Numerical Investigation on Two Compound Angles Film Cooling of Stator Blades

Abstract

AbstractRealizable k − ε turbulence model based on SIMPLEC algorithm was simulated though the discretization of the governing equation by means of the finite volume method. This model was performed to investigate the temperature field on pressure and suction surface and the film cooling effectiveness under normal conditions. All simulations of turbine blade cascade at the leading edge had fixed streamwise inclination angles of 30°and 90°, spanwise inclination angle of 45°, blowing rate of 0.5, 1.0 and 1.5, crossflow temperature of 473.15K. The results show that the same tendency of the cooling effectiveness curve is observable at different blowing rates for a nominal compound angle. On the suction surface, the cooling effectiveness η increases with improving blowing rate. The compound angle jet at the leading edge influenced strongly the cooling effectiveness. On the pressure surface, η increases with improving blowing rate at the compound angle of 30°, 45°. However, η decreases with improving the blowing rate at the compound angle of 90°, 45°.Keywordsfilm coolingnumerical simulationcompound anglesblade cascadetemperature fieldcooling effectiveness