离心压气机近失速工况叶尖流场特征及泄漏涡面涡模型
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摘要
为研究航空微型涡轮发动机离心压气机的失速机理,采用数值模拟的方法,对压气机在设计点和近失速点的流场特征进行了研究,并对叶尖泄漏涡进行了建模。结果表明:在近失速工况下,更多的来自轮毂处的低能流和二次流会汇入叶轮通道近壁面的低速区,使得叶尖的堵塞加重,泄漏涡轨迹的偏转及其卷吸作用可能是造成这种现象的原因。通过在压气机机匣外侧引入虚拟镜像涡的方法,应用机翼涡对的不稳定性理论和面涡模型对泄漏涡建立了模型。应用该模型对本文研究的离心压气机以及三个国内外具有典型代表性的压气机进行了预测,表明模型得到的频率同计算和实验结果具有较好的吻合性,对德国宇航院压气机的预测频率与其实际频率的误差仅为2.8%。总体而言,当间隙高度较大时,模型的预测更为准确。
To study the stall mechanism of air centrifugal compressor in micro turbine engine,a numerical simulation method is employed. By comparing the flow field characteristics of design point with near stall point and establishing a tip leakage vortex model,results show that in near stall condition,more low-energy flow from hub and secondary flow gather in the low momentum zones,making blockage more serious. Tip leakage vortex may play an important role in this phenomenon due to the deflection of its track and its entrainment effect. Besides,by introducing the virtual mirror vortex outside the casing,trailing vortex instability theory and rolling up vortex model can thus be used to analyse the tip leakage vortex. This model is applied to the compressor studied in this paper and three domestic and foreign typical compressors,and as a result the model frequency of each compressor are in good agreement with the CFD and experiment results. The relative deviation between the predicted frequency and the experiment frequency even reaches to 2.8% when the model is used for a compressor made by the German Aerospace Center,certifying the validity of the model. In general,as the height of tip gap increases,the prediction of leakage vortex model turns out to be more accurate.
To study the stall mechanism of air centrifugal compressor in micro turbine engine,a numerical simulation method is employed. By comparing the flow field characteristics of design point with near stall point and establishing a tip leakage vortex model,results show that in near stall condition,more low-energy flow from hub and secondary flow gather in the low momentum zones,making blockage more serious. Tip leakage vortex may play an important role in this phenomenon due to the deflection of its track and its entrainment effect. Besides,by introducing the virtual mirror vortex outside the casing,trailing vortex instability theory and rolling up vortex model can thus be used to analyse the tip leakage vortex. This model is applied to the compressor studied in this paper and three domestic and foreign typical compressors,and as a result the model frequency of each compressor are in good agreement with the CFD and experiment results. The relative deviation between the predicted frequency and the experiment frequency even reaches to 2.8% when the model is used for a compressor made by the German Aerospace Center,certifying the validity of the model. In general,as the height of tip gap increases,the prediction of leakage vortex model turns out to be more accurate.
引文
[1]陈杰,钟榈,黄国平.微型离心叶轮流动损失分析与削弱[J].推进技术,2013,34(7):904-910.(CHEN Jie,ZHONG Lu,HUANG Guo-ping. Analysis and Reduction of Flow Loss in a Micro Centrifugal Impeller[J]. Journal of Propulsion Technology,2013,34(7):904-910.)
[2]黄国平,梁德旺,何志强.大型飞机辅助动力装置与微型涡轮发动机技术特点对比[J].航空动力学报,2008,23(2):383-388.
[3]楚武利,刘前智,胡春波.航空叶片机原理[M].西安:西北工业大学出版社,2009.
[4]吴艳辉,李清鹏,张卓勋,等.轴流压气机转子近失速工况点叶尖区流动非定常性分析[J].推进技术,2010,31(5):562-566.(WU Yan-hui,LI Qingpeng,ZHANG Zhuo-xun,et al. Unsteady Behavior ofTip Clearance Flow in an Axial Flow Compressor Rotor at near Stall Condition[J]. Journal of Propulsion Technology,2010,31(5):562-566.)
[5] Lei V M,Spakovszky Z S,Greitzer E M. A Criterion for Axial Compressor Hub-Corner Stall[J]. Journal of Turbomachinery,2008,130(3).
[6] Suder K L,Celestina M L. Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor[J]. Journal of Turbomachinery,1996,118(2):218-229.
[7] Feng L,Tong Z,Geng S,et al. A Summary of Stall Warning and Suppression Research with Micro Tip Injection[R]. ASME GT 2011-46118.
[8] Hah C,Rabe D C,Wadia A R. Role of Tip-Leakage Vortices and Passage Shock in Stall Inception in a Swept Transonic Compressor Rotor[R]. ASME GT 2004-53867.
[9] Vo H D,Tan C S,Greitzer E M. Criteria for Spike Initiated Rotating Stall[J]. Journal of Turbomachinery,2008,130(1).
[10] Hazby R H,Xu L. Role of Tip Leakage in Stall of a Transonic Centrifugal Impeller[R]. ASME GT 2009-59372.
[11]李相君,楚武利,张皓光.高负荷跨声速轴流压气机周向浅槽处理机匣扩稳机理[J].推进技术,2013,34(5):629-637.(LI Xiang-Jun,CHU Wu-li,ZHANG Hao-guang. Stabilizing Mechanism of Shallow Circumferential Grooves on a High Loaded Transonic AxialFlow Compressor[J]. Journal of Propulsion Technology,2013,34(5):629-637.)
[12] YANG Qi-chao,LI Lian-sheng,ZHAO Yuan-yang,et al. Experimental Investigation of an Active Control Casing Treatment of Centrifugal Compressors[J]. Experimental Thermal and Fluid Science,2017,83:107-117.
[13]曹四.机匣处理对跨声速离心压气机性能影响[J].推进技术,2017,38(4):772-778.(CAO Si. Effects of Casing Treatment on Performance of Transonic Centrifugal Compressor[J]. Journal of Propulsion Technology,2017,38(4):772-778.)
[14] Bae J. Active Control of Tip Clearance Flow in Axial Compressors[D]. Massachusetts:Massachusetts Institute of Technology,2001.
[15]李伟,乔渭阳,许开富.涡轮叶尖间隙泄漏涡不稳定性分析[J].推进技术,2008,29(2):204-207.(LI Wei,QIAO Wei-yang,XU Kai-fu. Unsteadiness of Tip Clearance Vortex in Turbine[J]. Journal of Propulsion Technology,2008,29(2):204-207.)
[16]胡子俊,张楠,姚惠之,等.涡判据在孔腔涡旋流动拓扑结构分析中的应用[J].船舶力学,2012,16(8):839-846.
[17] Seiichi I,Masato F,Kenichiro I,et al. Vortical Flow Structure and Loss Generation Process in a Transonic Centrifugal Compressor Impeller[R]. ASME GT 2007-27791.
[18] Hah C,Hathaway M,Katz J. Investigation of Unsteady Flow Field in a Low-Speed One and a Half Stage Axial Compressor:Effects of Tip Gap Size on the Tip Clearance Flow Structure at near Stall Operation[R]. ASME GT 2014-27094.
[19]杜娟.跨音压气机/风扇转子叶顶泄漏流动的非定常机制研究[D].北京:中国科学院研究生院,2010.
[20] Yamada K,Kikuta H,Furukawa M,et al. Effects of Tip Clearance Flow on Rotating Stall Inception Process in an Axial Compressor Rotor[R]. ASME GT 2013-95479.
[21] Lin F,Du J,Chen J,et al. Flow Structures in the Tip Region for a Transonic Compressor Rotor[R]. ASME GT2010-23025.
[22] Hah C,Bergner J,Schiffer H P. Tip Clearance Vortex Oscillation,Vortex Shedding and Rotating Instabilities in an Axial Transonic Compressor Rotor[R]. ASME GT2008-50105.
[23]洪树立,黄国平.引入DMD方法研究有/无控气流分离的动态结构[J].航空学报,2017,38(8).
[24] Crow S C. Stability Theory for a Pair of Trailing Vortices[J]. AIAA Journal,1970,8(12):2172-2179.
[25] Du J,Lin F,Zhang H,et al. Numerical Investigation on the Self-Induced Unsteadiness in Tip Leakage Flow for a Transonic Fan Rotor[J]. Journal of Turbomachinery-Transactions of ASME,2010,132(2).
[26] Yamada K,Funazaki K,Furukawa M. The Behavior of Tip Clearance Flow at Near-Stall Condition in a Transonic Axial Compressor Rotor[R]. ASME GT 2007-27725.
[27] Hah C,Voges M,Müller M W,et al. Characteristics of Tip Clearance Flow Instability in a Transonic Compressor[R]. ASME GT 2010-22101.
[28] Cahuzac A,Boudet J,Jacob M C,et al. Large-Eddy Simulation of a Rotor Tip-Clearance Flow[R]. AIAA2002-0981.
[29] ZHANF Hong-wu,DENG Xiang-yang,CHEN Jingyi,et al. Unsteady Tip Clearance Flow in an Isolated Axial Compressor Rotor[J]. Journal of Thermal Science,2005,14(3):211-219.
[2]黄国平,梁德旺,何志强.大型飞机辅助动力装置与微型涡轮发动机技术特点对比[J].航空动力学报,2008,23(2):383-388.
[3]楚武利,刘前智,胡春波.航空叶片机原理[M].西安:西北工业大学出版社,2009.
[4]吴艳辉,李清鹏,张卓勋,等.轴流压气机转子近失速工况点叶尖区流动非定常性分析[J].推进技术,2010,31(5):562-566.(WU Yan-hui,LI Qingpeng,ZHANG Zhuo-xun,et al. Unsteady Behavior ofTip Clearance Flow in an Axial Flow Compressor Rotor at near Stall Condition[J]. Journal of Propulsion Technology,2010,31(5):562-566.)
[5] Lei V M,Spakovszky Z S,Greitzer E M. A Criterion for Axial Compressor Hub-Corner Stall[J]. Journal of Turbomachinery,2008,130(3).
[6] Suder K L,Celestina M L. Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor[J]. Journal of Turbomachinery,1996,118(2):218-229.
[7] Feng L,Tong Z,Geng S,et al. A Summary of Stall Warning and Suppression Research with Micro Tip Injection[R]. ASME GT 2011-46118.
[8] Hah C,Rabe D C,Wadia A R. Role of Tip-Leakage Vortices and Passage Shock in Stall Inception in a Swept Transonic Compressor Rotor[R]. ASME GT 2004-53867.
[9] Vo H D,Tan C S,Greitzer E M. Criteria for Spike Initiated Rotating Stall[J]. Journal of Turbomachinery,2008,130(1).
[10] Hazby R H,Xu L. Role of Tip Leakage in Stall of a Transonic Centrifugal Impeller[R]. ASME GT 2009-59372.
[11]李相君,楚武利,张皓光.高负荷跨声速轴流压气机周向浅槽处理机匣扩稳机理[J].推进技术,2013,34(5):629-637.(LI Xiang-Jun,CHU Wu-li,ZHANG Hao-guang. Stabilizing Mechanism of Shallow Circumferential Grooves on a High Loaded Transonic AxialFlow Compressor[J]. Journal of Propulsion Technology,2013,34(5):629-637.)
[12] YANG Qi-chao,LI Lian-sheng,ZHAO Yuan-yang,et al. Experimental Investigation of an Active Control Casing Treatment of Centrifugal Compressors[J]. Experimental Thermal and Fluid Science,2017,83:107-117.
[13]曹四.机匣处理对跨声速离心压气机性能影响[J].推进技术,2017,38(4):772-778.(CAO Si. Effects of Casing Treatment on Performance of Transonic Centrifugal Compressor[J]. Journal of Propulsion Technology,2017,38(4):772-778.)
[14] Bae J. Active Control of Tip Clearance Flow in Axial Compressors[D]. Massachusetts:Massachusetts Institute of Technology,2001.
[15]李伟,乔渭阳,许开富.涡轮叶尖间隙泄漏涡不稳定性分析[J].推进技术,2008,29(2):204-207.(LI Wei,QIAO Wei-yang,XU Kai-fu. Unsteadiness of Tip Clearance Vortex in Turbine[J]. Journal of Propulsion Technology,2008,29(2):204-207.)
[16]胡子俊,张楠,姚惠之,等.涡判据在孔腔涡旋流动拓扑结构分析中的应用[J].船舶力学,2012,16(8):839-846.
[17] Seiichi I,Masato F,Kenichiro I,et al. Vortical Flow Structure and Loss Generation Process in a Transonic Centrifugal Compressor Impeller[R]. ASME GT 2007-27791.
[18] Hah C,Hathaway M,Katz J. Investigation of Unsteady Flow Field in a Low-Speed One and a Half Stage Axial Compressor:Effects of Tip Gap Size on the Tip Clearance Flow Structure at near Stall Operation[R]. ASME GT 2014-27094.
[19]杜娟.跨音压气机/风扇转子叶顶泄漏流动的非定常机制研究[D].北京:中国科学院研究生院,2010.
[20] Yamada K,Kikuta H,Furukawa M,et al. Effects of Tip Clearance Flow on Rotating Stall Inception Process in an Axial Compressor Rotor[R]. ASME GT 2013-95479.
[21] Lin F,Du J,Chen J,et al. Flow Structures in the Tip Region for a Transonic Compressor Rotor[R]. ASME GT2010-23025.
[22] Hah C,Bergner J,Schiffer H P. Tip Clearance Vortex Oscillation,Vortex Shedding and Rotating Instabilities in an Axial Transonic Compressor Rotor[R]. ASME GT2008-50105.
[23]洪树立,黄国平.引入DMD方法研究有/无控气流分离的动态结构[J].航空学报,2017,38(8).
[24] Crow S C. Stability Theory for a Pair of Trailing Vortices[J]. AIAA Journal,1970,8(12):2172-2179.
[25] Du J,Lin F,Zhang H,et al. Numerical Investigation on the Self-Induced Unsteadiness in Tip Leakage Flow for a Transonic Fan Rotor[J]. Journal of Turbomachinery-Transactions of ASME,2010,132(2).
[26] Yamada K,Funazaki K,Furukawa M. The Behavior of Tip Clearance Flow at Near-Stall Condition in a Transonic Axial Compressor Rotor[R]. ASME GT 2007-27725.
[27] Hah C,Voges M,Müller M W,et al. Characteristics of Tip Clearance Flow Instability in a Transonic Compressor[R]. ASME GT 2010-22101.
[28] Cahuzac A,Boudet J,Jacob M C,et al. Large-Eddy Simulation of a Rotor Tip-Clearance Flow[R]. AIAA2002-0981.
[29] ZHANF Hong-wu,DENG Xiang-yang,CHEN Jingyi,et al. Unsteady Tip Clearance Flow in an Isolated Axial Compressor Rotor[J]. Journal of Thermal Science,2005,14(3):211-219.