A method for measuring 3-D unsteady flow at exits of a compressor rotor using combined probes
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摘要:
提出了一种组合高频压力探针测量跨声速多级压气机级间三维动态流场的方法，组合探针由经过风洞三维气动校准的圆柱单孔、楔顶单孔两支高频压力探针组成，采用位移机构将两支探针安装到被测压气机级间相同轴向位置和径向位置、不同周向位置的测点，采用锁相采样技术和旋转探针技术，在探针不同角度位置下各自获得级间动态压力信息，利用气动校准数据处理测量数据，可获取级间三维气动参数沿周向和径向的分布。和现有三维动态探针相比，具有尺寸小、空间分辨率高、频响快、测量范围宽、对被测流场干扰小、能测量小型压气机级间流场参数动态变化的特点。与二维动态压力探针相比，能测量气流俯仰角，测得的总压、静压和马赫数更准确，能更全面反映压气机级间三维流动特征，为小型跨声速多级轴流压气机流场诊断提供了一套有效的三维动态测量手段。
Abstract:A method for measuring 3-D unsteady flow at an exit of a transonic multistage compressor rotor was presented by using combined high-response pressure probes consisting of a cylinder 1-hole probe and a tip-wedged 1-hole probe, which were calibrated in a wind tunnel. The probes were put in the inter-stage at the same axial and radial but different tangential positions with the help of two traverse mechanisms, and unsteady pressure data were obtained utilizing a phase-locked technique at different angular positions. Distributions of 3-D flow parameters were obtained through data processing. Result showed that the combined probes were characterized by small size, high frequency, wide measurement range and weak interrupt compared with other current 3-D high-response probes, while the method can obtain flow pitch angle and more accurate total pressure, static pressure and Mach number compared with 2-D high-response probe techniques. The combined-probe technique provides a feasible 3-D flow measurement method for flow diagnosis in small multistage compressors.
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图 2 马赫数为0.5的圆柱单孔探针压力系数
Figure 2. Pressure coefficients of cylinder probe at Mach number of 0.5
图 3 马赫数为0.5的楔顶单孔探针压力系数
Figure 3. Pressure coefficients of tip-wedged probe at Mach number of 0.5
图 4 静压角与马赫数和俯仰角的关系
Figure 4. Relationship between static pressure angle and Mach number and pitch angle
图 5 总压系数和马赫数和俯仰角的关系
Figure 5. Relationship between total pressure coefficient and Mach number and pitch angle
图 6 俯仰系数与马赫数和俯仰角的关系
Figure 6. Relationship between pitch coefficient and Mach number and pitch angle
图 7 同相点锁相平均压力随探针角度变化
Figure 7. Variation of phase-locked averaged pressure at the same phase point with probe angle
图 10 组合探针测得第3级级间俯仰角云图
Figure 10. Contours of pitch angle at exit of 3rd rotor measured by combined probe
图 11 组合探针测得第3级级间俯仰角云图（局部）
Figure 11. Contours of pitch angle at exit of 3rd rotor measured by combined probe （part）
图 12 组合探针测得第3级级间偏转角云图
Figure 12. Contours of yaw angle at exit of 3rd rotor measured by combined probe
图 16 圆柱单孔探针与组合探针测得偏转角沿叶高分布
Figure 16. Spanwise variation of yaw angles measured by cylinder probe and combined probe
图 17 圆柱单孔探针与组合探针测得俯仰角沿叶高分布
Figure 17. Spanwise variation of pitch angles measured bycylinder probe and combined probe
图 18 圆柱单孔探针与组合探针测得静压沿叶高分布
Figure 18. Spanwise variation of static pressure measured by cylinder probe and combined probe
图 19 圆柱单孔探针与组合探针测得总压沿叶高分布
Figure 19. Spanwise variation of total pressure measured by cylinder probe and combined probe
图 20 圆柱单孔探针与组合探针测得马赫数沿叶高分布
Figure 20. Spanwise variation of Mach number measured by cylinder probe and combined probe
图 21 圆柱单孔探针测量总压和静压偏差沿叶高分布
Figure 21. Spanwise variation of total and static pressure deviations measured by cylinder probe
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[1] MA Hongwei,JIANG Haokang. Three-dimensional turbulent flow of the tip leakage vortex in an axial compressor rotor passage[R]. ASME 2000-GT-503,2000. [2] MA Hongwei,WEI Wei,OTTAVY X. Experimental investigation of flow field in a laboratory-scale compressor[J]. Chinese Journal of Aeronautics,2017,30(1): 31-46. doi: 10.1016/j.cja.2016.09.016 [3] MA Hongwei ,JIANG Haokang. Three-dimensional turbulent flow field downstream of a single-stage axial compressor rotor[R]. ASME 2000-GT-499,2000. [4] MA Hongwei,ZHANG Jun,ZHANG Jinghui,et al. Experimental study of effects of grooved tip clearances on the flow field in a compressor cascade passage[J]. Journal of Turbomachinery,2012,134(5): 051012.1-051012.12. [5] PERSICO G,GAETANI P,GUARDONE A. Design and analysis of new concept fast-response pressure probes[J]. Measurement Science and Technology,2005,16(9): 1741-1750. doi: 10.1088/0957-0233/16/9/005 [6] GEORGAKIS C,BENNETT I,IVEY P C. Fast response probes measuring unsteady flows in high-speed research compressors[R]. ASME GT2003-38160,2003. [7] PFAU A,SCHLIENGER J,KALFAS A I,et al. Unsteady,3-dimensional flow measurement using a miniature virtual 4 sensor fast response aerodynamic probe (FRAP)[R]. ASME GT2003-38128,2003. [8] BROUCKAERT J F. Fast response aerodynamic probes for measurements in turbomachines[J]. Journal of Power and Energy,2007,221(6): 801-813. [9] 蒋浩康,李雨春,张洪,等. 研究转子内流动的大尺寸轴流压气机实验装置和动态测量技术[J]. 航空动力学报,1992,7(1): 1-8.JIANG Haokang,LI Yuchun,ZHANG Hong,et al. A large-scale axial flow compressor facility and dynamic measurement techniques for rotor flow study[J]. Journal of Aerospace Power,1992,7(1): 1-8. (in Chinese) [10] 李雨春,蒋浩康. 圆柱单孔高频压力探针测量高亚音速二维周期流场的方法[J]. 航空动力学报,1992,7(2): 164-166. doi: 10.13224/j.cnki.jasp.1992.02.017LI Yuchun,JIANG Haokang. A method for measuring high-subsonic two-dimensional periodic flow field using a single-hole high-response cylindrical pressure probe[J]. Journal of Aerospace Power,1992,7(2): 164-166. (in Chinese) doi: 10.13224/j.cnki.jasp.1992.02.017 [11] 蒋浩康,李雨春,赵全春,等. 高速多级风扇转子后流场测量[J]. 航空动力学报,1992,7(2): 159-163. doi: 10.13224/j.cnki.jasp.1992.02.016JIANG Haokang,LI Yuchun,ZHAO Quanchun,et al. Rotor exit flow measurements in a high-speed multistage fan[J]. Journal of Aerospace Power,1992,7(2): 159-163. (in Chinese) doi: 10.13224/j.cnki.jasp.1992.02.016 [12] JIANG H K,LI Y C,XU L. A two-inclined-hole high frequency pressure probe for measurements of three-dimensional periodic flow field in turbomachines[R]. Beijing:International Conference on Fluid Dynamic Measurement and Its Applications,1989. [13] 马宏伟,蒋浩康. 压气机不同状态下转子出口三维紊流流场[J]. 航空动力学报,1997,12(3): 268-272.MA Hongwei,JIANG Haokang. 3D turbulent flow at compressor rotor exit under different flow conditions[J]. Journal of Aerospace Power,1997,12(3): 268-272. (in Chinese) [14] 马宏伟,蒋浩康. 压气机转子出口流场的发展及三维紊流特性[J]. 航空动力学报,1997,12(2): 113-118.MA Hongwei,JIANG Haokang. Development of three-dimensional turbulent flow field at exit of an axial compressor rotor passage[J]. Journal of Aerospace Power,1997,12(2): 113-118. (in Chinese) [15] 马宏伟,蒋浩康,董玉玺. 单转子轴流压气机不同状态下进出口三维时均流场[J]. 航空动力学报,2000,15(2): 119-123. doi: 10.3969/j.issn.1000-8055.2000.02.002MA Hongwei,JIANG Haokang,DONG Yuxi. Three-dimensional mean flow at both inlet and exit of an isolated axial compressor rotor passage in different conditions[J]. Journal of Aerospace Power,2000,15(2): 119-123. (in Chinese) doi: 10.3969/j.issn.1000-8055.2000.02.002 [16] 马宏伟,蒋浩康. 速度梯度、近壁效应和Re数对压力探针测量误差的影响[J]. 航空动力学报,1995,10(4): 337-342.MA Hongwei,JIANG Haokang. Effects of velocity gradient,wall-proximity and Reynolds number on measuring errors of pressure probes[J]. Journal of Aerospace Power,1995,10(4): 337-342. (in Chinese) [17] 李井洋,马宏伟,贺象. 楔顶双孔探针测量跨声多级压气机转子出口三维动态流场的方法[J]. 航空动力学报,2012,27(10): 2262-2268.LI Jingyang,MA Hongwei,HE Xiang. Method of measuring 3-D unsteady flow at exits of transonic compressor rotor passage using a two-hole tip-wedge pressure probe[J]. Journal of Aerospace Power,2012,27(10): 2262-2268. (in Chinese) [18] 马宏伟,贺象,单晓明,等. 一种测量跨音速多级压气机转子出口二维流场的方法[J]. 推进技术,2013,34(6): 754-759.MA Hongwei,HE Xiang,SHAN Xiaoming,et al. A method of measuring 2D flow-field at rotor exits of transonic multistage compressor[J]. Journal of Propulsion Technology,2013,34(6): 754-759. (in Chinese) -
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