Gas turbine engine blade with improved fatigue strength and manufacturing method thereof

摘要

An airfoil (2) having improved fatigue strength is disclosed. The airfoil comprises a tip (4), a root section (6), a platform (22), and an airfoil section (8) located between the tip and the platform. The airfoil section has a leading edge (16) and a trailing edge (14). A metallic coating (18) is located along the leading edge and the trailing edge excluding a portion of the leading edge and the trailing edge located near the platform. IMAGE