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 invention relates to a compressor module that forms a compressor gas duct for guiding a compressor gas that is to be compressed, wherein a flow bypass structure extends radially through the compressor gas duct between an inner housing wall and an outer housing wall, and wherein, in a wall surface of the inner housing, with which the inner housing wall bounds the compressor gas duct radially inward, an exhaust orifice for partial exhaust of the compressor gas guided in the compressor gas duct is arranged, wherein, for guiding the exhaust gas that is discharged through the exhaust orifice, an exhaust duct adjoins the exhaust orifice, and wherein the exhaust duct extends through the flow bypass structure radially outside of the compressor gas duct.

Abstract: A method and an arrangement for operating an internal combustion engine. According to the method, a load threshold is defined below which load control by a throttle valve is performed.

Abstract: An insert that can be positioned in a gap between a first front face of a cylinder liner, the first front face facing a cylinder head, and a second front face of the cylinder head, the second front face facing the cylinder liner. The insert includes at least one compressible material.

Abstract: The present invention relates to a process for producing a diffusion layer for protecting temperature-stressed components, in particular of turbomachines, against oxidation and corrosion. The process comprises application of at least one slip to a component surface on which the diffusion layer is to be produced, and drying and/or hardening of the at least one slip by a heat treatment at a first temperature and diffusion heat treatment at a second temperature. The slip comprises Al-containing powder, Si-containing powder and a binder and also a Cr-containing powder which does not comprise any hexavalent chromium. In addition, the invention provides a corresponding slip.

Abstract: The present invention relates to a method for designing a flow channel for a turbomachine, in particular a gas turbine that comprises a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a design of one of the flow passages is adapted to this support rib, that it is situated downstream of, in order to reduce a pressure loss and/or a vibrational stimulation.

Abstract: A device for attaching seal elements in a recess, particularly in an installation groove designed in a flow machine, is disclosed. At least one fixing body is arranged between a seal carrier element and a clamping body assigned to the seal carrier element, where the fixing body is integrally connected to the seal carrier element and the clamping body by bar-like connections that can be detached when subjected to a force. In addition, at least one plastic deformable structure is designed on the fixing body. An attachment method as well as a production method for the device is also disclosed.

Abstract: A powder build unit for a device for the additive manufacture of components, includes at least one electric lead and having at least one power source that is connected to the electric lead. The electric lead functions as a powder distributor and as a heating element. In addition, a device that contains this powder build unit, as well as a corresponding method of using the powder build unit, is disclosed.

Abstract: A low pressure turbine engine component for use in an engine, for propelling a vehicle such as an aircraft is formed by a disk portion and a plurality of low pressure turbine blades extending outwardly from the disk portion. Each of the low pressure turbine blades has an airfoil portion with an axial chord length and a trailing edge. The low pressure turbine blades are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance between the trailing edges of adjacent ones of the low pressure turbine blades and the chord is the axial chord length of the blades.

Abstract: An axially split inner ring for a fluid flow machine is disclosed. The inner ring is constructed for connecting to guide vanes and includes at least a first ring segment arranged upstream and a second ring segment arranged downstream. The second ring segment has a first sealing segment, where at least one section of the second ring segment is arranged in a radially inward manner relative to the first ring segment. A guide vane ring of a fluid flow machine and an aircraft engine are also disclosed.

Abstract: An inner ring according to the invention or an inner ring segment according to the invention for an adjustable guide vane assembly comprises a plurality of uptakes, each for the bearing of an adjustable guide vane. The uptakes here each form an essentially ellipsoidally shaped uptake space for a guide vane head of the respective guide vane. A guide vane according to the invention for an adjustable guide vane assembly has a blade body and a guide vane head. The guide vane head is essentially ellipsoidal in shape and is equipped to be accommodated pivotably in an uptake of an inner ring or inner ring segment of the guide vane assembly.

Abstract: Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.

Abstract: A method for operating a dual-fuel internal combustion engine, having an intake path and an engine having a number of cylinders. In the method the engine is operated in a first operating state in diesel operation with diesel or another liquid fuel, and in a second operating state in gas operation with gas as fuel in a charge mixture, and switching between diesel operation and gas operation takes place in a switchover range determined, in particular predetermined, by switchover operating parameters.

Abstract: An internal combustion engine including at least one combustion chamber having a main chamber and a prechamber, wherein the prechamber is in fluid connection with the main chamber via at least one bore. The at least one combustion chamber is connected to a charging path for the supply of a combustion air-fuel mixture into the combustion chamber via the charging path. A fuel intermixing region is arranged in a section of the charging path separately assigned to the combustion chamber, which fuel intermixing region is in fluid connection with the charging path on one side and with a fuel line on the other side for the supply of fuel into the fuel intermixing region via a controllable fuel valve. The internal combustion engine wherein the prechamber and the fuel intermixing region are in fluid connection with one another via a check valve.

Abstract: The present invention relates to an adjustable guide vane for a turbomachine, having a vane element and a turning disk, which has a first impact chamber, in which an impulse element is arranged with play of movement.

Abstract: A method for determining the aging of an oxidation catalyst in an exhaust gas aftertreatment system of an internal combustion engine, having the following steps: ascertaining a soot burn rate of a particle filter of the exhaust gas aftertreatment system; adapting a function having at least one adaptation parameter to the soot burn rate dependent on at least one variable, a value of the adaptation parameter depending on an aging of the oxidation catalyst; and determining the aging of the oxidation catalyst using the adaptation parameter value ascertained by adapting the function.

Abstract: A method for detecting the aging of a heterogeneous catalytic converter, including the following steps: acquiring at least one measurement signal in a media flow passing through the catalytic converter downstream of the catalytic converter; applying a time-variant input signal to the media flow and/or the catalytic converter; evaluating a behavior of the at least one measurement signal as a function of the time-variant input signal; and detecting a state of aging of the catalytic converter.

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 operating an internal combustion engine having a number of cylinders and an injection system having an injection system that has a common rail and a number of injectors associated with the cylinders, wherein an individual accumulator is associated with each injector and stores fuel from the common rail for the injector. The method has the following steps: starting the internal combustion engine, operating the internal combustion engine, shutting off the internal combustion engine. The following steps are also provided: a state indicating an engine standstill is detected, in particular after the internal combustion engine has been shut off, a high-pressure limit value is defined and a target high pressure is specified, a leakage is produced in the common rail without injection, the fuel pressure in the common rail is reduced to the defined high-pressure limit value below the target high pressure by way of the leakage.

Abstract: The invention relates to a sealing assembly for a fluid kinetic machine, in particular for an aircraft engine, for sealing a radial gap between a rotor and a stator, including at least one sealing support for retaining and/or fixing at least one sealing element, wherein the sealing support includes a first and a second radial web extending in a radial extension direction as well as an axial web extending in an axial extension direction, firmly bonded to the radial webs, and the radial webs form a receptacle for receiving an element of the stator. Therein, the radial webs are formed as sheet elements formed elongated in radial direction, wherein a radially interior end of the radial webs is respectively firmly bonded, in particular welded, to a radially exterior surface of the axial web.