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Abstract
To increase gas turbine efficiency, high inlet gas temperatures should be reached. However, such a high gas temperatures can cause serious damage on the turbine blades because of its melting point or the severe thermal stresses. Optimizing the blade material and using different blade cooling schemes enable working at such a harsh conditions. Film cooling is one of the most important cooling methods used to achieve that purpose. The present study concentrates on the numerical investigation of film cooling performance for axial and shaped holes under engine-like conditions. The effect of thermal barrier coatings (TBC) on lateral averaged effectiveness is investigated for both axial and shaped holes. Results show that coatings can contribute in increasing lateral averaged effectiveness with less number of holes if properly used to approaches slot film cooling. Blade surface curvature is also investigated for axial holes, shaped holes and axial trenched holes. Combined effect of surface roughness, surface deposition and near hole obstructions are investigated for axial, shaped and trenched holes