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 comprises 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.

Abstract: The present invention relates to a rotor arrangement for a turbomachine, having a rotor with a first rotor stage, a shaft, and a first hub for joining the first rotor stage to the shaft. The first hub has a balancing device for balancing the first rotor stage. In addition, the present invention relates to a compressor.

Abstract: An exhaust gas treatment device for an exhaust gas system of an internal combustion engine, including a housing which has at least two equivalently formed receiving elements for arranging the AGN modules, and at least one exhaust gas guide module which is inserted into one of receiving elements, and an exhaust gas guide module for an exhaust gas treatment device of this type.

Abstract: The invention relates to a method for the additive manufacture of at least one region of a component. Here, at least the following steps are carried out: a) layer-wise application of at least one powder-form component material onto a component platform in the region of a build-up and joining zone; b) layer-wise and local solidifying of the component material by selective exposure of the component material by at least one high-energy beam in the region of the build-up and joining zone, with the formation of a component layer; c) layer- wise lowering of the component platform by a pre-defined layer thickness; and d) repeating steps a) to c) until the component region or the component has been completely fabricated.

Abstract: A compressor for a gas turbine, in particular of an aircraft engine, having a plurality of arrays (10-25) of flow-directing elements that are serially disposed in a through flow direction from a compressor inlet to a compressor outlet (1, 2); at least one upstream, mistuned array (20) of flow-directing elements and at least one downstream, mistuned array (22) of flow-directing elements each having at least two types of flow-directing elements that differ structurally from one another; and at least 80%, in particular at least 95% of the rotor blades (45) of a furthest downstream rotor blade array (25) that, in the through flow direction, is configured downstream of the downstream, mistuned array (22) of flow-directing elements, being mutually identically constructed.

Abstract: A method for operating an internal combustion engine having a turbocharger, wherein a fuel quantity is supplied to the combustion chamber of the engine in a stationary state, which fuel quantity is determined according to a first predetermined relationship between a load requirement to the engine and a rating determining a fuel quantity to be supplied to the combustion chamber, wherein a second predetermined relationship between the rating and the load requirement is used, wherein according to the second relationship, a given load requirement is assigned a larger quantity of fuel than according to the first relationship. In a transient state of the engine, the fuel quantity supplied to the combustion chamber is determined based on an interpolated value of the rating, which is determined for the rating by an interpolation between a value resulting from the first relationship and a value resulting from the second relationship.

Abstract: The invention relates to a device for inductive heating of a component, having a component placement unit for the component, an induction coil, with which the component can be heated inductively, at least in regions, an electrical lead for the induction coil, and a positioning unit, at which the induction coil is arranged in such a way that it can be brought into different relative arrangements with respect to the component placement unit by way of the positioning unit, wherein the electrical lead is guided over a contact, which is formed by contact surfaces that rest against each other and are shifted in position in relation to each other in the contact position when the induction coil is shifted in position by means of the positioning unit.

Abstract: A method for manufacturing at least a metallic portion of a component: a) depositing metallic material layer by layer onto at least one building platform; b) locally fusing and/or sintering the material layer by layer by supplying energy by at least one high-energy beam in the region of a buildup and joining zone to form at least a portion of at least one component layer of the component portion and/or of the component; c) lowering the building platform layer by layer by a predefined layer thickness; and d) repeating the steps a) through c) until completion of the component portion and/or of the component. Before, during and/or after process step b), at least one further portion of the component layer is formed by locally fusing and/or sintering the material by inductive heating at a temperature or in a temperature range above the solidus temperature of the metallic material used. A system for manufacturing at least a portion of a component is also provided.

Abstract: The present invention relates to a method for producing a component of a ?-TiAl alloy, in which, in a first step, a forging blank made of a ?-TiAl alloy is built up from a powder material by an additive method, and subsequently, in a second step, the forging blank is reshaped into a semi-finished product, wherein the degree of reshaping over the entire forging blank is high enough that, in a third step, the structure is recrystallized during a heat treatment. In addition, the invention relates to a component produced therefrom.

Abstract: The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.

Abstract: A power system includes a synchronous electrical generator having a rotor driven by a shaft; a permanent magnet signaling generator, coupled to the shaft; and an angle computation unit configured to calculate a rotor angle or load angle based on a voltage from the permanent magnet signaling generator and a voltage from the synchronous electrical generator.

Abstract: A power system, including: a synchronous electrical generator having a rotor; and an angle computation unit configured to: determine a rotor angle in a steady state period of the synchronous electrical generator, determine a change in rotor angle in a transient period of the synchronous electrical generator, and estimate the rotor angle in the transient period based on the steady state rotor angle and the change in rotor angle.

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: An inner ring (14) for an annular guide vane assembly (10) of a turbomachine, which inner ring enables variable guide vanes (12) to be rotatably supported is provided. The inner ring (14) includes a first and a second securing ring (16a, 16b) which are connected together by at least one securing element (18) extending axially with respect to a centerline (M) of the inner ring (14). The at least one securing element (18) includes a vane bearing (20) which projects radially with respect to the centerline (M) and which corresponds to an associated guide vane (12) and is adapted for rotatably supporting the same. A method for manufacturing an annular guide vane assembly (10) of a turbomachine using such an inner ring (14) is also provided.

Abstract: The invention relates to an inner ring system for an inlet guide vane cascade of a turbomachine. The inner ring system comprises an intermediate casing for accommodating structural loads and an inner ring, which is divided axially into a first ring segment and a second ring segment, which together form recesses for bearing radially inner end portions of guide vanes of the inlet guide vane cascade, wherein at least the second ring segment is fixed in place on the intermediate casing by screw connection. The invention further relates to an inner ring and to an intermediate casing for such an inner ring system, as well as a turbomachine that has such an inner ring system.

Abstract: A guide vane assembly according to the invention comprises an inner ring, on whose radially outer surface an uptake channel runs in the peripheral direction; a plurality of bearing members, which are arranged in the uptake channel of the inner ring; a plurality of guide vanes, each of which is inserted by its radially inner end into one of the bearing members; and at least one sealing element for sealing at least one gap between the inner ring and at least one of the bearing members and/or between two bearing members. A turbomachine according to the invention comprises a guide vane assembly according to the invention. A method according to the invention serves for the installation of a guide vane assembly.

Abstract: A connection system for a hot gas-conducting annular duct of a turbine intermediate casing of a gas turbine includes a first housing element, a second housing element situated next to the first housing element in the circumferential direction, and a fastening unit configured for connecting the first housing element and the second housing element to one another at edges adjacent to one another in the circumferential direction, the fastening unit including a clamping element which is mounted on the one housing element with the aid of a connection, the clamping element resting on a clamping surface provided on the other housing element in such a way that the other housing element is accommodated between the clamping element and the one housing element.

Abstract: A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.

Abstract: An internal combustion engine including a cylinder head, a fresh air duct configured for providing a fresh air supply to the internal combustion engine, and a quick-closing valve arranged in the fresh air duct, upstream of the cylinder head of the internal combustion engine, in order to interrupt the fresh air supply. The internal combustion engine also includes an exhaust gas recirculation pipe that has an outlet opening that is arranged centrally in the fresh air duct and, in a flow direction of the fresh air supply, upstream of the quick-closing valve forming a minimum gap between the outlet opening and the quick-closing valve.

Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, having an additively built-up housing wall and a cover of the oil chamber, wherein, in each case referred to an axis of rotation of the shaft, the housing wall bounds radially outwardly an oil chamber of the bearing chamber housing and the cover of the oil chamber disposed on an axial end of the housing wall axially bounds a region of the oil chamber; the region bounds radially inwardly an inner shell of the bearing chamber housing.