冲击孔板和扰流柱组合结构流动传热特性的实验和数值研究  

Experimental and numerical study on flow and heat transfer characteristics of composite structure with impingement perforated plate and pin-fins

作　　者：谢立 马莉 曹俊 孔德海 刘存良[2] XIE Li;MA Li;CAO Jun;KONG Dehai;LIU Cunliang(Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710100,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]西北工业大学动力与能源学院,西安710100

出　　处：《航空动力学报》2024年第11期228-238,共11页Journal of Aerospace Power

摘　　要：实验和数值研究了涡轮叶片尾缘内部冷却通道中冲击孔板与扰流柱组合结构的流动和传热特性。扰流柱叉排地布置在叶片尾缘端面上。冲击孔板穿孔率为0.07~0.44,冲击距为1.5~4,基于进气通道水利直径和平均速度的雷诺数为1 600~4 000。采用瞬态液晶传热测量技术获得了柱肋通道壁面的局部表面传热系数分布,并分析了冲击孔板穿孔率、冲击距、雷诺数对柱肋通道流动结构以及表面传热特性的影响。研究结果表明:较小的穿孔率下形成的强烈冲击射流能够显著提升组合结构的平均传热性能,但是会极大地增加其流动损失;冲击距和穿孔率对冲击-扰流柱组合冷却结构的传热和压损特性具有显著的影响;组合冷却结构的传热性能是光滑通道传热性能的2.0~9.4倍,而其摩擦因数是光滑通道摩擦因数的136~1 800倍;获得了组合结构的强化传热因子与相关参数的实验关联式。The flow and heat transfer characteristics of the composite structure with impingement perforated plate and pin-fins in the cooling channel at the trailing edge of a turbine blade were experimentally and numerically studied.The pin-fins in a staggered array were arranged on the end face of the trailing edge.The perforation ratio varied between 0.07 and 0.44,and the jet-to-surface varied from 1.5 to 4.Reynolds number,based on the hydraulic diameter of the inlet channel,was tested within the range values from 1600 to 4000.The convective heat transfer coefficient distribution of the surface in the pin-fin channel was obtained by using the transient liquid crystal temperature measurement technique.The effects of perforated ratio and impingement distance on the flow structure and convective heat transfer characteristics of the pin-fin channel were analyzed.The results showed that the average heat transfer of the composite structure can be significantly improved by the strong impingement jet formed at a small perforation rate,but could greatly increase the flow loss.The impingement distance and perforation rate had a significant influence on the heat transfer and pressure loss characteristics of the impingement and pin-fin composite structure.The Nusselt number of the composite structure was 2.0—9.4 times that of the smooth channel,with a friction factor of 136—1800 times that of the smooth channel.The experimental correlations between heat transfer enhancement factors and key parameters of the combined structure were obtained.

关 键 词：叶片尾缘冷却 冲击孔板 扰流柱 瞬态液晶 传热 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]