Abstract: An apparatus for surface blasting gas turbine blades in the area of their blade roots includes a vibrator with an oscillating surface oriented so that the oscillating surface extends essentially in the horizontal direction. A processing chamber for receiving the blade root adjoins the oscillating surface. The processing chamber is embodied such that the turbine blade is orientable, during the blasting, with a profiled support surface of the blade root extending at least temporarily essentially parallel to the oscillating surface of the vibrator.

Abstract: An electrode (10) is provided for electrochemical reduction of a workpiece (20) that is to be treated. The electrode (10) has a predefined contour and contains an electrically conductive material. The electrically conductive material of the predefined contour forms an electrode core (12). The outside of the electrode core (12) is covered with an insulation layer (13). The insulation layer (13) is porous and is made of an electrically non-conductive material.

Abstract: The invention relates to a method for coating or decoating a component, in particular a gas turbine component, wherein, in order to regionally or partially coat or decoat a component, the component is preferably completely covered with a covering medium, and wherein the covering medium is removed from only those surface regions of the component in which the coating or decoating of the component is supposed to take place, so that a surface region of the component which is not to be coated or decoated is covered by the covering medium. According to the invention, the covering medium is removed by means of water jet machining.

Abstract: The invention relates to a method for the production of aero-dynamic structures during the production of integrally bladed gas turbine rotors. Aerodynamic structures of an integrally bladed gas turbine rotor are produced on a rotor disk base body, whereon the end contours are precise, by removing material according to an electrochemical removal process, i.e. by means of an electrochemical machining (ECM)-process. The method comprises the following steps: a) preparing a rotor disk base body which is made of a material which is difficult to machine; b) removing the material which is between the blade wings until a specific dimension is obtained, according to a removal process; c) preparing at least one working electrode in order to finish at least one aerodynamic structure of an integrally bladed gas turbine rotor.

Abstract: The invention relates to a peening chamber for surface peening, in particular for ultrasonic shot peening of gas turbine components (10), which, at least with a component region (20) comprising the surface to be treated, are to be arranged within a chamber wall (12), which spatially defines the peening chamber, wherein at least one wall region (26, 36, 48) of the chamber wall (12) is designed to be adjustable in order to vary the geometry of the peening chamber.

Abstract: A blade of a turbomachine, in particular of a gas turbine, is disclosed. The blade includes at least one fastening section for fastening the same in a locating section of a rotor-side or stator-side component of the turbomachine. The, or each, fastening section has a core region which is made of a relatively brittle and relatively light material and is embedded in an encasing region made of a material having relatively high ductility.

Abstract: A device (10) for suspending gas channel elements, in particular for suspending guide blades or guide blade segments or gas channel segments, on a housing of a gas turbines is provided. The device comprises first plate-shaped elements (11, 12, 13, 14) and second plate-shaped elements (15, 16, 17), whereby the first plate-shaped elements (11, 12, 13, 14) and the second plate-shaped elements (15, 16, 17) are connected together by web-like elements (18) which extend in an essentially perpendicular manner in relation to the first and second elements and form a meandering or crenelated profile.

Abstract: A running-in coating for gas turbines and a method for production of a running-in coating are provided. The running-in coating serves to seal a radial gap between a housing (11) of the gas turbine and the rotating blades (10) themselves, whereby the running-in coating (13) is applied to the housing. The running-in coating is made from a CoNiCrAIY-hBN material. The CoNiCrAIY-hBN material can be applied by thermal spraying, in particular plasma spraying.

Abstract: A process for electrochemical stripping of components is disclosed. An operating point of the electrochemical stripping is determined under actual process conditions prior to the actual electrochemical stripping and is determined anew continuously, i.e., monitored and optionally adjusted during the electrochemical stripping.

Abstract: A method for the selective removal of one or more layers from a power unit component, e.g., a turbine blade of a heavy-duty turbine, using high-energy radiation of such a wavelength that the supplied energy is so strongly absorbed by the layer to be removed in each case that the removal threshold of the specific material of the layer to be removed is exceeded, while this removal threshold is not reached in the subsurface to be preserved, a spectrometer connected to a control unit via a light-conducting fiber cable such that the method-specific characteristic values are determinable by spectroscopic methods during the removal of the respective layer and are used for the self-regulating process limitation.

Abstract: A brush seal for sealing a rotor with respect to a stator includes a bristle housing which is held on the stator or rotor, a cover plate, a supporting plate, a circumferential surface and two side surfaces and in which bristles oriented with their free ends to the rotor or stator are fastened. The bristle housing, for ensuring correct, anti-rotation installation in its seat, includes a first positioning arrangement on at least one side surface or the circumferential surface, the first positioning arrangement interacting in a positive-locking manner with a correspondingly configured second positioning arrangement on the stator or rotor or a separate fastening element for the definite positioning of the bristle housing.

Abstract: A heat-insulating layer system for a metallic structural component, especially for a structural component of a gas turbine such as an aircraft engine, includes an adhesion promoting layer (12), an inner contact layer (14), and an outer cover layer (15) , whereby the adhesion promoting layer (12). is disposed on a surface (11) of the gas turbine structural component (10). The inner contact layer (14) is formed of a zirconium oxide partially stabilized with yttrium or yttrium oxide, and the outer cover layer (15) is formed of a material that consists of at least one component with at least one phase, which stoichiometrically comprises 1 to 80 Mol-% Mx2O3, 0.5 to 80 Mol-% MyO and Al2O3 as a remainder with incidental impurities, wherein Mx is selected from the elements chromium and barium or mixtures thereof, and wherein My is selected from the alkaline earth metals, the transition metals and the rare earths or mixtures thereof.

Abstract: A seal arrangement for a turbo-engine, for sealing a peripheral gap between a rotor and a stator is provided. The stator a seal holder provided with at least one groove for respectively receiving a segmented, dynamic seal. Segments of the dynamic seal are made up of a plurality of brush seal segments, and free ends of bristles of the brush seal segments extend in the radial direction project from the respective groove and lie on the rotor. The or every groove for receiving the brush-type seal segments is designed without an undercut, the brush-type seal segments being received in the respective groove without an undercut in a positive manner.

Abstract: A method for determination of strain distribution in components, in particular in gas turbine components, is disclosed. In an embodiment, the method includes: a) vibrational excitation of the component and measured recording of a vibrational amplitude distribution of the component for a number of measured points by means of a vibrometer, each measuring point being determined by three coordinates and the measured vibrational amplitude distribution of each measuring point being a vectorial parameter; b) smoothing of the vibrational amplitude distribution recorded by measurement for each measuring point; c) definition of polygonal elements, wherein each measuring point forms a corner of at least one element; d) calculation of a tensor strain condition for each of the polygonal elements from the tensor vibrational amplitude distributions present in the corners of the elements; and e) calculation of the strain distribution in the corners of the elements from the strain conditions of the elements.

Abstract: A device and method for axially displacing at least one turbine rotor relative to at least one corresponding turbine stator in a multistage axial turbine is disclosed. The turbine shaft is provided with a split design and has a first axially displaceable shaft half, which is connected via a turbine disc to the turbine rotor and via a torque coupling to the second shaft half. By axially displacing the turbine rotor relative to the turbine stator and by controlling this axial displacement, the operation of the turbine is held in its possible optimum of efficiency.

Abstract: A method for generating process chains for product manufacturing is provided. Accordance to this method, all available data pertaining to the component to be manufactured is collected and the component to be manufactured is subdivided into component elements which can be manufactured independently of one another. The method further includes collecting all possible core technologies for the individual process blocks, where the core technologies are generating all possible manufacturing process chains by combining all core technologies of one process block with the core technologies of the other process blocks, and reducing all possible manufacturing process chains to a subset of possible manufacturing process chains. This reduction is based upon geometric and/or technological boundary conditions. The method includes ascertains data pertaining to per-unit costs for the component to be manufactured, .

Abstract: A lubricant system is disclosed, in particular for the supply of lubricant to a user in a gas turbine aircraft engine. The system includes a lubricant reservoir, where in the lubricant reservoir a lubricant can be set in rotation by at least one rotatable drum that is integrated into the lubricant reservoir or by at least one rotatable blade that is integrated into the lubricant reservoir, such that the lubricant, as a result of centrifugal force, comes into contact against a rotationally symmetrical wall of the lubricant reservoir, and from there can be transported toward a user. A drive system is included for the or each rotatable drum or the or each rotatable blade of the lubricant reservoir. At least one rotating lubricant separator is provided for the venting of the lubricant. The or each lubricant separator can be driven by the drive system of the or of each rotatable drum and/or of the or of each rotatable blade of the lubricant reservoir.

Abstract: A refractory, oxidation-resistant, and corrosion-resistant protective coating for application to a substrate, in particular for application to parts of turbines or aircraft propulsion engines, is described, including a spray coating made of a thermally sprayed, primarily metallic material, the coating being at least partially subjected to a thermochemical aluminum (Cr, Si) deposition process having a specifically high aluminum deposition activity after the application of the protective coating to the substrate, in such a way that the protective coating has alloy gradients of Al (Cr, Si) which increase from the substrate surface to the coating surface and isolated globulitic metal oxide particles. Furthermore, a method for manufacturing this protective coating and its use are described.

Abstract: A device for effecting heat transfer to rotating equipment, in particular gas turbines, is provided. A gas turbine (10) comprises a first rotating unit (11), i.e. an internal shaft and a second fixed unit (16), i.e. a housing. A third rotating unit (14, 17), i.e. rotor blades and plates connected to the rotor blades are disposed between the first unit (11) and the second unit (16). The first (11) and third (14, 17) units are rotatable around a common axis (12) and with respect to each other. At least one device (21) for improving heat transfer by convection is assigned to the first rotating unit (11), i.e. the internal shaft.

Abstract: A gas turbine rotor and a method for manufacturing a gas turbine rotor having integral blading, is disclosed. A rotor blade has a blade pan and a blade footing connected to the blade pan. The blade footing is designed with a V-shaped cross section in at least some portions and the blade footing is welded to a rotor mount by capacitor discharge welding.