Abstract: The present invention relates to a method for monitoring a turbomachine, in particular of an aircraft engine, wherein the turbomachine is equipped with a microphone array, wherein the microphone array has at least two microphones, which, in relation to the longitudinal axis of the turbomachine, are arranged at different axial positions and/or circumferential positions, in which during an operation of the turbomachine, sounds emitted by the turbomachine are captured with the microphone array.

Abstract: The invention relates to a turbomachine for an aircraft propulsion drive with a compressor, through which a gas flow streams in a flow direction of the turbomachine, a combustion chamber, a turbine, and a heat exchanger downstream of the turbine, wherein the heat exchanger is set up to produce steam from water by energy from the gas flow, which, in particular, can be fed to the gas flow for combustion with fuel in the combustion chamber.

Abstract: The invention relates to a turbomachine for a flight propulsion drive with a compressor, a combustion chamber, a turbine through which a gas flow flows in the flow direction of turbomachine, and a heat exchanger downstream of the turbine, wherein the heat exchanger is equipped to generate steam from water using energy from the gas flow, which can be supplied with fuel to the gas flow for combustion in the combustion chamber.

Abstract: A blade for a turbomachine is provided. The blade at its blade tip (4) includes blade tip armor (5), and an erosion protection layer (11) above the blade tip armor. For the blade, the erosion protection layer in the area of the blade tip has a layer thickness in the range of 5 ?m to 100 ?m, in particular 10 ?m to 50 ?m.

Abstract: The invention concerns a method for identifying a substance in a cavity of an apparatus, in particular in a cavity of a turbine engine or turbo machinery, comprising steps of introducing a probe tip of a borescope into the cavity; exposing a substance in the cavity to excitation light by means of the borescope; capturing a fluorescence of the excited substance by means of the borescope; and identifying the substance. The invention further concerns a borescope for identifying a substance in a cavity of an apparatus.

Abstract: The layer construction method comprises at least the following steps: a) applying at least one powder layer of a material to at least one construction and joining zone of at least one movable construction platform; b) locally solidifying the material to form a component layer, wherein the material is selectively scanned along scan lines by at least one energy beam and fused; c) lowering the construction platform layer by layer by a predefined layer thickness; and d) repeating the steps a) to c) until the component region is complete. In step b), a distance hs between at least two central lines of neighboring scan lines in at least one component layer is adjusted in accordance with Formula I 0.85?bsmin/hs?1.00??(I) wherein bsmin represents a minimum melt pool width of the scan lines.

Abstract: The invention is directed to a method for cleaning powder residues of an additive layer build-up method away from an at least partly additively manufactured component by a cleaning device, wherein a machine plate and the component arranged thereon are excited to mechanical oscillation during a cleaning process by a vibration actuator of the cleaning device with a set resonant frequency of the machine plate. According to the invention, before the cleaning process is carried out, a resonant frequency of the machine plate is set to the set resonant frequency by an arrangement of a mass element on a securing element of the machine plate.

Abstract: A guide vane for arrangement in a gas duct of a turbomachine, including a guide vane blade and an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade. The outer platform delimits the gas duct with an inner wall surface radially to the outside. The inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct.

Abstract: A method for investigating an electrolyte solution for processing a component, particularly a component or a component material of an aircraft engine, by near infrared spectroscopy.

Abstract: A method is provided including the steps: —first excitation of the object via a multifrequency signal; —detecting a first response signal of the object at one or multiple measuring points at the object; —transforming the first response signal from a time range into a frequency-dependent range; —selecting one or multiple frequencies, based on the frequency-dependent range; —second excitation of the object based on the selected frequencies; —detecting a second response signal of the object at one or multiple measuring points of the object; —ascertaining a mechanical parameter based on the second response signal.

Abstract: The invention relates to a guide vane for a gas turbine, comprising an airfoil, a platform arranged at a radial end of the airfoil, an upstream flange extending radially from the platform, and a downstream flange extending radially from the platform, wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element. A surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove. The invention further relates to a guide vane cluster, a housing for a gas turbine, as well as to a gas turbine.

Abstract: The invention relates to a braze alloy mix for application in a method for brazing a component that has a nickel-based superalloy as base material, wherein the braze alloy mix comprises the following powders in a predetermined mixing ratio: a powder of a first braze alloy, a powder of a second braze alloy, a powder of a third braze alloy, and a powder of an additive alloy.

Abstract: The present invention relates to an apparatus and a method for determining a scaling factor for a strain measurement in a machine element, comprising steps for measuring a strain in a measurement surface portion by means of a strain measuring device; for measuring a displacement of a detection surface portion of the machine element by an optical scanning; for determining a displacement field on a surface of the machine element on the basis of a model of the machine element and the measured displacement of the at least one detection surface portion; for determining a strain field on the surface of the machine element on the basis of the determined displacement field and the model of the machine element; and for determining a scaling factor of the strain measuring device on the basis of the determined strain field and the measured strain in the measurement surface portion.

Abstract: Rotor blade (20) to be arranged in a gas conduit (3) of a turbomachine (1), having a rotor blade airfoil (23), which radially inwardly has a chord length Si, radially outwardly has a chord length Sa, and in a radial position rx inbetween has a chord length Sx, the chord length Sx in the radial position rx being at least equal to the chord length Si radially inwardly (Si<Sx), and the chord length Sa radially outwardly corresponding at most 0.9 times the chord length Sx in the radial position rx inbetween (Sa<0.9 Sx).

Abstract: The invention relates to an axially divided inner ring as well as a variable vane cascade for an aircraft engine. The inner ring and the vane cascade improve the efficiency of the aircraft engine in that differently formed vanes and/or vane mounts are formed respectively in the inner ring or in the vane cascade.

Abstract: The invention relates to a method machining a particularly planar component by means of electrochemical machining, wherein the component has internal stresses resulting particularly from preceding manufacturing steps. In a first step a) of the method, the component to be machined is provided. Subsequently, in step b), at least two tools are provided in the form of electrodes and, in step c), an electrolyte is provided between the component and the at least two electrodes. In step d), a positive voltage is applied to the component and a negative voltage is applied to the at least two electrodes. Thus, in step e), by moving the at least two electrodes along their respective movement paths with respect to the component, electrochemical machining can take place; in the process, the gap between each electrode and the component is flushed with the electrolyte at least intermittently.

Abstract: The invention relates to an air conduction system for an aircraft engine with a primary flow channel and a branch channel, in which, in particular, the branch channel can be a secondary flow channel and/or a bleed air channel, wherein the branch channel branches off the primary flow channel at a connecting region, comprising a closing device arranged at or in the connecting region for separating the branch channel from the primary flow channel, wherein the closing device has at least one closing ring for closing the connecting region.

Abstract: A connecting structure (10) for load transfer, in particular in a gas turbine (1), including a strut (20) and at least one wall element (30) is provided. The strut (20) at one end is integrally joined to the wall element (30), and the strut (20) and the wall element (30) are enclosed by a fillet (40), at least in areas, and integrally joined to same. An elastic deformation of the involved elements of the structure during the load transfer and/or load absorption is improved in that a root section (50) that is formed by a ridge (56) and that extends from the strut (20) to the wall element (30) is situated on the fillet (40).

Abstract: The invention relates to a rotor shaft for an electric motor, in particular for an aircraft engine, wherein the rotor shaft has a forged attachment flange, wherein the attachment flange is provided for attachment to another shaft in order to transmit a force and/or a torque, comprises a first axial end facing the other shaft, and comprises a base plate on a second axial end opposite the first axial end. It is provided that the rotor shaft has a coolant distribution body that is additively manufactured at least in some regions, wherein the additively manufactured coolant distribution body is arranged on the base plate of the forged attachment flange in a radially centered manner, and the rotor shaft has a rotor device, which radially surrounds the additively manufactured coolant distribution body and is joined to the base plate of the forged attachment flange at least in a force-fitting manner.

Abstract: The present invention relates to a method for imaging a surface in an internal space of an axial turbomachine, wherein the surface is captured in a sequence using an imaging device, i.e.—only a portion is captured with the imaging device at a respective time, thus generating only a partial image of the surface; the imaging device and the surface are moved relative to each other such that different portions of the surface are captured over the course of time, thus generating different partial images, and wherein the partial images are stitched together to produce an image of the surface.