Abstract: A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and between at least one radially extending flange, the radially extending flange being formed with a plurality of bolt holes, includes the steps of removing a portion of the flange including at least one bolt hole. The removed portion is associated with a defect and a remaining portion of the flange includes at least one non-removed bolt hole. A replacement portion is obtained to replace the removed portion. The replacement portion is secured in an opening left in the flange by the removed portion. A repaired gas turbine engine casing is also disclosed.

Abstract: A bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A doubler is mechanically fastened adjacent to the separation. Another bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A cushioned tube support is welded to the bracket base. A doubler is mechanically fastened adjacent to the separation. A method of assembling a bracket assembly for a gas turbine engine includes mechanically fastening a doubler to a bracket base adjacent to a separation between a first bended feature and a second bended feature.

Abstract: A method of repairing a turbine engine case includes the steps of removing worn material from a retention hook in a casing, and inserting an insert into a recess within the hook.

Abstract: Methods for repairing gas turbine engine casings and repaired casings are provided. In this regard, a representative method for repairing a gas turbine engine casing includes: removing an annular portion of the engine casing; and attaching an annular replacement portion to the engine casing.

Abstract: A bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A doubler is mechanically fastened adjacent to the separation. Another bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A cushioned tube support is welded to the bracket base. A doubler is mechanically fastened adjacent to the separation. A method of assembling a bracket assembly for a gas turbine engine includes mechanically fastening a doubler to a bracket base adjacent to a separation between a first bended feature and a second bended feature.

Abstract: A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and between at least one radially extending flange, the radially extending flange being formed with a plurality of bolt holes, includes the steps of removing a portion of the flange including at least one bolt hole. The removed portion is associated with a defect and a remaining portion of the flange includes at least one non-removed bolt hole. A replacement portion is obtained to replace the removed portion. The replacement portion is secured in an opening left in the flange by the removed portion. A repaired gas turbine engine casing is also disclosed.

Abstract: A method of repairing a turbine engine case includes the steps of removing worn material from a retention hook in a casing, and inserting an insert into a recess within the hook.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Abstract: Gas turbine engines systems and related methods involving dimensionally restored fasteners are provided. In this regard, a representative method for dimensionally restoring a mechanical fastener for a gas turbine engine includes: providing a mechanical fastener; and relocating existing material of the fastener such that a dimension of the fastener is restored.

Abstract: Gas turbine engines systems and related methods involving dimensionally restored fasteners are provided. In this regard, a representative method for dimensionally restoring a mechanical fastener for a gas turbine engine includes: providing a mechanical fastener; and relocating existing material of the fastener such that a dimension of the fastener is restored.

Abstract: Methods for repairing gas turbine engine casings and repaired casings are provided. In this regard, a representative method for repairing a gas turbine engine casing includes: removing an annular portion of the engine casing; and attaching an annular replacement portion to the engine casing.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Abstract: A defect in a splitter fairing of a turbine engine is repaired by removing a forward portion of the splitter fairing and salvaging the remaining original portion of the splitter fairing. The forward portion includes an inner flange and outer surface that create a channel. A replacement ring is provided and welded to the original portion. The replacement ring has minimum dimensions equal to the maximum height and width of the removed forward portion. Material from the replacement ring is then removed to obtain a profile with essentially the same profile for the inner flange, outer surface, and channel as the original dimensions of the splitter fairing before the defect occurred.

Abstract: A peptide having growth factor type activity (mitogenic and agonist/antagonist for the EGF receptor) which is a TGF-.alpha. analog but contains a bicyclic Pro analog (for instance D-2-azabicyclo[2,2,1]heptane-3-carboxylic acid), an N-terminal Phe or Trp residue, and a disulfide bridge.