Abstract
Abstract Gas turbine components are exposed to very high temperature and pressure and require effective cooling to ensure the effective, efficient and prolonged service life period. In the present work ANSYS FLUENT was employed to numerically investigate performance of cooling on a flat surface using circular coolant hole with entrance of coolant at different blowing ratios entering at 300 forward and backward directions. The proposed simulative methodology was validated with a zero velocity coolant entrance which showed no change in the plate temperature, which was expected and also found. The results found were also validated using various experimental results available in different literatures. The simulation results indicated that orientation of cooling hole governs the extent of film cooling effectiveness. The results of this work had a mixed outcome. Forward coolant entrance provided better centerline cooling effectiveness but spreadability was better for backward entrance
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