| 摘要 |
PROBLEM TO BE SOLVED: To realize durability against fatigue damage by providing a laser shock peened surface extending along the front edge and/or rear edge of a blade, and a region having deep compressive residual stresses imparted by laser shock peening and extending into the blade from the laser shock peened surface. SOLUTION: A compressor blade 8 has a front edge part 50 extending along the front edge LE of an airfoil 34 from a platform 36 of the blade 8 to the blade tip 38. The front edge part 50 has a first width, and the front edge part 50 surrounds notches 52 and clefts that may be formed along the front edge LE of the airfoil 34. In order to oppose the fatigue damage of the blade 8 part, at least one of the pressure side 46 and suction side 48 is provided with a laser shock peened surface 54 and a prestressed region 56 having deep compressive residual stresses imparted by laser shock peening and extending into the airfoil 34 from the laser shock peened surface 54. |
