Computational prediction into staggered film cooling holes on convex surface of turbine blade

摘要: Abstract The purpose of this paper is to predict the film cooling performance inline configuration holes in comparison staggered arrangement on convex surface. Three‐dimensional computational study for 10° diffused hole (β = 10°, γ = 0°) and compound 45° with downstream direction γ = 45°) were investigated adiabatic effectiveness have been compared that simple (β = 0°, Both showed better than all models. In one row investigation, centerline slightly higher near trailing edge. case, was both two rows three rows. For lateral investigations row, right side while left dominated Staggered distribution protection present results are important dissemination many practical applications aero engine industry.