Abstract: The invention relates to a turbine blade which comprises at least one cavity that is defined by a wall with one or more surface discontinuities which preferably are selected from elevations, depressions and undercuts and preferably change at least one eigenmode of the blade. The blade may suitably be produced by a generative production method such as selective laser melting (SLM).

Abstract: The invention relates to a method for repairing flow channel segments of a turbomachine. The method comprises providing a monocrystalline or directionally solidified flow channel segment whose length and width extend along the flow channel, each being greater than the thickness thereof, and whose width and length delimit a surface which constitutes a bounding surface of a flow channel and has damage, cleaning the bounding surface to remove impurities, remelting at least a part of the bounding surface in a surface region so that melted material solidifies epitaxially in an inner region facing toward the unmelted material and forms a structural region in which the monocrystalline or directionally solidified structure is preserved, and that melted material solidifies in a polycrystalline fashion in an outer region which faces toward the flow channel and forms an edge region, and removing the edge region.

Abstract: A guide vane according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate for its support on an inner ring. The guide vane plate has a cover surface facing the vane element, a base surface lying opposite to the cover surface, and an edge surface joining the cover and base surfaces. In a first region, the edge surface forms a chamfer of the vane plate, and in a second region, which forms the edge of a sector of the guide vane plate that is different from that of the first region, the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes according to the invention into respective uptakes in an inner ring.

Abstract: A rotor blade airfoil (25) for a turbomachine (1) that is adapted for rotation about a longitudinal axis (2) of the turbomachine (1) is provided. The rotor blade airfoil (25) is built from an airfoil material reinforced with a fibrous material (30). At least a portion of the fibers of the fibrous material (30), in particular at least 20%, preferably at least 30% of the fibers, are oriented in a first fiber direction (31), and the first fiber direction (31) is tilted with respect to the stacking axis of the rotor blade airfoil (25).

Abstract: A method for model-based open-loop and closed-loop control of an internal combustion engine, in which method injection system setpoint values for activating the injection system control elements are calculated dependent on a setpoint torque by a combustion model, and gas path setpoint values for activating the gas path control elements are calculated by a gas path model. The combustion model is adapted during ongoing operation of the internal combustion engine. A quality measure is calculated by an optimizer dependent on the injection system setpoint values and the gas path setpoint values, the quality measure is minimized by the optimizer by varying the injection system setpoint values and gas path setpoint values within a prediction horizon. The injection system setpoint values and gas path setpoint values are set by the optimizer, based on the minimized quality measure, as being definitive for setting of the operating point of the internal combustion engine.

Abstract: The present invention relates to a guide vane arrangement for a turbomachine, comprising a guide vane segment and a housing part that are fastened to one another, for which a back guide vane hook that rises radially toward the outside from an outer shroud of the guide vane segment, when referred to a longitudinal axis of the turbomachine, and a housing hook, which is arranged radially inside circumferentially at the housing part, engage in one another in form-fitting manner, wherein, in a first peripheral segment of the guide vane arrangement the guide vane hook has a front wall and a back wall, and therewith forms a groove open radially toward the outside, in which a ring section of the housing hook is arranged and held axially.

Abstract: The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.

Abstract: A valve drive for an internal combustion engine, including a gas exchange valve; a first mechanically driven drive mechanism; and a second drive mechanism connected to the gas exchange valve to move same. The first and second drive mechanisms connected via a hydraulic coupling device that has a pressure chamber, which can be relieved of pressure via a valve device and is designed to couple the drive mechanisms by hydraulic pressure and to decouple same in a pressure-relieved state. The valve device has two switch valves fluidically connected to the pressure chamber in parallel and via which the pressure chamber is relieved of pressure in the open state of at least one of the switch valves. The valve drive has a controller that actuates the switch valves in a delayed manner to provide a variable valve stroke of the gas exchange valve during a stroke movement.

Abstract: The present invention relates to a turbomachine assembly with an annular flow cascade, which has a plurality of blades, which are arranged distributed in a peripheral direction, and a detuning device for different detuning of natural frequencies of the blades, wherein the detuning device has a ring that revolves in the peripheral direction, or wherein the detuning device has all detuning elements that are arranged at the blade, which follow one another in a row in the peripheral direction, and are designed in such a way that, during operation, first blades of the flow cascade each contact at most one, in particular, no movable detuning element of the detuning device.

Abstract: A method for monitoring a cylinder pressure sensor, in which method the sensor value is checked for admissibility and inadmissibility in a predefinable crankshaft angle range, when admissibility is detected the cylinder pressure sensor is used further and when inadmissibility is detected the cylinder pressure sensor is deactivated. A first sensor value of the cylinder pressure sensor is set as a start value, and a second sensor value is set as a stop value, a plateau range is determined from the number of sampling steps between the start value and the stop value, and the plateau range is set as decisive for the admissibility or inadmissibility of the sensor values.

Abstract: The present invention relates to a hydraulic extrusion tool for extruding a rotor shaft for a turbomachine, and a corresponding method. The turbomachine has a structure that is fastened to the rotor shaft by a press fit. The extrusion tool has a first tool part that is configured for the purpose of being arranged on a first side of the structure, and which has a coupling mechanism that is configured for the purpose of coupling the first tool part to the structure, in such a way that the first tool part and the structure cannot move away from each other, at least in one direction along an axis of the rotor shaft; and an induction device that is configured for the purpose of heating the structure by induction in the region of the press fit.

Abstract: A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root element (12) in the longitudinal direction of the blade (RR); respective centroids (24) of blade cross-sectional areas of the stream deflection portion residing on a common stacking axis (26). It is provided that, starting from a first centroid (24) of a first blade cross-sectional area adjoining the blade root element (12), the stacking axis (26) extend within a cone (28) whose apex resides within the first centroid (24), and whose cone height (KH) extends orthogonally to the plane of the blade cross-sectional area; the angle (?) of the cone (28) being greater than 0° and smaller than or equal to 4°; preferably greater than or equal to 0.5° and smaller than or equal to 2°.

Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions continuously and/or non-continuously at one or more circumferential positions, in particular separation points.

Abstract: Described is a connecting device (50) for a variable vane (51) of a gas turbine (10), in particular of an aircraft gas turbine, the connecting device including a trunnion element (52) connected to a respective vane (51); a lever element (54) connected to the trunnion element (52), the lever element (54) and the trunnion element (52) being movable together about a trunnion axis of rotation (ZD). It is provided that the lever element (54) and the trunnion element (52) be aligned with each other by a positioning element (68), the positioning element (68) being received in a trunnion receptacle (60) and a lever receptacle (66, 66a, 66b).

Abstract: A segmented ring for installation in a turbomachine, circumferentially divided into segments, considered with respect to a ring axis of the segmented ring, wherein the segmented ring is adapted for installation from radially inside; i.e., the segments can be assembled radially outwardly to form the segmented ring. At least two immediately circumferentially adjacent segments meet in a joint at which a sealing insert is provided. A pocket which is open toward the joint is formed in each of the at least two immediately circumferentially adjacent segments; i.e., two circumferentially mutually facing pockets are provided at the joint. The sealing insert is disposed in the two mutually facing pockets and axially retained therein and extends circumferentially across the joint, and a pocket of the two mutually facing pockets is additionally also open in a radial direction such that this segment can be radially slid onto the sealing insert.

Abstract: The present invention relates to a housing structure for a turbomachine, a turbomachine, and a method for cooling a housing portion of a housing structure of a turbomachine, wherein the housing structure has an outer housing wall, which is formed by at least one housing part, and an inner wall, wherein the inner wall is arranged in the radial direction inside of the housing wall and spaced apart from the housing wall and is designed to bound the main flow channel, at least partially, wherein the housing structure comprises a cooling air channel for cooling a housing portion to be cooled, and has an upstream end and a downstream end, wherein the cooling air channel extends, at least partially, between the housing wall and the inner wall.

Abstract: The invention relates to a method and a set of balance weights for balancing a rotor, particularly of a turbomachine, on which a plurality of balance weights, which are distributed over the periphery, can be arranged for balancing an imbalance. A set of balance weights, in particular plate-shaped weights, with a predetermined number of groups of balance weights, is used for balancing the rotor. Each of the balance weights of every group of balance weights has an identical weight that is assigned to this group and a shape assigned to this group, which differs in basic shape and/or thickness of the balance weights from the balance weights of the other groups.

Abstract: A combination including a seal (36-38) for sealing a gap (s) between blade platforms (11, 21) of two adjacent blades of a turbomachine and a reducer (31; 32-34) for reducing vibrations of at least one of the blades, the seal including at least one rib (36) having a rib thickness and at least one wall (37) having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing (32) having at least one cavity (33) in which at least one tuning element (34) is disposed with play for impacting contact with the tuning-element guide housing.

Abstract: Discloses are a method and apparatus for the additive manufacture of components by applying layers of powder material on a substrate or a previously produced part of a component and at least partial fusing of the powder material in the powder layer in line with the component cross-section contour along the powder layer and to an underlying solid material of the component or substrate for the purpose of building up several solid layers one on top of the other. Following fusion of the powder material the solid layer just generated is cleaned of powder material and, prior to deposition of the next solid layer, the edge of the solid layer is post-processed by softening the fusion-bonded material.

Abstract: A flow channel for a turbomachine, in particular a gas turbine, having a plurality of ribs that are disposed between a radially inner lateral surface and a radially outer lateral surface of the flow channel and are circumferentially distributed; a first rib of the ribs having a first rib thickness and a first rib length, and a second rib of the ribs having a second rib thickness and a second rib length, the second rib length being shorter than the first rib length, and/or the second rib thickness being smaller than the first rib thickness; a spacing in the circumferential direction between the first rib and the second rib adjacent thereto, and a spacing in the circumferential direction between at least two adjacent ribs of the ribs mutually deviating, and at least one of these ribs having a non-deflecting external profile and or an internal structure being disposed therein.