基于多点随机激励的发动机管路振动疲劳寿命分析
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摘要
针对航空发动机管路系统激振环境复杂、激振点多的现状和在此边界条件下单点随机振动方法无法准确分析与模拟的问题,提出了一种多点动力学振动分析方法,首先从理论上推导出多点激励的动力学振动方程,其次利用有限元模拟验证了结构多点振动的动强度响应特性,根据Dirlik模型预测了管路系统的随机振动疲劳寿命,对比分析了结构在多点振动激励与单点振动激励下响应动力学特性以及疲劳寿命的关系,针对载荷相关性问题探究管路应力响应与疲劳寿命的变化规律,最后针对于不同的约束条件,分析了弹性约束刚度值对于结构疲劳寿命的影响。对比分析发现:在多点激励下管路系统的的振动寿命仅为单点激励最低疲劳寿命的22.31%,管路应力响应与疲劳寿命随相位与相干系数变化而呈规律变化,随着约束刚度值的增加,结构的响应功率谱密度增加,结构共振区域对于功率谱密度放大作用减小,疲劳寿命降低,验证了多点动力学振动分析方法的有效性。
Aiming at the complicated exciting environment and many exciting points of the aeroengine pipeline system,the single point random vibration method can not be accurately analyzed and simulated under the boundary conditions. This paper proposes a multipoint dynamic vibration analysis method. Firstly,the dynamic vibration equation of multi-point excitation is deduced theoretically. Secondly,the dynamic response characteristics of multi-point vibration are verified by finite element simulation. According to the Dirlik model,the random vibration fatigue life of pipeline system is predicted. The dynamic characteristics and fatigue life of the structure under multi-point vibration excitation and single point vibration excitation are compared. The relationship between stress response and fatigue life of pipeline is explored according to load correlation. Finally,according to different constraint conditions,the effects of elastic constraint stiffness value on structural fatigue life are investigated. Comparative analysis found that the vibration life of pipeline system under multi-point excitation is only22.31% of the minimum fatigue life of single point excitation. The stress response and fatigue life of pipelines change regularly with the change of phase and coherence coefficient. Moreover,with the increase of restrained stiffness,the response power spectral density of the structure increases,the amplification effect of the resonance region on the power spectral density decreases,and the fatigue life decreases. The validity of the multipoint dynamic vibration analysis method is verified.
Aiming at the complicated exciting environment and many exciting points of the aeroengine pipeline system,the single point random vibration method can not be accurately analyzed and simulated under the boundary conditions. This paper proposes a multipoint dynamic vibration analysis method. Firstly,the dynamic vibration equation of multi-point excitation is deduced theoretically. Secondly,the dynamic response characteristics of multi-point vibration are verified by finite element simulation. According to the Dirlik model,the random vibration fatigue life of pipeline system is predicted. The dynamic characteristics and fatigue life of the structure under multi-point vibration excitation and single point vibration excitation are compared. The relationship between stress response and fatigue life of pipeline is explored according to load correlation. Finally,according to different constraint conditions,the effects of elastic constraint stiffness value on structural fatigue life are investigated. Comparative analysis found that the vibration life of pipeline system under multi-point excitation is only22.31% of the minimum fatigue life of single point excitation. The stress response and fatigue life of pipelines change regularly with the change of phase and coherence coefficient. Moreover,with the increase of restrained stiffness,the response power spectral density of the structure increases,the amplification effect of the resonance region on the power spectral density decreases,and the fatigue life decreases. The validity of the multipoint dynamic vibration analysis method is verified.
引文
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[14]王彬.振动分析与应用[M].北京:海潮出版社,1992.
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[16]Wijkerj J.Random Vibrations in Spacecraft Structures Design:Theory and Applications[M].New York:Springer Science&Business Media,2009.
[17]Dirlik T.Application of Computers in Fatigue Analysis[D].Coventry:University of Warwick,1985.
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[20]王桂华,刘海年,张大义,等.航空发动机成附件振动环境试验剖面确定方法研究[J].推进技术,2013,34(8):1101-1107.(WANG Gui-hua,LIU Hai-nian,ZHANG Da-yi,et al.Study on the Determination Method of the Experimental Profile of the Aero-Engine in the Attachment Vibration Environment[J].Journal of Propulsion Technology,2013,34(8):1101-1107.)
[21]王志伟,林深伟.随机振动下产品包装件动态响应的实验研究和有限元分析[J].振动与冲击,2017,36(13):223-229.
[2]刘元朋,陈良骥,李明,等.航空发动机管路测量数据分割方法[J].航空学报,2008,29(2):285-291.
[3]王帅,张明明,刘桢,等.预载荷作用下管路结构动强度评估方法[J].北京航空航天大学学报,2016,42(4):745-750.
[4]樊泽明,傅殿玉.充液管路流固耦合振动研究进展[J].西安工业大学学报,2013,33(5):345-351.
[5]李占营,王建军,邱明星.航空发动机空间管路系统的流固耦合振动特性[J].航空动力学报,2016,31(10):2346-2352.
[6]Bishop N W M.Vibration Fatigue Analysis in Finite Element Environment[C].Torremolinos:The XVI Encuentro Delgrupo Espanol De Fractura,1999:14-16.
[7]Kumaraswamy P.A Generalized Probability Density Function for Double-Bounded Random Processes[J].Journal of Hydrology,1980,46(1-2):79-88.
[8]权凌霄,孔祥东,俞滨,等.液压管路流固耦合振动机理及控制研究现状与发展[J].机械工程学报,2015,51(18):175-183.
[9]权凌霄,赵文俊,于辉,等.随机振动载荷作用下航空液压管路疲劳寿命数值预估[J].液压与气动,2017,44(6):43-48.
[10]刘文光,陈国平,贺红林,等.结构振动疲劳研究综述[J].工程设计学报,2012,19(1):1-8.
[11]张永国.发动机管路输送系统的振动可靠性分析[D].哈尔滨:哈尔滨工程大学,2008.
[12]丁镇军,丁富海,王喆,等.火箭增压管路多点随机激励试验技术研究[J].航天器环境工程,2017,34(5):500-504.
[13]贾宏宇,郑史雄,阳栋,等.非平稳多维多点虚拟激励法的快速模拟方法[J].振动与冲击,2013,32(18):108-112.
[14]王彬.振动分析与应用[M].北京:海潮出版社,1992.
[15]贺光宗,陈怀海,孙建勇.多轴向与单轴向随机激励下结构动力学响应对比研究[J].振动与冲击,2017,36(14):194-201.
[16]Wijkerj J.Random Vibrations in Spacecraft Structures Design:Theory and Applications[M].New York:Springer Science&Business Media,2009.
[17]Dirlik T.Application of Computers in Fatigue Analysis[D].Coventry:University of Warwick,1985.
[18]康晨辰.飞机尾翼声振疲劳寿命分析[D].南京:南京航空航天大学,2016.
[19]胡雨人,卢健琦.随机振动下的疲劳分析-RMS应力-寿命法[J].振动:测试与诊断,1988,8(4):5-14.
[20]王桂华,刘海年,张大义,等.航空发动机成附件振动环境试验剖面确定方法研究[J].推进技术,2013,34(8):1101-1107.(WANG Gui-hua,LIU Hai-nian,ZHANG Da-yi,et al.Study on the Determination Method of the Experimental Profile of the Aero-Engine in the Attachment Vibration Environment[J].Journal of Propulsion Technology,2013,34(8):1101-1107.)
[21]王志伟,林深伟.随机振动下产品包装件动态响应的实验研究和有限元分析[J].振动与冲击,2017,36(13):223-229.
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