激波诱导可调向心涡轮叶片高周疲劳失效
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摘要
对一种存在高周疲劳失效现象的导流叶片可调向心涡轮进行三维定常流场的数值模拟,并与试验结果进行对比,验证数值计算结果的有效性.通过三维非定常流场计算,确定激波和导流叶片叶尖间隙泄漏流所导致的转子叶片表面的压力波动特性.通过插值方法把非定常压力场加载到有限元计算的节点上,对涡轮转子叶片进行模态分析及静态应力分析,得到涡轮转子叶片应力水平及对称循环应力.分析表明,在导流叶片尾缘激波的诱导下,涡轮转子叶片前缘受到波动较大的压力场作用,并与叶片发生谐振,引发涡轮转子叶片的高周疲劳失效的可能性增大.
The shock wave located near the trailing edge of the nozzle can induce the pressure fluctuation on the surface of the rotor blade.However,the physical mechanism of the shock wave induced high cycle fatigue is ignored.A variable vane radial turbine,suffered the high cycle fatigue in the test,was investigated by the three-dimensional numerical method.The characteristic of the shock wave and pressure fluctuation on the surface of rotor induced by the guide vane gap leakage were analyzed in details.Threedimensional finite element analysis coupled with the results from unsteady simulation was used to perform modal analysis and structure analysis.The blade stress level and the symmetrically circulating stress are obtained.Results showed that the pressure fluctuation with large amplitude near the leading edge of the rotor blade,induced by the shock wave on the trailing edge of the nozzle,can resonance with the rotor blade vibration,and this phenomenon severely increases the risk of high cycle fatigue.
The shock wave located near the trailing edge of the nozzle can induce the pressure fluctuation on the surface of the rotor blade.However,the physical mechanism of the shock wave induced high cycle fatigue is ignored.A variable vane radial turbine,suffered the high cycle fatigue in the test,was investigated by the three-dimensional numerical method.The characteristic of the shock wave and pressure fluctuation on the surface of rotor induced by the guide vane gap leakage were analyzed in details.Threedimensional finite element analysis coupled with the results from unsteady simulation was used to perform modal analysis and structure analysis.The blade stress level and the symmetrically circulating stress are obtained.Results showed that the pressure fluctuation with large amplitude near the leading edge of the rotor blade,induced by the shock wave on the trailing edge of the nozzle,can resonance with the rotor blade vibration,and this phenomenon severely increases the risk of high cycle fatigue.
引文
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[2]Minegashi H,Matsushita H,Sakakida M.Develop-ment of a small mixed-flow turbine for automotive turbo-chargers[C].ASME Paper 95-GT-53,1995.
[3]杨策,马朝臣,沈宏继.大型柴油机可变几何涡轮增压器的研制及试验研究[J].内燃机学报,2002,20(6):55-60.
[4]Hu Liangjun,Yang Ce,Sun Harold,et al.Numericalanalysis of nozzle clearance's effect on turbine perform-ance[J].Chinese Journal of Mechanical Engineering,2011,24(4):618-625.
[5]Kawakubo T.Unsteady rotor-stator interaction of a ra-dial-inflow turbine with variable nozzle vanes[C].ASME Paper GT2010-23677,2010.
[6]杨策,刘尚涛,赵奔,等.导流叶片可调的向心涡轮转子叶片压力波动叠加激励机制[R].中国工程热物理学会热力学会议,哈尔滨,2012.
[7]Stephan M.Senn M S,Ottmar S.Blade excitation inpulse-charged mixed-flow turbocharger turbines[J].ASME Journal of Turbomachinery,2011,133(2):1-6.
[8]Kulkarni A,Tisserant D,Hosny D,et al.Turbinewheel high cycle fatigue reliability prediction[C]//9,thInternational Conference on Turbochargers and Turbo-charging,London:Proceedings of ASME TurboExpo,2010:171-181.
[9]洪杰,张大义,陈璐璐.气流激励下的叶片高周疲劳寿命研究的发展[J].航空动力学报,2009,24(3):652-660.
[10]吴承伟,关振群,郭杏林,等.大型离心压缩机叶轮叶片疲劳可靠性分析[J].装备制造技术,2008(8):1-3.
[11]Huang Nguyen-Schafer.Rotordynamincs of automotiveturbochargers[M].Stuttgart,Germany:Springer BerlinHeidelberg,2012:33-57.
[12]姚卫星.结构疲劳寿命分析[M].北京:国防工业出版社,2003:61-63.
[13]赵少汴,王忠保.抗疲劳设计——方法与数据[M].北京:机械工业出版社,1997:301-323.