Abstract: A method for coating a component, in particular a component of a gas turbine or of an aircraft engine, is disclosed. The coating is applied to the component by kinetic cold gas spraying, where prior to the deposition of the coating, the surface of the component to be coated is cleaned and compacted by shot peening with a blasting media. A component produced in this manner is also disclosed.

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: The invention relates to a method of nondestructive and contactless testing of components (3), wherein ultrasonic waves (6) are irradiated onto the surface of the component (3) at a predefinable, non-perpendicular angle of incidence (9) using an ultrasonic transmission sound transducer (1) arranged spaced apart from the surface of the component (3) and the intensity of the ultrasonic waves (7) reflected from the surface of the component (3) is detected with time resolution and/or frequency resolution by the antenna array elements (2n) of an ultrasonic antenna array (2) configured for detecting ultrasonic waves (7) and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves (7) directly reflected at the surface of the component (3).

Abstract: The invention relates to a method for joining two components (10, 12) made of a metal material, which are connected on two mutually associated joining surfaces (14, 16) by means of a joined connection, wherein at least one of the components (10) is strengthened in at least a partial region of the joining surface (14) thereof prior to joining. The invention further relates to a joined connection of two components (10, 12) made of a metal material.

Abstract: The invention relates to a method of nondestructive and contactless testing of components (3), wherein ultrasonic waves (6) are irradiated onto the surface of the component (3) at a predefinable, non-perpendicular angle of incidence (9) using an ultrasonic transmission sound transducer (1) arranged spaced apart from the surface of the component (3) and the intensity of the ultrasonic waves (7) reflected from the surface of the component (3) is detected with time resolution and/or frequency resolution by the antenna array elements (2n) of an ultrasonic antenna array (2) configured for detecting ultrasonic waves (7) and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves (7) directly reflected at the surface of the component (3).

Abstract: The present invention relates to a method and a device for material processing with a high-energy beam (7), with a beam-generating device (4) for generating a high-energy beam and with a component holder (2), in which is disposed the material that is to be processed with the high-energy beam, wherein the beam-generating device and the component holder are disposed or can be disposed relative to one another so that the high-energy beam impinges on the material surface (12) of the material to be processed at an angle not equal to 0° or 180° or a whole-number multiple thereof, and wherein the beam-generating device or at least parts thereof and/or another beam-generating device can be disposed, and/or that the beam-generating device comprises a deflection means (5, 6), so that a high-energy beam (7a) can be aligned parallel to and at a distance from the material surface (12) to be processed.

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 according to the invention, a reference body (22) with a known edge layer characteristic is arranged on the surface of the component (12). At least one ultrasonic wave (18) is introduced into the surfaces of the component (12) and the reference object (22) by means of an ultrasonic transmitter (16). At least one ultrasonic wave (18) resulting from the exchange between the component (12) and the reference body (22) is detected by means of an ultrasonic detector (20), and an edge layer characteristic of the component (12) is ascertained by means of an ascertaining device (28) using a difference between the at least one generated ultrasonic wave (18) and the at least one resulting ultrasonic wave (18).

Abstract: A method for joining at least two components by inductive high-frequency pressure welding is disclosed. The first component has a first material structure with a first hardness and the second component has a second material structure with a second hardness which is smaller than the first hardness. Both components are inductively heated in the region of the joining surfaces and are subsequently pressed together by a compressive force. The joining surface of the first component with the first hardness, which is greater than the second hardness of the second component, is pre-contoured in a spherical, conical or convex manner prior to joining the two components.

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: 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: 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.

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 method for nondestructive testing of workpiece surfaces by a fluorescent penetration test is disclosed. An embodiment of the method includes a) cleaning the area of the workpiece surface that is to be inspected; b) applying a fluorescent liquid penetrant to the area of the workpiece surface that is to be inspected, where the penetrant penetrates into possible recesses in the workpiece surface; c) removing the excess penetrant from the workpiece surface; d) applying a developer to the area of the workpiece surface that is to be inspected; e) bleaching the fluorescent penetrant by a beam of light in the layer formed by applying the developer to the workpiece surface; and f) visual evaluation of the fluorescent penetrant remaining in the recesses present in the workpiece surface.

Abstract: A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base (12) made of a high temperature-resistant nickel alloy and a plurality of turbine blades (14) joined to the rotor base, whereby each turbine blade includes a rotor blade (16) made of a titanium alloy and a blade root. The blade root is configured as an adapter element (18) that is made of a material that can be welded to the titanium alloy as well as to the high temperature-resistant nickel alloy and that is integrally joined to the rotor base (12) and to the rotor blade (16) fusion. A method for the production of the component is also described.

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: A component, in particular an engine component, which has at least one mark with a predetermined three-dimensional shape for determining a stress in the component and where the component is constructed by a generative manufacturing method, is disclosed.

Abstract: The invention relates to a method for the generative production of a component (2) and to a device for carrying out such a method, having 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 (2) 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: A method for imaging at least one three-dimensional component, which is produced by a generative manufacturing method, is disclosed. The method, in an embodiment, includes determining at least two layer images of the component during production thereof by a detection device, which is designed to detect with spatial resolution a measured quantity characterizing the energy input in the component. The method further includes generating a three-dimensional image of the component based on the determined layer images by a computing device and displaying the image by a display device. A device for carrying out the method is also disclosed.

Abstract: A method for coating a component, in particular a component of a gas turbine or of an aircraft engine, is disclosed. The coating is applied to the component by kinetic cold gas spraying, where prior to the deposition of the coating, the surface of the component to be coated is cleaned and compacted by shot peening with a blasting media. A component produced in this manner is also disclosed.

Abstract: A component, in particular an engine component, which has at least one mark with a predetermined three-dimensional shape for determining a stress in the component and where the component is constructed by a generative manufacturing method, is disclosed.