摘要
为了深入了解涡轮叶片尾缘扰流柱区域的流动结构和换热情况,通过数值计算研究了小间距梯形扰流柱通道内的流动和换热.数值计算结果表明:①数值计算得到的端壁静压分布、弦向出流量分布、总压系数与实验结果符合良好,端壁换热分布规律总体上与实验结果一致.②扰流柱区域的流动方向基本为弦向.沿弦向湍流度是逐渐升高的,靠近弦向出口扰流柱后的湍流度比较低.数值计算结果对涡轮叶片内部冷却计算具有重要的参考价值.
Numerical simulation was conducted to gain greater insight into the flow structure of trapezoidal pin-fin duct and get detailed knowledge of the heat transfer on the endwall surface. The array geometries have short pin heights and small chord-wise pin spacing. Numerical results show that, the calculated flow resistances and chord-wise ejection mass flow rate agree well with the experimental data, and the heat transfer pattern is well simulated. The numerical results also show that the flow direction in pin-fin region is mainly chord-wise. There are a lower velocity and lower turbulence intensity region behind the cylinder.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第1期13-17,共5页
Journal of Aerospace Power
基金
APTD项目(APTD-1203-02-03)
关键词
流动换热
小间距扰流柱
数值计算
燃气轮机
冷却叶片
flow and heat transfer
small spacing pin-fin
numerical simulation
gas turbine
cooling blade