Gas turbine cooling can be classified into two different schemes; internal and external
cooling. In the internal cooling method, the coolant provided by compressor is forced into the cooling
flow circuits inside turbine components. Meanwhile, for the external cooling method, the injected
coolant is directly perfused from coolant manifold to save downstream components from hot gases.
Furthermore, in the latter coolant scheme, coolant is used to quell the heat transfer from hot gas stream
to a component. There are several ways in external cooling. Film cooling is one of the best cooling
systems for the application on gas turbine blades. This study concentrates on the comparison of
experimental, computational and numerical investigations of advanced film cooling performance for
cylindrical holes at different angles and different blowing ratios in modern gas turbines.