Abstract: A method for checking at least one subregion of a component, in particular a component of a turbomachine, including at least the steps of a) providing a blank; b) producing at least the subregion from the blank by machining the blank using at least one tool and using at least one force sensor-to record at least one force curve of at least one force acting during machining on the at least one tool; c) checking whether there is at least one deviation-of the at least one force curve from at least one predetermined target curve-of the at least one force curve, the at least one deviation-characterizing at least one material defect-contained in an unmachined segment of the subregion. A checking device for checking at least a subregion of a component is also provided.

Abstract: The invention relates to a method for nondestructively acoustically examining at least one region of a component of a turbomachine, wherein at least the following steps are performed: a) arranging a transmitter comprising a plurality of individual oscillators on the region of the component to be examined, b) introducing at least one ultrasound beam into the component by means of the transmitter, c) receiving at least one ultrasound beam reflected by the component by means of a receiver comprising a plurality of individual receivers and d) checking, on the basis of the received ultrasound beam, whether there is a deviation in the region of the component which characterizes a segregation. The invention further relates to a device for carrying out a method of this type.

Abstract: The invention relates to a method and device for generatively producing components, said device comprising a radiation device for selectively radiating a powder bed, and an induction device for inductively heating the component produced by radiating the powder bed, Said induction device comprising at least one voltage source which can simultaneously produce alternating voltages with at least two different frequencies.

Abstract: The invention relates to a method for manufacturing a brush seal with inclined bristles. In order to be able to manufacture these brush seals in an especially cost-effective manner, at least the following steps are provided: provision of a brush blank with at least one metal thread or wire packing fastened at or in at least one wire core; local, at least partial heating of at least the wire core and/or a subregion of the thread or wire packing adjacent to the wire core, by a current flow through the wire core; bending of the thread or wire packing relative to the wire core for producing of the inclined position of the bristles of the brush seal. The invention further relates to an apparatus for manufacturing brush seals and a brush seal for a turbomachine, in particular for an aircraft engine.

Abstract: A seal carrier for a turbomachine for sealing a gap between a stator section and a rotor section, having a base body, which is provided on one side with a run-in coating; the base body at least having one hollow space, which is open via at least one opening to the run-in coating, creating a Helmholtz resonator; the area of the run-in coating, which is provided with the at least one opening, providing the oscillating mass of the Helmholtz resonator, and the at least one hollow space, the spring volume thereof.

Abstract: The present invention relates to a device as well as a method for the additive manufacture of components by deposition of material layers by layer-by-layer joining of powder particles to one another and/or to an already produced pre-product or substrate, via selective interaction of the powder particles with a high-energy beam, wherein, for smoothing a surface of the component being produced running crosswise to the deposited material layers in between the deposition of two layers of the component, the complete edge region of the last layer that is applied and that runs along a surface of the component being produced is compacted in a direction of action that has a directional component parallel to the build-up direction of the layers, and/or at least one edge region of a surface of the component is also compacted.

Abstract: Disclosed is a method for generatively producing components by layer-by-layer building from a powder material by selective material bonding of powder particles by a high-energy beam. An eddy current testing is carried out concurrently with the material bonding. Also disclosed is an apparatus which is suitable for carrying out the method.

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: Disclosed are a method for forming a thermal barrier layer for a metallic component, which method involves forming a ceramic coat in which at least in part aluminum oxide and titanium oxide are disposed, the aluminum oxide and the titanium oxide being introduced by infiltration of aluminum-containing and titanium-containing particles or substances or by physical vapor deposition.

Abstract: The invention relates to a layer-by-layer construction method for the additive manufacture of at least one region of a component. The layer-by-layer construction method comprises at least the following steps: a) application of at least one powder layer of a metallic and/or intermetallic material onto at least one buildup and joining zone of at least one lowerable building platform; b) layer-by-layer and local melting and/or sintering of the material for the formation of a component layer by selective exposure of the material with at least one high-energy beam in accordance with a predetermined exposure strategy; c) layer-by-layer lowering of the building platform by a predefined layer thickness; and d) repetition of steps a) to d) until the component region has been finished. The invention further relates to a layer-by-layer construction apparatus for the additive manufacture of at least one region of a component by an additive layer-by-layer construction method.

Abstract: A method for the generative production of a component and a device for carrying out such a method, includes the following steps: applying a material layer with a constant layer thickness; solidifying a region of the material layer according to a component cross section; generating an eddy-current scan of the solidified region, a scan depth corresponding to a multiple of the layer thickness; determining a material characterization of the solidified region taking into consideration a previous eddy-current scan of solidified regions of lower-lying material layers; and repeating the steps until the component is assembled. An electric material characterization of each individual layer is determined using a recursive algorithm of individual measurements (monolayer by monolayer), and thus the entire component is tested step by step completely in a highly resolved manner.

Abstract: The invention relates to a method for the determination, at least in regions, of a contour of at least one additively manufactured component layer, in which a contour line of the component layer is traveled over, at least in regions, by a laser beam, and a time exposure of the traveled contour line is produced by a camera system. The invention further relates to a device for the determination, at least in regions, of a contour of at least one additively manufactured component layer. For this purpose, the device comprises at least one laser system, by which a contour line of the component layer can be traveled over, at least in regions, by a laser beam, and a camera system, which is designed to produce a time exposure of the contour line traveled over by the laser beam.

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: The present invention relates to a device as well as a method for the additive manufacture of components by deposition of material layers by layer-by-layer joining of powder particles to one another and/or to an already produced pre-product or substrate, via selective interaction of the powder particles with a high-energy beam, wherein, for smoothing a surface of the component being produced running crosswise to the deposited material layers in between the deposition of two layers of the component, the complete edge region of the last layer that is applied and that runs along a surface of the component being produced is compacted in a direction of action that has a directional component parallel to the build-up direction of the layers, and/or at least one edge region (19) of a surface of the component (3?) is also compacted.

Abstract: The invention relates to a method for manufacturing a brush seal with inclined bristles. In order to be able to manufacture these brush seals in an especially cost-effective manner, at least the following steps are provided: provision of a brush blank with at least one metal thread or wire packing fastened at or in at least one wire core; local, at least partial heating of at least the wire core and/or a subregion of the thread or wire packing adjacent to the wire core, by a current flow through the wire core; bending of the thread or wire packing relative to the wire core for producing of the inclined position of the bristles of the brush seal. The invention further relates to an apparatus for manufacturing brush seals and a brush seal for a turbomachine, in particular for an aircraft engine.

Abstract: A method for determining residual stresses of a component (14), in particular a component of an aircraft engine, while it is being manufactured by an additive manufacturing process. The method includes the following steps: creating at least one local melt pool (26) in a surface (24) of the component (14) to be manufactured after a predetermined portion of the component is completed; optically detecting surface distortions and/or elongations occurring at least in a region around the created melt pool (26); and determining the residual stresses of the component (14) which are present at least in the region around the created melt pool (26) based on the optically detected surface distortions and/or elongations. Further an apparatus for determining residual stresses of a component (14) while it is being manufactured by an additive manufacturing process is provided.

Abstract: The invention relates to a method and device for ascertaining an edge layer characteristic of a component (12), in particular a component (12) for an aircraft engine. In the method, a reference body (22) with a known edge layer characteristic is arranged on the surface of the component (12). An ultrasonic wave (18) is introduced into the surfaces of the component (12) and the reference object (22) by an ultrasonic transmitter (16). An ultrasonic wave (18) resulting from the exchange between the component (12) and the reference body (22) is detected by an ultrasonic detector (20), and an edge layer characteristic of the component (12) is ascertained by an ascertaining device (28) using a difference between the generated ultrasonic wave (18) and the resulting ultrasonic wave (18).

Abstract: The invention relates to a method for the quality assurance of at least one component (14) during the production thereof, wherein the production takes place by means of at least one additive manufacturing process, which comprises the following steps: building up the component (14) layer by layer, and themographically recording at least one image of each individual layer applied. In order to facilitate nondestructive crack detection in a metal component (14) during the production process (inspection by means of an online process), at least some of the layers applied are subjected to a controlled heat treatment below the melting point of the material of the component before the thermographic recording of the associated image, wherein the heat treatment causes the last layer applied to radiate heat which, if at least one crack develops in the layer, exhibits a characteristic heat profile at the crack.

Abstract: The invention relates to a method and a device for the quality assurance of at least one component (14) during its production, wherein production is achieved by means of an additive manufacturing method with at least one processing laser (22), said method comprising the following steps: —layered assembly of the component (14), —thermographic recording of a plurality of images, over a defined period, of at least one component region (17) in the laser beam by means of at least one recording sensor (18), —detecting a temporal change in the heat distribution in a molten-pool-free component region, wherein the occurrence of a defect, (e.g. a crack, foreign material, a pore, a bonding fault or similar) in the uppermost component layer or beneath same is detected on the basis of a characteristic temporal change in the heat distribution at the defect (30).

Abstract: Disclosed is a method for the non-destructive testing of workpiece surfaces of a workpiece by means of fluorescent penetrant testing or dye penetrant testing. The method comprises applying a penetrant to the region of the workpiece surface to be examined, thereby allowing the penetrant to penetrate into possible recesses in the workpiece surface, applying a developer to the region of the workpiece surface to be tested; bleaching the penetrant by a gaseous or liquid oxidant; and visually assessing the penetrant that has remained in the recesses present in the workpiece surface.