摘要
对前缘上游有单排孔板射流冲击的涡轮叶片内扰流柱通道柱面进行了详细的传热实验研究 ,获得了不同实验条件下扰流柱表面的局部换热系数分布 ,结合流场测量结果分析了柱面换热规律。结果表明换热系数分布很大程度上受射流冲击的影响 ,在扰流柱前缘附近存在高强度换热区域 ,沿柱面随角度的增加努谢尔特数逐渐减小 ,角度 θ为 90°附近存在一片低强度换热区域 ,尾缘区换热强度最低。结果还表明尽管平均努谢尔特数随雷诺数的增大而显著增大 ,平均换热强化系数却随雷诺数的增加先增大而后逐渐减小。有射流冲击的柱面换热效果明显优于无射流冲击情况。
Much experimental research has been done on efficient cooling of trailing-edge region of turbine blade. The structure changes of this trailing-edge region were proposed, and then a new structure of this trailing-edge region is proposed, which leads to better cooling according to heat transfer tests. Results show that the distribution of heat transfer coefficients is influenced by jet impingement. It was also observed that the overall average Nusselt number Nu increased remarkably with the increase in Reynolds number Re∞ and the overall average heat transfer augmentation coefficients ch increased firstly and then decreased gradually.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2002年第4期586-589,共4页
Journal of Northwestern Polytechnical University
