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.

Abstract: A method for operating an internal combustion engine, including aligning an injection behavior of the number of injectors. Aligning the injection behavior includes switching off one injector of the number of injectors, detecting a signal of the internal combustion engine that is to be assigned to the switched off injector, determining an alignment characteristic from the signal and assigning the alignment characteristic to the switched off injector as an alignment characteristic assigned to the injector, and switching on the previously switched off injector. Aligning the injection behavior further includes performing the aforementioned steps sequentially for the other injectors of the number of injectors and correcting a control of an injector that is to be corrected using the measured value assigned to the injector that is to be corrected.

Abstract: Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.

Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, comprising an additively built-up housing section and a cover, which, in each case referred to an axis of rotation of the shaft, connects axially to the housing section and has a radially extending collar, which collar axially bounds an oil space of the bearing chamber housing, wherein the cover is assembled with the housing section and is connected therewith via a weld.

Abstract: A method for model-based control and regulation of an internal combustion engine. An emission class for operating the engine is read from a first library by an optimizer; a maximum mechanical component load is read from a second library by the optimizer using the engine type; and the emission class and the component load are set as mandatory for a combustion model and a gas path model. Injection system target values for actuating injection system actuators are calculated using the combustion model based on a target torque. Gas path target values for actuating gas path actuators are calculated using the gas path model based on the target torque. A quality measurement is calculated by the optimizer based on the injection system and gas path target values. The quality measurement is minimized by the optimizer by changing the injection system and gas path target values within a prediction horizon.

Abstract: A method for operating an internal combustion engine. The method includes providing a piston engine. The piston engine includes a crankshaft and a torque sensor system. The torque sensor system includes at least one first rotary angle sensor and at least one second rotary angle sensor. The method further includes measuring a first and a second rotary angle in a spacing region and determining an angular offset between the first and the second rotary angle. The angular offset results from the torsion of the loaded crankshaft wherein the spacing region is limited along the crankshaft to an actual partial region of the spacing between the bearing journals. The partial region includes an actual subgroup of at least one of the number of offsets and the number of shaft journals, so that the angular offset is assigned to the actual subgroup.

Abstract: A valve train for the variable actuation of an inlet valve and an outlet valve of a combustion chamber of an internal combustion engine, having a first operative connection between a valve actuating device and the inlet valve and a second operative connection between the valve actuating device and the outlet valve. The first operative connection and the second operative connection are assigned an interrupting element which is set up to temporarily interrupt the operative connections. The first operative connection and the second operative connection are connected to the same interrupting element in such a way that the first operative connection and the second operative connection can be interrupted temporarily by way of the interrupting element.

Abstract: A method for operating an internal combustion engine, involving the following steps: determining a target lambda value and measuring an actual lambda value for combustion in a combustion chamber of an internal combustion engine; establishing, in accordance with the target lambda value and the actual lambda value, a point in time for an intake valve associated with the combustion chamber to open; and opening the intake valve at the established point in time.

Abstract: A blade (10) for a turbomachine is provided. The blade (10) includes an airfoil (16) having at least one thickening (22) on a pressure side (20) of the airfoil (16). The thickening (22) has a region (B) of constant thickness (D). A turbomachine, a compressor and a turbine having stator vanes and/or rotor blades including at least one such blade (10) is also provided.

Abstract: Described are an airfoil array segment (100, 200, 300) having at least two airfoils (20, 30) and a platform (10) that features an axis asymmetrical platform surface (12). This platform surface features an elevation (110, 210, 310) that extends from the pressure side (21) of the first to the suction side (32) of the second airfoil (30). A highest point (111, 211, 311) of the elevation is more proximate to the suction side 32 of the second airfoil (30) than to the pressure side (21) of the first airfoil (20). Also described are an airfoil, a platform, an airfoil passage and a turbomachine.

Abstract: A method for identifying a continuously injecting combustion chamber of an internal combustion engine which has an injection system with a high-pressure accumulator for a fuel, having the following steps: time-dependent sensing of a high pressure in the injection system; starting a continuous-injection detection process at a starting time while the internal combustion engine is operating; identifying a start time of a pressure drop which occurs chronologically before the starting time and at which the high pressure in the injection system begins to drop if continuous injection has been detected; and identifying at least one combustion chamber to which the continuous injection can be assigned, on the basis of the start time of the pressure drop.

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: The present invention relates to a blade or vane for a turbomachine, particularly for an aircraft engine, with a blade element for interacting with the flow medium, wherein the blade has different diffusion protective coatings in various regions on its surface for protection against corrosion and/or oxidation, wherein the diffusion protective coatings are produced by chromizing and/or aluminizing, wherein the blade element is divided into two regions along the longitudinal axis of the blade element, wherein the first region extends over 80 to 95% of the length of the blade element, and the second region extends over the remainder of the length of the blade element, and wherein in both regions, an AlCr diffusion protective coating is applied, and wherein in one of the regions, the AlCr diffusion protective coating has a higher Cr content.

Abstract: A shroud segment (100) for disposition on a blade of a turbomachine is provided, in particular a gas turbine, the shroud segment having a stiffening structure raised above a shroud segment surface (15), the stiffening structure including at least three interconnected ribs (3, 5, 7), and a first end portion of the ribs (3, 5, 7) being connected to an upstream sealing tip (11) of the shroud segment (100), and a second end portion of these ribs (3, 5, 7) being connected to a downstream sealing tip (13) of the shroud segment (100). The angles (W1, W2, W3) between the direction of the axis of rotation (a) of the blade and the longitudinal orientations (21, 23, 25) of the ribs (3, 5, 7), as viewed in the direction of flow (9) through the turbomachine, are between zero degrees and eighty degrees. The present invention also relates to a blade (200) of a turbomachine.

Abstract: A method for operating an internal combustion engine with a motor having a number of cylinders and an injection system having a common rail with a number of injectors assigned to the cylinders and similar high pressure components, which is designed to hold fuel from the common rail for the injector, wherein the method has the steps: injecting fuel from the common rail into a cylinder by way of an injector, determining a fuel pressure for a high-pressure component, in particular the common rail, the injector and/or the individual reservoir, having at least one high-pressure sensor measuring the fuel pressure. Provision is made for a defect in the high-pressure sensor to be detected in that a check is made as to whether magnitude of the high-pressure control deviation (ep) during a predetermined time interval (tLimit1SD, tLimit2SD, tLimit3SD) exceeds a predetermined limiting value (eLimit1SD, eLimit2SD, eLimit3SD).

Abstract: A method for implementation with the operation of an internal combustion engine, having an ignition plug, which is arranged on a combustion chamber of a cylinder of the internal combustion engine, wherein: in a first step, a cylinder pressure at the ignition time at the combustion chamber is detected, as well as a breakdown voltage at the ignition plug; and in a second step, a current electrode distance of the ignition electrodes, representing a current ignition electrode wear state, is determined based on the detected cylinder pressure, the detected breakdown voltage and a constant of proportionality.

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.

Abstract: A containerized generator set comprises a container, a generator set, a radiator, and a cooling fan. The generator set, radiator, and cooling fan are disposed within an interior volume defined by the container. The interior volume has a length, width, and height. The generator set comprises an engine and a generator. The cooling fan is mechanically coupled to the engine, and the cooling fan has a diameter that is substantially the same as the width of the interior volume. The cooling fan may further have a swept cross-sectional area that is at least 60% of the cross-sectional area of the interior volume.

Abstract: A cooling system including a first coolant line and a second coolant line, at least one first component to be cooled, into which the first coolant line opens, and a first ventilation line. The first ventilation line is fluidically connected to the at least one first component and is configured for ventilating the at least one first component. The first ventilation line opens into the second coolant line.

Abstract: The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (?) that is different from a zero angle.