Abstract: A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.

Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.

Abstract: An air-cooled combustor liner segment, including a plurality of spaced apart radially outwardly extending integral heat exchange protuberances or pins is repaired by providing a replacement edge member for a service damaged edge portion including such pins. The damaged edge portion is removed to provide a segment body with a body repair surface, of a first shape, from which the damaged edge portion was removed. A replacement edge member is provided including a plurality of spaced apart radially outwardly extending integral pins to replace pins in the removed edge portion. The replacement edge member includes a replacement edge member repair surface of a second shape matched with the first shape of the body repair surface. The body repair surface and the replacement edge member repair surface are disposed in juxtaposition at a matched junction therebetween so that their respective radially outer surfaces substantially are coextensive.

Abstract: A wear-resistant assembly of a turbine outer case and a turbine vane is fabricated by providing a turbine outer case, and a turbine vane that, when assembled, is supported on the turbine outer case in a support region such that a vane-support area of the turbine vane contacts a case-support area of the turbine outer case. A wear-resistant material is welded to a weld area of at least one of the vane-support area and the case-support area. In some circumstances, as where the turbine outer case and the turbine vane have previously been in service, material may be machined from the support region before the welding.

Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.

Abstract: The present invention provides a method of repairing a turbine nozzle segment having one or more vanes disposed between outer and inner bands. The method includes separating at least one of the outer and inner bands from the vanes. The vanes are cut through in close proximity to the band being replaced. A newly manufactured replacement band including protruding vane stubs is provided for each one of the original bands being replaced. The replacement band is attached to the vanes by welding.

Abstract: A combustor dome assembly includes a spectacle plate having an opening formed therein that defines an inner circumferential edge, at least one swirler assembly defining an inner cylindrical surface, and at least one deflector having an outer cylindrical surface. These components are arranged such that the outer cylindrical surface is joined to the inner circumferential edge and to the inner cylindrical surface. One preferred method of manufacturing the combustor dome assembly includes placing a first ring of joining material over the outer cylindrical surface. Then, the outer cylindrical surface is inserted into the spectacle plate opening so that the first ring is sandwiched between a first surface of the spectacle plate and a shoulder formed on the deflector. A second ring of joining material is next placed over the outer cylindrical surface, and a third ring of joining material is inserted into an annular groove formed in the inner cylindrical surface.

Abstract: A method and apparatus for aiding in positioning during assembly of a locomotive wheel with respect to a drive gear mounted adjacent the wheel during assembly and for maintaining the position of the drive gear during locomotive operation. The apparatus includes a lateral stop including a spacer formed of a semi-elastomeric material having a low coefficient of friction and specially adapted to fit into a stress relief groove of an axle between a hub of the drive gear and a hub of the wheel. The spacer is so designed as to be installable on the locomotive axle after installation of the drive gear, to be self-centering on the axle and to inhibit rotation of the spacer with respect to the axle such that the axle will not be marked circumferentially by spacer rotation.

Abstract: A stator frame comprises a connection end (CE) casting having at least one CE integral partial tie bar extending from an inboard side of the CE casting and a pinion end (PE) casting having at least one PE integral partial tie bar extending from an inboard side of the PE casting. Each PE partial tie bar is welded to a respective CE partial tie bar.