In a developing aviation market, the necessity of augmenting the thermal efficiency of aero engines leads to the increase of thermomechanical constraints on the HP turbine blades. In particular, the trailing edge zone of blades is one of the most difficult parts to be cooled, presenting the highest levels of temperature. As a consequence, this limits the possibility to further increase the turbine inlet temperature. The current challenge for motorists such as Safran Aircraft Engines is to develop advanced blade trailing edge cooling technologies in high-pressure turbines. However, the modification of blade thickness and shape at trailing edge has also a great impact on the aerodynamic performance of the turbine, leading to the need of a compromise with thermomechanical requirements.