跨声轴流压气机转子尾迹的总压平均方法
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摘要
对一台跨声轴流压气机转子的尾迹流场进行了数值模拟研究和总压实验测量,结合理论分析方法,研究了面积平均和质量平均这两种常用的总压平均方法在跨声轴流压气机转子尾迹测量中的联系与差异.结果表明:在靠近转子尾缘的测量截面,由于转子尾迹流场中存在总压高而轴向速度低的区域,导致面积平均总压大于质量平均总压;而随着尾迹与主流在下游逐渐掺混均匀,面积平均总压又小于质量平均总压.两种总压平均方法的这一规律性关联可以在研究压气机转子尾迹特征尤其是进行数值计算和实验测量结果对比分析时提供一些有价值的参考.
Numerical simulation and experimental measurements were conducted to investigate the rotor wake of a transonic axial compressor.Combined with theoretical analysis,the relations between area-average total pressure and mass-average total pressure that are commonly calculated in transonic rotor wake flow fields were studied.The results showed that the area-average total pressures were larger than the mass-average total pressures at surfaces close to rotor trailing edge because of the existence of the wake flow,which had highertotal pressure and lower axial velocity than the main flow.However,the downstream areaaverage total pressure changed to become smaller than the mass-average total pressure as the wake dissipated under the interaction with the main flow.These results can provide some references for investigations on the compressor rotor wakes,especially during comparative analysis of computational and experimental results.
Numerical simulation and experimental measurements were conducted to investigate the rotor wake of a transonic axial compressor.Combined with theoretical analysis,the relations between area-average total pressure and mass-average total pressure that are commonly calculated in transonic rotor wake flow fields were studied.The results showed that the area-average total pressures were larger than the mass-average total pressures at surfaces close to rotor trailing edge because of the existence of the wake flow,which had highertotal pressure and lower axial velocity than the main flow.However,the downstream areaaverage total pressure changed to become smaller than the mass-average total pressure as the wake dissipated under the interaction with the main flow.These results can provide some references for investigations on the compressor rotor wakes,especially during comparative analysis of computational and experimental results.
引文
[1]Mailach R,Vogeler K.Aerodynamic blade row interactions in an axial compressor:Part 1unsteady boundary layer development[J].Journal of Turbomachinery,2004,126(1):35-44.
[2]Mailach R,Vogeler K.Aerodynamic blede row interactions in an axial compressor:Part 2unsteady pressure profile distribution and blade forces[J].Journal of Turbomachinery,2004,126(1):45-51.
[3]Zachcial A,Nurnberger D.A numerical study on the influence on vane-blade spacing on a compressor stage at suband transonic operating conditions[R].ASME Paper GT-2003-38020,2003.
[4]毛明明,宋彦萍,王仲奇.跨声压气机动静干涉效应的数值研究[J].航空动力学报,2007,22(9):1468-1474.MAO Mingming,SONG Yanping,WANG Zhongqi.Numerical research on influence of rotor-stator interactions in transonic compressor[J].Journal of Aerospace Power,2007,22(9):1468-1474.(in Chinese)
[5]Nolan S P R,Botros B B,Tan C S,et al.Effects of upstream wake phasing on transonic axial compressor performance[J].Journal of Turbomachinery,2011,133(2):021010.1-021010.12.
[6]邹正平,綦蕾,李维,等.上游尾迹与涡轮转子泄漏流相互作用数值模拟[J].航空动力学报,2010,25(1):58-65.ZOU Zhengping,QI Lei,LI Wei,et al.Numerical simulations of upstream wake-tip leakage vortex interactions in turbine rotor[J].Journal of Aerospace Power,2010,25(1):58-65.(in Chinese)
[7]CHEN Fu,GU Zhonghua,LU Huawei,et al.Experimental study of stator clocking effects in an axial compressor[J].Chinese Journal of Aeronautics,2006,19(4):278-185.
[8]Müller L,Mailach R,Vogeler K,et al.Unsteady blade loading with clocking in multistage axial compressors:Part2[J].Journal of Propulsion and Power,2010,26(1):36-45.
[9]Key N L,Lawless P B,Fleeter S.An experimental study of vane clocking effects on embedded compressor stage performance[J].Journal of turbomachinery,2010,132(1):011018.1-011018.10.
[10]Van Zante D E,Adamczyk J J,Strazisar A J,et al.Wake recovery performance benefit in a high-speed axial compressor[J].Journal of Turbomachinery,2002,124(2):275-284.
[11]史亚锋,吴虎,陈立新,等.轴向间距对某跨声速轴流压气机叶排间干扰的影响规律[J].航空动力学报,2011,26(5):1085-1091.SHI Yafeng,WU Hu,CHEN Lixin,et al.Effect of different axial spacing between blade rows on transonic axial compressor performance[J].Journal of Aerospace Power,2011,26(5):1085-1091.(in Chinese)
[12]Greitzer E M,Tan C S,Graf,M B.Internal flow concepts and applications[M].Cambridge:Cambridge University Press,2004:244-258.
[13]Kazimierski Z,Trojnarski J.Time-averaged pressure of fluctuating gas motion in small-diameter tubes[J].AIAA Journal,1987,25(4):567-572.
[14]Kazimierski Z,Horodko L.Total pressure averaging by small-diameter tubes in pulsating flows[J].AIAA Journal,1990,28(1):140-145.
[15]Camreron J D,Gendrich C P,Morris S C,et al.A transonic axial compressor facility for fundamental research and flow control development[R].AIAA-2006-416,2006.
[16]WANG Sichen,Morris S C,WANG Kai,et al.Numerical study on a Kiel probe used in rotor wake of a high-speed axial compressor[R].ACGT 2012-1070,2012.
[2]Mailach R,Vogeler K.Aerodynamic blede row interactions in an axial compressor:Part 2unsteady pressure profile distribution and blade forces[J].Journal of Turbomachinery,2004,126(1):45-51.
[3]Zachcial A,Nurnberger D.A numerical study on the influence on vane-blade spacing on a compressor stage at suband transonic operating conditions[R].ASME Paper GT-2003-38020,2003.
[4]毛明明,宋彦萍,王仲奇.跨声压气机动静干涉效应的数值研究[J].航空动力学报,2007,22(9):1468-1474.MAO Mingming,SONG Yanping,WANG Zhongqi.Numerical research on influence of rotor-stator interactions in transonic compressor[J].Journal of Aerospace Power,2007,22(9):1468-1474.(in Chinese)
[5]Nolan S P R,Botros B B,Tan C S,et al.Effects of upstream wake phasing on transonic axial compressor performance[J].Journal of Turbomachinery,2011,133(2):021010.1-021010.12.
[6]邹正平,綦蕾,李维,等.上游尾迹与涡轮转子泄漏流相互作用数值模拟[J].航空动力学报,2010,25(1):58-65.ZOU Zhengping,QI Lei,LI Wei,et al.Numerical simulations of upstream wake-tip leakage vortex interactions in turbine rotor[J].Journal of Aerospace Power,2010,25(1):58-65.(in Chinese)
[7]CHEN Fu,GU Zhonghua,LU Huawei,et al.Experimental study of stator clocking effects in an axial compressor[J].Chinese Journal of Aeronautics,2006,19(4):278-185.
[8]Müller L,Mailach R,Vogeler K,et al.Unsteady blade loading with clocking in multistage axial compressors:Part2[J].Journal of Propulsion and Power,2010,26(1):36-45.
[9]Key N L,Lawless P B,Fleeter S.An experimental study of vane clocking effects on embedded compressor stage performance[J].Journal of turbomachinery,2010,132(1):011018.1-011018.10.
[10]Van Zante D E,Adamczyk J J,Strazisar A J,et al.Wake recovery performance benefit in a high-speed axial compressor[J].Journal of Turbomachinery,2002,124(2):275-284.
[11]史亚锋,吴虎,陈立新,等.轴向间距对某跨声速轴流压气机叶排间干扰的影响规律[J].航空动力学报,2011,26(5):1085-1091.SHI Yafeng,WU Hu,CHEN Lixin,et al.Effect of different axial spacing between blade rows on transonic axial compressor performance[J].Journal of Aerospace Power,2011,26(5):1085-1091.(in Chinese)
[12]Greitzer E M,Tan C S,Graf,M B.Internal flow concepts and applications[M].Cambridge:Cambridge University Press,2004:244-258.
[13]Kazimierski Z,Trojnarski J.Time-averaged pressure of fluctuating gas motion in small-diameter tubes[J].AIAA Journal,1987,25(4):567-572.
[14]Kazimierski Z,Horodko L.Total pressure averaging by small-diameter tubes in pulsating flows[J].AIAA Journal,1990,28(1):140-145.
[15]Camreron J D,Gendrich C P,Morris S C,et al.A transonic axial compressor facility for fundamental research and flow control development[R].AIAA-2006-416,2006.
[16]WANG Sichen,Morris S C,WANG Kai,et al.Numerical study on a Kiel probe used in rotor wake of a high-speed axial compressor[R].ACGT 2012-1070,2012.