Recently, film cooling has been studied as a part of increasing the efficiency of gas turbines. In this paper, we propose a structure in which a basic hole and two sister holes are combined to improve the film cooling performance. The injection angle and compound angle of the film cooling hole are 35 degrees and 0 degrees. The blowing ratios of the main flow and the coolant flow are 0.3-2.0. Cooling performance, vortex distribution and heat t ... 전체 초록 보기