ABSTRACT

A numerical investigation was performed to determine the effect of the lateral angle injection on film cooling effectiveness over a turbine blade. The rows are located in the vicinity of the stagnation line. One row is located on the suction side and the other one is on the pressure side. The predicted pressure field for various blowing ratios (M = 0.5, 1.1, and 1.5) is compared to available experimental results at the design condition. Moreover, the effect of three lateral angles 30, 45, and 60 deg at three blowing rates is investigated by analyzing the results of both laterally averaged and area-averaged values of adiabatic film cooling effectiveness. The outcomes of the numerical results indicate that the thermal protection of the blade can be strongly influenced by the lateral angle. The coolant structure flow is characterized by a dominant single asymmetric vortex on both sides. Lateral injection at angle γ = 60 deg significantly improves film cooling effectiveness. From γ = 30 to 45 deg, overall, no appreciable improvement could be noted in cooling performance except for the lower blowing ratio M = 0.5. At suction side, the increase of blowing ratio has an adverse effect on the blade thermal protection.