超声速气膜冷却数值模拟  

Numerical simulation of supersonic gaseous film cooling

作　　者：王建[1] 孙冰[1] 魏玉坤[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国人民解放军空军第四飞行学院模拟训练中心,石家庄050071

出　　处：《航空动力学报》2008年第5期865-870,共6页Journal of Aerospace Power

摘　　要：应用SSTk-ω湍流模型,对三维粘性掺混流场进行了数值模拟,得到了切向入射的超声速气膜在不同吹风比和冷却通道下的绝热温比分布.计算结果表明:吹风比是决定超声速气膜冷却效果的重要因素,吹风比增大,冷却效果随之提高;冷却通道不同,冷却效率的分布规律也不同,矩形孔在出口处存在冷却效果较低的区域;离散孔冷却通道在下游和冷却通道中间线上的冷却效果存在明显差异,侧向倾角的引入使这种差异消失;扩散孔和侧向倾角两种结构上游冷却效果好,但下游衰减更快;引入的评价参数可以为比较不同的气膜冷却方式提供参考.The SST k-ω turbulence model was employed to simulate numerically 3D vis cous mixing flow field in order to investigate the supersonic gaseous film cooling injected from different cooling channels tangentially. Results show that blowing rate is an important factor, the adiabatic film cooling effectiveness is enhanced with the increase of the blowing rate. Through different cooling channels, the film cooling has different distribution rules, the cuboids channel is the worst one. The film cooling effectiveness is different between 2 kinds of centerlines in the discrete coolant channels, which can be avoided by the β angle. The distribution of adiabatic film cooling effectiveness on the wall indicates that the outspread hole and column with β are better in the foreside, but decline more quickly. 3 valuable parameters are introduced to evaluate the supersonic film cooling.

关 键 词：航空、航天推进系统 超声速 气膜冷却 数值模拟 绝热温比 

分 类 号：TK124[动力工程及工程热物理—工程热物理]