燃气涡轮静叶表面气膜冷却效率实验研究

Investigation of Film Cooling Effectiveness Investigation on Gas Turbine Vane Surface

采用放大的燃气涡轮静叶模型,利用大尺度叶栅风洞进行实验,测量了涡轮静叶表面完全气膜覆盖下气膜冷却特性。风洞实验段由三个叶片组成,中间叶片为实验叶片,由有机玻璃制成。对叶片前腔和后腔表面换热情况分别进行实验,主要研究了不同主流雷诺数及不同质流比对气膜冷却效率影响。研究结果表明:气膜对前腔壁面冷却效果总体上优于后腔壁面,在叶片不同区域气膜冷却效率变化规律有所不同。

Detailed film cooling performance on gas turbine vane surface with full coverage film was studied experimentally. A three-vane liner cascade in a large-scale wind tunnel was used in the experiment. The experiments were carried out on anterior cavity and posterior cavity of vane respectively under different mainstream Reynolds numbers and various mass ratios. The results reveal that the film cooling influence on surface of anterior cavity is better than that of posterior cavity on the whole, the distributions of film cooling effectiveness in different location of vane are different with various Reynolds numbers and mass ratios.