Laser Shock Peening for Gas Turbine Engine Weld Repair

Author:  Ferrigno et al.
Source:  US Patent 5,735,044
Doc ID:  1995029
Year of Publication:  1995
Abstract:  
A crack weld repair and method, particularly for a gas turbine engine blade or other metallic component in the engine, providing a metallic substrate, a metallic filler bonded onto a substrate, and a region having deep compressive residual stresses imparted by laser shock peening extending into the substrate beneath the substrate bond surface. One embodiment provides a laser shock peened surface below the weld material filled void in a damaged area of the component forming a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the component. Optionally, the surfave over the repaired area of the weld filled void may also be laser shock peened forming a second region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the weld rerair. Another embodiment provides a weld buildup tip overlay on a substrate bond surface of an airfoil tip having a laser shock peened region beneath the substrate bond surface.