摘要
在模拟实际燃烧室室壁加热情况下,对三组不同几何参数的冲击/气膜复合冷却结构进行了热态实验研究,得到了不同冷却气流量下沿轴向的壁温分布,并与纯气膜和夹层气膜冷却的相应实验结果进行了分析比较,冲击/气膜冷却效果优于纯气膜和夹层气膜冷却。
This research has been conducted by simulating the heating of the real combustion chamber wall. The distribution of 1-D axial wall temperature of coolant air with different coolant air flow rate is investigated in terms of three impingement and film cooling test components with different geometric designs heated hot gas and is compared with experimental results of pure film and channel film cooling. It can be concluded that the cooling result of the impingement and film cooling is superior to that the pure film and channel film.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1994年第1期14-17,5,共5页
Journal of Propulsion Technology
关键词
燃气轮机
燃烧室
壁温
空气冷却
Gas turbine, Combustor, Wall temperature, Air Cooling