摘要
为了解冷气喷射对涡轮叶片前缘气膜冷却特性的影响,对圆柱形前缘双排孔气膜冷却进行全三维N-S方程数值模拟。计算域网格采用FNM形式的多块结构化网格。研究了射流与主流的流动机理,分析了不同吹风比下对壁面冷却效率的影响。计算结果表明,壁面平均绝热效率随吹风比的增大而升高。针对第二排孔结构参数进行优化设计,优化后的冷却效果要明显优于原始结构。
Film cooling characteristics were numerically analyzed on the circular leading edge with two rows of staggered holes based on a 3D N-S equation solver. An FNM （full non-match） form multi-block structural mesh was used for the compu- tational domain. The flowfield mechanisms resulting from the interactions between the cooling jets and the freestream were ex- amined and the effect of different blowing ratios on the adiabatic effectiveness was expounded. The results show that the film cooling effectiveness is improved with the increase of blowing ratio. Finally, the cooling effectiveness is improved with the opti- mization of the geometric parameters of the second row of holes.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2012年第5期704-709,770,共7页
Journal of Propulsion Technology
基金
国家自然科学基金(50676043)
国家重点基础研究发展计划(2007CB210108)
关键词
航空发动机
涡轮叶片
气膜冷却
数值模拟
绝热效率
吹风比
Aero-engine
Turbine blade
Film cooling
Numerical simulation
Adiabatic effectiveness
Blowing ratio
