几何结构对尾缘层板气膜冷却特性的影响

Lamilloy models are applied to blade trailing edge. Numerical simulations are used to change the location of impingement holes and pin fins, the thickness of lip and the width of slot to study changes to study the effect of these changes on the vane's trailing edge outer film cooling performance. The results show that different location of impingement holes and pin fins have little impact on the vane's trailing edge outer film cooling performance. Different thicknesses of lip have an influence on film cooling effectiveness and heat transfer coefficient; The film cooling effectiveness of slots becomes smaller with the decrease of lip's thickness and film cooling effectiveness between slots becomes larger with the decrease of lip's thickness,and the heat transfer coefficient becomes larger with the decrease of lip's thickness. Compared to the original structure, the maximum increase of the spanwise averaged film cooling effectiveness is 65.0% with the changing of the lip's thickness. Different widths of slot have a great influence on film cooling effectiveness and heat transfer coefficient, the film cooling effectiveness becomes larger with the increase of slot's width. The heat transfer coefficient of slots becomes smaller with the increase of slot's width and the heat transfer coefficient between slots becomes larger with the increase of slot's width. The best film cooling performance can be achieved by increasing slot's width, the maximum increase of the spanwise averaged film cooling effectiveness is 116.5%.