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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。
In order to improve the quality of the exit flow field and suppress the total pressure distortion, a reason why the total pressure distortion is caused is firstly analyzed. That is, the boundary layer of the inlet expansion section Then the flow control method of installing the vortex vortex generator in the air intake is put forward and simulated. Finally, the wind tunnel test of the inlet reduction model is carried out. The experimental results show that when the vortex generator with vane design Mach number (0.65) and non-design Mach number (0.21) is installed, the flow field at the outlet of the inlet is within the range of flow coefficient of 0.4-0.85 The distortion index decreased by 14.7% and 23.8% respectively on average, thus verifying the effectiveness of the flow control method.