| 摘要 |
PROBLEM TO BE SOLVED: To provide a method and a device for reducing vibration to be induced to a rotor blade. SOLUTION: The airfoil profile 42 of a gas turbine engine 10 comprises a leading edge 48, a trailing edge 50, a tip 54, a first side wall 44 extended between a root 52 and the tip of the airfoil profile over a radial directional span to define a first side surface of the airfoil profile, a second side wall 46 extended between the root and the tip of the airfoil profile over the radial directional span to define a second side surface of the airfoil profile, and a winglet 70 extended outward from at least one of the first and the second side walls so that radius R<SB>1</SB>is extended between one of the first and the second side walls. COPYRIGHT: (C)2005,JPO&NCIPI |
