压气机试验用流量管气动设计与应用验证  

Aerodynamic Design and Application Validation of Flow Tube Used in Compressor Experiment

作　　者：向宏辉[1,2] 侯敏杰[2] 葛宁[1] 刘志刚[2] 魏崇[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司中国燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油621703

出　　处：《燃气轮机技术》2015年第4期28-34,共7页Gas Turbine Technology

摘　　要：针对压气机性能试验中存在的流量管应用问题,采用附面层厚度修正与实流标定方法,开展了系列流量管流量系数的吹风校准试验,分析了两种校准方法的差异、不同流量管壁面静压分布特性与流量系数变化规律。研究结果表明:在消除试验舱漏气和探针流道堵塞影响作用后,标准音速喷嘴实流标定结果与附面层厚度修正结果吻合,实测流量与计算流量的最大相对偏差为0.3%;流量管壁面静压对来流马赫数变化的数值敏感性可作为评定流量管有效工作范围上限的重要依据;不同流量管附面层粘性堵塞影响程度较为接近,可以采用统一平均流量系数来综合评定流量管的气动特性,本文给定的统一平均流量系数为0.995 4。Based on flow tube application problems that existed in the compressor aerodynamic performance experiment, a series of cal- ibration experiment of flow tubes flow coefficient were conducted using boundary layer thickness correction and real sonic nozzle flow calibration methods, furthermore, the comparison of both calibration methods, the different flow tubes wall surface static pressure dis- tribution characteristics and flow coefficient variation law were analyzed in detail. The results show that the real flow calibration results of standard sonic nozzle are consistent with the results of boundary layer thickness correction in avoiding experimental facility cabin leakage and the measuring probes flow blocking effect, the maximum relative deviation between the measured and calculational flow is 0.3%. The numerical sensitivity of wall surface static pressure to inlet Mach number can be used as an important basis for assessing the upper limit of the effective operating range of flow tube. The viscous boundary layer blockage impact of different flow tube is rela- tively close, unified average flow coefficient can be used to comprehensive evalution of the aerodynamic characteristic of flow tube, in this paper, the given unified average flow coefficient is O. 994 5.

关 键 词：流量管 附面层厚度 附面层位移厚度 流量系数 音速喷嘴 校准试验 

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]