亚声速进气道出口流场畸变控制研究

Investigation on flow distortion control of a subsonic inlet

关键词:  涡轮喷气发动机  进气道  进气道畸变  边界层分离  风洞试验

Key words:  Turbojet engine  Inlet  Inlet distortion  Boundary layer separation  Wind tunnel test

摘要:

一种亚声速进气道出口流场存在较严重的总压畸变,为改善其出口流场品质,抑制总压畸变,首先分析了引起总压畸变的原因,即进气道扩张段内边界层发生分离;其次提出了在进气道内安装叶片式涡流发生器的流动控制方法,并进行了仿真验证;最后进行了进气道缩比模型的风洞试验。试验结果表明,在进气道设计马赫数(0.65)和非设计马赫数(0.21)条件下,安装叶片式涡流发生器后,在流量系数0.4～0.85范围内,进气道出口流场的综合畸变指数分别平均降低14.7%和23.8%,因此验证了流动控制方法的有效性。

Abstract:

In order to suppress the total pressure distortion at the exit plane of a subsonic inlet,the cause was analyzed and it indicated that the boundary layer separated severely in the inlet diffuser section. Then the flow control method of vane-type vortex generators (VG) was proposed,and the simulation results showed that vane-type VG were effective to suppress flow separation. Finally,the wind tunnel experiment of inlet scale model with or without vane-type VG was developed. When operating at design Mach number (0.65) and off-design Mach number (0.21),respectively,the vane-type VG averagely decreased the inlet distortion index by 14.7% and 23.8%,respectively with flow coefficient of 0.5~0.85. This demonstrated that the proposed flow control method is effective.