以某型双喉道气动矢量喷管为研究对象,采用在喷管收缩段内壁面布置隔热屏的冷却方式,基于Realizable k-ε模型的雷诺时均方法,数值研究了隔热屏与壁面间距(Δl=1mm,2mm,3mm)、尾部翻边结构对喷管壁面冷却效率及矢量性能的影响,并在Δl=2mm下进一步研究了隔热屏气膜孔对喷管冷却及矢量性能的影响。比较了喷管壁面冷却效率分布云图及对称面流线图,探究了隔热屏与壁面间距、翻边结构和气膜孔等对于冷却效率及矢量角的影响机理。结果表明:随着隔热屏与壁面间距的增加,承受热负荷最重的凹腔上壁面冷却效率从0.387增加至0.899,但喷管矢量角损失也从0.79°增大到1.64°,增加隔热屏尾部翻边结构可提升凹腔上壁面冷却效率并减少隔热屏对喷管矢量性能的不利影响。开设隔热屏气膜孔可进一步提高凹腔侧壁面冷却性能并减小矢量角损失。

Based on the Reynolds time-mean method of Realizable k-ε model, the effects of the distance between the heat shield and the wall (Δl=1mm, 2mm, 3mm) and the tail flanging structure on the cooling efficiency and vector performance of the nozzle wall were investigated numerically. The effect of the heat shield film hole on the cooling and vector performance of the nozzle was further studied at Δl=2mm. The effect mechanism of the distance between the heat shield and the wall, flanging structure and the gas film hole on the cooling efficiency and the vector Angle was investigated. The results show that with the increase of the distance between the heat shield and the wall, the cooling efficiency of the top wall of the cavity with the heaviest heat load increases from 0.387 to 0.899, but the nozzle vector Angle loss also increases from 0.79° to 1.64°. Adding the flange structure of the tail of the heat shield can improve the cooling efficiency of the top wall of the cavity and reduce the adverse effect of the heat shield on the nozzle vector performance. The cooling performance of the side wall of the cavity can be further improved and the vector Angle loss can be reduced by opening the heat insulation film hole.

TK221

中国科协青年人才托举工程；进排气技术教育部重点实验室