迷宫复合冷却结构冷流入射角对压力损失的影响  

Numerical Simulation on Pressure Coefficient with Different Deflection Angle of Maze Composite Cooling Structure

作　　者：李名魁[1] 何立明[1] 蒋永健[1] 金涛[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2006年第5期4-6,共3页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(50276070)

摘　　要：针对燃烧室新型迷宫复合冷却结构,采用数值模拟方法研究了该冷却结构外侧壁上冷却孔开孔角度分别为-60°、-30°、+30°、+60°时内外流场的分布情况,获得了其流场及压力损失的分布规律。研究表明开孔角度为+30°时压力损失最低。In order to gain the flow field and pressure coefficient distribution characteristics with different deflection angles on the first layer of the maze composite coding structure in combustor, a two - dimensional numerical simulation model is employed in this paper. The results show that the pressure coefficient is the lowest at α = ＋ 30°, which can provide beneficial references for the experimental investigation in the cooling performance and design of the maze composite coding structure.

关 键 词：燃烧室 迷宫复合冷却结构 开孔角度 压力损失 数值模拟 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]