| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a method for facilitating repairing a gas turbine engine compressor blade airfoil. <P>SOLUTION: The method comprises the steps of removing a titanium alloy material 61 from along leading and trailing edges 34 and 36 of the airfoil, and along a radially outer tip 40 of the airfoil to form respective leading edge, trailing edge, and tip cut-backs 62, 64 and 66 which each define cut-back depths D<SB>1</SB>, D<SB>3</SB>and D<SB>2</SB>, and depositing a titanium weld material 80 onto the leading edge, trailing edge, and tip cut-backs. The method also comprises the step of removing at least some of the titanium weld bead material to obtain pre-desired finished dimensions for the leading and trailing edges, and radially outer tip. <P>COPYRIGHT: (C)2005,JPO&NCIPI |
