Abstract: A method for powder-bed-based additive manufacturing of a component, includes setting irradiation vectors for a layer to be irradiated for the component, wherein, irradiation vectors are irradiated below a length of 1 mm in a pulsed irradiation operation; and a pulse frequency below 3 kHz and a scan speed below 250 mm/a are selected. A correspondingly manufactured component is produced.

Abstract: A method for providing CAM manufacturing instructions for the powder-bed-based additive manufacturing of a component wherein a geometry of the component, with a solid material region, a transition region, and a porous component region, is defined on the basis of CAD data. Irradiation parameters for the manufacturing of the component, including an irradiation power, a scanning speed, a scanning pitch, and a layer thickness, are varied within the transition region in such a way as to form a porosity gradient of the structure of the component between the solid material region of the component and the porous component region.

Abstract: A method for providing data for selectively irradiating a powder layer in additive production, the method includes: providing a predefined component geometry for a component; dividing the component geometry into at least one first component layer and an overlying second component layer for additive production, wherein a contour of the second component layer is incongruent with a contour of the first component layer; and continuously defining at least one production parameter for additively producing the second component layer in region of a molten bath of a contour of the first component layer. A corresponding component is produced and a computer program product implements the method.

Abstract: A method for providing manufacturing instructions for the powder-bed-based additive manufacturing of a component includes providing first irradiation vectors for a layer to be additively manufactured, which first irradiation vectors, upon appropriate irradiation by an energy beam, in particular a laser beam or electron beam, cause a porous structure of the layer, as well as providing the first irradiation vectors for a layer which is to be additively manufactured and which follows the layer, in such a way that paths of a porous structure of the layer and of the following layer at least partially overlap in order to allow for a flow through the manufactured component along a build-up direction.

Abstract: A method for producing a support structure in the additive manufacturing of a component, includes: a) providing a geometry for the component having a region to be supported, b) providing a support structure for the region of the component, c) defining an irradiation pattern for an irradiation of layers of a raw material for the support structure, wherein surface vectors for an irradiation for a structure of the component extend into a region of the support structure, wherein common surface vectors are defined for the component and for the support structure, and d) selective irradiation of layers of the raw material for the component and the provided support structure according to the defined irradiation pattern.

Abstract: A method for the additive construction of a structure for a component includes the following steps: providing a prefabricated component for the component on a building board, wherein the component has a separating plane, providing a powder bed from a base material for the structure, moving the building board closer to a coating device, aligning a processing surface and the separating plane of the component for preventing adhesion between the component and the coating device, and optically measuring a surface of the powder bed.

Abstract: A method of additive manufacturing includes a) providing a component geometry with a hole and, b) selectively irradiating a powder bed with an energy beam according to the geometry in a layerwise manner, wherein in layers of the component including the hole, the respective regions which define the hole are irradiated with the energy beam such that a supporting structure is generated in the hole having a lower rigidity than a structure of the component. The supporting structure is used for counteracting stress or distortion during the additive buildup. A computer program product and apparatus correspond to the method.

Abstract: A computer-implemented method of calculating a gap distance between a support structure and a component which is to be build up additively by powder bed fusion, includes: a) providing a component design of the component, b) selecting at least on support surface of the component based on the provided component design and a process analysis, wherein the support surface requires support during the buildup, c) providing a support design of a support structure for supporting the component during the buildup, d) recording CAM-data for the buildup of the component, and, e) calculating an optimal gap distance to be hold during the buildup between the support structure and the support surface, wherein the calculation is based on the selected support surface and the recorded CAM-data, wherein the gap distance is further rated to be large enough to avoid a structural connection between the support surface and the support structure.

Abstract: A method for heating a base material in additive manufacturing includes a) providing an energy beam for the heating of the base material, wherein the base material is arranged to at least partly form a manufacturing plane, and b) irradiating the manufacturing plane for the heating with the energy beam under scaled irradiation parameters, wherein the scaled irradiation parameters are derived in that irradiation parameters for fusing the base material are scaled by a scaling factor, and wherein the scaling factor includes a quotient of a heating beam diameter and a fusion beam diameter.

Abstract: A seal segment for a turbine and an assembly for sealing the gaps between seal segments and stator vanes of a turbine. The seal segments have a plate-shaped wall, the first lateral surface of which faces the vane tips in the assembled state of the seal segments, is surrounded by a closed circumferential edge, and can be divided into four lateral wall sections, and the plate-shaped wall has a seal element which is arranged over the entire surface of the lateral surface. A number of seal lamellae which are secured on one side are provided on at least one of the lateral wall sections and/or on at least one of the seal lateral wall sections facing adjacent seal segments when the seal segments are assembled in a turbine so as to form a ring in order to reduce a flow along the corresponding lateral wall section.

Abstract: A method for additively manufacturing a tip structure on a pre-existing part includes: a) placing the part in a build space of a beam-assisted additive manufacturing setup and below a transparent aligning plate, b) engraving a top contour of the part onto the aligning plate with an energy beam of the setup, c) aligning a top surface of the part such that the top surface coincides with the engraved contour, d) removing the aligning plate from the setup, and e) additively manufacturing the tip structure according to a predefined geometry on the top surface.

Abstract: A component wall of a hot gas component for a gas turbine, which in a double-walled design, has an outer wall which is hotter and an inner wall which is cooler during operation. The interior is divided by partition walls extending between the inner and outer walls. A coolant flows into the interior through inlet openings in the inner wall and out through outlet openings in the outer wall. An inlet cavity is directly connected to at least one of the inlet openings without being directly connected to outlet openings. A second cavity is provided directly next to the inlet cavity. The second cavity is directly connected, as an outlet cavity, only to at least one of the outlet openings, without being directly connected to inlet openings. The partition wall has at least one through-opening for conducting the coolant from the inlet cavity into the outlet cavity.

Abstract: A method for determining the position of a construction platform for additive manufacturing of a component, includes marking a construction platform for additive manufacturing, providing a marking region of the construction platform with reference features, wherein the reference features are arranged and designed in such a way that a position of the reference features relative to a reference point are captured using an optical scanning method, and optically scanning the construction platform in the marking region and capturing the relative position with the aid of the reference features and the reference point.

Abstract: A seal segment for a turbine and an assembly for sealing the gaps between seal segments and stator vanes of a turbine. The seal segments have a plate-shaped wall, the first lateral surface of which faces the vane tips in the assembled state of the seal segments, is surrounded by a closed circumferential edge, and can be divided into four lateral wall sections, and the plate-shaped wall has a seal element which is arranged over the entire surface of the lateral surface. A number of seal lamellae which are secured on one side are provided on at least one of the lateral wall sections and/or on at least one of the seal lateral wall sections facing adjacent seal segments when the seal segments are assembled in a turbine so as to form a ring in order to reduce a flow along the corresponding lateral wall section.

Abstract: An irradiating method for the additive production of a component in order to heal structural defects in an additively constructed structure for the component. The method includes the providing of a laser or electron beam and the selective irradiating of a defect region of an additively constructed layer of the structure by the laser or electron beam according to a predetermined, in particular closed trajectory, which defines the defect region, wherein the defect region contains a structural defect. A method for additive production, a correspondingly produced component and a computer program product utilize the method.

Abstract: A method of providing an abrasive structure for additive manufacturing includes determining of a design of a portion of a powdery base material and selectively solidifying the portion in a bed of the base material according to the determined design such that an abrasive structure is generated, wherein the abrasive structure is still movable in the bed of the base material. Further, an additively manufactured component has an internal surface with a surface roughness of less than 100 ?m, preferably less than 60 ?m.

Abstract: A component wall of a hot gas component for a gas turbine, which in a double-walled design, has an outer wall which is hotter and an inner wall which is cooler during operation. The interior is divided by partition walls extending between the inner and outer walls. A coolant flows into the interior through inlet openings in the inner wall and out through outlet openings in the outer wall. An inlet cavity is directly connected to at least one of the inlet openings without being directly connected to outlet openings. A second cavity is provided directly next to the inlet cavity. The second cavity is directly connected, as an outlet cavity, only to at least one of the outlet openings, without being directly connected to inlet openings. The partition wall has at least one through-opening for conducting the coolant from the inlet cavity into the outlet cavity.

Abstract: A method for additively manufacturing a tip structure on a pre-existing part includes: a) placing the part in a build space of a beam-assisted additive manufacturing setup and below a transparent aligning plate, b) engraving a top contour of the part onto the aligning plate with an energy beam of the setup, c) aligning a top surface of the part such that the top surface coincides with the engraved contour, d) removing the aligning plate from the setup, and e) additively manufacturing the tip structure according to a predefined geometry on the top surface.

Abstract: A method for selectively irradiating a material layer in additive manufacturing, the method includes: providing a predetermined component geometry which contains geometrical information of individual layers of a component to be manufactured additively; and defining layer by layer an irradiation pattern in areas of a layer to be constructed for the manufacturing of the component, the irradiation pattern comprising irradiation vectors in each area; and, if a predefined irradiation vector length is not reached in a first area, lengthening irradiation vectors in a second area of the layer adjacent to the first area as far as a component contour.

Abstract: A method in which a three-dimensional component is produced and is provided on its component surface with a machine-readable code, wherein the code is produced in one part with the component and has a plurality of three-dimensional code elements, which represent the coded data in binary form on the basis of raised regions and non-raised regions in relation to a reference plane. A method in which a three-dimensional component is produced and is provided on its component surface with a machine-readable code, wherein the code is produced in one part with the component and has a plurality of three-dimensional code elements which represent the coded data in binary form on the basis of recessed regions and non-recessed regions in relation to a reference plane. A component includes such a code.