Abstract: A preform, for repairing an abradable seal component of a gas turbine engine, includes a multilayer stack that has a first layer and a second layer. The first layer is operative to bond the multilayer stack to a structural substrate of an abradable seal. The first layer includes structural material that corresponds to a material of the structural substrate and braze material that is compatible with the structural material. The second layer includes an abradable material. The multilayer stack is operative to bond to the structural substrate of the abradable seal component during a brazing process such that the second layer forms a replacement abradable layer of the abradable seal component.

Abstract: Methods for repairing abradable seals of gas turbine engines include providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; providing a first preform to restore the structural substrate; and providing a second preform to form an abradable layer of the component. Preforms include a multilayer stack having a first layer and a second layer.

Abstract: Methods for repairing abradable seals of gas turbine engines include providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; providing a first preform to restore the structural substrate; and providing a second preform to form an abradable layer of the component. Preforms include a multilayer stack having a first layer and a second layer.

Abstract: A method for dimensionally restoring a stationary shroud segment, the method comprising removing at least a portion of a damaged flowpath of the stationary shroud segment to provide an exposed surface, casting a replacement flowpath, positioning the replacement flowpath on the exposed surface, and diffusion bonding the replacement flowpath to the stationary shroud segment.