复合材料风扇叶片-机匣碰摩振动的数值模拟
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摘要
基于全三维模型的复合材料风扇叶片-机匣碰摩动力学特性的数值研究。建立了复合材料三维风扇叶片-机匣实体有限元模型,考虑叶片离心刚度的影响,机匣由贝塞尔曲面拟合,风扇叶片采用3种不同铺层形式。基于该模型,在机匣二节径变形的情况下,计算了不同铺层叶片在不同转速下与机匣碰摩后的动力学响应。计算结果表明:铺层形式对叶片中、低转速下的碰摩振动形式影响较大,带有90°铺层的叶片的最高振幅及不稳定振动所在区域的转速相对较低,改变铺层形式可以对复合材料风扇叶片-机匣的碰摩动力学特性加以控制。当转速靠近由3倍频与叶片1阶模态造成的共振点附近,或由6倍频与叶片2阶模态造成的共振转速附近时,叶片与机匣的碰摩会导致非稳定振动的产生。该方法与结果对复合材料风扇叶片的碰摩动力学特性研究具有一定指导意义。
A full three-dimensional composite fan blade rubbing vibration calculating model was established.A complete composite fan blade modeling method was used to establish composite fan blade and casing solid element models.The influence of the blades'centrifugal stiffness was taken into consideration,Bezier surface was used to fit casing nodes.Rubbing phenomena of three blades with difference stacking sequences were studied under the assumption of a two-nodal diameter casing distortion.Results indicated that the stacking sequence pattern had a great impact on the blade rub-impact vibration characteristic at low rotational speeds.The rotating speeds of maximum amplitude and unstable vibration regions of blade with 90°layers were relatively low.The rubbing dynamic characteristics of the composite fan blade can be controlled by the stacking sequence,and when the rotating speed was close to the first-order mode resonance point of the blade caused by the third engine order,or close to the second-order mode resonance position of the blade caused by the sixth engine order,non-steady blade rubbing vibrations were generated.The method and results have certain guiding significance to the study of the rubbing dynamic characteristics of composite fan blades.
A full three-dimensional composite fan blade rubbing vibration calculating model was established.A complete composite fan blade modeling method was used to establish composite fan blade and casing solid element models.The influence of the blades'centrifugal stiffness was taken into consideration,Bezier surface was used to fit casing nodes.Rubbing phenomena of three blades with difference stacking sequences were studied under the assumption of a two-nodal diameter casing distortion.Results indicated that the stacking sequence pattern had a great impact on the blade rub-impact vibration characteristic at low rotational speeds.The rotating speeds of maximum amplitude and unstable vibration regions of blade with 90°layers were relatively low.The rubbing dynamic characteristics of the composite fan blade can be controlled by the stacking sequence,and when the rotating speed was close to the first-order mode resonance point of the blade caused by the third engine order,or close to the second-order mode resonance position of the blade caused by the sixth engine order,non-steady blade rubbing vibrations were generated.The method and results have certain guiding significance to the study of the rubbing dynamic characteristics of composite fan blades.
引文
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[29]XIAO J G Y,CHEN Y,OUYANG H,et al.Investigation of fan blades vibration due to blade/casing rubbing interactions using in-plane two-dimensional model[R].Oslo,Norway:ASME Turbomachinery Technical Conference and Exposion,2018.
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[33]YANG J,SONG B,ZHONG X,et al.Optimal design of blended composite laminate structures using ply drop sequence[J].Composite Structures,2016,135:30-37.
[34]ABDALLA M,GURDAL Z,KASSAPOGLU C.Formulation of composite laminate robustness constraint in lamination parameters space[R].Palm Springs,California,USA:AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,2013.
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[36]XIAO J G Y,CHEN Y,ZHU Q,et al.A general ply design for aero engine composite fan blade[R].Charlotte,USA:ASME Turbomachinery Technical Conference and Exposition,2017.
[37]ANSYS Corporation.ANSYS 17.0documentation[R].Pittsburgh,USA:ANSYS Corporation,2016.
[38]BATAILLY A,MEINGAST M,LEGRAND M.Unilateral contact induced blade/casing vibratory interactions in impellers:analysis for rigid casings[J].Journal of Sound and Vibration,2015,337:244-262.
[39]OLSSON W J,MARTIN R L.B747/JT9D Flight loads and their effect on engine running clearances and performance deterioration;nacelle aerodynamic and inertial loads(NAIL)/JT9Djet engine diagnostics programs[R].NASACR-165573,1982.
[2]TURNER K E,ADAMS M,DUNN M.Simulation of engine blade tip-rub induced vibration[R].ASME Paper GT2005-68217,2005.
[3]TURNER K E,DUNN M,PADOVA C.Airfoil deflection characteristics during rub events[J].Journal of Turbomachinery,2012,134(1):112-121.
[4]JIANG J,AHRENS J,ULBRICH H,et al.A contact model of a rotating,rubbing blade[R].Riga,Latvia:the 5th International Conference on Rotor Dynamics of the International Federation for the Promotion of Mechanism and Machine Science(IFTOMM),1998.
[5]PADOVAN J,CHOY F K.Nonlinear dynamics of rotor/blade/casing rub interactions[J].Journal of Turbomachinery,1987,109(4):527-534.
[6]MA H,TAI X Y,HAN Q K,et al.A revised model for rubbing between rotating blade and elastic casing[J].Journal of Sound and Vibration,2015,337:301-320.
[7]刘书国,洪杰,陈萌.航空发动机叶片-机匣碰摩过程的数值模拟[J].航空动力学报,2011,26(6):1282-1288.LIU Shuguo,HONG Jie,CHEN Meng.Numerical simulation of the dynamic process of aero-engine blade-to-case rub-impact[J].Journal of Aerospace Power,2011,26(6):1282-1288.(in Chinese)
[8]LEGRAND M,BATAILLY A,MAGNAIN B,et al.Full three-dimensional investigation of structural contact interactions in turbomachines[J].Journal of Sound and Vibration,2012,331(11):2578-2601.
[9]太兴宇,马辉,谭祯,等.脉冲力加载下的叶片-机匣动力学特性研究[J].东北大学学报(自然科学版)2012,33(12):1759-1799.TAI Xingyu,MA Hui,TAN Zhen,et al.Research on dynamic characteristics of blade-casing with impulse loading[J].Journal of Northeastern University(Natural Science),2012,33(12):1758-1761.(in Chinese)
[10]马辉,孙祺,太兴宇,等.旋转叶片-机匣碰摩振动响应分析[J].振动与冲击,2017,36(14):27-32.MA Hui,SUN Qi,TAI Xingyu,et al.Vibration response analysis on the rotating blade-casing rubbing[J].Journal of Vibration and Shock,2017,36(14):27-32.(in Chinese)
[11]BATAILLY A,LEGRAND M.Conjectural bifurcation analysis of an aircraft engine blade undergoing 3Dunilateral contact constraints[R].Düsseldorf,Germany:ASME Turbine Technical Conference and Exposition,2014.
[12]DINA A.Vibration analysis of compressor blade tip-rubbing[D].Cranfield:Cranfield University,2012.
[13]LEGRAND M,PIERRE C,CARTRAUD P,et al.Twodimensional modeling of an aircraft engine structural bladed disk-casing modal interaction[J].Journal of Sound and Vibration,2009,319(1):366-391.
[14]陈果,王海飞,刘永泉,等.新型叶片-机匣碰摩模型及其验证[J].航空动力学报,2015,30(4):952-965.CHEN Guo,WANG Haifei,LIU Yongquan,et al.A new blade-casing rubbing model and its verification[J].Journal of Aerospace Power,2015,30(4):952-965.(in Chinese)
[15]MANDARD R,WITZ J F,BOIDIN X,et al.Interacting force estimation during blade/seal rubs[J].Tribology International,2015,82:504-513.
[16]PADOVA C,BARTON J,DUNN M G,et al.Experimental results from controlled blade tip/shroud rubs at engine speed[J].Journal of Turbomachinery,2007,129(4):1165-1177.
[17]PADOVA C,DUNN M,BARTON J,et al.Controlled fan blade tip/shroud rubs at engine conditions[R].Vancouver,Canada:ASME Turbine Technical Conference and Exposition,2011.
[18]WEI F,CHEN Y,WU Z,et al.Failure analysis of rubbing of the fan tip and case of an engine[J].Procedia Engineering,2015,99:1289-1296.
[19]CORONEOS R M,GORLA R S R.Structural analysis and optimization of a composite fan blade for future air-craft engine[J].International Journal of Turbo Jet-Engines,2012,29(3):131-164.
[20]SIDDENS A,BAYANDOR J.Multidisciplinary impact damage prognosis methodology for hybrid structural propulsion systems[J].Computers and Structures,2013,122(2):178-191.
[21]HONG Y,HE X D,WANG R G.Vibration and damping analysis of a composite blade[J].Materials and Design,2012,34:98-105.
[22]刘强,赵龙,黄峰.商用大涵道比发动机复合材料风扇叶片应用现状与展望[J].航空制造技术,2014,459(15):58-62.LIU Qiang,ZHAO Long,HUANG Feng.Present conditions and development of composite fan blades of high bypass ratio commercial jet engines[J].Aeronautical Manufacturing Technology,2014,459(15):58-62.(in Chinese)
[23]刘晶波,杜修力.结构动力学[M].北京:机械工业出版社,2005.
[24]STERNCHUSS A,BALMES E.On the reduction of quasicyclic disks with variable rotation speeds[R].Paris,France:International Conference on Advanced Acoustics and Vibration Engineering(ISMA),2006.
[25]BATAILLY A,MAGNAIN B,CHEVAUGEON N.Acomparative study between two smoothing strategies for the simulation of contact with large sliding[J].Computational Mechanics,2013,51(5):581-601.
[26]KONYUKHOV A,SCHWEIZERHOF K.Computational contact mechanics:geometrically exact theory for arbitrary shaped bodies[M].New York:Springer,2013.
[27]CARPENTER N J,TAYLOR R L,KATONA M G.Lagrange constraints for transient finite element surface contact[J].International Journal for Numerical Methods in Engineering,1991,32(1):103-128.
[28]张雄,王天舒,刘岩.计算动力学[M].北京:清华大学出版社,2015.
[29]XIAO J G Y,CHEN Y,OUYANG H,et al.Investigation of fan blades vibration due to blade/casing rubbing interactions using in-plane two-dimensional model[R].Oslo,Norway:ASME Turbomachinery Technical Conference and Exposion,2018.
[30]HALLQUIST J O.LS-DYNA3Dtheoretical manual[R].Livermore,USA:Livermore Software Technology Corporation,1994.
[31]EVANS C R,FUHRMAN B J,JONES J D,et al.Foreign object damage resistant composite blade and manufacture:US5375978[P].1994-12-27.
[32]LAKSHMI K,RAO A R M.Hybrid shuffled frog leaping optimisation algorithm for multi-objective optimal design of laminate composites[J].Computers and Structures,2013,125:200-216.
[33]YANG J,SONG B,ZHONG X,et al.Optimal design of blended composite laminate structures using ply drop sequence[J].Composite Structures,2016,135:30-37.
[34]ABDALLA M,GURDAL Z,KASSAPOGLU C.Formulation of composite laminate robustness constraint in lamination parameters space[R].Palm Springs,California,USA:AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,2013.
[35]IRISARRIF X,LASSEIGNE A,LEROY F H,et al.Optimal design of laminated composite structures with ply drops using stacking sequence tables[J].Composite Structures,2014,107:559-569.
[36]XIAO J G Y,CHEN Y,ZHU Q,et al.A general ply design for aero engine composite fan blade[R].Charlotte,USA:ASME Turbomachinery Technical Conference and Exposition,2017.
[37]ANSYS Corporation.ANSYS 17.0documentation[R].Pittsburgh,USA:ANSYS Corporation,2016.
[38]BATAILLY A,MEINGAST M,LEGRAND M.Unilateral contact induced blade/casing vibratory interactions in impellers:analysis for rigid casings[J].Journal of Sound and Vibration,2015,337:244-262.
[39]OLSSON W J,MARTIN R L.B747/JT9D Flight loads and their effect on engine running clearances and performance deterioration;nacelle aerodynamic and inertial loads(NAIL)/JT9Djet engine diagnostics programs[R].NASACR-165573,1982.