Numerical Analaysis of Shaped Holes Filmcooling for Leading Edge of A Gas Turbine Blade

This study investigates the performance of Cylindrical- conical- and clover-shaped film cooling holes of gas turbine blades and the effect of transverse trench on film cooling hole efficiency. The purpose of the research was to achieve the optimal film cooling geometry in order to gain the highest film cooling hole of gas turbine blade efficiency. In this study, a three-dimensional blade simulation that based on k-e realizable turbulence model. Cooling fluid was injected into the mainstream at 30◦ on leading edge stagnation row, with BR=1, 1.5, 2. After injecting the cooling fluid into Cylindrical- conical- and clover-shaped film cooling holes geometries with and without the presence of transverse trench, it was observed that clover-shaped hole with transverse trench along, at BR=2 and film cooling efficiency of 0.147 offers the highest film cooling efficiency. Investigation on transverse trench effect for all geometries showed that the presence of trench leads to a higher film cooling efficiency.