| 摘要 |
PROBLEM TO BE SOLVED: To offset a laser shock peening-induced twist part of an airfoil part of a blade in a gas turbine engine rotor blade provided with a leading edge and a trailing edge having local compression residual stress given by laser shock peening. SOLUTION: Laser shock peening is carried out by a step of laser shock-peening a thin airfoil part 34 of a gas turbine engine blade 8, a step of forming a laser shock-induced twist part DB in the airfoil part, and a step of offsetting the laser shock-induced twist part DB in the airfoil part 34 by shot-peening part of the airfoil part 34. The step of shot-peening can be carried out before or after the step of laser shock peening. The step of shot-peening can be applied with a laser shock peening surface 54 formed in the step of laser shock peening covered. The step of shot-peening can be respectively executed asymmetrically to a positive pressure side zone and a negative pressure side zone 76 and 77 asymmetrically shot-peened on the positive pressure side and the negative pressure side of the airfoil part 34. COPYRIGHT: (C)2007,JPO&INPIT |
