Abstract: Described is a heat-protection element (50) for a gas turbine (10), in particular an aircraft gas turbine, the heat-protection element (50) being adapted to at least partially surround a bearing chamber (60) of the gas turbine (10) and having at least one connecting portion (52) which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element (54) of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion (58) which is disposed in an axially central region (MB) and adapted to support the heat-protection element (50) radially on the bearing chamber (60), an end portion (64) which is disposed in an axially rearward region (HB) and forms a free end (66) of the heat-protection element (50) and which is configured such that the end portion surrounds (64) the bearing chamber (60) in a contactless manner.

Abstract: According to an aspect, a gas turbine engine includes a turbine section with a turbine case and a plurality of turbine blades within the turbine case. The gas turbine engine also includes an active clearance control system with an active clearance control cooling air supply, a valve pneumatically coupled to the active clearance control cooling air supply, and a controller. The controller is configured to determine an active cooling control schedule adjustment based on a condition of the gas turbine engine, operate the active clearance control system according to an active cooling control schedule as modified by the active cooling control schedule adjustment, apply a decay function to the active cooling control schedule adjustment to reduce an effect on the active cooling control schedule adjustment, and resume operating the active clearance control system according to the active cooling control schedule based on an active cooling control condition being met.

Abstract: Disclosed is a borescope-based inspection method for inspecting a condition of an externally invisible component of a device, in which method a change in the microstructure of the component material is determined based on a physical property and evaluated in relation to at least one reference physical value that accounts for aging of the component. Also disclosed is a system having a computing unit and at least one probe for performing such an inspection method for selecting, with the aid of or, in particular, by a computer, a non-destructive testing method for measuring the physical property and for actually measuring the physical property, for performing a comparison between a measured value and the reference value and for performing an evaluation of a tolerance between the measured value and the reference value.

Abstract: The present invention relates to an aircraft having at least one wing, on which at least one propulsion unit is arranged, comprising at least one heat engine, especially a gas turbine, as well as an exhaust gas passage for conducting exhaust gas of the heat engine into and inside the wing.

Abstract: The invention relates to a method for the electromechanical machining of a component with at least one electrode which has a first working face with an outer contour which is shaped so as to form a gap complementary to a surface, to be produced by the electrochemical machining, of the component and which has a second working face which is able to be arranged at an edge of the produced surface of the component. In the method, first of all the component is provided, and the first working face of the electrode is positioned in a first machining position with respect to the component. Then, the component is machined with the first working face in order to produce the surface, before the machining of the component with the first working face is ended at a predetermined position. Subsequently, the component is machined with the second working face of the electrode.

Abstract: The present invention relates to a method for producing a component of a turbomachine from a metal alloy as well as a correspondingly produced component, wherein the method includes defining at least one first component region that will have a first property profile, and at least one second component region that will have a second property profile which is different from the first property profile; providing at least one powder of the metal alloy or several different powders of constituents of the metal alloy; additive manufacture of the component from the at least one powder, wherein the powder is melted for cohesive joining of the powder particles to each other and to a substrate or to an already produced part of the component.

Abstract: The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.

Abstract: The invention relates to a method for providing a metallic surface with a coating by applying one or more layers of one or more metal-containing slips to the surface. At least one of the slips comprises a coloring and/or color-imparting substance which has no influence on the properties of the completed coating and/or can be decomposed by thermal treatment, and the local thickness of the applied slip layer is determined on the basis of the local color intensity of the layer.

Abstract: Blade root receptacle for receiving a blade root of a rotor blade of a turbomachine. The blade root receptacle, for radially bearing in a form-fitting manner on the blade root, has a supporting flank which, in terms of a rotation axis, at least in proportions faces radially inward, wherein the supporting flank is provided with a convexity which, when viewed in an axially perpendicular section, at least in portions has a convex shape and, also when viewed in an axially parallel section, at least in portions has a convex shape.

Abstract: The invention is directed to a method for cleaning a component from powder residues of an additive layering method using a cleaning device, wherein a machine plate and the component arranged thereon are excited during a cleaning process by a vibration actuator of the cleaning device with a set resonance frequency of the machine plate to carry out a mechanical vibration. It is provided that the machine plate is excited by predefined vibration movements of the at least one vibration actuator to the predefined mechanical vibration, wherein the predefined vibration movements of the at least one vibration actuator occur in parallel to a main plane of the machine plate. The invention also relates to a cleaning device for cleaning an at least partially additively manufactured component, in particular a component of a turbomachine.

Abstract: An example hybrid power system includes a mobile platform comprising: a generator set comprising: a reciprocating engine configured to convert natural gas into rotational mechanical energy; and a generator configured to convert rotational mechanical energy sourced from the reciprocating engine into electrical energy; an electrical energy storage system (ESS) configured to store electrical energy; an electrical motor configured to convert electrical energy sourced from a combination of the generator set and the ESS into rotational mechanical energy; and a pump configured to operate using rotational mechanical energy sourced from the electrical motor.

Abstract: The present invention relates to a method for coating a component of a turbomachine in a bath, in which method, the component is partially immersed in the bath containing a coating material; the component is rotated at least intermittently around an axis of rotation, which lies outside of the bath, during the at least partial immersion; the component is at most immersed partially over and beyond the rotation.

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 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: The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.

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: An intermediate element is for a blade/rotor disk connection in a rotor of a fluid flow machine. The intermediate element is adapted to a shape of a blade root of a blade and to a blade root slot in a rotor disk for receiving the blade root such that, when arranged between the blade root and rotor disk, the intermediate element prevents contact between the blade root and rotor disk. The intermediate element has, on an outer surface that faces the rotor disk, at least one protrusion to reduce an air flow parallel to an axis of rotation of the rotor between the rotor disk and the intermediate element; and on an inner surface that faces the blade root, a recess that corresponds to the at least one protrusion.

Abstract: An arrangement reduces oscillation (vibration) of an oscillatory structure. The arrangement has a structure having at least one mode in at least one direction; and an oscillation-reducing device (vibration-reducing device). The oscillation-reducing devices has a housing formed by or provided on the structure, a cavity, and a body configured for making impact contacts with the housing and disposed in the cavity in such a manner that the body is configured to make impact contacts with the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least on direction.

Abstract: A method is described for reducing contrails during operation of an aircraft (100, 100?) having a heat engine 10. The method includes inducing a condensation of moisture contained in the exhaust gas (A) of the heat engine by mixing at least a portion of the exhaust gas with ambient air (U) of the aircraft as well as separating the condensed-out water on the aircraft. Also described is an aircraft (100, 100?) having a heat engine (10). The aircraft includes at least one nozzle (30) which is adapted for conducting exhaust gas (A) from the heat engine of the aircraft at least partially into ambient air (U) of the aircraft and thus to produce a gas mixture, and at least one separator device (40) for separating condensed-out water from the gas mixture.

Abstract: An arrangement reduces oscillation of an oscillatory structure. The arrangement has: a structure having at least one mode in at least one direction; and an oscillation-reducing device. The oscillation-reducing device includes a housing on the structure; a cavity; and a body. The body is configured to make impact contact with a first surface portion and a second surface portion of an inner wall of the housing and disposed is in the cavity such that the body can make impact contact with the first surface portion and the second surface portion of the inner wall of the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least one direction. The first surface portion or the second surface portion of the inner wall of the housing has a curved profile.