Abstract: A device (20) for inductively heating at least one region (12, 14) of a component (10) includes a coil device (30) for generating a magnetic field in at least the region (12, 14) of the component (10) and includes an auxiliary member (40) to be configured adjacently to the component (10) in the magnetic field of the coil device (30) in such a way that the auxiliary member (40) faces the component (10) in a direction that is orthogonal or substantially orthogonal to the direction of a magnetic field that the coil device (30) can generate in the region between the component (10) and the auxiliary member (40).

Abstract: A method for mounting an integral inner ring (10) of a turbocompressor stator to a guide vane ring (12) comprises the following steps: Providing the guide vane ring (12) with an inner radius S; Providing inner ring (10) with an outer radius R, which corresponds to the inner radius S; Pre-tensioning inner ring (10) to an outer radius r that is smaller than the outer radius R of the untensioned inner ring (10); and Relaxing inner ring (10) to the outer radius R.

Abstract: A probe for a magnetic remanence measurement method, in particular for detecting foreign material deposits and inclusions in hollow spaces, the hollow spaces being formed in a non-ferromagnetic material and the foreign material deposits and inclusions being made of a ferromagnetic material, wherein the probe includes at least one magnetic field sensor, at least one first and one second magnet, the magnets being configured before the at least one magnetic field sensor in a direction of introduction into the hollow space, and being situated relative to one another in such a way that their pole axes run non-parallel to one another.

Abstract: A method for repairing a rotor system (2) of a turbomachine, having a rotor (4) which has a groove (26) extending in the circumferential direction (58) of the rotor for accommodating an annular section (18; 28). The method has the following steps: chamfering a notch (40) in the groove (26); introducing a recess (44) into the groove (26); and inserting the annular section (18; 28) into the groove (26). At least one engagement element (48; 49) formed on the annular section (18; 28) engages in the recess (44) in order to form a lock against rotation in the circumferential direction (58).

Abstract: A method for manufacturing an integrally bladed rotor (10), in particular for a gas turbine, including the following method steps: preparing a rotor base member (12) having at least one first weld surface (16) and one blade (14) having a second weld surface (18); positioning the rotor base member (12) and the blade (14) in such a way that a join zone (20) is formed between the first and second weld surface (16, 18); and filling the join zone (20) with metal powder (24) and the laser welding or electron beam welding of the metal powder (24). An integrally bladed rotor (10) has a join zone (20) between the rotor base member (12) and blades (14), the join zone (20) being filled with welded metal powder (24).

Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).

Abstract: A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element.

Abstract: A replacement part for a gas turbine blade is disclosed. The replacement part is designed to replace a removed portion of the blade, the portion including a section of the blade tip and a section of the leading edge and/or the trailing edge, and the replacement part having at least one joining side with which it can be brought to contact with the blade that is reduced by the removed portion and joined therewith. The joining side has at least one section, the cross-section of which is U-shaped.

Abstract: A method and device for the production of components having a three-dimensionally formed surface by a lowering operation with an electrochemical ablation process, namely a Precise Electro Chemical Machining (PECM) process, is disclosed. The method includes the steps of: a) providing a specially pre-formed workpiece featuring a specific dimensional allowance; b) providing at least one working electrode, in which case the contour of the working electrode, or of each working electrode, is adapted to the contour of the three-dimensionally formed surface to be produced; and c) lowering the three-dimensionally formed surface by placing the pre-formed workpiece and the working electrode, or each working electrode, in an electrolyte and by applying an electrical voltage or an electrical current, in which case the working electrode, or each working electrode, is moved in the sense of a circular advance motion in the direction toward the workpiece.

Abstract: The invention relates to a method for repairing components that consist of a superalloy. The method comprises the following steps: a solder material is applied to the repair site; the repair site with the applied solder material is heated until the latter melts; and the melted solder material is left to solidify. A powder blend, whose average composition corresponds to the component alloy constitutes the solder material, the blend comprising at least one elementary powder of the component alloy as one powder type and/or a pre-alloy of the component alloy.

Abstract: A method for compensating positional and/or shape deviations in NC-controlled cutting production machines. The method including the steps of securing a new workpiece, processing the workpiece using nominal data of the NC program, acquiring set deviation, optimizing the NC program using the acquired data and repeating the above steps until at least one of required positional and shape tolerances are achieved.

Abstract: The present invention relates to a capacitor arrangement having a capacitor and a first terminal plate and a second terminal plate. The capacitor has a first contact face and a second contact face arranged opposite one another. The terminal plates are each connected to one of the contact faces and have protrusions on one end suitable for engaging in recesses in a power rail.

Abstract: The present invention relates to a method for determining a selected machining quality of components in a manufacturing process, particularly during metal cutting, having at least the following method steps: determining process-relevant variables by sensors and/or from the data stream in the machine controller, extracting variable curves characteristic for the respective machining process, selecting a number of different characteristics of the extracted variable curves, the linking of which enables a clear assignment to the selected machining quality, and multivariate linking of the selected characteristics to a characteristic pattern correlating with the selected machining quality.

Abstract: The invention relates to a device (1) and to a method associated with an assembly mechanism for a rotor system of an axial turbo engine having a central tension anchor, as is particularly known from engine technology. To this end, the invention provides a tensioning tool that pre-tensions or biases the tension anchor prior to and during the insertion of the anchor into the compound rotor assembly. After inserting the biased tension anchor in the compound rotor assembly, the tension anchor is relaxed, whereby the anchor exercises a compressive force on the compound rotor assembly. According to a preferred embodiment, the compound rotor assembly is also biased (compressed) and relaxed after assembling the tension anchor, so that a desired nominal bias Sigmanominal can be particularly easily achieved. The use of a shaft locking nut is no longer necessary in the device according to the invention, thus avoiding the difficulties that are associated with the use of this nut, such as complexity and safety problems.

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: The invention relates to a brush seal to seal a gap between two structural components, in particular between a rotor and a stator, having a bristle packet comprising bristles, with the bristles of the bristle packet being firmly attached to a bristle carrier via a fixation element. According to the invention, the bristle packet comprises several layers of bristles that are made of different materials.

Abstract: The invention relates to a turbo engine, in particular a gas turbine aircraft engine, having a plurality of compressor components, at least one combustion chamber and a plurality of turbine components, wherein at least one support rib (36) is positioned in a flow channel (35) between two turbine components (32, 34) connected one behind the other, wherein the support rib (36) or each support rib (36) has a suction side, a pressure side, a front edge (37) and a rear edge (38), wherein the support rib or each support rib diverts a flow that flows through flow channel (35), and wherein a preferably cylindrical guide element runs in an inside space of the support rib or of each support rib.

Abstract: A method and device are provided for welding structural parts, preferably of a gas turbine, especially of an aircraft engine. A structural component is laser-welded by means of at least one laser source, the one or more laser sources being operated in a pulsed mode. Pulse duration and/or pulse shape and/or output of the one or more laser sources are adjusted in a variable manner. The wire advance of the welding wire is controlled subject to the pulses of the one or more laser sources.

Abstract: A mask and method for kinetic cold gas compacting is disclosed. The mask includes a body for covering a not-to-be-coated region of a substrate to be coated having a work side exposed to a coating substance. The work side has a hardness such that the work side is not plastic deformable by a striking coating particle.

Abstract: The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored.