A method for repairing a turbine housing of an air cycle machine that includes removing damaged material from a journal bearing bore of the turbine housing and forming the journal bearing bore. Next, the inner diameter of the journal bearing bore is determined and a cylindrical insert is formed. The cylindrical insert includes a first end, a second end, an inner surface, a step located at the first end, and an outer surface with an outer diameter that provides a diametric interference with the inner diameter of the journal bearing bore. The second end of the cylindrical insert is inserted into an inlet of the journal bearing bore up to the step. The cylindrical insert is secured to the turbine housing and both are stress relieved by heating. Following the stress relief, the inner surface of the cylindrical insert is formed and seal grooves are formed on the inner surface.

Methods for repairing composite cylindrical components are provided. One exemplary method for repairing a cylindrical component defining an axial direction, a radial direction, and a circumferential direction includes removing a damaged region of the cylindrical component. A flange extending from a cylindrical body of the cylindrical component is included in the damaged region. One or more arc segments that extend along the circumferential direction are connected with the existing cylindrical component. At least one of the arc segments includes a prefabricated flange. One or more plies are laid up to connect the arc segments with the existing cylindrical component to repair the damaged region of the cylindrical body and the prefabricated flange formed integrally with one of the arc segments replaces the damaged portion of the flange. Repaired cylindrical components are also provided.

A method and apparatus for a hammer mill's worn discs. The disc can be refurbished by removing a peripheral portion of the disc and placing a ring on the peripheral rim left on the disc. The ring preferably has a tapered, radially inwardly facing surface that abuts the peripheral rim of the disc to form annular gaps on both sides of the disc/ring junction. Molten metal, such as during a welding process, is placed in the annular gaps to form annular beads that mount the ring to the disc effectively as if the ring, beads and disc were one integral piece. The disc/ring combination is preferably heat-treated to metallurgically improve the disc in order to prepare the disc's peripheral edge, which is made up of the ring, for impacts during use.

A method for repairing a bucket of a piece of earthwork equipment is provided, the method being specifically applicable to the repair of electric shovel buckets.

The present application discloses a method for repairing a damaged counterbore in a variable vane shroud. A layer of base material is removed from the vane shroud adjacent the counterbore such that a damaged portion of the counterbore is removed. A shrink-fit insert having a size slightly larger than that corresponding to the layer of base material removed from the shroud is placed into the area of removed material such that the counterbore is restored to pre-damaged dimensions upon installation of the shrink-fit insert.

Disclosed is a method for repairing a receiving hook for guide vanes, wherein the receiving hook is arranged in a housing of a turbomachine. The method comprises removing first material in a region of the receiving hook, which region extends over the circumference of the housing and thereafter applying second material in or on a region which extends over the circumference of the housing. The application of second material is performed using localized heat.

A repaired article includes a body extending between a first side and a second side. The body has a repair section with an associated thickness between the first side and the second side. The repair section includes regions of plastic deformation distributed through the thickness. A gas turbine engine including the body is also disclosed.

A gearbox housing of an aircraft includes a surface configured to contact with and support a load of a component of the aircraft such that the surface is susceptible to corrosion. The surface has an area from which a portion of material was removed. A structural deposit is formed by cold spraying one or more layers of powdered material within the area. The structural deposit is configured to share the load applied to the surface by the component.

A method for repairing bucket which saves time in maintenance operations, wherein the bucket is cut by separating it into two parts, an upper part which is maintained and repaired, and an original bottom one, which is retired replacing it once the repairs of the top are completed with a new bottom part. Repairs are made at the top which has been maintained, and once said repairs are finished the top is welded to the new bottom. The original door is removed and replaced by a new door or a previously repaired one which is kept in Stock. Accessory parts and the new door are mounted and the corresponding tests are done to obtain a new reconditioned bucket.

The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component.