摘要
本文以航空发动机涡轮转子叶片前缘为模型,对冲击孔形状分别为长圆形和圆形的两种结构进行数值模拟,并对长圆形冲击孔结构进行实验研究。得到了不同流动参数下的流阻系数、平均流量系数及两种结构冲击腔内壁面的平均努塞尔数。结果表明:1)流阻系数及平均流量系数受射流雷诺数的影响不大;2)从圆形冲击孔冲击到冲击腔内壁时的流体折转角更大,圆形冲击孔结构的流阻系数要大于长圆冲击孔结构;3)对于叶片前缘,相对于圆形,气流经过长圆形冲击孔冲击后,冲击腔内壁面的换热更均匀,换热效果也更好。
According to a certain structure of aero engine turbine blade leading edge, flow and heat transfer characteristics about impact on the concave of the single-rowed oblong hole with overflow are researched by using numerical calculation and experimental method. Round hole are also studied by calculation. Average flow coefficient, Nusselt number and flow resistance coefficient are received with different Reynolds number. Several conclusions are drawn. 1） Flow resistance coefficient and average flow coefficient are not sensitive to Reynolds number; 2） Bending degree of flow from round hole is stronger, therefore, flow resistance of round impact hole is larger than oblong hole; 3） As for leading edge, heat transfer performance of oblong hole is better than round hole.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2013年第2期352-355,共4页
Journal of Engineering Thermophysics
关键词
涡轮叶片
前缘
长圆孔
流动
换热
turbine blade
leading edge
oblong hole
flow
heat transfer
