Abstract: A probe for a capacitive sensor device, and a gap measuring system using the probe, is disclosed. The probe has a probe head including a measuring element with at least one measuring and front face, a first electrically non-conductive isolator element, and a first partial element of a first shield. The measuring and front face, the first isolator element, and the first partial element of the first shield are adhesively connected to one another and configured as a multilayer, where the first isolator element is disposed between the measuring element with its measuring and front face and the first partial element.

Abstract: A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter.

Abstract: A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.

Abstract: A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades (38, 40), whereby a narrow cross section and a degree of overlap between the blades of the upstream row of blades and the blades of the downstream row of blades vary starting at the center of the main flow path in the direction of at least one main flow limiter.

Abstract: A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.

Abstract: A linear guide, in particular for a device for electrochemical metal machining, that guides a linear movement of a quill that is moved periodically in a machine frame in order to periodically modify a working gap between a cathode situated on the quill and a workpiece in the direction of the longitudinal axis of the quill, the quill being connected to the machine frame by a plurality of connecting rods, the connecting rods being situated, in the no-load, non-deflected state, essentially parallel to the longitudinal axis of the quill, and the connecting rods having at the point of connection to the quill, as well as at the point of connection to the machine frame, a notch hinge in order to enable, via the hinge, the periodic linear movement of the quill, and the flexibilities of these notch hinges being based on elasticities in their structures formed by targeted thinning of the material.

Abstract: The invention concerns a method for the machining of a metallic structural component, particularly a structural component of a gas turbine, by means of finishing with a pulsed electrochemical ablation process, whereby the structural component features a pre-contour, to be finished, with different over-measures. The method is characterized by the following processing steps: a) determination of the different over-measures of the pre-contour, and b) bilateral and simultaneous finishing by means of a simultaneous feed of respectively at least one electrode disposed on different sides of the structural component, whereby the feed velocity of the electrode in the area of the largest over-measure of the pre-contour is higher than the feed velocity in the area of the smaller over-measure of the pre-contour.

Abstract: A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed.

Abstract: A device for surface peening, in particular for ultrasonic shot peening, of a component of a gas turbine, having at least one vibration device that includes a surface that impinges the blasting material, and having a holding device by which a surface area of the component can be positioned relative to the surface of the vibration device, the surface of the vibration device being subdivided into at least two adjacent partial surfaces, each including an overlapping part by which a part of the surface area of the component can be treated by blasting material impinged both by the one and by the other partial surface.

Abstract: A sealing device for a coolant supply on a rotating spindle includes a first brush seal and a second brush seal arranged one after another in series on the spindle. An annular leakage chamber is formed axially between the first and second brush seals, and radially between the spindle and a spindle housing.

Abstract: Disclosed is an electrode arrangement for the defined rounding or deburring of edges of electrically conductive components, in particular turbine components, by means of electrochemical machining with at least one working electrode (5), which has a tubular electrode carrier, through which an electrolyte inflow line (10) is provided, the electrode carrier having on the front end a closure (13, 18), which is arranged such that the electrolyte inflow line in the axial direction of the electrode carrier is closed, and at least one outlet opening (19) being arranged in the radial direction. Also disclosed is a self-centering electrode arrangement and an installation for the defined rounding or deburring of edges of electrically conductive components by means of electrochemical machining with at least one corresponding electrode arrangement and also a method using the electrode arrangements and the described installation.

Abstract: A method for producing a locally limited diffusion coat on a metallic component is disclosed. In an embodiment, the method includes arranging the component and at least one dispenser pack containing the material to be diffused, making available at least one protective gas stream, which flows around the at least one region of the component that is not to be provided with a diffusion coat, and heating the component and the dispenser pack to a temperature for carrying out the diffusion and maintaining the temperature for a specific time. A reactor for producing a locally limited diffusion coat on a metallic component is also disclosed.

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 0 visual evaluation of the fluorescent penetrant remaining in the recesses present in the workpiece surface.

Abstract: The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (1-3) connected to one another in the circumferential direction (U), wherein shells adjacent in the axial direction have cross sections opened counter to a throughflow direction (A) and/or a thread axis inclined counter to the throughflow direction.

Abstract: A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades (10a, 10b) having blade platforms (14a, 14b) engaged flush with one another, the blade ring including at least two groups of differently designed rotor blades (10a, 10b), each group of rotor blades (10a, 10b) being assigned blade platforms (14a, 14b), each of which is engageable flush with a matching blade platform (14a, 14b) of at least one other group of rotor blades (10a, 10b) and not with a blade platform (14a, 14b) of the same group of rotor blades (10a, 10b). A method for manufacturing a blade ring of a rotor for a turbomachine as well as a jet engine.

Abstract: A system for injecting a fluid into a wall boundary layer of a flow in a turbomachine is disclosed. The system has a plurality of nozzles which are disposed in a side wall limiting the flow and are oriented diagonally in the direction of flow. The nozzles each have a rectangular, flat nozzle cross-section. A compressor having such a system, as well as a turbomachine having such a compressor, are also disclosed.

Abstract: A machining or processing apparatus (14) for machining or processing a sealing element (16) located within a housing (12) of a gas turbine (10), the machining or processing apparatus (14), at least in the partially assembled state of the gas turbine (10), being at least partly introducible through a port (22) of the housing (12) into an interior space (24) of the gas turbine (10) and including a machining or processing device (15) which allows work to be performed on the sealing element (16) upon introduction of the machining or processing apparatus (14) under relative movement of the machining or processing device (15) and the sealing element (16). In addition, a method for machining or processing a sealing element (16) located within a housing (12) of a gas turbine (10).

Abstract: A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour.

Abstract: A mounting device and method for mounting a component is disclosed. The mounting device includes a component carrier and an adapter. The adapter is insertable into a guide of the component carrier. The method uses the mounting device to mount a component on the mounting device.

Abstract: A turbomachine stage including guide vanes, radially inner and/or radially outer airfoil platforms, which together form a guide vane cascade, and further including rotor blades, radially inner and/or radially outer airfoil platforms, which together form a rotor blade cascade adjacent to the guide vane cascade. Radially outer airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies, in particular periodically, in the radial and/or axial direction around the circumference.