超燃冲压发动机U型冷却通道的流道方案  

Flow channel scheme of U-shaped cooling channel in scramjet

作　　者：胡家瑛 王振国[1] 潘余[1] 李佩波[1] HU Jiaying;WANG Zhenguo;PAN Yu;LI Peibo(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航空动力学报》2022年第1期11-25,共15页Journal of Aerospace Power

摘　　要：对四流道U型流道平板的不同流道方案进行三维仿真模拟。主要针对同向入口U型流道平板和反向入口U型流道平板这两种构型进行研究,并在每一种构型中采用不同的冷却剂出入口方案,并对不同方案的冷却效果进行研究和对比。研究表明:两种构型的出入口相间排布的流道方案更适合于有一定规律的非均匀热流;两种构型的入口流道位于平板两侧的流道方案,更适用于相对较均匀的热流环境;U型通道中相邻通道间冷却剂的温差较大,伴随强烈的肋间传热,并且较低温的冷却剂通道能够从燃烧室壁面吸收更多的热流,能明显减小相邻高温通道的冷却负担。Three-dimensional simulation of different channel schemes of four channel U-shaped channel plate were conducted. The two configurations of U-shaped channel plate with the same direction inlet/the reverse direction inlet were mainly studied,and the cooling effects of different entrance and exit schemes in each configuration were also discussed and compared. The results showed that the channel scheme with alternate inlet arrangement of the two configurations was more suitable for the regular non-uniform heat flow,the channel scheme with the inlet channel located on both sides of the plate of the two configurations was more suitable for relatively uniform heat flow environment. In the U-shaped channel,the temperature difference between the adjacent channels was large, accompanied by strong heat transfer between the channels, and the lower temperature coolant channel can absorb more heat flow from the combustion chamber wall,which can significantly reduce the cooling burden of the adjacent high temperature channels.

关 键 词：超燃冲压发动机 再生冷却 结构设计 温度控制 流道方案 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]