Numerical study on the effect of jet spacing on the Swirl flow and heat transfer in the turbine airfoil leading edge region
Numerical study on the effect of jet spacing on the Swirl flow and heat transfer in the turbine airfoil leading edge region
复制标题
射流间距对涡轮翼型前缘区域旋流及传热影响的数值研究
DOI：
10.1080/10407782.2016.1230381
复制
发表时间：
2016-01-01
影响因子：
2
通讯作者：
Simon, Terrence
中科院分区：
文献类型：
--
作者：
Liu, Zhao;Li, Jun;Simon, Terrence
本文采用数值模拟的方法研究了燃气涡轮翼型前缘内冷却通道旋流室的流动和传热特性。其几何结构由圆形管道和矩形入口组成，矩形入口引导进口气流切线撞击圆形管道。研究了射流间距与旋流腔半径之比和雷诺数对旋流冷却性能的影响。结果表明，随着雷诺数和射流间距与涡流室半径之比的增大，涡流室壁面上的压力损失和全局平均努塞尔数均增大。提出了这些参数的努塞尔数相关关系。旋流室表面的努塞尔数随射流间距与旋流室半径之比的增大而增大。
ABSTRACT In this paper, flow and heat transfer of a swirl chamber that models an internal cooling passage for a gas turbine airfoil leading edge is studied with numerical simulation. The geometry consists of a circular pipe, and rectangular section inlets that lead inlet flow to impinge tangentially on the circular pipe. The effects of the ratio of jet spacing to swirl chamber radius and Reynolds numbers on swirl cooling performance are investigated. The results indicate how the pressure loss and globally averaged Nusselt number on the swirl chamber wall increase with increases of Reynolds number and the ratio of jet spacing to swirl chamber radius. A Nusselt number correlation on these parameters is suggested. Also shown is how Nusselt numbers on the swirl chamber surface increase with the ratio of jet spacing to swirl chamber radius.