Abstract: A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7?), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7?) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

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 turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating.

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 leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a plurality of spaced-apart leaves disposed in a concentric circle around the axis and fixed in position. Each of the leaves includes a surface oriented essentially parallel to the axis and an integrally formed element configured to position and retain the leaves in the leaf seal.

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 component, especially a hot gas component of a turbomachine, has at least one passage (7, 7?), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7?) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

Abstract: A measuring apparatus (1) for contactless detection of a distance between a surface (7) of a measurement object (8) and the measuring apparatus (1), and for simultaneous contactless visual detection of the surface (7), has a measuring head (2) holding a distance measuring device (4), a camera apparatus (5) and an illumination device (6), the illumination device (6) illuminating an operating point (9) on the surface (7) of the measurement object (8) that is simultaneously focused by the camera apparatus (5) and the distance measuring device (4). On an optical axis (10), between the illumination device (6) and the operating point (9), a mirror and filter device (11), that has at least one dichroic mirror (12) that transmits or reflects light beams as a function of wavelength, and thereby splits light reflected by the operating point (9) between the distance measuring device (4) and the camera apparatus (5), is provided.

Abstract: A method of removing unwanted coating material from cooling passages of a turbine component includes determining coordinates of the position and orientation of cooling passages at the surface of the turbine component and determining reference points in the region of the cooling passages. After coating of the turbine component, the reference points are measured once again and the thickness of the coating is calculated. In a basic processing program, the data for the position, passage orientation and coating thicknesses and also CAD data for the cooling passages are interlinked and a laser processing program is automatically adapted for each individual cooling passage. Using the laser processing program, a pulsed laser is guided over disk-shaped volume segments of the unwanted coating material and the material is removed in the process.

Abstract: It is disclosed a method of applying a coating (12) with a controlled laser metal forming process. A light source with a specific power and a signal capturing apparatus is moved over an article (1) to form locally a melt pool (7) on the surface (5) of the article (1) to which a coating powder (8) is injected. An optical signal (13) is captured from the melt pool (7), and the monitored optical signal (13) is used for the determination of the temperature and temperature fluctuations of the melt pool (7). Furthermore, a control system (16) is used to adjust at least one process parameter such as the power of the light source to obtain desired melt pool properties. Subsequently the melt pool (7) solidifies. The high degree of control over the microstructure provides an efficient tool for generating laser metal formed hard coatings (12) with optimised wear properties.

Abstract: A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7?), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7?) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

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 controlled remelting of or laser metal forming on the surface (5) of an article (1) can include moving a light source and a signal capturing apparatus over the article (1). The light source having a specific power can be used to melt the surface (5) of the article (1) locally and to form a melt pool (7). Thereby an optical signal (13) is captured by the signal capturing apparatus from the melt pool (7), and the monitored optical signal (13) is used for the determination of temperature and temperature fluctuations as properties of the melt pool (7). Furthermore, a control system (16) with a feedback circuit is used to adjust at least one process parameter such as the power of the light source such that desired melt pool properties are obtained. Subsequently the melt pool (7) solidifies.

Abstract: A measuring apparatus (1) for contactless detection of a distance between a surface (7) of a measurement object (8) and the measuring apparatus (1), and for simultaneous contactless visual detection of the surface (7), has a measuring head (2) holding a distance measuring device (4), a camera apparatus (5) and an illumination device (6), the illumination device (6) illuminating an operating point (9) on the surface (7) of the measurement object (8) that is simultaneously focused by the camera apparatus (5) and the distance measuring device (4). On an optical axis (10), between the illumination device (6) and the operating point (9), a mirror and filter device (11), that has at least one dichroic mirror (12) that transmits or reflects light beams as a function of wavelength, and thereby splits light reflected by the operating point (9) between the distance measuring device (4) and the camera apparatus (5), is provided.

Abstract: A thermal turbomachine is disclosed having at least one row of rotor blades. At least one first rotor blade has a greater radial length than the others and at the blade tip is equipped with a first abrasive layer. At least one rotor blade which has a shorter radial length than the first rotor blade is equipped with a second abrasive layer at the blade tip. The first abrasive layer has a better cutting capacity and a lower thermal stability than the second abrasive layer. During commissioning of the thermal turbomachine, the first abrasive layer is in contact with the abradable layer of the stator, and during continuous operation of the thermal turbomachine the second abrasive layer is in contact with the abradable layer of the stator.

Abstract: A method for repairing or renewing cooling holes of a coated component of a gas turbine, includes the step of removing an old coating from an outer side of the component. The cooling hole, after removing the old coating, in a longitudinal section, has an old cross section which is larger than a nominal cross section which the cooling hole has in this longitudinal section in an original new state of the finished component. The method also includes applying a new coating to the component at least in the longitudinal section of the cooling hole so that the cooling hole, in the longitudinal section, has an interim cross section which is smaller than the nominal cross section. The method also includes partially removing the new coating inside the cooling hole so that the cooling hole, in the longitudinal section, has a new cross section which is about the same size as the nominal cross section.

Abstract: An automated machining process for machining of an obstructed passage (5) of an article (1) includes the steps of deriving the position and orientation of the passage (5) from automated processing of images of the passage (5) and additional information from a distance measurement device and saving positions and orientations of the passage (5) as local coordinates with respect to a reference coordinate system attached to the material that surrounds the passage (5). The saved positions and orientations of the passage (5) are used for subsequent removal of unwanted material from the obstructed passage (5).

Abstract: A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a plurality of spaced-apart leaves disposed in a concentric circle around the axis and fixed in position. Each of the leaves includes a surface oriented essentially parallel to the axis and an integrally formed element configured to position and retain the leaves in the leaf seal.