TURBINE AIRFOIL COOLING SYSTEM WITH FILM COOLING HOLE WITHIN PROTRUDED COOLING HOLE SUPPORT

摘要

A turbine airfoil (10) for a gas turbine engine (12) having a more resilient film cooling hole (14) configuration is disclosed. The film cooling hole (14) may be positioned in an outer wall (16) of the airfoil (10) and may have an inlet (18) in communication with a cooling system (20) and an outlet (22) in an elevated film cooling exhaust surface (24) that extends outwardly further than an adjacent outer surface (26) of the outer wall (16). A thermal barrier coating (28) may be positioned on the outer wall (16), and the outer surface (30) of the elevated film cooling exhaust surface (24) may be positioned between the outer surface (26) of the outer wall (16) and an outer surface (32) of the thermal barrier coating (28), thereby positioning the elevated film cooling exhaust surface (24) above the outer surface (26) of the outer wall (16) of the airfoil (10). Such position reduces thermal stress at the film cooling hole (14) and improving local stress and bonding adjacent to the outlet (22).