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Higher allowable gas turbine inlet temperatures are limited by the maximum allowable temperature the turbine blade material can handle. In gas turbines using a cooling technique is crucial to allow higher gas turbine inlet temperature and to enhance the durability of the gas turbine blade. A higher gas turbine inlet temperature allows boosting gas turbine efficiency which reduces fuel consumption. Film cooling where a relatively low temperature air is used to form a protective layer of cool air around the blade to shield it from high temperature gases. Many complex interrelated geometry and flow parameters affect the effectiveness of the film cooling. The complex interrelations between these parameters are considered the main challenge in properly understanding the effect of these parameters on film cooling. Numerical techniques are viable analysis techniques that are used to improve film cooling techniques. In this study, a simplified 2D film cooling jet blown from a slot jet is used to understand the interconnected relation between blowing ratio and injection angle. The effect of injection angles on adiabatic film effectiveness was found to be negligible at very low blowing ratios. However, as the blowing ratio increases the effect of angle becomes pronounced. In general, for wide range of blowing ratio M=0.1-1.0, decreasing blowing angle causes an increase in adiabatic film efficiency which mean film attachment is dominating the turbine blade shielding. But at high blowing ratio such as M=2, the cool film thickness dominates the heat transfer hence high angle mean thicker cooling film. Increasing blowing angle to obtain thicker film eventually cause detachment of cooling film and deteriorate the adiabatic film effectiveness.

Numerical Analysis of Film Cooling Effectiveness under Variable Blowing Ratio and Injection Angles