Abstract: The present invention relates to equipment for the generative manufacture and/or repair of components, in particular of gas turbines, having a solidifying means (3) 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 (1.1, 7-10) for the electrostatic deposition of particles (6) and/or gas from a region between a layer (2.1) of material, which is to be solidified or is solidified, and the solidifying means (3), 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: Selective laser solidification apparatus is described that includes a powder bed onto which a powder layer can be deposited and a gas flow unit for passing a flow of gas over the powder bed along a predefined gas flow direction. A laser scanning unit is provided for scanning a laser beam over the powder layer to selectively solidify at least part of the powder layer to form a required pattern. The required pattern is formed from a plurality of stripes or stripe segments that are formed by advancing the laser beam along the stripe or stripe segment in a stripe formation direction. The stripe formation direction is arranged so that it always at least partially opposes the predefined gas flow direction. A corresponding method is also described.

Abstract: A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

Abstract: A beacon device is provided in proximity to a computing system within a computing center. A request to locate the computing system in the computing center is triggered on a central control unit. In response to the request to locate the computing system, the control unit generates specification data for a unique radio signal identifier, sends an activation request and the specification data to the beacon device, and provides the specification data to a portable device and stores the specification data on the portable device. In response to receiving the activation request, the beacon device sends a radio signal identifier generated from the specification data.

Abstract: A device for generative production of at least one component area of a component, in particular a component of a turbine or a compressor, is disclosed. The device includes at least one powder feed for application of at least one powder layer to a build-up and joining zone of a component platform that can be lowered and at least one radiation source for generating at least one high-energy beam by which the powder layer can be fused and/or sintered locally in the area of the build-up and joining zone to form a component layer. The device further includes a camera system which can produce at least one stereoscopic image for three-dimensional detection of at least one area of the component layer. A method for producing at least one component region of a component, in particular a component of a turbine or a compressor, is also disclosed.

Abstract: The invention relates to a bearing cage of a bearing means, in particular a ball or roller bearing, which is produced by means of a generative manufacturing method and has an outer flange and a bearing seat, which are joined together via a plurality of spring beams.

Abstract: The present invention relates to an apparatus and method for the generative production of a component (4A, 4B, . . . ) with a movably dispensing structure (1) for the disposal of a starting material layer (2); a bonding device, such as a laser (3), for the local bonding of this starting material layer to a cross section (4A, 4B, . . . ) of the component being produced; a platform (5) 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 (6) for sensing a position or change in position, such as vibration (z(t)), of the platform in the direction of layer buildup with the capability of sensing interference (7) as to whether the movement of the dispensing structure is or is not free of interference on the basis of the sensed position or change in position.

Abstract: The presently disclosed subject matter relates to a dispersible, nonwoven multistrata wipe material that is stable in a wetting liquid and flushable in use. More particularly, the presently disclosed subject matter relates to multilayered structures including, but not limited to, two, three, or four layers to form the dispersible nonwoven wipe material. The layers contain combinations of cellulosic and noncellulosic fibers, and optionally a binder or additive.

Abstract: A manipulation device for manipulating and/or processing a workpiece includes a first motion unit for generating a linear motion of a first component and a second motion unit for generating a linear motion of a second component. The motion units are arranged relative to each other such that the motions that can be generated by the motion units are aligned parallel to each other. The first and second components are connected via first and second hinge joints, respectively, to a fastening element that is suitable for receiving a workpiece and/or a tool. The first and second hinge joints comprise first and second guide arms, respectively, which are coupled to the first and second components, respectively, via revolute joints. The first and second guide arms are coupled directly or indirectly to each other by at least one revolute joint so as to be pivotable relative to each other.

Abstract: A beacon device is provided in proximity to a computing system within a computing center. A request to locate the computing system in the computing center is triggered on a central control unit. In response to the request to locate the computing system, the control unit generates specification data for a unique radio signal identifier, sends an activation request and the specification data to the beacon device, and provides the specification data to a portable device and stores the specification data on the portable device. In response to receiving the activation request, the beacon device sends a radio signal identifier generated from the specification data.

Abstract: The present invention relates to a method for the generative production of components, particularly of single-crystalline or directionally-solidified components, particularly for the production of components for turbomachines, in which the component is constructed in layers on a substrate or a previously produced part of the component (3), wherein a construction in layers takes place by melting of powder material in layers with a high-energy beam (14) and solidification of the powder melt (16) takes place, wherein the high-energy beam has a beam cross section (19) in the area of its impingement on the powder material that is altered in comparison to a circular or other symmetrical cross section and/or the beam energy is distributed non-uniformly, in particular asymmetrically or eccentrically, over the beam section.

Abstract: A rotor (10) has a basic rotor body (12) and a plurality of rotating blades (14) mounted on the basic rotor body (12). The rotating blades (14) in this case are mounted rigidly or non-detachably, in particular, cohesively, on the basic rotor body (12). Thus, at least one rotating blade (14) has at least one integral sealing element (24), by means of which a root intermediate space (22) is sealed in the region of a blade root (20) radially underneath a blade platform (18) of the rotating blade (14). In addition, the invention relates to a method for producing a rotor (10), in particular, for an aircraft engine, in which a plurality of rotating blades (14) is mounted on a basic rotor body (12), wherein at least one rotating blade (14) having at least one integral sealing element (24) is mounted on the basic rotor body (12).

Abstract: A beacon device is provided in proximity to said entity. A request to locate said entity is triggered on a central control unit. In response to the request to locate said entity, said control unit generates specification data for a unique radio signal identifier, sends an activation request and said specification data to said beacon device, and provides said specification data to a portable device and storing said specification data on the portable device. In response to receiving said activation request, said beacon device sends a radio signal identifier generated from said specification data. Signals are received on said portable device and compared with the specification data stored on the portable device. Based on the results of the comparison by said portable device, information is provided about at least one of a direction and distance to said entity. The location of said entity is detected using said direction information.

Abstract: A component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment.

Abstract: A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

Abstract: The invention relates to a process for producing an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine. The insulation element (12) is produced from a solid body (24) provided with a metallic shell (26), the solid body (24) consisting at least partially of a ceramic material. The invention also relates to an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine, and to an aero engine having a housing (10), in which at least one insulation element (12) is arranged radially above at least one guide vane (14).

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 sealing device (1) is disclosed for sealing a radially inner gas channel (2) between a guide vane ring (4) and a rotor (6) of a turbomachine, wherein the sealing device (1) has a sealing ring (8) for forming a sealed space (10) with a rear segment, with an inner wall structure (30) oriented in the opposite direction, which are joined to each other via an annular arch (32), wherein the radial flange (18) transitions into the outer wall structure (28) and the cylinder (26) forms the sealing ring (8), wherein the inner wall structure (30) transitions, via an annular web (36), into at least one inner body segment (38, 50), wherein the sealing device (1) has a uniform, preferably relatively reduced wall thickness over its individual segments integrally formed with one another, so that the sealing device (1) is resilient within certain limits.

Abstract: In a method for the generative production of a component (3), in particular of a turbo-engine component, wherein material (4) is bonded layer-by-layer selectively to a layer disposed therebeneath or to a substrate (6), according to the invention a laser (1A; 1B; 2) additionally acts on the material (4) before, during and/or after the bonding.