A method facilitates repairing a gas turbine engine compressor blade airfoil (20). The method comprises removing 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 1 , D 3 , D 2 ), and depositing titanium weld material onto the leading edge, trailing edge, and tip cut-backs. The method also comprises 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.