engine is established,and the support and mounting stiffness parameters are taken as the connection stiffness parameters to be optimized.Secondly,the natural frequencies under different connection stiffness parameters are obtained through the finite element simulation,and the regression function from the stiffness to the natural frequency is constructed by the method of support vector machines.Then,the genetic algorithm is applied to the multi-objective optimization.Based on the real natural frequencies of the whole machine(which can be obtained by modal test),a fitness function of multi-objective optimization of genetic algorithm is established,and the real number encoding is used to finally accomplish the connection stiffness parameter identification.An aero-engine rotor tester with casing is taken as an example to verify the method.The support and mounting stiffness parameters of the whole tester are identified based on the results of the modal test,and the results show the effectiveness of the proposed method.
引文
[1]《航空发动机设计手册》总编委会.航空发动机设计手册第19测:转子动力学及整机振动[M].北京:航空工业出版社,2000:208-226.Aeroengine Design Manual Committee.Aero-Enging Design Manual 19th Part:Rotor Dynamics and WholeEngine Vibration[M]. Beijing:Aviation Industry Press,2000:208-226.
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[3] Ewins D J.Modal Testing II—Theory,Practice and Application[M].Baldock,Hertfordshire,England:Research Studies Press Ltd,2000.
[4] Govers Y,Link M.Stochastic model updating-Covariance matrix adjustment from uncertain experimental modal data[J].Mechanical Systems&Signal Processing,2010,24(3):696-706.
[5] Mottershead J E,Link M,Friswell M I.The sensitivity method in finite element model updating:A tutorial[J].Mechanical Systems&Signal Processing,2011,25(7):2275-2296.
[6] Gutierrez-Wing E S,Ewins D J.Characterisation of rotating machinery dynamics within limited frequency intervals using modal analysis[J].Australian Journal of Mechanical Engineering,2015,2(1):11-20.
[7] Link M,Friswell M.Generation of validated structural dynamic models—Results of a benchmark study utilising the GARTEUR SM-AG19test-bed[J].Mechanical Systems&Signal Processing,2003,17(1):9-20.
[8] Bohle K,Fritzen C P.Results obtained by minimising natural frequency and MAC-value errors of a plate model[J].Mechanical Systems&Signal Processing,2003,17(1):55-64.
[9] Mares C,Mottershead J E,Friswell M I.Results obtained by minimising natural-frequency errors and using physical reasoning[J].Mechanical Systems&Signal Processing,2003,17(1):39-46.
[10]Box G E,Wilson K B.On the experiment attainment of optimum conditions[J].Journal of Royal Statistical Society,Series B,1951,13(1):332-654.
[11]马双超,臧朝平,兰海波.某航空发动机机匣的动力学模型修正[J].航空动力学报,2013,28(4):878-884.Ma S C,Zang C P,Lan H B.Dynamic model updating of an aero-engine casing[J].Journal of Aerospace Power,2013,28(4):878-884.
[12]赵斌,陈果,冯国全.航空发动机整机振动半实物建模方法研究[J].推进技术,2016,37(2):346-353.Zhao B,Chen G,Feng G Q.Study on a semi-physical method for modeling overall vibration of an aero-engine[J].Journal of Propulsion Technology,2016,37(2):346-353.
[13]Zang C,Ewins D J.Model validation for structural dynamics in the aero-engine design process[J].Frontiers of Energy&Power Engineering in China,2009,3(4):480.
[14]Liu W,Ewins D J.Neural networks:A method for joint dynamic parameter identification[J].Proceedings-SPIE the International Society for Optical Engineering,2001,2(4359):1490-1496.
[15] Miao H,Zang C,Friswell M.Model updating and validation of a dual-rotor system[C].Proceedings of ISMA 2014Including USD 2014,Leuven,Belgium,2014:2723-2737.
[16]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,2014:389-401.Li Q H,Wang Y R.The Design Problem of Aero-Engine Structure Strength[M].Shanghai:Shanghai Jiaotong University Press,2014:389-401.
[17]赵文涛.考虑实测支承动刚度的航空发动机整机振动建模及验证[D].南京:南京航空航天大学,2012:27-45.Zhao W T.Research on the whole engine vibration modeling and validation of aero-engine considering the dynamic stiffness of the tested casing bearing[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2012:27-45.
[18]韩清凯.故障转子系统的非线性振动分析与诊断方法[M].北京:科学出版社,2010:70.Han Q K.Nonlinear Vibration Analysis and Diagnosis of Faulted Rotor System[M].Beijing:Science Press,2010:70.
[2] Wang W,Mottershead J E,Ihle A,et al.Finite element model updating from full-field vibration measurement using digital image correlation[J].Journal of Sound&Vibration,2011,330(8):1599-1620.
[3] Ewins D J.Modal Testing II—Theory,Practice and Application[M].Baldock,Hertfordshire,England:Research Studies Press Ltd,2000.
[4] Govers Y,Link M.Stochastic model updating-Covariance matrix adjustment from uncertain experimental modal data[J].Mechanical Systems&Signal Processing,2010,24(3):696-706.
[5] Mottershead J E,Link M,Friswell M I.The sensitivity method in finite element model updating:A tutorial[J].Mechanical Systems&Signal Processing,2011,25(7):2275-2296.
[6] Gutierrez-Wing E S,Ewins D J.Characterisation of rotating machinery dynamics within limited frequency intervals using modal analysis[J].Australian Journal of Mechanical Engineering,2015,2(1):11-20.
[7] Link M,Friswell M.Generation of validated structural dynamic models—Results of a benchmark study utilising the GARTEUR SM-AG19test-bed[J].Mechanical Systems&Signal Processing,2003,17(1):9-20.
[8] Bohle K,Fritzen C P.Results obtained by minimising natural frequency and MAC-value errors of a plate model[J].Mechanical Systems&Signal Processing,2003,17(1):55-64.
[9] Mares C,Mottershead J E,Friswell M I.Results obtained by minimising natural-frequency errors and using physical reasoning[J].Mechanical Systems&Signal Processing,2003,17(1):39-46.
[10]Box G E,Wilson K B.On the experiment attainment of optimum conditions[J].Journal of Royal Statistical Society,Series B,1951,13(1):332-654.
[11]马双超,臧朝平,兰海波.某航空发动机机匣的动力学模型修正[J].航空动力学报,2013,28(4):878-884.Ma S C,Zang C P,Lan H B.Dynamic model updating of an aero-engine casing[J].Journal of Aerospace Power,2013,28(4):878-884.
[12]赵斌,陈果,冯国全.航空发动机整机振动半实物建模方法研究[J].推进技术,2016,37(2):346-353.Zhao B,Chen G,Feng G Q.Study on a semi-physical method for modeling overall vibration of an aero-engine[J].Journal of Propulsion Technology,2016,37(2):346-353.
[13]Zang C,Ewins D J.Model validation for structural dynamics in the aero-engine design process[J].Frontiers of Energy&Power Engineering in China,2009,3(4):480.
[14]Liu W,Ewins D J.Neural networks:A method for joint dynamic parameter identification[J].Proceedings-SPIE the International Society for Optical Engineering,2001,2(4359):1490-1496.
[15] Miao H,Zang C,Friswell M.Model updating and validation of a dual-rotor system[C].Proceedings of ISMA 2014Including USD 2014,Leuven,Belgium,2014:2723-2737.
[16]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,2014:389-401.Li Q H,Wang Y R.The Design Problem of Aero-Engine Structure Strength[M].Shanghai:Shanghai Jiaotong University Press,2014:389-401.
[17]赵文涛.考虑实测支承动刚度的航空发动机整机振动建模及验证[D].南京:南京航空航天大学,2012:27-45.Zhao W T.Research on the whole engine vibration modeling and validation of aero-engine considering the dynamic stiffness of the tested casing bearing[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2012:27-45.
[18]韩清凯.故障转子系统的非线性振动分析与诊断方法[M].北京:科学出版社,2010:70.Han Q K.Nonlinear Vibration Analysis and Diagnosis of Faulted Rotor System[M].Beijing:Science Press,2010:70.
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