Abstract: The invention relates to a method for determining individual vectors for open-loop and/or closed-loop control of at least one energy beam of a layering apparatus, comprising at least the steps of: providing layer data characterizing at least one component layer of a component to be additively manufactured, on the basis of the layer data, determining individual vectors, according to which at least one energy beam is to be moved relative to a construction and joining zone of the layering apparatus in order to solidify a material powder selectively to the component layer, determining at least one node point of a plurality of individual vectors, and adapting at least one property of at least one individual vector of the at least one node point, the at least one property being selected from a group comprising spatial orientation, radiation sequence in relation to at least one other individual vector, and vector length.

Abstract: A method for ascertaining the concentration of at least one material in a powder mixture used as starting material for the production of a component in an additive production method, comprising: providing the powder mixture having at least two different materials; guiding a high-energy beam generated by a radiation source over the surface of the powder mixture; detecting by a detection unit at least one brightness value of at least one subregion of the surface irradiated by the high-energy beam during the irradiation; ascertaining by an analysis unit the concentration of at least one material in the powder mixture depending on the detected at least one brightness value and at least one predetermined reference brightness value for a concentration and/or a concentration range of the material.

Abstract: The invention relates to a method for the additive manufacture of at least one region of a component. Here, at least the following steps are carried out: a) layer-wise application of at least one powder-form component material onto a component platform in the region of a build-up and joining zone; b) layer-wise and local solidifying of the component material by selective exposure of the component material by at least one high-energy beam in the region of the build-up and joining zone, with the formation of a component layer; c) layer- wise lowering of the component platform by a pre-defined layer thickness; and d) repeating steps a) to c) until the component region or the component has been completely fabricated.

Abstract: A method for manufacturing at least a metallic portion of a component: a) depositing metallic material layer by layer onto at least one building platform; b) locally fusing and/or sintering the material layer by layer by supplying energy by at least one high-energy beam in the region of a buildup and joining zone to form at least a portion of at least one component layer of the component portion and/or of the component; c) lowering the building platform layer by layer by a predefined layer thickness; and d) repeating the steps a) through c) until completion of the component portion and/or of the component. Before, during and/or after process step b), at least one further portion of the component layer is formed by locally fusing and/or sintering the material by inductive heating at a temperature or in a temperature range above the solidus temperature of the metallic material used. A system for manufacturing at least a portion of a component is also provided.

Abstract: A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.

Abstract: The invention relates to a device and a method for the additive manufacture of components through the layered bonding of powder particles to one another and/or to a semi-finished product or substrate already produced, using selective interaction of the powder particles with a high-energy beam, wherein, during the bonding of the powder particles into a layer made of powder particles with the aid of the high-energy beam, a gas flow, which has a flow direction having a directional component directed at least partially parallel to the layer of powder particles, is provided across the layer of powder particles and/or the bonding region in the layer of powder particles, wherein the directional component of the gas flow directed at least partially parallel to the layer of powder particles during the bonding of the powder particles in a layer is generated in at least two directions, which have oppositely directed directional components.

Abstract: A layer-by-layer manufacturing method for the additive production of a region of a component, in particular of a turbomachine. The layer-by-layer manufacturing method includes: a) depositing a powder layer of a material onto a buildup and joining zone of a lowerable build platform; b) locally solidifying the material to form a component layer by selectively irradiating the material using an energy beam in accordance with a predetermined exposure strategy; c) lowering the build platform layer-by-layer by a specified layer thickness; and d) repeating the steps a) through c) until completion of the component region. Following at least one of the steps a) through c), a monitoring system ascertains and evaluates a result of the respective step; at least one intermediate correction step e) is executed for improving the ascertained result when the evaluation reveals an unacceptable deviation from a result specified for the respective step. Also, a corresponding layer-by-layer manufacturing apparatus.

Abstract: Equipment for the generative manufacture and/or repair of components, in particular of gas turbines, includes a solidifying means for the layer-by-layer, local, particularly optical, thermal, and/or chemical solidification of particularly powdered, granular, and/or fluid material, and an electrodeposition means for the electrostatic deposition of particles and/or gas from a region between a layer of material, which is to be solidified or is solidified, and the solidifying means, as well as a method for the generative manufacture and/or repair of components, in particular of gas turbines, by means of such equipment.

Abstract: A blade of a turbomachine is provided, including at least one cooling channel in the interior of the blade for cooling the blade with the aid of a fluid flowing through the cooling channel, the cooling channel having at least one inlet and at least one outlet, between which the cooling channel extends along its longitudinal axis, and the cooling channel being radially delimited by at least one wall, at least one displacement body being situated in the cooling channel, so that an annular or tubular gap between the displacement body and the wall of the cooling channel results in the area of the displacement body/bodies, which is available for the through-flow of the fluid, or at least two or multiple subchannels being formed in the area of the displacement body/bodies. The invention also relates to a method for manufacturing a corresponding blade.

Abstract: The present invention relates to sealing element for sealing a radial gap relative to a counter element of a turbomachine, wherein the sealing element has a number of adjacent cells in the peripheral direction and/or in the axial direction, which are joined to one another by common walls, wherein an extension of a least one, in particular front-side, cross section of at least one cell in a first axial section of the sealing element in the peripheral direction and/or in the axial direction for sealing against a radial flange of the counter element is smaller than that in a second axial section of the sealing element that adjoins the first axial section upstream and/or in a second axial section that adjoins the first axial section downstream.

Abstract: The invention relates to a device for the manufacture or repair of a three-dimensional object, comprising at least one construction chamber for a successive solidification of at least one solidifiable material layer by the layer in predefined regions for the layer-by-layer buildup of the three-dimensional object or for the layer-by-layer repair of individual regions of the three-dimensional object within the construction chamber, and at least one inlet nozzle and at least one suction nozzle for a process gas, wherein the inlet nozzle and the suction nozzle are arranged in such a way that a gas flow that passes at least partially over a construction platform formed in a construction chamber is created.

Abstract: A seal carrier (63) for a turbomachine (60) which is assembled from seal carrier segments, is provided. The seal carrier segments each have a seal structure (1a, b) on the radially inward side. These seal structures (1a, b) are either interleaved in the circumferential direction (4) such that a cross-sectional plane containing the longitudinal axis (2) of the turbomachine (60) intersects both the first seal structure (1a) and the second seal structure (1b), or the seal structures (1a, b) rest against each another.

Abstract: A method for the quality evaluation of a component produced by an additive manufacturing method and device includes at least the following steps: providing image data that characterizes at least one component site of a component produced by an additive manufacturing method; converting the image data into a binary image; eroding the binary image into a structure image; determining contour data of the structure image; determining at least one image section of the image data that is delimited by the contour data; inspecting the at least one image section for the presence of an image region corresponding to a quality defect; and classifying the component as being qualitatively OK if no quality defect is present, or classifying the component as being qualitatively not OK if a quality defect is present.

Abstract: The invention relates to a repair method for a component and includes the steps of removal of a damaged region of the component with the formation of at least one separating surface; arrangement of the component in a processing chamber of a device for the additive restoration of at least the region of the component that has been removed; determining first structural data of the component disposed in the processing chamber; providing second structural data of the component; determining third structural data based on the first and the second structural data; and additive restoration of the component region that has been removed on the at least one separating surface of the component. In addition, the invention relates to a device for the additive repair of a component.

Abstract: The invention relates to a method for the quality assessment of a component produced by means of an additive manufacturing method. In the course of the method, it is checked first of all whether the component violates predetermined absolute limits in order to rule out the existence of serious malfunctions in the additive manufacturing process. Subsequently, a component-dependent targeting process is determined. On the basis of this targeting process, the limits for deviations are established and deviating actual values of the component are isolated and assessed by means of various parameters.

Abstract: An apparatus and method for the generative production of a component includes a movably dispensing structure for the disposal of a starting material layer; a bonding device, such as a laser, for the local bonding of this starting material layer to a cross section of the component being produced; a platform for supporting the component being produced, which can be displaced counter to a direction of layer buildup in a motor-driven manner; a position sensing device for sensing a position or change in position, such as vibration, of the platform in the direction of layer buildup with the capability of sensing interference as to whether the movement of the dispensing structure is not free of interference on the basis of the sensed position or change in position.

Abstract: A method for additively manufacturing at least a portion of a component, in particular a component of a turbomachine. The method includes the following steps: a) depositing at least one powder layer of a component material in powder form layer by layer onto a component platform in the region of a buildup and joining zone; b) locally solidifying the powder layer by selectively irradiating the same using at least one high-energy beam in the region of the buildup and joining zone, forming a component layer; c) lowering the component platform by a predefined layer thickness; and d) repeating steps a) through c) until completion of the component portion or of the component.

Abstract: A method for manufacturing at least a metallic portion of a component: a) depositing metallic material layer by layer onto at least one building platform; b) locally fusing and/or sintering the material layer by layer by supplying energy by at least one high-energy beam in the region of a buildup and joining zone to form at least a portion of at least one component layer of the component portion and/or of the component; c) lowering the building platform layer by layer by a predefined layer thickness; and d) repeating the steps a) through c) until completion of the component portion and/or of the component. Before, during and/or after process step b), at least one further portion of the component layer is formed by locally fusing and/or sintering the material by inductive heating at a temperature or in a temperature range above the solidus temperature of the metallic material used. A system for manufacturing at least a portion of a component is also provided.

Abstract: The invention relates to a method for the additive manufacture of at least one region (16) of a component. Here, at least the following steps are carried out: a) layer-wise application of at least one powder-form component material onto a component platform in the region of a build-up and joining zone (14); b) layer-wise and local solidifying of the component material by selective exposure of the component material by at least one high-energy beam (12) in the region of the build-up and joining zone (14), with the formation of a component layer (15); c) layer-wise lowering of the component platform by a pre-defined layer thickness; and d) repeating steps a) to c) until the component region (16) or the component has been completely fabricated.

Abstract: A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.