动叶下游非定常特征的实验
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摘要
在自主搭建的低速大尺寸轴流压气机实验台上,使用动态四孔探针和壁面安装的Kulite动态压力传感器进行了详细的实验测量,研究了动叶下游的非定常特征及其流动机理。通过分析动叶下游总压的功率谱密度PSD(power spectrum density),发现在叶顶区域存在0.4倍叶片通过频率BPF(blade passing frequency)左右的非定常频带。这种总压波动频带主要是由轴向速度的波动引起,随流量工况点接近失速点而逐渐增强,在向下游传播的过程中逐渐衰减。波动区域根据总压PSD的衰减速度可以分成两个部分,靠近机匣壁面的部分波动强度衰减较快。综合分析动叶下游的涡量和机匣壁面静压PSD等测量结果,发现这种非定常频带的强弱和衰减跟叶顶泄漏涡与边界层、尾迹的互相作用密切相关。
Dynamic measurements were performed on a large scale low speed research compressor,with a dynamic four-hole probe and casing-mounted Kulite dynamic pressure transducer to study the unsteady flow feature downstream the rotor and its flow mechanism.PSD(power spectrum density)spectrum around 0.4 times BPF(blade passing frequency)was found in tip region at rotor exit.The fluctuation intensity was enhanced during throttling process and decayed gradually while propagating downstream.The unsteady region can be divided into two parts according to the decay rate of total pressure PSD.It indicated that the intensity of the fluctuation was determined by the interaction between tip leakage flow and casing boundary layer flow based on the analysis of vorticity at rotor exit and static pressure PSD on casing,etc.
Dynamic measurements were performed on a large scale low speed research compressor,with a dynamic four-hole probe and casing-mounted Kulite dynamic pressure transducer to study the unsteady flow feature downstream the rotor and its flow mechanism.PSD(power spectrum density)spectrum around 0.4 times BPF(blade passing frequency)was found in tip region at rotor exit.The fluctuation intensity was enhanced during throttling process and decayed gradually while propagating downstream.The unsteady region can be divided into two parts according to the decay rate of total pressure PSD.It indicated that the intensity of the fluctuation was determined by the interaction between tip leakage flow and casing boundary layer flow based on the analysis of vorticity at rotor exit and static pressure PSD on casing,etc.
引文
[1]CAMP T R,DAY I J.A study of spike and modal stall phenomena in a low-speed axial compressor[J].Journal of Turbomachinery,1998,120(7):393-401.
[2]DAY I J.Stall inception in axial flow compressors[J].Journal of Turbomachinery,1993,115(1):1-9.
[3]MCDOUGALL N M,CUMPSTY N A,HYNES T P.Stall inception in axial flow compressors[J].Journal of Turbomachinery,1990,112(1):116-125.
[4]VO H D,TAN C S,GREITZER E M.Criteria for spike initiated rotating stall[J].Journal of Turbomachinery,2008,130(1):1-9.
[5]BENNINGTON M A,ROSS M H,DU J,et al.An experimental and computational investigation of tip clearance flow and its impact on stall inception[R].ASME Paper2010-GT-23516,2010.
[6]邓向阳.压气机叶顶间隙流的数值模拟研究[D].北京:中国科学院,2006.DENG Xiangyang.Numerical investigation on tip clearance flow in compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
[7]童志庭.轴流压气机中叶尖泄漏涡、失速先兆、叶尖微喷气非定常关联性的实验研究[D].北京:中国科学院,2006.TONG Zhiting.The interactive unsteady mechanism between tip leakage vortex,stall inception and micro tip injection in low-speed axial compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
[8]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,2010.DU Juan.Investigation on the unsteady mechanism of tip leakage flow in transonic compressor/fan rotors[D].Beijing:Chinese Academy of Sciences,2010.(in Chinese)
[9]MAILACH R,LEHMANN I,VOGELER K.Rotating instabilities in an axial compressor originating from the fluctuating blade tip vortex[J].Journal of Turbomachinery,2001,123(3):453-460.
[10]FURUKAWA M,SAIKI K,YAMADA K,et al.Unsteady flow behavior due to breakdown of tip leakage vortex in an axial compressor rotor at near-stall condition[J].Journal of Engineering for Gas Turbines and Power,1986,108(1):7-14.
[11]王偲臣.稳定性调控状态下的轴流压气机转子叶顶尾迹实验研究[D].北京:中国科学院,2013.WANG Sichen.Experimental investigation on rotor tip wake of axial compressors with stability controls[D].Beijing:Chinese Academy of Sciences,2013.(in Chinese)
[12]姚君,聂超群,李成勤.基于数字信号处理实现的三维动态探针研制[J].工程热物理学报,2010,31(10):1651-1654.YAO Jun,NIE Chaoqun,LI Chengqin.The development of fast response aerodynamic probe based on digital signal processing[J].Journal of Engineering Thermalphysics,2010,31(10):1651-1654.(in Chinese)
[13]WISLER D C.Loss reduction in axial-flow compressors through low-speed model testing[J].Journal of Engineering for Gas Turbines and Power,1985,107(4):354-363.
[14]MLLER R,MAILACH R,LEHMANN I.The design and construction of a four-stage low-speed research compressor[R].Gdansk,Poland:The IMP'97 Conference on Modelling and Design in Fluid-Flow Machinery,1997.
[15]林峰,张堃元,彭成一.五孔探针的标定技术[J].航空动力学报,1990,5(3):236-238.LIN Feng,ZHANG Kunyuan,PENG Chengyi.Calibration technique of five-hole probe[J].Journal of Aerospace Power,1990,5(3):236-238.(in Chinese)
[16]INOUE M,KUROUMARU M.Three-dimensional structure and decay of vortices behind an axial flow rotating blade row[J].Journal of Engineering for Gas Turbines and Power,1984,106(3):561-569.
[17]INOUE M,KUROUMARU M.Structure of tip clearance flow in an isolated axial compressor rotor[J].Journal of Turbomachinery,1989,111(3):250-256.
[2]DAY I J.Stall inception in axial flow compressors[J].Journal of Turbomachinery,1993,115(1):1-9.
[3]MCDOUGALL N M,CUMPSTY N A,HYNES T P.Stall inception in axial flow compressors[J].Journal of Turbomachinery,1990,112(1):116-125.
[4]VO H D,TAN C S,GREITZER E M.Criteria for spike initiated rotating stall[J].Journal of Turbomachinery,2008,130(1):1-9.
[5]BENNINGTON M A,ROSS M H,DU J,et al.An experimental and computational investigation of tip clearance flow and its impact on stall inception[R].ASME Paper2010-GT-23516,2010.
[6]邓向阳.压气机叶顶间隙流的数值模拟研究[D].北京:中国科学院,2006.DENG Xiangyang.Numerical investigation on tip clearance flow in compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
[7]童志庭.轴流压气机中叶尖泄漏涡、失速先兆、叶尖微喷气非定常关联性的实验研究[D].北京:中国科学院,2006.TONG Zhiting.The interactive unsteady mechanism between tip leakage vortex,stall inception and micro tip injection in low-speed axial compressor[D].Beijing:Chinese Academy of Sciences,2006.(in Chinese)
[8]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,2010.DU Juan.Investigation on the unsteady mechanism of tip leakage flow in transonic compressor/fan rotors[D].Beijing:Chinese Academy of Sciences,2010.(in Chinese)
[9]MAILACH R,LEHMANN I,VOGELER K.Rotating instabilities in an axial compressor originating from the fluctuating blade tip vortex[J].Journal of Turbomachinery,2001,123(3):453-460.
[10]FURUKAWA M,SAIKI K,YAMADA K,et al.Unsteady flow behavior due to breakdown of tip leakage vortex in an axial compressor rotor at near-stall condition[J].Journal of Engineering for Gas Turbines and Power,1986,108(1):7-14.
[11]王偲臣.稳定性调控状态下的轴流压气机转子叶顶尾迹实验研究[D].北京:中国科学院,2013.WANG Sichen.Experimental investigation on rotor tip wake of axial compressors with stability controls[D].Beijing:Chinese Academy of Sciences,2013.(in Chinese)
[12]姚君,聂超群,李成勤.基于数字信号处理实现的三维动态探针研制[J].工程热物理学报,2010,31(10):1651-1654.YAO Jun,NIE Chaoqun,LI Chengqin.The development of fast response aerodynamic probe based on digital signal processing[J].Journal of Engineering Thermalphysics,2010,31(10):1651-1654.(in Chinese)
[13]WISLER D C.Loss reduction in axial-flow compressors through low-speed model testing[J].Journal of Engineering for Gas Turbines and Power,1985,107(4):354-363.
[14]MLLER R,MAILACH R,LEHMANN I.The design and construction of a four-stage low-speed research compressor[R].Gdansk,Poland:The IMP'97 Conference on Modelling and Design in Fluid-Flow Machinery,1997.
[15]林峰,张堃元,彭成一.五孔探针的标定技术[J].航空动力学报,1990,5(3):236-238.LIN Feng,ZHANG Kunyuan,PENG Chengyi.Calibration technique of five-hole probe[J].Journal of Aerospace Power,1990,5(3):236-238.(in Chinese)
[16]INOUE M,KUROUMARU M.Three-dimensional structure and decay of vortices behind an axial flow rotating blade row[J].Journal of Engineering for Gas Turbines and Power,1984,106(3):561-569.
[17]INOUE M,KUROUMARU M.Structure of tip clearance flow in an isolated axial compressor rotor[J].Journal of Turbomachinery,1989,111(3):250-256.