Methods provided for remotely stopping a crack in a component of a gas turbine engine are provided, along with methods of remotely cleaning a surface area of a component of a gas turbine engine. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; and drilling a hole into the base of the defect. An integrated repair interface is also provided.

A method for design in indenter apparatus for plastically straining a workpiece including a weld nugget, adjacent heat affected zones, and the adjacent parent-metal portions or new metal portions, throughout the weld nugget volume and heat affected zone, to produce threshold levels of uniform plastic strain which meet or exceed plastic strain levels that provide, when the weld nugget and heat affected zone is heat treated, a recrystallized grain structure metallurgically comparable to the grain structure of the parent-metal. The indenter provided by the optimization methods may be used to advantageously in a method for the repair of damaged rotors, including integrally bladed rotors, in gas turbine engines, such as in aircraft engines. Blades for gas turbine engines, including integrally bladed rotors, may be advantageously provided constructed by the methods taught.

Systems and methods for repairing corrosion damage of a part of a thrust reverser assembly. The method includes removing the part having an inner surface and an outer surface. The method also includes removing an outer skin from the inner surface and the outer surface of the part. The method further includes installing a ply of synthetic fiber material onto an area of the inner surface or the outer surface of the part. The method also includes installing one or more doublers onto the ply of synthetic fiber material and heat curing layers of film adhesive. The method further includes applying an edge seal to gaps between the one or more doublers and the inner surface or outer surface of the part. The method also includes installing the outer skin to the inner surface and the outer surface of the part and installing the part to the thrust reverser assembly.

Systems and methods for repairing corrosion damage of a part of a thrust reverser assembly. The method includes removing the part having an inner surface and an outer surface. The method also includes removing an outer skin from the inner surface and the outer surface of the part. The method further includes installing a ply of synthetic fiber material onto an area of the inner surface or the outer surface of the part. The method also includes installing one or more doublers onto the ply of synthetic fiber material and heat curing layers of film adhesive. The method further includes applying an edge seal to gaps between the one or more doublers and the inner surface or outer surface of the part. The method also includes installing the outer skin to the inner surface and the outer surface of the part and installing the part to the thrust reverser assembly.

Provided is a crack repair method of melting and eliminating a crack generated in a steel material, the method including holding a tab plate in surface contact with the steel material in which the crack is generated, thereafter continuously irradiating the tab plate to a first end portion of the crack in the steel material with a laser beam, and subsequently continuously irradiating the crack with the laser beam along the crack to a second end portion of the crack to melt and eliminate the crack. Consequently, when eliminating the crack generated in a constituent member of an existing structure or a constituent member such as a machine component, the crack can be eliminated without forming a through hole in the constituent member.

A method is provided for servicing a jointed rotor blade of a wind turbine. The jointed rotor blade is positioned in a six o'clock position and a blade tip support element is secured to a tip section of the jointed rotor blade. A lift-support element is secured at a mounting location above the blade tip support element. A lifting line is coupled between the lift-support element and the blade tip support element. The tip section is separated from the root section of the jointed rotor blade such that the tip section is suspended above a support surface of the wind turbine via the blade tip support element and the lifting line. The tip section of the jointed rotor blade is serviced.

A method of furnace-less brazing of a substrate is provided. The method includes providing a substrate having a brazing region thereon; disposing braze precursor material containing a nickel powder, an aluminum powder, and a platinum group metal powder on the brazing region; and initiating an exothermic reaction of the braze precursor material such that the exothermic reaction produces a braze material that reaches a braze temperature above the liquidus temperature for the braze material. A braze precursor material is also provided.

A power end frame includes a housing and a face plate secured to the housing. During use, components of the power end frame, including the housing and the face plate, are subjected to large tensile stresses. This disclosure describes a method of imparting compressive stresses in the power end frame to resist these large tensile stresses.

A lock and pin for the structural and fluid tight repair of cracks not amenable to high temperature repairs or synthetic material patches. Fluid tight pins and locks seal the crack while one or more locks prevent the crack from growing. These repairs need to endure the remaining life cycle of the machinery part while withstanding all the strain, pressure, heat and expansion and contraction of the part before the crack(s) were formed. Often these cracks evolved due to engineering design flaws that will require even greater strength from these areas than when new.

A lock and pin for the structural and fluid tight repair of cracks not amenable to high temperature repairs or synthetic material patches. Fluid tight pins and locks seal the crack while one or more locks prevent the crack from growing. These repairs need to endure the remaining life cycle of the machinery part while withstanding all the strain, pressure, heat and expansion and contraction of the part before the crack(s) were formed. Often these cracks evolved due to engineering design flaws that will require even greater strength from these areas than when new.