带分流叶片叶轮的气动阻尼仿真
|
摘要
为了探究涡轮轴发动机离心叶轮分流叶片周向位置对其气动阻尼的影响。通过有限元仿真的方法,对涡轮轴发动机叶轮进行了模态分析和气动激振力作用下的谐响应分析,确定叶轮叶片在特定频率内的振动形式。建立基于叶轮结构的气动阻尼仿真模型,通过数值计算的方法,获得并分析分流叶片在不同周向位置时的叶轮气动阻尼。计算结果表明:计算获得的气动阻尼和机械阻尼量级相同,在特定分析中不能忽略。分流叶片周向位置对叶轮气动阻尼有显著影响。分流叶片不偏置时气动阻尼最小,可以通过偏置分流叶片的方法提升叶轮的气动弹性稳定性。
In order to study the influence of circumferential position on aerodynamic damping of centrifugal impeller's splitter blade in turboshaft engine, modal analysis and harmonic response analysis under the action of aerodynamic force were made to obtain the vibration form of a turboshafts engine impeller blade at specific frequency. A simulation model of aerodynamic damping was established based on impeller structure, and by using numerical calculation method, aerodynamic dampings of the impeller at different circumferential positions were obtained and then analysised. The result shows that the calculated aerodynamic damping and mechanical damping are in the same level, the aerodynamic damping can not be ignored in a specific analysis, circumferential position of split blade has a significant influence on the aerodynamic damping of the blade, aerodynamic damping is minimum when splitter is unbiased, and aerodynamic stability of the impeller can be improved by the method of bias shunting blade.
In order to study the influence of circumferential position on aerodynamic damping of centrifugal impeller's splitter blade in turboshaft engine, modal analysis and harmonic response analysis under the action of aerodynamic force were made to obtain the vibration form of a turboshafts engine impeller blade at specific frequency. A simulation model of aerodynamic damping was established based on impeller structure, and by using numerical calculation method, aerodynamic dampings of the impeller at different circumferential positions were obtained and then analysised. The result shows that the calculated aerodynamic damping and mechanical damping are in the same level, the aerodynamic damping can not be ignored in a specific analysis, circumferential position of split blade has a significant influence on the aerodynamic damping of the blade, aerodynamic damping is minimum when splitter is unbiased, and aerodynamic stability of the impeller can be improved by the method of bias shunting blade.
引文
[1] 于航,李琳.叶栅流场中的气动阻尼研究[J].航空动力学报,2009,24(4):819-824.
[2] Albert Kammerer,S Reza.Abhari.Experimental Study on Impeller Blade Vibration During Resonance—Part II:Blade Damping[J].Journal of Engineering for Gas Turbines & Power,2008,131(2):319-331.
[3] 郭雪莲,李琳.亚声速叶片与跨声速叶片的气动阻尼比较[J].推进技术,2010,31(3):296-300,308.
[4] 郭雪莲,李琳.压气机叶片气动阻尼的改善设计[J].航空动力学报,2012,27(8):1855-1860.
[5] 杨晓东,等.栅距非谐对跨声速压气机转子气动阻尼的影响[J].推进技术,2017,38(1):94-102..
[6] 黄钟山,王延荣,付志忠.轴流压气机大小叶片气动弹性稳定性分析[J].航空动力学报,2016,31(8):1964-1972.
[7] 陈矛章.风扇/压气机技术发展和对今后工作的建议[J].航空动力学报,2002,(1):1-15.
[8] 卜远远,楚武利.分流叶片周向位置对离心叶轮性能及内部流动的影响[J].流体机械,2011,39(09):16-20,44.
[9] 李章勇.空发动机轴流盘使用寿命与裂纹扩展分析[D].湖南大学,2010.
[10] R E Kielb,H D Chiang.Recent advancements in turbo machinery forced response analyses[R].AIAA 92-0012,1992.
[11] 何敏祥.分流叶片对离心压气机性能影响研究[D].南京航空航天大学,2013.
[2] Albert Kammerer,S Reza.Abhari.Experimental Study on Impeller Blade Vibration During Resonance—Part II:Blade Damping[J].Journal of Engineering for Gas Turbines & Power,2008,131(2):319-331.
[3] 郭雪莲,李琳.亚声速叶片与跨声速叶片的气动阻尼比较[J].推进技术,2010,31(3):296-300,308.
[4] 郭雪莲,李琳.压气机叶片气动阻尼的改善设计[J].航空动力学报,2012,27(8):1855-1860.
[5] 杨晓东,等.栅距非谐对跨声速压气机转子气动阻尼的影响[J].推进技术,2017,38(1):94-102..
[6] 黄钟山,王延荣,付志忠.轴流压气机大小叶片气动弹性稳定性分析[J].航空动力学报,2016,31(8):1964-1972.
[7] 陈矛章.风扇/压气机技术发展和对今后工作的建议[J].航空动力学报,2002,(1):1-15.
[8] 卜远远,楚武利.分流叶片周向位置对离心叶轮性能及内部流动的影响[J].流体机械,2011,39(09):16-20,44.
[9] 李章勇.空发动机轴流盘使用寿命与裂纹扩展分析[D].湖南大学,2010.
[10] R E Kielb,H D Chiang.Recent advancements in turbo machinery forced response analyses[R].AIAA 92-0012,1992.
[11] 何敏祥.分流叶片对离心压气机性能影响研究[D].南京航空航天大学,2013.