摘要
以平行入射缝槽气膜冷却为研究对象,开展了主、次流分别为亚声速和超声速流动状态下的气膜冷却数值模拟。计算结果表明:对于主流为超声速、次流为亚声速的气膜冷却,主流热量和动量很快就输运到亚声速次流中,气膜核心区很快被破坏,气膜冷却效率不高;在主流为超声速流动的情况下,施加相同吹风比的超声速冷却次流可将其核心向下游更远的地方输运,与常规的亚声速气膜冷却结构类似。为了获得较高的气膜冷却效率,在主流为超声速流动的情况下,建议施加超声速次流进行气膜冷却。
The film cooling flow of two parallel flows with supersonic or subsonic velocity was simulated to reveal the differences between the supersonic cooling and the subsonic cooling. The results show that： the film cooling with supersonic primary flow and subsonic coolant flow,the coolant flow with lower momentum is sheared and dragged by the higher momentum primary flow because of the viscous fluid. The thermal and momentum of the primary flow transfer into the coolant flow rapidly. It cause the great damage to the core of film and decrease the cooling efficiency dramatically. In contrast,supersonic coolant flow could deliver the film further than the subsonic flow on the same blowing ratio. The two supersonic flows have some similarity of shear lay with the two subsonic flows in the manner..
出处
《航空计算技术》
2015年第1期30-34,共5页
Aeronautical Computing Technique
基金
江苏省自然科学基金项目资助(BK20130790)
关键词
超声速气膜冷却
吹风比
数值模拟
流动特性
冷却特性
supersonic film cooling
blowing ratio
numerical simulation
flow characteristic
cooling characteristic
