进气道旋流模拟及测量的风洞试验研究  

Research on Simulation and Measurement of Inlet Swirl by Wind Tunnel Test

作　　者：邓小宝[1] 姜健[1] 屈霁云[1] 张堃元[2] 叶飞[2] 

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《燃气涡轮试验与研究》2009年第4期51-56,共6页Gas Turbine Experiment and Research

摘　　要：利用设计的叶片式旋流发生器,在某小型低速风洞中进行了整体涡旋流、局部涡旋流、对涡旋流的模拟,对三孔探针、五孔探针进行了标定,对所模拟出的旋流进行了测量。风洞试验结果表明:发动机进口前2倍直径处安装旋流发生器可保证旋流的强度最大;设计的旋流发生器可产生28°的整体涡旋流;旋流发生器叶片攻角对旋流强弱的影响较为明显;不同叶片布局方式可得到不同形式的旋流流场;旋流的诱导速度对旋流中心位置有较大的影响;三孔探针用于测量旋流时受径向偏转气流的影响,时有不稳定现象。Applying designed swirl generator, local swirl and bulk swirl and twin swirl were simulated in a low-speed wind tunnel facility. Three-hole probe and five-hole probe were calibrated and used to measure the generated swirl. The results of the wind tunnel test show that： （1） Fixing generator two times of diameter before the engine inlet can make sure the strongest intensity of the simulated swirl. （2） The intensity of generated bulk swirl at 0.87R can reach to 28 degree. （3） The angle of attack affects swirl intensity most. （4） All kinds of typical swirl can be simulated by different blade distribution. （5） Induced velocity has definite effect on the center of the simulated swirl. （6） Using three-hole probe to measure swirl may generate unstableness because of the existence of radial velocity.

关 键 词：进气道 旋流 旋流发生器 三孔探针 五孔探针 风洞试验 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]