关键词: 涡轮叶片;叶片前缘+;薄膜冷却;冷却效率;实验

Abstract: Film cooling effectiveness on leading edge with one row of holes were measured.The model was blunt body with a half cylinder leading edge and two flat plates.One row of holes was located at 2 hole diameters from the stagnation line.Foreign gas injection was used to obtain a density ratio of approximately 1.5.High turbulence intensity was produced by a passive grid.The ratio of hole pitch to hole diameter is 2,3,4,respectively.Radial angle is 0°,45°,65°,respectively.The effect of hole pitch and radial angles on film cooling effectiveness was studied.The results indicate that film cooling effectiveness decreased with increasing hole pitch on both leading edge and flat plate.Radial angle has sophisticated influence on the film cooling effectiveness.Film cooling effectiveness decreases with increasing radial angle in the case of low momentum flux ratio(I=0.5) and film cooling effectiveness varies weakly in the case of other momentum flux ratios on the half cylinder leading edge.Film cooling effectiveness decreases with increasing radial angle on the flat plate in the case of all the momentum flux ratios.

Key words: Turbine blade;Leading edge+;Film cooling,Cooling effectiveness;Experimentation