The present study experimentally explores the effect of the film-hole-row layout and hole angle on the film cooling characteristics of the multi-rows of micro-film-hole by the transient infrared technique. Reynolds number based on the diameter of the micro film hole and Knudsen number are 7000 and 7 × 10⁻⁵, respectively, and the dimensionless parameters of the experiment are the same as those of the real turbine blade. Two blowing ratios of 0.5 and 1.0 are investigated. Five rows of the film hole in leading edge have a pronouncedly positive effect on the film cooling effectiveness in the upstream region, and obtain an excellent coolant coverage at the blowing ratio of 1.0. The Nusselt number of the whole test surface is significantly decreased by five rows of the film hole in leading edge with the hole angle of 45° at the blowing ratio of 1.0. Increasing the hole angle from 45° to 90° decreases the span-wise averaged film cooling effectiveness of the test surface, and this phenomenon is obvious at the blowing ratio of 1.0, the maximum is about 29 %. There is a high heat transfer region at the beginning of the test surface of the five rows of the film hole in leading edge with the hole angle of 90° structure due to the mainstream-blockage-effect.

本研究采用瞬态红外技术，实验探讨了膜孔排布和孔角对多排微膜孔膜冷却特性的影响。基于微膜孔直径的雷诺数和克努森数分别为 7000 和 7 × 10 ^-5, 且实验的无量纲参数与真实涡轮叶片相同。研究了 0.5 和 1.0 两种吹塑比。前缘的五排油膜孔对上游区域的油膜冷却效果有显着的积极影响，并在1.0的吹风比下获得了良好的冷却剂覆盖率。在吹塑比为1.0时，前缘有5排薄膜孔，孔角为45°，整个测试面的努塞尔数显着降低。孔角从45°增加到90°会降低试验面的展向平均气膜冷却效果，这种现象在吹气比为1.0时很明显，最大值约为29%。