Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: A gas turbine engine component includes a blade section having an inner end and an outer end, a shroud section at the outer end, and a platform at the inner end. A protective coating is disposed on the shroud, where the blade section is substantially free of the protective coating. The protective coating may also be disposed on the platform.

Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: A method of repairing a component of a gas turbine engine that includes a metallic substrate, an existing aluminide coating, and a diffusion layer formed in the metallic substrate adjacent to the coating. The method includes removing at least a portion of the existing aluminide coating, removing material forming the diffusion layer, applying a new metallic layer to the metallic substrate, and applying a new aluminide coating over the new metallic layer to form a new diffusion layer in the new metallic layer. The new metallic layer is a substantially homogeneous material that is substantially similar in chemical composition to that of the metallic substrate, and the new metallic layer forms a structural layer having a thickness selected to provide a specified contour to the component.

Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: Methods for inspecting gas turbine component parts for possible distress after hydrogen fluoride cleaning are disclosed. The methods selectively remove a small amount of material for IGA inspection and restore the material using the same procedures as when the parts were manufactured.

Abstract: A gas turbine engine component includes a blade section having an inner end and an outer end, a shroud section at the outer end, and a platform at the inner end. A protective coating is disposed on the shroud, where the blade section is substantially free of the protective coating. The protective coating may also be disposed on the platform.

Abstract: A method of repairing an airfoil for a gas turbine engine includes removing a damaged portion of the airfoil at a radially outward tip of the airfoil, securing temporarily a portion of a ceramic core stub within an internal cavity of the airfoil, applying new metallic material to the airfoil covering an exposed portion of the ceramic core stub, machining the airfoil to remove an excess portion of the new metallic material, and removing the ceramic core stub from the internal cavity of the airfoil.

Abstract: A method of repairing a component of a gas turbine engine that includes a metallic substrate, an existing coating, and a diffusion layer formed in the metallic substrate adjacent to the coating. The method includes removing at least a portion of the existing aluminide coating, removing material forming the diffusion layer, applying a new metallic layer to the metallic substrate, and applying a new aluminide coating over the new metallic layer to form a new diffusion layer in the new metallic layer. The new metallic layer is a substantially homogeneous material that is substantially similar in chemical composition to that of the metallic substrate, and the new metallic layer forms a structural layer having a thickness selected to provide a specified contour to the component.

Abstract: Methods for inspecting gas turbine component parts for possible distress after hydrogen fluoride cleaning are disclosed. The methods selectively remove a small amount of material for IGA inspection and restore the material using the same procedures as when the parts were manufactured.

Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: A method for restoring a turbine engine blade includes removing material from a wear/damage site on an OD shroud of the blade. Additional material is laser cladded to the site and then machined to restore the shroud.