Abstract: A method for repairing a damaged portion (144) of a brazed-on gas turbine engine seal (142) without the need to remove and to replace the entire seal. The damaged portion is removed to reveal a repair surface (146) of the underlying superalloy material, and a new seal structure (148) is formed by an additive manufacturing processes using a laser beam (124) to melt a powder (116) including superalloy material (116?) and flux material (116?). The flux material forms a protective layer of slag (132) over the melted superalloy material, thereby permitting the new seal structure to be formed directly onto the underlying superalloy material without the need for an intervening braze layer.