Abstract: A composite material is formed of several assembled discs of matrix material, wherein each disc preferably has at least one groove therein, and at least one fiber (14) is inserted in each groove. A composite of matrix material and fibers (14) is present in an inner section (16), whereas exclusively the matrix material is present in an outer section (17). The inner section with the fibers (14) reaches to different radial extents toward the outer section (17), to achieve a strength-optimizing intermeshing of the inner section (16) with the outer section (17).

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: A joining method, in particular for gas turbine components, is provided wherein applying inductive heating, using at least one inductor, to a joining zone of a first component section and a second component section; following and/or during the step of applying inductive heating, exerting a press force on the first component second and the second component section to weld the first and second component section together, additionally heating by a capacitor discharge of the joining zone of the first and second component sections.

Abstract: A flow structure is for a gas turbine, e.g., for an aircraft engine, in a transition channel between two compressors or in a transition channel between two turbines or in a transition channel of a turbine outlet housing downstream from a low-pressure turbine, having support ribs positioned in the transition channel spaced apart from one another around the circumference of the transition channel. A channel wall which delimits the transition channel radially on the inside and/or a channel wall which delimits the transition channel radially on the outside may be drawn inwardly into the transition channel in the area of the outflow edges of the support ribs.

Abstract: An arrangement is provided for a non-hermetical seal between the stator and the rotor of a gas turbine. The arrangement comprises a brush seal which is arranged in a receiving chamber that is formed by at least one spacer or reinforcing element arranged between preferably two cover or guide elements. The brush seal is hub-centered via sliding elements, especially via sliding pads, said sliding elements being integrated into the spacer or reinforcing element.

Abstract: A method and a device for cutting freeform surfaces is disclosed. In 5-axis cutting, a workpiece is milled by a tool, i.e., a milling cutter, in such a way that a desired freeform surface is obtained. The tool is moved for cutting along at least one tool path, i.e., cutting path, defined on the basis of interpolation points in relation to the workpiece. According to this invention, a tool vector in the form of leading angles and setting angles is defined for each interpolation point on the tool path. For each interpolation point a normal vector is determined from the leading angles and the setting angles and also from a drive vector determined for each interpolation point. The normal vector in each interpolation point on the tool path is used for a 3D-radius correction for equalizing/compensating for deviations in dimensions of the milling cutter.

Abstract: A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another.

Abstract: A method and a device for locally removing coatings from components. An absorbent medium supplied with a coating removal liquid is brought into contact with one or more areas of a component from which a coating is to be removed.

Abstract: The present technology concerns one or more methods for joining of metal components especially components of a gas turbine, in which joining of the corresponding joining surfaces of the components occurs by means of an inductive low or high-frequency pressure welding and in which, before heating and joining of the components by means of inductive low or high-frequency pressure welding, sputter etching of the joining surfaces is carried out. The present technology also concerns a device for execution of an inductive low or high-frequency pressure welding method for joining the metal components, especially components of a gas turbine, with at least one induction generator and at least one inductor, as well as a component produced with the method according to the present technology.

Abstract: A method for producing a ceramic thermal barrier coating on a component part for use in compressor and turbine components by a vapor depositing process, and a ceramic thermal barrier coating, is disclosed. The method includes: a) provision of a ceramic vapor for depositing on the component part; b) depositing of the ceramic vapor on the component part to form a thermal barrier coating having a columnar structure, the columns being oriented substantially perpendicular to a surface of the component part; and c) varying of at least one method parameter during method step b) such that the resultant thermal barrier coating has columns of alternating decreasing and increasing diameters. The ceramic thermal barrier coating has a columnar structure and the columns are oriented substantially perpendicular to a surface of the corresponding part. The columns have alternately decreasing and increasing diameters.

Abstract: An apparatus and method for attaching a rotor blade to a rotor, particularly for a gas turbine, is disclosed. The rotor blade has a blade vane and a blade root, such that the blade vane can be attached to or anchored in the rotor by the blade root. The blade root is configured asymmetrically, such that the front region of the blade root as seen in the direction of rotation of the rotor blade is provided with more anchoring teeth than a rear region of the blade root as seen in the direction of rotation of the rotor blade.

Abstract: A gas turbine, particularly an aircraft engine includes at least one compressor. The gas turbine comprises at least one stator, at least one rotor and at least one generator (19) for generating electrical energy. An engine rotor has a rotor shaft (11) and rotor disks (12, 13, 14), which are driven by the rotor shaft (11) and which have rotating rotor blades (15). A stator has a housing (17) and fixed guide vanes (18). A generator (19) has at least one stator (21) and at least one rotor (20). The electrical energy generated by the generator (19) preferably serves to operate at least one attachment or one auxiliary unit of the gas turbine. According to the invention, the generator (19) is integrated in the interior of the gas turbine in such a manner that each rotor (20) of the generator is allocated to the compressor rotor and the stator (21) of the generator is allocated to the compressor stator, whereby kinetic energy of the rotor is convertible into electrical energy by the generator (19).

Abstract: A component having a platinum-aluminum substrate surface region which is formed in the area of the substrate surface of the component by diffusion of platinum and aluminum into the substrate surface and which contains platinum and aluminum as well as the constituents of the substrate composition. The integrated aluminum content and/or the integrated platinum content in the substrate area is less than 18 wt %.

Abstract: A method for producing metallic components, and metallic components produced by the method, particularly for turbo machines, having small edge radii, is disclosed. The method includes mechanical and/or electrochemical machining of a component while producing a small edge radius and solidifying the small edge radius by ultrasonic shot peening. As a result of the method, the disadvantages of the prior art are avoided and a machine process that can be automated has been provided, the method permitting considerable savings of time and labor and leading to reproducible results.

Abstract: A brush seal for sealing off components movable relative to one another with respect to a pressure difference is disclosed. The brush seal having bristles which are arranged in a bristle housing which consists of two housing halves having free ends of legs which project into the area of the ends of the bristles, which legs carry mutually facing supporting surfaces for the bristles.

Abstract: A method is provided for producing a sealing segment for use in compressor and turbine components, by powder injection molding, the method comprising the following steps: a) preparing a first homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binding agent; b) producing a first molded article by injection molding the first mixture; c) preparing a second homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binding agent, the second mixture being selected to exhibit a lower abrasion resistance than the first mixture following a subsequent joint sintering process; d) producing a second molded article as a rub strip by injection molding the second mixture; and e) joining the first and second molded articles to produce the sealing segment.

Abstract: A honeycomb seal which is manufactured by powder metallurgical injection molding is disclosed. The honeycomb seal is composed preferably of several segments. Each segment is embodied as a single piece and has a base element as well as honeycomb elements that are embodied as a single piece with the base element.

Abstract: A jet engine includes a fan arranged upstream of a core engine having a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure turbine. The high pressure turbine is drive-connected to the high pressure compressor. The low pressure turbine is drive-connected through a transmission to the low pressure compressor and to the fan, which are respectively driven in opposite rotation directions. A compressor disk of the low pressure compressor is positioned downstream directly after the fan so that a hub end section of the fan and the compressor disk together form a counter-rotating compressor stage.

Abstract: A method for machining components of a gas turbine, in particular for machining turbine blades, is described. The method includes the following steps: a) providing at least one component carrier having at least one component receptacle for detachable accommodation and fastening component to be machined, the component receptacle being designed with a contour similar to at least one contour of subarea of component to be accommodated; b) introducing at least one subarea of the component into component receptacle and form-fitting and/or substance-to-substance bonding of the subarea of the component to component receptacle; c) machining the component, which is attached to the component carrier; and d) releasing the machined component from the component carrier.

Abstract: A rotor of a turbine machine having several rotor blade rings positioned in succession in the axial direction, is disclosed. Each rotor blade ring has a rotor base body with several rotor blades anchored by blade footings in axial grooves of the rotor base body that extend essentially in the axial direction and, in their anchored position in the rotor base body, are secured against displacement in the axial direction. The rotor blades of at least one rotor blade ring have hook-like securing elements, which, in the anchored position on a low-pressure side of the rotor blade ring, abut the rotor base body. The hook-like securing elements, between the rotor base body and a sealing element, which extends between the rotor base body and a rotor base body of a rotor blade ring that connects on the low-pressure side, are fixed in the axial direction on both sides.