航空发动机涡轮叶片尾缘楔形通道交错肋冷却实验

Experiment on Wedge-Shaped Latticework Channel Cooling Applied in Aero Engine Gas Turbine Blade Trailing Edge

为研究涡轮叶片尾缘部分楔形通道交错肋流动传热性能,对其进行实验研究.实验应用瞬态液晶测试技术,对比研究了交错肋上、下主表面的局部传热特性,同时用压力扫描阀测得不同雷诺数下的通道压力损失.研究结果表明:尾缘段转折流动配置下,楔形通道交错肋上、下主表面传热差异显著,下主表面平均努塞尔数比上主表面平均高30%以上,尾缘楔形通道内交错肋结构主表面平均换热系数高出针肋结构约46%;交错肋上、下通道之间的交界面处存在强烈的质量交换作用,上、下主表面间断性的高换热区与上、下通道交界面呈现对应关系;随入口雷诺数的增加,通道压降快速增大.楔形通道交错肋压降是针肋的5~7倍,但其换热面积高出针肋107.4%,仍比针肋冷却增加约66%的综合换热性能.

In order to study the flow and heat transfer performance of wedge-shaped latticework channels in the turbine blade trailing edge, this paper conducted an experimental study by employing the transient liquid crystal(TLC) technique to investigate the local heat transfer characteristics of the upper and lower main surfaces and applying the pressure scanning valve to mesure the pressure loss of the channels at different Reynolds numbers. The experiment shows that there is a significant difference between the upper and lower main surfaces under the turning flow configuration condition at the trailing edge section. The average Nusselt number of the lower main surface is over 30% higher than that of the upper main surface. In heat transfer coefficient, the wedge-shaped latticework channel is over 46% higher than that of the needle rib channel. There is a strong mass exchange at the interface between the upper and lower channels of the latticework channel. The intermittent high heat transfer areas on the upper and lower main surfaces are corresponding to the interface. As the inlet Reynolds number increases, the channel pressure drop increases rapidly. The pressure drop of the wedge-shaped latticework channel is 5 to 7 times that of the needle ribs, but the heat transfer area of latticework channel is 107.4% higher than the needle ribs channel, and the overall thermal performance of the wedge-shaped latticework channel is still approximately 66% higher than that of the needle ribs channel.