In a modern gas turbine, up to about 20% of the main compressor flow is bled off to perform cooling and sealing of hot-section components. As the energy demand increased, the technology behind the gas turbine cooling system has developed, adopting new designs to enhance the performance of the machine. This work focuses on the analysis of rib-turbulated cooling channels, adopted in the first row blades of an industrial gas turbine engine. Rib-turbulated cooling channels paved their way in the last decades to substitute smooth channels. The implementation of turbulators has the main effect to enhance the heat transfer between the cooling fluid and the blade material.