|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||416/241R ; 219/128.85|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 54 인용 특허 : 0|
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 bond surface on the metallic 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 stre...
[ We claim:] [1.] A gas turbine engine component comprising:a metallic substrate,a metallic filler bonded onto a substrate bond surface on said metallic substrate, anda region having deep compressive residual stresses imparted by laser shock peening extending into said substrate beneath said substrate bond surface.