Abstract: A computer-implemented method of providing structured data of an additive manufacturing process includes providing a first type of data (i) with coded information about a machine set up and/or about a prepared build job, providing a second type of data (ii) with coded information about a build area, providing a third type of data (iii) with coded information about a quality monitoring during the manufacturing process, the information from each type of data being different from one another, and mapping the first, the second and the third type of data to a voxel field (Vn). Each voxel of the field, representing a three-dimensional portion of a 3D-model of the component to be manufactured, is correlated to the first, second and third type of data in a coded way. A related data structure product, apparatus, communication apparatus, and additive manufacturing device are provided.

Abstract: A nickel-base alloy composition includes nickel as the main constituent and the further constituents in percent by weight (% by weight): 0.04 to 0.10% carbon (C), 8 to 13% tantalum (Ta), 12 to 20% chromium (Cr), 3 to 25% cobalt (Co), less than 0.03% manganese (Mn), less than 0.06% silicon (Si), 0 to 6% molybdenum (Mo), less than 5.0% iron (Fe), 2 to 4% aluminum (Al), less than 0.01% magnesium (Mg), less than 0.02% vanadium (V), 0 to 6% tungsten (W), less than 1% titanium (Ti), less than 0.03% yttrium (Y), 0.005 to 0.015% boron (B), less than 0.003% sulfur (S), 0.005 to 0.04% zirconium (Zr) and less than 3% hafnium. Additionally provided are an additive manufacturing method, a method of additively manufacturing a component part from a powder of the alloy composition provided, a corresponding intermediate alloy, and a component part consisting of the nickel-base superalloy.

Abstract: For the first time, components can be produced from MAX-phases due to the use of an additive production method. A method for producing a component from MAX phases, in particular from Ti3SiC2 and/or Cr2AlC, in which an additive manufacturing process is disclosed. Powder is applied layer by layer and densified, the grain sizes of the powder lying at 10 ?m to 60 ?m, in which the scanning speed between the energy beam of the laser or electron beam and substrate with powder lies between 400 mm/s and 2000 mm/s, in particular at 1000 mm/s to 1500 mm/s, in which the power output is between 80 W and 250 W, in particular is 100 W to 170 W, in which a spot size of the energy beam lies between 30 ?m and 300 ?m.

Abstract: The use of a specific molybdenum-silicon-boron alloy and a particular production process in which powder is used makes it possible to achieve components which have a particular fiber-matrix structure and can be used for high-temperature applications and can also be produced inexpensively.

Abstract: A method for producing a component by the successive solidification of individual layers of powdered, granular or liquid material by irradiation with laser radiation using a laser, each layer being divided into an inner region and an edge region with an edge region surface, and, for each layer, after irradiation with the laser, at least the edge region surface of the edge region of the layer being irradiated with an ultrashort pulse laser. An optical irradiation device produces a component by successive solidification of individual layers of powdered, granular or liquid material.

Abstract: A method for generating, in layers, an application structure made of high heat resistant super alloys on a substrate is provided. A powdery construction material is melted by an energy beam at a working point, wherein the working point is guided across the substrate along a primary movement direction and thus swings transversely to the primary movement direction. The working point thereby swings from a first edge of a respective layer of the application structure to a second edge of the layer. In this way, a time interval passes between departure from a respective edge and a return to the respective edge directly following the departure, such that a melt bath on the respective edge solidifies into a paste-like zone during the time interval.

Abstract: An apparatus for a facility for additively manufacturing a component having a base forming a manufacturing surface, wherein the base includes a plurality of portions, and a plurality of temperature sensors being arranged in or below the manufacturing surface. At least one temperature sensor is further arranged in each portion and the temperature sensors are configured such that a temperature of each of the portions can be measured individually by the temperature sensors.

Abstract: The use of a specific molybdenum-silicon-boron alloy and a particular production process in which powder is used makes it possible to achieve components which have a particular fiber-matrix structure and can be used for high-temperature applications and can also be produced inexpensively.

Abstract: For the first time, components can be produced from MAX-phases due to the use of an additive production method. A method for producing a component from MAX phases, in particular from Ti3SiC2 and/or Cr2AlC, in which an additive manufacturing process is disclosed. Powder is applied layer by layer and densified, the grain sizes of the powder lying at 10 ?m to 60 ?m, in which the scanning speed between the energy beam of the laser or electron beam and substrate with powder lies between 400 mm/s and 2000 mm/s, in particular at 1000 mm/s to 1500 mm/s, in which the power output is between 80 W and 250 W, in particular is 100 W to 170 W, in which a spot size of the energy beam lies between 30 ?m and 300 ?m.

Abstract: A multi component braze filler alloy is described having a melting temperature less than about 1235 deg. C. and greater than about 1150 deg. C. This alloy can be processed by hot isostatic pressing (HIP) at a temperature above about 1065 deg. C. and is particularly suited for the repair of gas turbine blades and vanes, especially those made from Alloy 247. The relatively low Ti content in the present braze alloy tends to form less MC carbides at the joint interface, particularly in comparison with other braze alloys high in Zr and/or Hf. Processes for employing this braze filler alloy in processing of nickel-base superalloys, especially Alloy 247, are presented.

Abstract: A method for generating, in layers, an application structure made of high heat resistant super alloys on a substrate is provided. A powdery construction material is melted by an energy beam at a working point, wherein the working point is guided across the substrate along a primary movement direction and thus swings transversely to the primary movement direction. The working point thereby swings from a first edge of a respective layer of the application structure to a second edge of the layer. In this way, a time interval passes between departure from a respective edge and a return to the respective edge directly following the departure, such that a melt bath on the respective edge solidifies into a paste-like zone during the time interval.

Abstract: An oscillating welding method is provided. The oscillating movement during welding in the vertical and/or horizontal direction results in smaller grains being obtained, the smaller grains preventing the development of cracks during welding.

Abstract: A method for producing a component by the successive solidification of individual layers of powdered, granular or liquid material by irradiation with laser radiation using a laser, each layer being divided into an inner region and an edge region with an edge region surface, and, for each layer, after irradiation with the laser, at least the edge region surface of the edge region of the layer being irradiated with an ultrashort pulse laser. An optical irradiation device produces a component by successive solidification of individual layers of powdered, granular or liquid material.

Abstract: A nozzle for laser powder build-up welding, in particular, an annular powder channel for feeding powdery material into a processing region in front of the laser outlet opening, wherein the powder channel is designed in such a way that the angle included between the radially outer wall of the powder channel and the axis of the powder channel is constant or decreases in the direction of the material outlet opening at least in the region extending from the at least one material inlet opening to the material outlet opening is provided.

Abstract: A substrate (4) is remelted prior to deposition welding, thereby substantially reducing stresses in the region of the interface between the deposition welded portion (13) and the substrate (4).

Abstract: A crack repair method for a turbine component using spark plasma sintering: Applying filler material on a cracked portion of the turbine component. Applying joining pressure on the cracked portion of the turbine component by punches pressing on the component. Simultaneously heating the filler material by an application of electric current. Then cooling the heated filler material to form a joint at the cracked portion.

Abstract: Remelting during deposition welding of layers (7, 7?, 7?) enables a desired micro structure (10?) having enlarged grains to be controlled, which leads to improved properties at high temperatures.

Abstract: A powder supply device (1) for a laser powder welding device and a laser powder welding device having such a powder supply device (1). The powder supply device (1) has a nozzle head (3) which tapers along a longitudinal axis (2) of the powder supply device (1) in the direction to a first end (4). A cavity (6) is arranged radially about the longitudinal axis (2) in an interior of the nozzle head (3) and tapers to the first end (4) of the nozzle head (3). The cavity (6) opens out into an annular opening (7) at the first end (4) for discharging a powder. The powder supply device (1) has a plurality N of powder feed lines (8-1, 8-2, 8-3) which extend through a second end (5) of the nozzle head (3), which lies opposite the first end (4) of the nozzle head, in the direction toward the cavity (6) and direct the powder from a powder reservoir into the cavity (6).

Abstract: A multi component braze filler alloy is described having a melting temperature less than about 1235 deg. C. and greater than about 1150 deg. C. This alloy can be processed by hot isostatic pressing (HIP) at a temperature above about 1065 deg. C. and is particularly suited for the repair of gas turbine blades and vanes, especially those made from Alloy 247. The relatively low Ti content in the present braze alloy tends to form less MC carbides at the joint interface, particularly in comparison with other braze alloys high in Zr and/or Hf. Processes for employing this braze filler alloy in processing of nickel-base superalloys, especially Alloy 247, are presented.

Abstract: A multi component braze filler alloy is described having a melting temperature less than about 1235 deg. C. and greater than about 1150 deg. C. This alloy can be processed by hot isostatic pressing (HIP) at a temperature above about 1065 deg. C. and is particularly suited for the repair of gas turbine blades and vanes, especially those made from alloy 247. The relatively low Ti content in the present braze alloy tends to form less MC carbides at the joint interface, particularly in comparison with other braze alloys high in Zr and/or Hf.