TURBOMACHINE TURBINE BLADE COMPRISING A COOLING CIRCUIT WITH IMPROVED HOMOGENEITY

摘要

The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-side wall in pressure-side cavities, and radially toward the inside along the suction-side wall in a suction-side cavity that is separated from the pressure-side cavities by an internal wall of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-side and suction-side walls thereby limiting the inhomogeneity.