Abstract: A method for repairing a gas turbine stationary flowpath shroud. The method comprises providing a superalloy gas turbine stationary flowpath shroud that has previously been in service. The method further comprises preparing a restoration coating for application to the flowpath surface of the shroud by the steps of providing a precursor mixture comprising a higher-melting-point alloy component, a lower-melting-point alloy component, and a fugitive binder. A perform is prepared from the components and pre-sintered into a mildly curved form. The partially densified perform is applied to the flowpath surface and thermally bonded to the flowpath surface, forming a restoration coating.

Abstract: A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.