Abstract: A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade (12) is situated, the guide blade (12) including at least one shroud configuration (21) having a radially outer shroud (16) and having a shroud holding device (23) with the aid of which the shroud (16) is secured on the housing, as well as including a turbine blade (18) extending radially inward from the shroud configuration (21). The shroud holding device (23) or parts thereof include(s) at least one air passage channel (28), which permits a flow passage through the shroud holding device (23). The invention also relates to a guide blade (12) for placement on a housing of a gas turbine as well as a method for manufacturing such a guide blade (12).

Abstract: A blade for a turbomachine, in particular a jet engine, including a shroud, having two opposite lateral edges, for delimiting a main flow channel and including a blade which extends away from the shroud, a rounded transition area being provided which encompasses the blade on its root side and is guided beyond the one lateral edge, a section of the transition area protruding beyond the one lateral edge being severed and situated in the area of the other lateral edge as an elevation offset in the transverse direction, a blade arrangement having at least two of such blades as well as a turbomachine having a plurality of such blades.

Abstract: A joining device for arranging a component on a component carrier is disclosed. The joining device includes an application system for positioning the component in the joining device and a receptacle for clamping the component carrier in the joining device. The component is arranged on the component carrier by an adapter. A method for arranging the component on the component carrier is also disclosed.

Abstract: Solder alloy based on nickel is composed of a mixture with a first soldering material, a second soldering material, and a base material, wherein the base material is a nickel-based material which corresponds to the material to be soldered and is present in a proportion of 45-70% by weight in the mixture, the first soldering material is a nickel-based material including chromium, cobalt, tantalum, aluminum and boron, and is present in a proportion of 15-30% by weight in the mixture, and the second soldering material is a nickel-based material including chromium, cobalt, molybdenum, tungsten, boron and hafnium, and is present in a proportion of 15-25% by weight in the mixture.

Abstract: Proposed is a method for controlling and regulating an internal combustion engine (1) having a common rail system and having a passive pressure limiting valve (11) for discharging fuel out of a rail (6) into the fuel tank (2), in which method, in a first stage, the pressure limiting valve (11) is set as open when the rail pressure, proceeding from a steady-state rail pressure, exceeds a first threshold value and subsequently falls below a second threshold value within a first critical time, wherein the first threshold value characterizes a higher pressure level than the steady-state rail pressure and the second threshold value characterizes a lower pressure level than the first threshold value, and in which method the opening duration of the opened pressure limiting valve (11) is monitored.

Abstract: The invention relates to a method for producing and repairing a part comprising at least two joined metal components, especially components of a gas turbine. In said method, corresponding joining surfaces of the components are joined together and connected by means of a pressure welding process, a machining allowance in the area of a joining zone of the two joining surfaces is upset during the joining process, and once the two components have been joined together, the machining allowance is machined by means of a precise electrochemical machining (PECM) process until a predefined final contour of the part has been obtained. The invention further relates to a gas turbine part obtained by means of the disclosed method.

Abstract: A method for removing a layer made of a first material from a surface of a body made of a second material is disclosed. The body is subjected to a pressurized jet containing a blasting medium composed of particles, where the pressurized jet at least intermittently has an Almen intensity of at most 0.35 Almen A, preferably at most 0.3 Almen A and particularly preferably at most 0.25 Almen A.

Abstract: The invention relates to an apparatus (10) for securing sealing elements (12, 14) in a recess (16), more particularly in an installation slot in a turbomachine, having at least one sealing support element (18) comprising at least one sealing element (12, 14). At least one fixing piece (20) is fitted between the sealing support element (18) and a clamping piece (22) associated with the sealing support element (18), and the fixing piece (20) is integrally joined to the sealing support element (18) and the clamping piece (22) by strut-like connections (24) that can be broken by the application of force. The invention also relates to a securing method and to a method for manufacturing the claimed apparatus (10).

Abstract: A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.

Abstract: A method for operating a driving system having an internal combustion engine and an exhaust gas purifying device through which exhaust gas from the internal combustion engine flows in order to be purified. The exhaust gas purifying device has at least one catalyst element for catalytic conversion of nitrogen monoxide into nitrogen dioxide at a determined conversion rate. In order to compensate for an agerelated decrease in the conversion rate of the catalyst element the nitrogen monoxide emission from the internal combustion engine and/or the exhaust gas temperature before the catalyst element are adjusted as a function of the current conversion rate and/or the age of the catalyst element so that the nitrogen dioxide concentration after the catalyst element is greater than or equal to a minimum concentration and/or that the molar ratio between nitrogen monoxide and nitrogen dioxide after the catalyst element corresponds to a predetermined ratio.

Abstract: The invention relates to a method for the open-loop control and the closed-loop control of an internal combustion engine (1), the rail pressure (pCR) being controlled in the normal operating state in a closed loop control mode via an intake throttle (4) on the lower pressure side as the first pressure control member in a rail pressure control loop and at the same time a rail pressure disturbance variable being applied to the rail pressure (pCR) via a pressure control valve (12) on the high pressure side as the second pressure control member. For this purpose, a pressure control valve volume flow (VDRV) is redirected from the rail (6) to a fuel tank (2) via the pressure control valve (12) on the high pressure side, and an emergency operation mode is activated once a defective rail pressure sensor (9) is detected, in which emergency operation the pressure control valve (12) on the high pressure side and the intake throttle (4) on the low pressure side are actuated depending on the same set point value.

Abstract: The invention relates to a method of nondestructive and contactless testing of components (3), wherein ultrasonic waves (6) are irradiated onto the surface of the component (3) at a predefinable, non-perpendicular angle of incidence (9) using an ultrasonic transmission sound transducer (1) arranged spaced apart from the surface of the component (3) and the intensity of the ultrasonic waves (7) reflected from the surface of the component (3) is detected with time resolution and/or frequency resolution by the antenna array elements (2n) of an ultrasonic antenna array (2) configured for detecting ultrasonic waves (7) and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves (7) directly reflected at the surface of the component (3).

Abstract: A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided.

Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.

Abstract: A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.

Abstract: A method for vibration damping of at least one blade of a turbomachine, wherein initially at least one damping element is arranged on the blade such that it can move in the axial direction, employs a damping element having a larger permeability constant than the blade (?rD>?rB), and then a magnetic field acting in the radial direction is generated at least temporarily during rotation of a rotor hub of the turbomachine in order to adjust the mass of the damping element in real time. A damping device includes, for example, a ferromagnetic damping element as well as a magnetic field source, and a turbomachine.

Abstract: In an exhaust gas turbocharger system for charging an engine including a compressor arrangement at a charging fluid side LL and a turbine arrangement at an exhaust gas side AG, a further compressor which is driven by a separate controllable drive and whose primary side is connected to the charging fluid side LL while its secondary side is connected to the exhaust gas side is provided for compressing charge air taken from the charging fluid side and supply it to the exhaust gas side for assisting driving the exhaust gas turbines so as to maintain them at relatively high speeds in transition periods including engine idling.

Abstract: A method for manufacturing a component having at least one element configured in the component, in particular at least one conduit, conduit unit, or supporting element configured within an aerodynamic rib, the component having an element leadthrough for leading through the at least one element, the method including the following step: building up in layers of the component including the element leadthrough, together with the at least one element in a generative production process.

Abstract: A method for repairing run-in coatings is provided. The method includes the steps of filling a damaged site of the run-in coating with a filling material having a material composition that corresponds to a material composition of the run-in coating or is comparable to the material composition of the run-in coating or having material properties that are comparable to material properties of the run-in coating; drying the filling material that has been filled into the damaged site; depositing a donor diffusion layer over an area of the damaged site and onto the dried filling material; and thermally treating the run-in coating at least in the area of the damaged site to locally diffuse at least one metallic element from the donor diffusion layer into the filling material.