Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

Abstract: The invention relates to a turbomachine including: a guide baffle, whose sv guide blades are situated on c guide blade carriers; and an adjacent moving baffle including sb moving blades; the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ? i = 1 n v ? ? m i s v - c of sum ? i = 1 n v ? ? m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv?c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.

Abstract: A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.

Abstract: A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of: preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; the additive including a titanium aluminide.

Abstract: The invention relates to a device (10) for generative production of at least one component area of a component (12), in particular of a component (12) of a flow machine, wherein the device (10) includes at least one coater (14) for applying at least one powder layer of a component material to at least one construction and joining zone (20) of at least one lowerable component platform (16), wherein the coater (14) is movable relative to the component platform (16); and at least one radiation source for generating at least one high-energy beam (22), by means of which the powder layer can be locally melted and/or sintered to a component layer in the area of the construction and joining zone (20). In addition, at least one heating device (24, 28) is disposed on the coater (14).

Abstract: The invention relates to a device (10) for generative production of at least one component area of a component (12), in particular of a component (12) of a flow machine. Therein, the device (10) can include at least one lowerable component platform (16) with at least one construction and joining zone (20) for receiving at least one powder layer of a component material, at least one heating device (24, 28) movable relative to the component platform (16) and at least one radiation source for generating at least one high-energy beam (22), by means of which the powder layer can be locally melted and/or sintered to a component layer in the area of the construction and joining zone (20), as well as at least one suction and/or gas supply device (36) disposed on the heating device (24, 28). However, the device (10) can also include at least one coater (14).

Abstract: The invention relates to a method for additively manufacturing at least one component region of a component, in particular of a turbine or compressor component, said method comprising at least the following steps: applying a layer of powder (10a-c) to a component platform in the region of a building and joining area; locally melting and/or sintering the powder layer (10a-c), wherein, in the region of the building and joining area, at least one high-energy beam is moved in relation to the component platform, selectively impinging the powder layer (10a-c), at least part of which at least one high-energy beam and the component platform are moved in relation to one another, in the form of a parallel arrangement (16) arranged along a linear feed direction (12); lowering the component platform by a predetermined layer thickness in a lowering direction; and repeating the above-mentioned steps unfil the component region is completed.

Abstract: The present invention relates to a method for arranging a reinforcement (8, 9) on a TiAl component (1) of a turbomachine, the reinforcement being formed by a reinforcing molding, which is applied to the TiAl component (1) by means of brazing, a nickel-base alloy with the chemical composition 7.5% to 22.5% by weight Cr, 0.5% to 7% by weight B, remainder Ni, being used as the brazing filler metal.

Abstract: A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.

Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.

Abstract: The present invention relates to a device for the additive manufacturing of components (4) by selectively irradiating a powder bed (6), the device having a working chamber (1) in which at least one powder bed chamber (2) and at least one radiation source are arranged such that the radiation source can irradiate a powder in the powder bed chamber (2), and wherein the device comprises at least one induction coil (3, 13) such that the powder bed and/or a component, which is generated by irradiating (7) the powder bed, can be at least partially inductively heated.

Abstract: The present invention relates to a device for the generative production of a component (7A, 7B), particularly a component of a gas turbine engine, having a working chamber, a hardening means, in particular a laser (6), for the layerwise local hardening of an initial material (4) disposed in the working chamber, in order to produce the component layerwise in a direction of layer construction; and a movable induction heating arrangement with a first inductor (10) and a second inductor (20) for induction tempering in pre-determinable regions of the working chamber, wherein the first inductor engages in the second inductor at least in one operating position and/or the first and/or second inductor is disposed on a distribution means, in particular a slider (1), for the layerwise disposal of initial material (4) in the working chamber.

Abstract: An apparatus and method for additive manufacturing of components, in particular for manufacturing components for turbomachines, where the component is at least partially built up layer by layer on a substrate or a previously produced part of the component, and where layer-by-layer build-up is performed by layerwise melting of powder material using a high-energy beam and solidification of the molten powder is provided. The high-energy beam moves along a path across the powder material and produces a melting region at the front of the path. A solidification region forms subsequently in the path. In the solidification region, the temperature distribution is temporally and/or locally selected in such a way that residual compressive stresses are produced in the solidified or solidifying powder material.

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 method for producing a low-pressure turbine blade from a TiAl material by means of a selective laser melting process, wherein during production in the selective laser melting process the already partially manufactured low-pressure turbine blade is preheated by inductive heating, and wherein the selective laser melting process is carried out under protective gas, the protective gas atmosphere containing contaminants of oxygen, nitrogen, and water vapor in each case of less than or equal to 10 ppm.

Abstract: A device for additive manufacturing of components by selective irradiation of a powder bed, having a processing chamber -in which at least one powder bed chamber and at least one radiation source are arranged such that the radiation source can irradiate a powder in the powder bed chamber, and wherein the device includes at least one induction coil, so that a component which is produced by irradiation of the powder bed can be at least partially inductively heated, and wherein the induction coil is movable relative to one or more powder bed chambers. A method for additive manufacturing of components by selective irradiation of a powder bed, in which method the component being manufactured is inductively heated at the same time, wherein the position of one or more induction coils for inductive heating is determined and adjusted based on the geometry of the component to be produced.

Abstract: A method for connecting metallic components, in particular components of a gas turbine, including: corresponding connecting surfaces of the components being connected by means of inductive HF pressure welding, and that during or after a sufficiently great heating of the connecting surfaces, the first component is moved by a definite path toward the second component, and is pressed against it and held there.

Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.

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 device for the production or repair of a blade for a gas turbine, said device comprising: a holding device for holding a blade or an aerofoil of a blade; a lowering mechanism for lowering the blade or the aerofoil; a container for receiving power and/or for receiving the blade or the aerofoil; a heating device; and a radiation source, wherein the heating device is formed as an induction coil.