PROFIL AÉRODYNAMIQUE DE ROTOR DE TURBINE ET PROCÉDÉ CORRESPONDANT POUR LA RÉDUCTION DE LA PERTE DE PRESSION DANS UNE CAVITÉ À L'INTÉRIEUR D'UNE PALE

摘要

A blade airfoil (10) for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits (40) with a leading edge circuit (22) and a trailing edge circuit (24). The entrance (54) of a cavity in the leading edge circuit (22) has a narrowing of a cavity width (48) that expands further downstream to a consistent cavity width (48) similar to the cavity width (48) of the rest of the leading edge circuit (22).