| 摘要 |
<P>PROBLEM TO BE SOLVED: To repair airfoils of a compressor blade of a gas turbine engine. <P>SOLUTION: According to this repairing method, an airfoil material (50) of an airfoil (34) is removed by machining, to form front edge, rear edge and tip cuttings (62, 63, 64). Bead of a welding material (72) is welded on the front edge, rear edge and tip cuttings. One part of the welding bead material is removed from a welding bead (70) by machining to obtain desired finishing dimensions (66, 68, 69) at the front edge, the rear edge, and a radial outside tip. Only a blade material along a radial outermost portion (80) of a front edge and a rear edge (LE, TE) extending from the tip of the airfoil (32) towards a base is removed by machining. A round corner (30) is formed between the front edge and rear edge cuttings (62, 63), and an unmachined portion (74) of the airfoil (34) formed between the outermost portion (80) and the base (32) at the front edge and the rear edge of the airfoil. <P>COPYRIGHT: (C)2003,JPO |
