Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.

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: 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 process for manufacturing a honeycomb seal is disclosed. The process includes the following steps: a) the honeycomb structure is brought to the desired three-dimensional form and is fixed in this form; b) then the honeycomb structure is filled with a filler material; c) then the honeycomb structure filled with the filler material is machined on a side on which a carrier element is arranged, such that this side has the desired contour and that the end edges of the honeycomb structure are sealed flushly with the filler compound; d) then the side contoured in this way is coated with a coating; e) next the carrier element is applied to the coating, preferably by laser powder build-up welding.

Abstract: A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension.

Abstract: A method for machining workpieces provides a machining electrode, which is guided at a specific distance to the workpiece. An electrolyte is provided between the workpiece and the machining electrode, through which an operating current flows between the machining electrode and the workpiece. The operating current results from an operating voltage (UA), which is produced at the machining electrode, the workpiece being connected to ground. To perform the machining procedure, the distance between the machining electrode and the workpiece is regulated and the operating voltage (UA) is determined in such a way that the resulting operating current is a DC current or a pulsed DC current—i.e., the operating voltage is a DC voltage of fixed or specific dimension. A measuring voltage (UM) is superimposed on the operating voltage (UA) for producing the operating current.

Abstract: A plunge milling method includes: a) the area of material that is to be removed is enclosed by a plurality of milling paths, each milling path defining end positions of a milling head during the formation of plunge milling bores; b) to each milling path there is allocated a guide curve for the tool axis, each guide curve defining initial positions of the milling head during the formation of plunge milling bores; c) during the formation of plunge milling bores, the tool axis is oriented, as a function of a milling path and the respective guide curve, so that there is no danger of collision of the milling tool with a contour formed by plunge milling; d) for each milling path, bore axes for plunge milling bores are determined as a function of the respective guide curve, corresponding to a prespecified overlap of milling bores formed along the milling paths.

Abstract: Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24?), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24?) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).

Abstract: A device and a method are disclosed for visualizing positions on a surface by means of a marking which is produced by an optically detectable radiation. In order to permit a residue-free marking which can be observed with a camera from partly extremely oblique observation directions, the device has an optical waveguide, which is coupled to a radiation source and whose light output region can be located at a desired position of the surface in order to emit optically detectable radiation at the desired position of the surface through the optical waveguide. As a result, the radiation is emitted at the desired position of the surface in various spatial directions.

Abstract: A method for hardfacing a metal component surface (14, 16), especially a shroud surface of a turbine blade made of a TiAl alloy, with at least one metal material (18, 20), in particular a Co—Cr alloy. The hardfacing coating is produced separately from the component surface and is then joined to the component surface in a high-temperature soldering process. A turbine blade including such a hardfacing coating, primarily in a shroud region (2).

Abstract: A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area.

Abstract: A method for manufacturing a component, in particular a component of a turbine or a compressor, in which at least these steps are carried out: application in layers of at least one powdered component material to a component platform in the area of a buildup and joining zone; melting and/or sintering locally in layers of the component material by supplying energy with the aid of at least one electron beam in the area of the buildup and joining zone; lowering of the component platform in layers by a predefined layer thickness; and repeating steps a) through c) until completion of the component. During the manufacturing, electrons emitted due to the interaction of the electron beam with the component material are detected, after which material information, characterizing the topography of the melted and/or sintered component material, is ascertained on the basis of the emitted electrons.

Abstract: A gas turbine having a rotor which includes a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one rotor disk and a rotor cone leading from the or a rotor disk to the shaft, the downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, the interior space of the shaft being designed as a flow channel for bearing-chamber sealing air, and the space surrounding the rotor cone upstream of the same being designed as a flow space for cooling air is disclosed. In the region of the rotor connection, the shaft exhibits an expanded portion, at whose upstream end, openings are provided to allow cooling air to enter, and, at whose downstream end, openings are provided to allow cooling air to exit into the space between the bearing chamber and the rotor cone, a wall separating the streams of the cooling air and of the sealing air in the shaft interior from one another.

Abstract: A turbo compressor in an axial type of construction is disclosed. The turbo compressor has a bladed stator and a bladed rotor, and has a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside.

Abstract: A method and apparatus for the fabrication and/or repair of an integrally bladed rotor, specifically of an integrally bladed gas turbine rotor, is disclosed. At least one rotor blade is joined to a main rotor body for fabrication and/or repair. The joining is carried out by diffusion welding.

Abstract: The invention relates to a process and an apparatus for automatic laser focusing. The core concept of the process is the automatable and especially preferably the automated photographing of the focal spot generated during a focus series by camera and a determination of the particular focal spot diameter as well as an evaluation of this data by an interpolated or approximating function that allows a conclusion about the focal spot with the smallest focal spot diameter and thus with the associated optimal focal distance. A series of disadvantages present in the state of the art can be avoided by using the process in accordance with the invention, in particular the great expenditure of time in the determining of the optimal focal distance and the uncertainty in the selection of the optimal focal spot associated with an operator are eliminated in the framework of the photographing of a focus series.

Abstract: A turbine engine is disclosed. A blade ring is surrounded by a housing wall, the housing wall being configured as an outer ring, and delimits therewith a gap, the gap being adjustable by deformation of the outer ring. The outer ring is concentrically surrounded by an adjusting element, opposite faces of the outer ring and the adjusting element having the contour of a truncated cone, and rolling bodies being positioned between the outer ring and the adjusting element, the rolling bodies being put at an oblique angle in relation to the axial direction in the radial direction and in the peripheral direction, making it possible for the adjusting element to be rotated in relation to the outer ring while simultaneously adjusting the gap.

Abstract: A brush seal and a method for mounting a brush seal is disclosed. The brush seal includes a sealing element provided with a plurality of filaments or wires that are joined at a filament or wire end to form a filament or wire bundle and a clamp-like sealing housing for receiving and fixing the filament or wire end between a first and a second limb and for fixing the brush seal in a mounting recess of a housing. A free end of the filament or wire bundle of the sealing element is clamped between a partial area of an inner contour of the second limb that is adjacent to a region of an outlet opening of the mounting recess of the housing and an area of the outlet opening that is opposite from the partial area.

Abstract: A device for detecting a shaft rupture in a rotor of a turbine, in particular a medium-pressure turbine, of a gas turbine, in particular of an aircraft engine, at least one stator-side sensor element being positioned downstream from the turbine, in particular in the area of a stator-side blade ring of another turbine, in particular a low-pressure turbine, and, in case of a shaft rupture of the rotor of the turbine, a radially externally situated segment of a last (seen in the direction of flow) rotor-side blade ring of the turbine working together with the, or with each, sensor element to generate an electrical signal corresponding to the shaft rupture.

Abstract: A method for processing a surface of a component, in particular in the aviation sector, including the following steps: spraying the component with a first powder and coating the component with a second powder, the first powder having the same chemical composition as the second powder.