带三棱锥体群通道流动和传热特性的数值模拟  

Numerical simulation of flow and heat transfer characteristics in passage with triangular pyramids

作　　者：鲍锋 侯昶 江裕荣 BAO Feng;HOU Chang;JIANG Yurong(School of Aerospace Engineering,Xiamen University,Xiamen Fujian 361102,China)

机构地区：[1]厦门大学航空航天学院,福建厦门361102

出　　处：《航空动力学报》2020年第12期2543-2552,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(11072206);福建省自然科学基金(2012J01023)。

摘　　要：对带有三棱锥体群的涡轮叶片内部冷却通道进行了数值模拟,对比了三棱锥体群在迎风和背风状态、顺排和交错排列以及不同横向列数、不同流向间距时冷却通道内部的流动和传热特性。结果表明:三棱锥体群所产生的纵向涡能够兼顾压损的降低与传热效果的改善;背风顺排状态放置的三棱锥体群具有最高的综合传热效率,较其他放置方案高出20%~30%;在背风顺排时,较优横向列数为5,流向间距比为4~6。Numerical simulation was performed for the internal cooling passage of turbine blades with triangular pyramids,and the focus was put on the flow and heat transfer characteristics in the cooling passage,with respect to the differences between cases of windward and leeward conditions,aligned and stagger arrangements,different horizontal columns and different streamwise spacing ratios.Results revealed that the decrease of pressure loss and improvement of heat transfer efficiency attributed to the longitudinal vortex generated by the triangular pyramids.The case of leeward condition with aligned arrangement had the highest comprehensive heat transfer efficiency,which was 20%-30%higher than other cases;while in this case,the most suitable number of horizontal columns was 5,and the streamwise spacing ratio was 4-6.

关 键 词：涡轮叶片冷却 传热特性 三棱锥体群 横向列数 流向间距比 

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]