|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||416/241R ; 416/500 ; 416/230 ; 416/229A ; 416/236R ; 415/119 ; 298/897 ; 298/891|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 33 인용 특허 : 20|
A gas turbine engine airfoil assembly for damping airfoil vibrations includes a metallic airfoil having an outer surface and a chordwise extending cavity beneath the outer surface of the airfoil. A damper is trapped within the cavity and a region in the airfoil surrounding the cavity has compressive residual stresses imparted by laser shock peening. The damper is preferably a chordwise extending linear wire having a distal end tacked down within the cavity. The invention includes a method for constructing the assembly for damping airfoil vibrations.
[ We claim:] [1.] A gas turbine engine airfoil assembly, comprising:a metallic airfoil having an outer surface,a chordwise extending cavity beneath the outer surface of said airfoil;a damper trapped within said cavity; anda region in said airfoil surrounding said cavity, said region having compressive residual stresses imparted by laser shock peening.