Abstract: The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.

Abstract: The present invention relates to a rotor blade shroud for a turbomachine, comprising a sealing tip and a support structure that abuts the sealing tip. The support structure has at least one intermediate region in which a structural segment is arranged, wherein the radially outwardly arranged surface of the support structure and of the structural segment forms an essentially planar surface. The present invention further relates to a rotor blade for a turbomachine, comprising a rotor blade shroud as well as two methods of manufacturing a rotor blade shroud and a method of manufacturing a rotor blade.

Abstract: A rotor blade for disposition in a hot gas duct of a turbomachine, the rotor blade having an airfoil and an inner platform radially inwardly thereof, the inner platform having a chamber formed therein which is radially outwardly bounded by an inner shroud of the inner platform and is axially bounded between a forward chamber wall and a rearward chamber wall of the inner platform. A forward sealing plate is disposed at the forward chamber wall and extends axially forwardly away from the chamber, and a rearward sealing plate is disposed at the rearward chamber wall and extends axially rearwardly away from the chamber. Furthermore, an axial partition is disposed in the chamber, which axial partition divides the chamber into a radially inner chamber wall region and a radially outer chamber wall region and which, when viewed in an axial cross section, extends into the forward chamber wall at the level of the forward sealing plate and into the rearward chamber wall at the level of the rearward sealing plate.

Abstract: A rotor, for a turbomachine, in particular a gas turbine, having a first flange and a second flange with recesses that are distributed in a direction of distribution, in particular in the peripheral direction, wherein the second flange is fastened to the first flange, in particular detachably, by at least one fastener, which engage in the first of these recesses of the first and second flanges, wherein second ones of these recesses of the first flange, which are free of a fastener, are covered by the second flange.

Abstract: The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.

Abstract: The invention refers to a method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

Abstract: An engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.

Abstract: The invention relates to a method for the layered manufacturing of a structural component from powder, comprising the following steps: establishing at least one parameter (t) of a depression (1) in a produced layer (2) of the structural component; smoothing out the depression (1) if the at least one parameter (t) exceeds a predetermined value; and filling the smoothed-out depression (1) with powder (13).

Abstract: A method determines a generator system load and/or rotor angle. The generator system has a generator with a generator terminal outputting electrical power generated by the generator, a transformer and a point of common coupling, PCC, terminal. The transformer is between the generator and PCC terminals. The method includes: determining the generator field current; determining the output voltage, the output current and the power factor and/or angle of the output voltage and output current from the generator terminal, and determining the load angle of the generator system, output voltage from the generator terminal, output current from the generator terminal and the power factor and/or angle; and/or determining the output voltage, the output current and the power factor and/or angle of the output voltage and output current, and determining the rotor angle of the generator system, output voltage, output current from the PCC terminal and the power factor and/or angle.

Abstract: A method for regulation of an internal combustion engine with an SCR catalytic converter in which the operating point of the engine is predefined by an engine control unit and the operating point of the catalytic converter is predefined by an SCR control unit. An overall system quality measure is calculated by an optimizer in accordance with fed back values of the engine control unit and fed back values of the SCR control unit, by changing the default values for the engine control unit and the SCR control unit, the optimizer minimizes the overall system quality measure for a prediction horizon regarding operating costs. On the basis of the minimized overall system quality measure the optimizer sets the default values for the engine control unit and the default values for the SCR control unit as decisive for setting the operating point of the engine and the catalytic converter.

Abstract: A method for operating an internal combustion engine having an engine with a first number of cylinders and a second number of cylinders and a supercharger arrangement, wherein a charge air flow supplied to the engine is compressed by means of at least one compressor and at least one turbine is acted on by an exhaust gas flow discharged from the engine. In a main operating mode, the engine operates the first number of cylinders in two-stroke operation and the second number of cylinders in four-stroke operation. A scavenging gradient of the engine is greater for the cylinders operated in the two-stroke operation than for the cylinders operated in the four-stroke operation.

Abstract: A method for requirement-based servicing of an injector in a common-rail system in which, during ongoing operation of the engine, a current operating point is stored as a function of the rail pressure and of the fuel injection mass, and the current operating point is multiplied by a damage factor and is stored as a reference injection cycle as a function of the rail pressure as well as of the fuel injection mass. A total reference injection cycle is calculated by forming sums over the reference injection cycles, and a load factor is calculated as a function of the total reference injection cycle and the permissible injection cycles, and the load factor is set as decisive for the servicing recommendation of the injector.

Abstract: The present invention relates to a guide vane ring element for a turbomachine, such as a gas turbine, with at least one drilled hole for the at least partial uptake of a flange of a rotatable guide vane, wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion and, in particular, has a radius.

Abstract: The invention relates to a method for nondestructively acoustically examining at least one region of a component of a turbomachine, wherein at least the following steps are performed: a) arranging a transmitter comprising a plurality of individual oscillators on the region of the component to be examined, b) introducing at least one ultrasound beam into the component by means of the transmitter, c) receiving at least one ultrasound beam reflected by the component by means of a receiver comprising a plurality of individual receivers and d) checking, on the basis of the received ultrasound beam, whether there is a deviation in the region of the component which characterizes a segregation. The invention further relates to a device for carrying out a method of this type.

Abstract: The invention relates to a blade or vane, a blade or vane segment, and an assembly for a turbomachine, wherein the blade or vane has a blade or vane element with a blade or vane element profile and a radially inner end of the blade or vane element and a radially outer end of the blade or vane element, and wherein the blade or vane has, in addition to the blade or vane element profile, at least one first guide profile in the region of the radially inner end of the blade or vane element (EI) and/or of the radially outer end of the blade or vane element and is spaced apart from the associated blade or vane element end in the radial direction, and extends at least partly in the axial direction and at least partly in the peripheral direction and/or at least partly in the tangential direction.

Abstract: A method for the model-based control and regulation of an internal combustion engine. The method includes calculating, as a function of a set torque, injection system set values for controlling the injection system actuators via a combustion model and calculating gas path set values for controlling the gas path actuators via a gas path model. The combustion model is adapted during operation of the internal combustion engine into the form of a complete data-based model. A measure of quality is minimized by an optimizer by changing the injection system set values and gas path set values within a prediction horizon, and the injection system set values and gas path set values are set by the optimizer, which is critical for adjusting the operating point of the internal combustion engine by using the minimized measure of quality.

Abstract: A sealing assembly for sealing a first sealing bank of a first static component and a second sealing bank of a second static component of an axial turbomachine, the static components axially movable relative to each other, the sealing assembly including the two static components and a sealing element segmented in the circumferential direction, a first end of the sealing element being axially coupled in a groove at the first sealing bank facing an opposite second end bearing axially against the second sealing bank, as well as a stator vane assembly including a casing component of an axial turbomachine, which has at least one casing hook, and further including a stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook which projects from the platform and bears against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air.

Abstract: The invention relates to a work station for electrochemically machining a workpiece, having a number of recesses, including a base structure; a module which is fastened to the base structure and is configured to electrochemically machine the workpiece. A workpiece holder is fastened to the base structure. The workpiece holder is movable relative to the base structure along a feed axis which is parallel to the axis of rotation of the module. The module includes an electrode carrier arrangement, which is coupled to the module base body so the electrode carrier arrangement can be rotated together with the module base body about the axis of rotation of the module. The electrode carrier arrangement has a carrier frame and an electrode frame, where at least one electrode is detachably fastened to the electrode frame.

Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

Abstract: A method for evaluating the quality of a component produced by means of an additive laser sintering and/or laser melting method, in particular a component for an aircraft engine, includes at least the steps of providing a first data set, which comprises spatially resolved color values, which each characterize the temperature of the component at an associated component location during the laser sintering and/or laser melting of the component, providing a second data set, which comprises spatially resolved color values corresponding to the first data set, which color values each characterize the temperature of a reference component at an associated reference component location during the laser sintering and/or laser melting of the reference component.