TURBINE AIRFOIL AND METHOD FOR THERMAL BARRIER COATING

摘要

A turbine airfoil (1) comprising an airfoil body (10) is disclosed. The airfoil (1) comprises a leading edge (9), a trailing edge (11), an exterior surface including a suction side (13) extending from the leading edge (9) to the trailing edge (11) and a pressure side (15) extending from the leading edge (9) to a trailing end (12). The pressure side (15) is located opposite to the suction side (13) on the airfoil body (10). The complete pressure side (15) of the exterior surface is coated by a thermal barrier coating (20) with a thickness (22) decreasing towards the trailing end (12).