Nowadays, gas turbines are among the most widespread energy sources for both energy production and aircraft propulsion. Over the last decades, the turbine has undergone strong improvements in efficiency thanks to the higher turbine inlet temperatures, which easily exceed the material's allowable temperature. Consequently, cooling systems play a key role in protecting the turbine components from high thermal stresses. Rib roughened internal cooling channels are one of the most consolidated cooling technologies in gas turbine blades. In this context, this activity aims to study the cooling performance of a traditional rib roughened internal cooling channel using numerical CFD simulations. Subsequently, the original channel shape was optimized to improve the wall heat transfer coefficient.