摘 要：本文在跨音速叶栅风洞中进行流动实验，对按相似原理放大的模型叶片的压力面和吸力面进行了压力测量，研究了接近真实状态的雷诺数以及马赫数对叶片流动系数的影响，并通过数值模拟来验证实验的准确程度。研究结果表明，压力面和吸力面的压力系数随着雷诺数的增大几乎没有变化；叶栅出口马赫数变化对叶片表面流动系数的分布呈现不同的规律；计算出的压力系数在大部分区域都与实验结果吻合较好。
关键词：高速叶栅风洞；叶片；雷诺数；马赫数；流动系数
中图分类号：V231.3 文献标识码：A 文章编号：2096-4706（2019）05-0007-04
Flow Experiment and Numerical Simulation of Turbine Blades Without Film Cooling
CHENG Wenjuan1，2，FU Meng1
（1.AECC Hunan Aviation Powerplant Research Institute，Zhuzhou 412002，China2.Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine ，Zhuzhou 412002，China）
Abstract：In this paper，flow experiments were carried out in a transonic cascade heat transfer wind tunnel，the pressure and suction surfaces of model blades enlarged according to similarity principle were measured.The effects of Reynolds number and Mach number on the flow coefficients of the blades were studied. The accuracy of the experiments was verified by numerical simulation. The results show that the pressure coefficients of pressure surface and suction surface hardly change with the increase of Reynolds number； the distribution of flow coefficients on blade surface varies with the change of Mach number at cascade outlet；and the calculated pressure coefficients agree well with the experimental results in most regions.
Keywords：short-duration transonic cascade wind tunnel；blades；Reynolds number；Mach number；transfeflowr coefficient
参考文献：
[1] Holger Brandt，Wolfgang Ganzert，Leonhard Fottner，2000，“A Presentation of Detailed Experimental Data of a Suction Side Film Cooled Turbine Cascade”，ASME 2000-GT-0296.
[2] Gregory M.Laski，Anil K.Toopadi，Michael C.Ostrowski，2007，“Heat Transfer Predictions of Film Cooled Stationary Turbine Airfoils，”ASME GT-2007-27497.
[3] Holger Brandt，Wolfgang Ganzert，Leonhard Fottner，2000，“Systematic Experimental and Numerical Investigations on the Aerothermodynamics of a Film Cooled Turbine Cascade With Variation of the Cooling Hole Shape：Part I — Experimental Approach”，ASME 2000-GT-0295.
作者简介：成文娟（1986-），女，汉族，山西临汾人，工程师， 硕士，研究方向：航空发动机涡轮结构设计。