| Citation: | MA Hongwei, HE Xiang, SHAN Xiaoming, et al. A method for measuring 3-D unsteady flow at exits of a compressor rotor using combined probes[J]. Journal of Aerospace Power, 2022, 37（10）：2253-2260 doi: 10.13224/j.cnki.jasp.20220276
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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.
| [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.1992.02.017
LI 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.1992.02.016
JIANG 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.1000-8055.2000.02.002
MA 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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