Abstract: A metallic coating for protecting a substrate from high temperature oxidation and hot corrosion environments comprising about 2.5 to about 13.5 wt. % cobalt, about 12 to about 27 wt. % chromium, about 5 to about 7 wt. % aluminum, about 0.0 to about 1.0 wt. % yttrium, about 0.0 to about 1.0 wt. % hafnium, about 1.0 to about 3.0 wt. % silicon, about 0.0 to about 4.5 wt. % tantalum, about 0.0 to about 6.5 wt. % tungsten, about 0.0 to about 2.0 wt. % rhenium, about 0.0 to about 1.0 wt. % molybdenum and the balance nickel.

Abstract: A method of securing an workpiece for machining the trailing edge. The workpiece has a platform from which extends an airfoil, the airfoil including a leading edge and a trailing edge, and a pressure side and a suction side. A fixture with at least one locating datum that relates to the platform and at least one locating datum that relates to the leading edge is provided. The fixture does not contact the trailing edge of the workpiece. The workpiece is positioned so that the platform is against the related locating datum and the leading edge is against the related locating datum. The workpiece is secured within the fixture, and the trailing edge of the workpiece is machined.

Abstract: A method of repairing a vane segment for a gas turbine engine includes removing an engine-run cooling baffle from the vane segment, forming a non-engine-run manufacturing detail that includes an inner platform, an outer platform, and an airfoil, attaching the engine-run cooling baffle to the non-engine-run manufacturing detail, and marking the non-engine-run manufacturing detail with a serial number associated with the vane segment from which the engine-run cooling baffle was removed.

Abstract: A method of processing turbine airfoils includes depositing a protective coating on first and second turbine airfoils, and bonding the first and second turbine airfoils together after the deposition such that there is an open throat between the first and second turbine airfoil and at least portions of surfaces in the open throat are coated with the protective coating.

Abstract: A method for coating a nozzle segment, the method comprising separating an outer shroud and an inner platform of the nozzle segment along pathways that bisect a first stator vane and a second stator vane of the of the nozzle segment, coating the first stator vane and the second stator vane after separating the outer shroud and the inner platform, and rejoining the separated outer shroud and the separated inner platform after coating the first stator vane and the second stator vane.

Abstract: A nickel braze alloy composition includes a blend of a first nickel alloy and a second nickel alloy. The first nickel alloy includes about 4.75 wt %-10.5 wt % of chromium, about 5.5 wt %-6.7 wt % of aluminum, up to about 13 wt % cobalt, about 3.75 wt %-9.0 wt % of tantalum, about 1.3 wt %-2.25 wt % of molybdenum, about 3.0 wt %-6.8 wt % of tungsten, about 2.6 wt %-3.25 wt % of rhenium, up to about 0.02 wt % of boron, about 0.05 wt %-2.0 wt % of hafnium, up to about 0.14 wt % of carbon, up to about 0.35 wt % of zirconium, and a balance of nickel. The second nickel alloy includes about 21.25 wt %-22.75 wt % of chromium, about 5.7 wt %-6.3 wt % of aluminum, about 11.5 wt %-12.5 wt % of cobalt, about 5.7 wt %-6.3 wt % of silicon, boron in an amount no greater than 1.0 wt %, and a balance of nickel.

Abstract: A layered structure comprising a base structure having a major surface, and a brazing layer secured to the major surface of the base structure, where the brazing layer is applied to the major surface prior to positioning the layered structure in contact with a turbine engine component.

Abstract: A method of repairing a vane segment for a gas turbine engine includes removing an engine-run cooling baffle from the vane segment, forming a non-engine-run manufacturing detail that includes an inner platform, an outer platform, and an airfoil, attaching the engine-run cooling baffle to the non-engine-run manufacturing detail, and marking the non-engine-run manufacturing detail with a serial number associated with the vane segment from which the engine-run cooling baffle was removed.

Abstract: A method of repairing a turbine engine component involves offering two repair options to a customer. A first repair option is based on an operating environment of the turbine engine component and the second repair option is based on cost. The first repair option is priced higher than the second repair option. The turbine engine component is examined. The turbine engine component is then repaired according to the selected repair option.

Abstract: A method of repairing a vane cluster for a gas turbine engine includes attaching a first registration block to a salvageable airfoil segment of the vane cluster, machining a face of the first registration block relative to datum surfaces of the vane cluster, removing a damaged airfoil segment from the vane cluster, adding new material to the salvageable airfoil segment, joining a replacement airfoil segment having a second registration block to the salvageable airfoil segment to replace the damaged airfoil segment, removing the first registration block, and removing the second registration block. The respective first and second registration blocks of the salvageable airfoil segment and the replacement airfoil segment are aligned in a configuration substantially identical to a configuration of the vane cluster prior to undergoing repair.

Abstract: The present invention is a method for processing a metal component comprising exposing a carbide-based coating to fluoride ions, thereby extracting a carbide material from the carbide-based coating to provide a residual coating on the metal component, and removing the residual coating from the metal component.

Abstract: A method for processing a metal component comprising inserting a graphitic preform into an aperture of the metal component, brazing the metal component, and removing at least a portion of the graphitic preform from the aperture with a thermal process in an oxygen-containing atmosphere.

Abstract: A method for repairing a metal component having a crack, the method comprising depositing a brazing material into the crack of the metal component, and exposing the metal component to a plurality of heating cycles. Each successive heating cycle has a temperature that is less than a temperature of a previous heating cycle, and a duration that is at least as long as a duration of the previous heating cycle. The plurality of heating cycles comprises an initial heating cycle having a temperature sufficient to at least substantially melt the brazing material within the crack.