Abstract: A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

Abstract: A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

Abstract: A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

Abstract: A method for holding a sintering filler material during a brazing/sintering operation for repairing a damaged area of a component wherein the component is in either a bonding face down position, bonding face vertical position or bonding face up position. The method includes providing a wire mesh and attaching the wire mesh to the component in a location corresponding to the damaged area. Further, the method includes forming a gap between the wire mesh and the component. Moreover, the sintering filler material may be inside the wire mesh or both inside and outside the wire mesh in order to secure the sintering filler material to the damaged area.

Abstract: A method for holding a sintering filler material during a brazing/sintering operation for repairing a damaged area of a component wherein the component is in either a bonding face down position, bonding face vertical position or bonding face up position. The method includes providing a wire mesh and attaching the wire mesh to the component in a location corresponding to the damaged area. Further, the method includes forming a gap between the wire mesh and the component. Moreover, the sintering filler material may be inside the wire mesh or both inside and outside the wire mesh in order to secure the sintering filler material to the damaged area.

Abstract: A method of braze repair of a base alloy component that includes a braze thermal cycle including a specially chosen peak braze temperature holding time segment and a purposely selected subsequent diffusion heat treatment segment. A multi-layer braze filler material structure used for the braze repair of a base alloy component including at least a first superalloy layer and a single mixture layer. The single mixture layer including at least a braze alloy and a second superalloy.

Abstract: A process for repairing combined heavy erosion and thermal fatigue cracks and/or other defects, such as large cracks, in a high temperature superalloy component, such as a vane in a turbine section of a gas turbine engine, that does not require mechanical grinding to prepare the defect site. The process includes depositing a loose finely granulated superalloy powder or a low viscosity superalloy slurry in the crack up to a suitable level and then depositing a superalloy putty layer on the superalloy powder or slurry at the top of the crack A braze putty layer is then deposited over the superalloy putty layer and the component is sintered in a vacuum furnace to harden the superalloy putty and powder or slurry to repair the defect.

Abstract: A method for holding a sintering filler material during a brazing/sintering operation for repairing a damaged area of a component wherein the component is in either a bonding face down position, bonding face vertical position or bonding face up position. The method includes providing a wire mesh and attaching the wire mesh to the component in a location corresponding to the damaged area. Further, the method includes forming a gap between the wire mesh and the component. Moreover, the sintering filler material may be inside the wire mesh or both inside and outside the wire mesh in order to secure the sintering filler material to the damaged area.

Abstract: A process for repairing combined heavy erosion and thermal fatigue cracks and/or other defects, such as large cracks, in a high temperature superalloy component, such as a vane in a turbine section of a gas turbine engine, that does not require mechanical grinding to prepare the defect site. The process includes depositing a loose finely granulated superalloy powder or a low viscosity superalloy slurry in the crack up to a suitable level and then depositing a superalloy putty layer on the superalloy powder or slurry at the top of the crack A braze putty layer is then deposited over the superalloy putty layer and the component is sintered in a vacuum furnace to harden the superalloy putty and powder or slurry to repair the defect.