Three-dimensional time-resolved measurements on rotor wake of low-speed axial compressor
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摘要: 对一台低速轴流压气机的转子尾迹进行了三维动态测量,采用锁相平均、方均根和功率谱密度等分析方法对低速轴流压气机转子在节流过程中尾迹流场的稳态和动态特征进行了研究.结果显示:在绝对坐标系下,转子尾迹有高总压和高方均根特征,且在不同叶高的强度不同;转子尾迹与主流的掺混作用导致平均总压升系数的快速衰减;功率谱密度分析表明,在接近失速点时,转子尾迹90%叶高以上出现0.5倍叶片通过频率的特征频带且其功率随着流量减小而增大.Abstract: Three-dimensional time-resolved measurements were conducted on the rotor wake of a low-speed axial compressor. Methods such as phase lock average, root mean square and power spectral density were used to analyze the steady and dynamic characteristics of the rotor wake of a low-speed axial compressor in throttle process. The results show that the rotor wake has high total pressure and high root mean square under absolute frame, and the wake intensity varies along spanwise direction. The averaged total pressure rise coefficient decreases sharply because of the interaction between the rotor wake and main flow. Power spectral density analysis shows that as the rotor running is close to stall, a frequency band around 0.5 blade passing frequency appears in the region over 90% span and its power increases as the mass flow decreases.
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[1] Mailach R,Vogeler K.Aerodynamic blade row interactions in an axial compressor:Part 1 unsteady boundary layer development[J].Journal of Turbomachinery,2004,126(1):35-44. [2] Mailach R,Vogeler K.Aerodynamic blade row interactions in an axial compressor:Part 2 unsteady 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 sub- and transonic operating conditions[R].ASME Paper GT2003-38020,2003. [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] 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):278-285. [6] Müller L,Mailach R,Vogeler K,et al.Unsteady blade loading with clocking in multistage axial compressors:Part 2[J]. Journal of Propulsion and Power,2010,26(1):36-45. [7] 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. [8] 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. [9] 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) [10] 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. [11] 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) [12] Van Zante D E,Suder K L,Strazisar A J,et al.An improved aspirating probe for total-temperature and total-pressure measurements in compressor flows[J].Journal of Turbomachinery,1995,117(4):642-649. [13] Han B,Goldstein R J.Instantaneous energy separation in a free jet:Part Ⅱ total temperature measurement[J].International Journal of Heat and Mass Transfer,2003,46(21):3983-3990. [14] Buttsworth D R,Jones T V.A fast-response total temperature probe for unsteady compressible flows[J].Journal of Engineering for Gas Turbines and Power,1998,120(4):694-702. [15] Buttsworth D R,Jones T V,Chana K S.Unsteady total temperature measurements downstream of a high-pressure turbine[J].Journal of Turbomachinery,1998,120(4):760-767. [16] Buttsworth D R,Jones T V.A fast-response high spatial resolution total temperature probe using a pulsed heating technique[J].Journal of Turbomachinery,1998,120(3):601-607. [17] Estevadeordal J,Gorrell S E,Copenhaver W W.PIV study of wake-rotor interactions in a transonic compressor at various operating conditions[J].Journal of Propulsion and Power,2007,23(1):235-242. [18] Wernet M P,Van Zante D,Strazisar T J,et al.Characterization of the tip clearance flow in an axial compressor using 3-D digital PIV[J].Experiments in Fluids,2005,39(4):743-753. [19] Corket T,Matlis E.AC plasma anemometer for hypersonic Mach number experiments[R].East Rutherford:American Physical Society,Division of Fluid Dynamics 56th Annual Meeting,2003. [20] Matlis E H,Corket T C,Gogineni S P.AC plasma anemometer for hypersonic Mach number experiments[R].Piscataway:21st International Congress on Instrumentation in Aerospace Simulation Facilities,2005. [21] Sieverding C H,Arts T,Denos R,et al.Measurement techniques for unsteady flows in turbomachines[J].Experiments in Fluids,2000,28(4):285-321. [22] Kupferschmied P,Kppel P,Gizzi W,et al.Time-resolved flow measurements with fast-response aerodynamic probes in turbomachines[J].Measurement Science and Technology,2000,11(7):1036-1054.
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