Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).

Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.

Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).

Abstract: A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.

Abstract: A method for repairing an ex-service gas turbine component (10) includes the steps of: removing a damaged section (13) from the gas turbine component (10), manufacturing a 3-D article, which fits in the gas turbine component (10) to replace the removed damaged section (13), and joining the gas turbine component (10) and the 3-D article inserted therein. Reduced cost, improved flexibility and productivity, and simplified handling are achieved by removing the damaged section (13) in the form of a cut-out section along a split line (14) as one single cut-out piece (15), measuring the cut-out piece (15) to obtain the actual non-parametric geometry data set of the cut-out piece (15), and manufacturing the 3-D article based on the geometry data set of the cut-out piece (15).

Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.

Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).

Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).

Abstract: A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.