| 摘要 |
<p>A method for refurbishing turbine engine vanes in which the airfoils are removed and replaced. The original configuration of the vanes can be modified from a single casting or welded pair to a multi-piece component assembly comprising individual airfoil segments attached to the inner and outer platforms. The component assembly allows replacement of airfoils (8, 10) and/or platforms (4, 6) with improved casings in the form of improved alloys, improved physical geometry, or both. Modifications can be made in the vanes class area without the need to modify the airfoil contours by brazing or other contour alteration processes. According to the method, the platforms (4, 6) are separated from the airfoils (8, 10), the openings in the platforms are sealed, new airfoil sockets are cut into the platforms, and the vane is reassembled.</p> |
