Laser Shock Peened Gas Turbine Engine Blade Tip
Author: Mannava et al.
Source: US Patent 5,620,307
Doc ID: 1995037
Year of Publication: 1995
Abstract:
Gas turbine engine blade with a metallic airfoil having a radially outer extending chordwise between a leading edge and a trailing edge and at least one laser shock peened surfaced extending radially along at least a portion of the tip and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.