Abstract: A method for repairing a tip portion of a turbine component having a structural defect is provided. The method includes removing a damaged section in turbine component with a structural defect in a tip portion of the turbine component. A pre-sintered preform is provided including a first portion having a first composition and a second portion having a second composition. The pre-sintered preform is configured to mate with an upper surface of a remaining portion of the turbine component. The method also includes applying the pre-sintered preform to the upper surface, wherein the PSP comprises a superalloy material and a braze material. The PSP and the remaining portion of the turbine component are subjected to a brazing process to melt the braze material and fill in the structural defect.

Abstract: A method for repairing a tip portion of a turbine component having a structural defect is provided. The method includes removing a damaged section in turbine component with a structural defect in a tip portion of the turbine component. A pre-sintered preform is provided including a first portion having a first composition and a second portion having a second composition. The pre-sintered preform is configured to mate with an upper surface of a remaining portion of the turbine component. The method also includes applying the pre-sintered preform to the upper surface, wherein the PSP comprises a superalloy material and a braze material. The PSP and the remaining portion of the turbine component are subjected to a brazing process to melt the braze material and fill in the structural defect.

Abstract: A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on the gas turbine engine blade damaged portion; and heat treating the preform and the blade such that the preform is brazed to the blade.

Abstract: A method, including: replacing an original blade shelf (16) of a gas turbine engine blade (10) with a new blade shelf (64) that is located closer to a base (18) of the blade than the original blade shelf; adding mass to the blade until a mass of the blade with the new blade shelf is greater than a mass of the blade with the original blade shelf in order to maintain a same contribution by the blade with the new blade shelf as a contribution by the blade with the original blade shelf to a dynamic balance of a rotor arrangement.

Abstract: A coating arrangement (16), including: a layer (18) of bond coat material (20); and a light-transmissive thermal barrier coating (TBC) mesh (28) having a TBC material (24) and secured in position relative to the layer of bond coat material. The coating arrangement may be positioned over a superalloy substrate material (12) and melted with a laser beam (62) to metallurgically bond the thermal barrier coating onto the substrate.

Abstract: A coating arrangement (16), including: a layer (18) of bond coat material (20); and a light-transmissive thermal barrier coating (TBC) mesh (28) having a TBC material (24) and secured in position relative to the layer of bond coat material. The coating arrangement may be positioned over a superalloy substrate material (12) and melted with a laser beam (62) to metallurgically bond the thermal barrier coating onto the substrate.

Abstract: A method, including: replacing an original blade shelf (16) of a gas turbine engine blade (10) with a new blade shelf (64) that is located closer to a base (18) of the blade than the original blade shelf; adding mass to the blade until a mass of the blade with the new blade shelf is greater than a mass of the blade with the original blade shelf in order to maintain a same contribution by the blade with the new blade shelf as a contribution by the blade with the original blade shelf to a dynamic balance of a rotor arrangement.

Abstract: A flux sheet (20A) and method of using the flux sheet to restore a surface (24) of a metal substrate (26). A laser beam (32) is directed onto the flux sheet to melt it and the surface, then allowed to cool and solidify to produce a restored surface. The flux sheet may be formulated to optically transmit at least 40% of electromagnetic energy from a laser onto the substrate surface. The flux sheet contains a flux composition that may include: a metal oxide, a metal silicate, or both; a metal fluoride; and a metal carbonate. The flux composition may limit the content of certain elements and compounds such as Fe, Li2O, Na2O and K2O. The flux composition may include constituents providing air shielding, contaminant scavenging, viscosity/fluidity enhancement, and optical transmission of laser energy through the flux sheet.

Abstract: A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on the gas turbine engine blade damaged portion; and heat treating the preform and the blade such that the preform is brazed to the blade.