摘要
对于超音速进气道来说,激波／边界层相互干扰是常见的现象,达到一定程度甚至会出现边界层的分离,并最终影响到发动机的正常运转。所以,对进气道边界层的有效控制对于推进系统是至关重要的。吹除式边界层控制是一种非常有效的方法。
本文以二维平板／楔结构为基础,首先,数值模拟了斜激波冲击平板诱导平板边界层产生分离的现象,并得出相应的分离区的范围。然后,构造了带有吹除喷嘴的模型。数值模拟了加入边界层的吹除控制后,流场中产生的现象。比较了有／无边界层吹除控制的流场波系结构和壁面参数分布。最后,计算并比较了不同的喷嘴进口压力和相对位置,边界层吹除控制对分离区和流场的影响情况。
结果表明,数值模拟边界层的吹除控制是可行的。边界层的吹除对于激波／边界层分离和边界层的厚度能够进行有效地控制。在加入吹除控制的情况下,流场中波系发生了复杂的变化,出现了激波之间,激波和膨胀波之间的相互作用,这种现象的主要影响因素是吹除喷嘴的进口总压和吹除喷嘴的位置。
Shock wave/boundary layer interaction is a universal phenomenon in supersonic inlets. It will cause the separation of boundary layer when this phenomenon reach to a certain extent, and this will eventually produce an effect on the nomal work of the engine. So, efficient control of inlet boundary layers is essential for propulsion systems, blowing boundary layer control is a good one which is worth studying.
In this paper, first of all, the separation of boundary layer induced by impinging shock-wave generated by 2D wedge/plate configuration is numerically studied, and the scope of the separation is given. Then, a 2D wedge/plate configuration with a blowing nozzle is designed. Based on this model, the phenomenon of flow field is numerically studied. A comparison between the two model is drawn, which is about the wave structure of the flow field and the distribution of the parameters along wall. At last, the effects of entrance pressure and relative position of the nozzle on the separation region and flow field are compared and analyzed.
The results show that, numerical simulation of blowing boundary layer control is feasible. The separation of shock wave/boundary layer and the thinkness of boundary layer can be controlled effectively by a blowing boundary layer control system. However, there are complex changes in the flow field. Specifically, the interactions between shock waves, the interactions between shock wave and dilatiational wave, the main influencing factor is the blowing total pressure of the nozzle, the relative position of the blowing nozzle is other factor.
引文
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