Abstract: A method of repairing a tip for an airfoil is disclosed herein. In various embodiments, the method comprises: removing a portion of the airfoil that reduces a radial height of the airfoil and at least partially removes a defect of the airfoil; removing a remainder of the defect; joining, via gas tungsten arc welding, a filler material to the airfoil to repair the defect; and joining a first mating surface of the airfoil to a second mating surface of a blade tip body via a solid-state joining process.

Abstract: Aspects of the disclosure are directed to a method of repairing a non-line of sight feature on a surface, the method comprising machining a worn irregular non-line of sight surface to provide a substantially planar repair surface, depositing a nickel plate base layer having a base layer thickness on the substantially planar repair surface, and depositing a protective layer having a protective layer thickness on the nickel plate base layer.

Abstract: Aspects of the disclosure are directed to repairing or restoring a liner associated with a combustor of an aircraft engine. The liner is at least partially stripped of at least one detail. An automated welding operation is applied to the liner. A coating of the liner on a cold side of the liner is retained on the liner during the welding operation.

Abstract: A method is provided that involves a component including a first fastener aperture that extends through the component. During the method, the component is machined to enlarge the first fastener aperture to provide an enlarged aperture. The component is friction plug welded to plug the enlarged aperture with friction plug welded material. A second fastener aperture is machined in the friction plug welded material, where the second fastener aperture extends through the component.

Abstract: A method of additively repairing a combustor liner panel includes removing a combustor liner panel from a combustor, inspecting the combustor liner panel to identify a damaged portion, removing material from the combustor liner panel around the damaged portion to form a repair zone having a substantially flat platform, and adding repair material to the repair zone on a layer by layer basis using an additive repair process.

Abstract: Aspects of the disclosure are directed to repairing or restoring a liner associated with a combustor of an aircraft engine. The liner is at least partially stripped of at least one detail. An automated welding operation is applied to the liner. A coating of the liner on a cold side of the liner is retained on the liner during the welding operation.

Abstract: A method to fill a gap in a liner panel according to one disclosed non-limiting embodiment of the present disclosure includes: applying a nickel braze alloy composition onto a gap in a liner panel; subjecting the nickel braze alloy composition to a melt cycle; and subjecting the nickel braze alloy composition to a diffusion cycle after the melt cycle.

Abstract: A liner panel for a gas turbine engine includes a cold side having a backside feature and a hot side with a variable polarity weld.

Abstract: A process for repairing a workpiece includes the steps of: providing a workpiece having at least one interior surface requiring restoration; providing a source of repair material; and depositing the repair material onto the at least one interior surface using a technique which is a near non-line of sight technique.

Abstract: A method of repairing a braze joint and the resulting joint includes removing an unsuitable portion of a first joining material in a joint between a first member and a second member of an aerospace assembly and cleaning the joint. A stripping solution is used to remove the unsuitable portion of the first joining material. A first cleaning solution is used to clean the joint, and the joint is further cleaned using a second cleaning solution. During a rebrazing step, a second joining material moves into a void left by the removed unsuitable portion from the removal step to form a new joint between the first member and the second member that includes the remaining first joining material and the second joining material.

Abstract: In accordance with a first embodiment of the present invention, a nickel alloy welding wire is made from a material comprising from about 4.75 to 5.25 wt % chromium, from about 5.5 to 5.8 wt % aluminum, from about 5.6 to 6.2 wt % tungsten, from about 8.0 to 8.3 wt % tantalum, from about 1.7 to 2.1 wt % molybdenum, from about 9.5 to 10.5 wt % cobalt, from about 2.8 to 3.2 wt % rhenium, from about 0.07 to 0.30 wt % carbon, from about 0.02 to 0.04 wt % boron, from about 0.08 to 0.12 wt % zirconium, from about 0.08 to 0.12 wt % yttrium, from about 1.0 to 1.5 wt % hafnium, and the balance nickel. In a second embodiment of the present invention, a nickel alloy welding wire is made from a material comprising from about 4.75 to 5.25 wt % chromium, from about 5.5 to 5.8 wt % aluminum, from about 5.6 to 6.2 wt % tungsten, from about 8.0 to 9.0 wt % tantalum, from about 1.7 to 2.1 wt % molybdenum, from about 9.5 to 10.5 wt % cobalt, from about 2.8 to 3.2 wt % rhenium, from about 0.18 to 0.30 wt % carbon, from about 0.

Abstract: A method of repairing a braze joint and the resulting joint includes removing an unsuitable portion of a first joining material in a joint between a first member and a second member of an aerospace assembly and cleaning the joint. A stripping solution is used to remove the unsuitable portion of the first joining material. A first cleaning solution is used to clean the joint, and the joint is further cleaned using a second cleaning solution. During a rebrazing step, a second joining material moves into a void left by the removed unsuitable portion from the removal step to form a new joint between the first member and the second member that includes the remaining first joining material and the second joining material.

Abstract: A method of homogeneously welding a superalloy which includes preheating the superalloy prior to welding and allowing it to cool prior to welding. The alloy is then welded, cooled to room temperature and then heated to stress relieve.