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

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

1.
北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京 100191
2.
中国航空工业集团公司沈阳发动机设计研究所,沈阳 110015

基金项目: 国家自然科学基金(51161130525); 高等学校学科创新引智计划(B07009)

计量
- 文章访问数: 1726
- HTML浏览量: 1
- PDF量: 572
- 被引次数: 0
出版历程
- 收稿日期: 2012-02-29
- 刊出日期: 2012-10-28

Method of measuring 3-D unsteady flow at exits of transonic compressor rotor passages using a two-hole tip-wedge pressure probe

1.
National Key Laboratory of Science and Technology on Aero-Engines Thermo-dynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China
2.
Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China,Shenyang 110015,China

摘要

摘要: 发展了1种楔顶圆柱双孔高频压力探针测量三维动态流场的方法,并应用于某跨声速多级轴流压气机转子出口流场测量.该探针测量方法基于4孔针测量原理,通过旋转探针在3个角度测量的方法实现,并采用最小二乘拟合方法对探针气动校准数据进行处理,对拟合误差进行优化,得到最佳拟合阶次,进而获得精度较高的求解流场参数的近似函数.相比国内外同类探针,该楔顶圆柱双孔高频压力探针尺寸小、频响快、测量范围宽、测量精度高.借助高速锁相数据采集技术,利用该探针测量了某跨声速多级压气机转子出口三维动态流场,测量结果反映了该转子流动特征,提供了转子出口气流偏转角、俯仰角、总压、马赫数分布,并为优化压气机级间匹配指明了方向,为压气机流场诊断提供了一套行之有效的测量手段,验证了该高频压力探针测量技术的工程应用价值.
- 跨声速多级轴流压气机 /
- 级间测量 /
- 高频压力探针 /
- 误差分析 /
- 三维流场
Abstract: A method of measuring 3-D(three-dimensional) dynamic flow field with a two-hole fast-response tip-wedged cylindrical pressure probe has been developed and applied in a transonic multistage axial compressor.The measuring method was based on the four-hole pneumatic probe and realized by rotating the probe at three angular positions.The least square fitting method was used to process the calibration data and the optimal fitting order was determined through optimizing the fitting error.In this way,the approximate functions of the flow parameters with higher accuracy were obtained.The probe is characterized by small size,high frequency,wide measurement range and high measurement precision compared with other similar probes.The unsteady flow field at the exit of the rotor was measured utilizing phase locked technique.The measurement results reflect the flow features of the compressor rotor,providing distributions of flow yaw angle,pitch angle,total pressure and Mach number at the rotor exit,which is the key to optimize the stage performance.Therefore,it verifies the engineering application of this fast-response pressure probe measuring technique which can provide a feasible measurement method for the flow diagnoses in transonic multistage compressors.
- transonic multistage axial compressor /
- inter-stage measurement /
- fast-response pressure probe /
- error analysis /
- 3-D (three-dimensional) flow field

HTML

参考文献(16)

[1]	Kupferschmied P,Köppel P,Gizzi W,et al.Time-resolved flow measurements with fast-response aerodynamic probes in turbomachines[J].Measurement Science Technology,2000,11(7):1036-1054.
[2]	Ainsworth R W,Miller R J,Moss R W,et al.Unsteady pressure measurement[J].Measurement Science Technology,2000,11(7):1055-1076.
[3]	Sieverding C,Arts T,Denos R,et al.Measurement techniques for unsteady flows in turbomachines[J].Experiments in Fluids,2000,28(4):285-321.
[4]	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.
[5]	Georgakis C,Bennett I,Ivey P C.Fast response probes measuring unsteady flows in high-speed research compressors .ASME GT2003-38160,2003.
[6]	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) .ASME GT2003-38128,2003.
[7]	Brouckaert J F.Fast response aerodynamic probes for measurements in turbomachines[J].Journal of Power and Energy,2007,221(6):801-813.
[8]	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)
[9]	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. 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)
[10]	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. 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)
[11]	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 //SHEN Xiong,SUN Xijiu.Proceedings of International Conference on Fluid Dynamic Measurement and its Applications,D-9.Beijing:Interational Academic Publishers,1989:428-434.
[12]	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)
[13]	蒋浩康,马宏伟.压气机转子三维紊流流场[J].航空动力学报,1998,19(3):287-292. JIANG Haokang,MA Hongwei.Three-dimensional turbulent flow field of axial compressor rotor passage[J].Journal of Aerospace Power,1998,19(3):287-292.(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,2000,15(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,2000,15(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. 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)
[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)