Laser Shock Peened Gas Turbine Engine Fan Blade Edges

Author:  Mannava et al.
Source:  US Patent 5,591,009
Doc ID:  1995039
Year of Publication:  1995
Abstract:  
Gas turbine engine fan blade with a metallic airfoil having a leading edge, a trailing edge, and a radially outer tip, and at least one laser shock peened surface located along the leaning edge with a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.