下缘板孔对涡轮叶片尾缘内冷通道流动换热影响的数值研究  

Numerical Study on Effect of Lower Edge Plate Hole on Flow and Heat Transfer of Internal Cooling Passage in Trailing Edge of Turbine Blades

作　　者：郑光华[1] 陈文彬 赵顺 吕文召 刘俊杰[1] ZHENG Guanghua;CHEN Wenbin;ZHAO Shun;L Wenzhao;LIU Junjie(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Hunan Aviation Powerplant Research Institute,Aero Engine(Group)Corporation of China,Zhuzhou 412002,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]中国航空发动机集团有限公司湖南动力机械研究所,株洲412002

出　　处：《航空工程进展》2020年第5期701-709,共9页Advances in Aeronautical Science and Engineering

摘　　要：涡轮叶片下缘板出气孔对内冷通道的流动和换热性能有较大影响。通过数值模拟方法研究下缘板出气孔对尾缘和下缘板双路出气涡轮叶片尾缘内冷通道内的流动和换热特性,对比分析孔径、孔形和孔位置对尾缘溢流孔流量系数、尾缘出流比、尾缘通道内总压系数和尾缘内冷腔壁面换热特性的影响。结果表明:下缘板出气孔孔径对流量系数分布的影响显著,孔径增大,尾缘溢流孔流量系数下降,尾缘出流比减小,尾缘内冷通道内压力损失降低,内冷腔平均换热系数增大;孔形对上游内冷通道内流动和换热几乎没有影响;孔位置变化对内冷通道壁面整体的换热系数影响很小,对局部影响较大。The air outlet hole of lower edge plate of turbine blade can influence the flow and heat transfer performance.The numerical simulation method is used to study the effect of air outlet hole of lower edge plate on the flow and heat transfer performance in internal cooling passage of turbine blade from the trailing edge and the lower edge plate.The effects of hole size,hole shape and hole position of the lower edge plate on the flow coefficient and outflow rate of the overflow hole in the trailing edge,total pressure coefficient in trailing edge passage,and heat transfer property of inner-cooling cavity wall in the trailing edge are analyzed.The results show that the diameter of the hole has great influence on the flow coefficient distribution of the lower edge of the plate.With the increase of the hole diameter,the flow coefficient of the overflow hole of the trailing edge is decreased.With the increase of hole diameter,the tailing edge outflow ratio and pressure loss in the cold passage in the trailing edge are decreased,and the average heat transfer coefficient of the internal cooling passage is increased.The shape of the hole is of small effect on the flow and heat transfer in the upstream inner cold passage.The change of the hole position has small effect on the heat transfer coefficient of the inner wall of the inner cold passage,and has great effect on the local part.

关 键 词：涡轮叶片 下缘板出气孔 内冷通道 流量系数 流量分配 换热系数 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]