燃烧室新型迷宫复合冷却结构二维壁温数值模拟  

Numerical Simulation of 2-D Wall Temperature of Combustor′s Maze Composite Cooling Structure

作　　者：李名魁[1] 何立明[1] 蒋永健[1] 

机构地区：[1]空军工程大学工程学院,西安710038

出　　处：《机械科学与技术》2007年第2期245-248,共4页Mechanical Science and Technology for Aerospace Engineering

基　　金：国家自然科学基金项目(50276070)资助

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的流场结构和内外壁温分布情况,获得了结构内部的流场及多层壁温的分布规律,并且计算了席壁层热侧面的压力分布情况。计算结果表明,迷宫复合冷却结构沿轴向的壁温梯度较全气膜冷却结构更加平缓,外侧壁最高温度较全气膜冷却结构低大约200 K左右。The paper studied the cooling structure＇s flow-field structure and its inside and outside wall teinperature distribution using the numerical simulation method, thus obtaining its inside flow field and multi-layer wall temperature distribution law. It also calculated the static pressure coefficient at the hot side of the multi-layer wall of a combustor＇s maze composite cooling structure. The calculation results show that the wall temperature gradient along the axis of the maze composite cooling structure is smoother than that of the film cooling structure and that the highest temperature at the outside wall is approximately 200 K lower than that of a film cooling structure.

关 键 词：燃烧室 迷宫复合冷却结构 壁温 数值模拟方法 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]