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  

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

作　　者：李井洋[1,2] 马宏伟[1] 贺象[1] 

机构地区：[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

出　　处：《航空动力学报》2012年第10期2262-2268,共7页Journal of Aerospace Power

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

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.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.

关 键 词：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 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]