Gas turbines represent nowadays one of the most important sources of energy, covering a big slice of the energy need finding a good compromise between energy production and efficiency. Generally, as the system is conceived, to find the aforesaid compromise high temperatures needs to be reached. Thus, cooling mechanisms are adopted by spilling a percentage of the compressor mass-flow rate to refrigerate the areas mostly subjected to this high thermal stresses. Therefore, cooling phenomena represent one of the main subjects to be studied and elaborate in-depth avoiding or at least containing thermo-mechanical stress leading to fatigue cracks. The present thesis aims at investigating and increasing cooling effectiveness within an industrial gas turbine high-pressure blade by means of turbulators.