Abstract: A method of removing an aluminide diffusion coating from a gas turbine engine component having a nickel alloy base material may comprise: disposing the gas turbine engine component in a solution, the solution including an acid between 5% and 15% vol./vol. and water between 85% and 95% vol./vol.; placing the gas turbine engine component in electrical contact with a graphite plate; and removing the aluminide diffusion coating from the gas turbine engine component in response to placing the gas turbine engine component in electrical contact with the graphite plate and disposing the gas turbine engine component in the solution.

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: A process for controlling fatigue debit when coating an article includes the steps of: cleaning at least one surface of an article including a structural material; depositing a bond coat material upon at least one cleaned surface of the article to form a bond coat layer substantially free of the structural material; depositing an oxidation resistant material in the presence of an activator upon the bond coat layer at a temperature range from about 1,775° F. (968° C.) to about 1,825° F. (996° C.) to form an additive layer substantially free of the structural material; and wherein the bond coat layer and the additive layer together form a thin film, oxidation resistant coating having a thickness of at least about 0.5 mils.

Abstract: An alloy composition includes a blend of a first alloy and a second, different alloy. The blend has a combined composition including about 17.2 wt %-24.25 wt % of chromium, about 6 wt %-10.51 wt % of aluminum, about 3 wt %-23 wt % of cobalt, about 1.5 wt %-3.6 wt % of silicon, about 0.1 wt %-0.175 wt % of boron, up to about 0.163 wt % of hafnium, about 0.075 wt %-0.7 wt % of yttrium, and a balance of nickel.

Abstract: A method of repairing an abradable, nickel single crystal material having an abraded surface area by applying a diffusion layer to the abraded surface area comprising a nickel-based alloy having a quantity of an additional element selected from silicon and boron; and also applying an abradable layer to the material comprising a cobalt-based alloy to restore the abraded surface area.

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: 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 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: An alloy composition includes a blend of a first alloy and a second, different alloy. The blend has a combined composition including about 17.2 wt %-24.25 wt % of chromium, about 6 wt %-10.51 wt % of aluminum, about 3 wt %-23 wt % of cobalt, about 1.5 wt %-3.6 wt % of silicon, about 0.1 wt %-0.175 wt % of boron, up to about 0.163 wt % of hafnium, about 0.075 wt %-0.7 wt % of yttrium, and a balance of nickel.

Abstract: An alloy composition includes a blend of a first alloy and a second alloy, the first alloy having a first composition including about 17 wt %-25 wt % of chromium, about 6 wt %-12.5 wt % of aluminum, about 18 wt %-22 wt % of cobalt, up to 4 wt % of tantalum, up to about 8 wt % of tungsten, up to about 0.4 wt % of silicon, about 0.25 wt %-1 wt % of hafnium, about 0.1 wt %-1 wt % of yttrium, and a balance of nickel, and the second alloy having a second composition including 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 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 method of repairing an abradable, nickel single crystal material having an abraded surface area by applying a diffusion layer to the abraded surface area comprising a nickel-based alloy having a quantity of an additional element selected from silicon and boron; and also applying an abradable layer to the material comprising a cobalt-based alloy to restore the abraded surface area.

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: An alloy composition includes a blend of a first alloy and a second alloy, the first alloy having a first composition including about 17 wt %-25 wt % of chromium, about 6 wt %-12.5 wt % of aluminum, about 18 wt %-22 wt % of cobalt, up to 4 wt % of tantalum, up to about 8 wt % of tungsten, up to about 0.4 wt % of silicon, about 0.25 wt %-1 wt % of hafnium, about 0.1 wt %-1 wt % of yttrium, and a balance of nickel, and the second alloy having a second composition including 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 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 process for controlling fatigue debit when coating an article includes the steps of: cleaning at least one surface of an article including a structural material; depositing a bond coat material upon at least one cleaned surface of the article to form a bond coat layer substantially free of the structural material; depositing an oxidation resistant material in the presence of an activator upon the bond coat layer at a temperature range from about 1,775° F. (968° C.) to about 1,825° F. (996° C.) to form an additive layer substantially free of the structural material; and wherein the bond coat layer and the additive layer together form a thin film, oxidation resistant coating having a thickness of at least about 0.5 mils.

Abstract: A method of treating a coating includes the steps of providing the coating on a substrate and laser peening the coating. The laser peening consolidates the coating to reduce porosity and permits uniform consolidation in corners and tight spaces on articles such as gas turbine engine components.

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 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.