高超声速飞行器激波干扰区缝隙流动传热特性研究

Heat Transfer Characteristics of Gap Flows in Shock-Wave Interference Region of Hypersonic Vehicles

针对高超声速飞行器激波干扰区附近缝隙流动传热问题,建立激波发生器和缝隙的二维模型,利用CFD仿真分析技术,分别研究了激波作用于缝隙前、缝隙中和缝隙后情况下缝隙内部流动传热特性。结果表明,相比较无激波的状态,激波作用于缝隙前和缝隙中时,会明显改变缝隙内部流体的旋涡结构,使得缝隙内部流动强度和热量急剧增加;当激波作用于缝隙后部时,缝隙内部流体的旋涡结构没有明显改变,且靠近缝隙口的远端壁面热流有局部降低,有利于热防护结构的维型。研究结果表明,结构热防护设计时应避免激波作用在缝隙前部和中部的位置。

In view of the heat transfer problems of gap flows near the shock-wave interference region of hypersonic vehicles,a two-dimensional model of the shock generator and gap was established.By using CFD technology,the internal flow heat transfer characteristics with shock waves in the front,middle and back of the gap were studied.The results showed that compared to the flow fields without shock wave,the vortex structure of the flow inside the gap changes obviously when the shock wave acts on the front and middle of the gap,resulting in a sharp increase in the flow intensity and heat inside the gap.However,when the shock wave acts on the rear part of the gap,the vortex structure inside the gap does not change significantly,and the far-end wall heat flux near the gap lip decreases locally,which is beneficial to the shape protection of the thermal protection structure.The results clearly indicated that it is necessary to avoid the position where shock wave acts on the front and middle part of gap in structural thermal protection design.