Abstract: A method for producing a high-pressure turbine rotor, as well as a turbine rotor, is disclosed. The turbine rotor is designed as a blisk (i.e., bladed disk) and forms a radially inward disk and several vanes or blades that project from the disk. The turbine rotor has an internal duct system for air cooling and at least one section of the turbine rotor is manufactured in a generative production process.

Abstract: The invention relates to a method for repairing components that consist of superalloys, in particular for repairing components that consist of a superalloy with an aligned microstructure in such a way that the repaired site likewise has an aligned microstructure. The method comprises the following steps: a solder material is applied to the repair site; the repair site with the applied solder material is heated until the latter melts; and the melted solder material is left to solidify. The solder material is an alloy with the same alloy components as the component alloy. At least the fraction of one alloy component in the solder material composition is modified in relation to the fraction of that alloy component in the component alloy composition, in such a way that the melting temperature of the solder material is reduced in relation to the melting temperature of the component alloy.

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 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 method for the production of a run-in coating is provided, whereby a metallic run-in coating material is provided on a component on the stator side of a turbomachine, especially a gas turbine. According to an embodiment of the invention, the provided run-in coating undergoes a heat treatment for purposes of improving its run-in characteristics.

Abstract: A method for the repair of a component by a solder is disclosed. The method is performed under specifically selected vacuum conditions in order to prevent oxidation and vaporization.

Abstract: A process and apparatus for the manufacture of adapted, fluidic surfaces on a gas turbine blade is disclosed. In an embodiment, the process includes: (a) generating a nominal milling program for the manufacture of fluidic surfaces in the region of one flow inlet edge and/or one flow outlet edge for an ideal gas turbine blade; (b) measuring the area of an actual gas turbine blade in the region of one flow inlet edge and/or one flow outlet edge thereof; (c) generating a milling program adapted to the actual gas turbine blade, where measured values determined in step (b) are used to adapt the nominal milling program generated in step (a) to the milling program for the actual gas turbine blade; and (d) manufacturing of the fluidic surfaces on the actual gas turbine blades by milling with the use of the milling program generated in step (c).

Abstract: An electric centrifugal pump for conveying a fluid, in particular for conveying fuel to an aircraft engine, is disclosed. The pump includes a housing in which a rotor shaft is rotationally mounted and an impeller for conveying the fuel which is arranged on the rotor shaft. A motor arrangement is provided for driving the rotor shaft in a rotary manner around a rotor axis. The impeller includes at least one rotor, and at least one stator is arranged in the housing in a plane-parallel manner adjacent to the rotor such that the rotor and the stator form the motor arrangement.

Abstract: A probe for a capacitive sensor device, and a gap measuring system using the probe, is disclosed. The probe has a probe head including a measuring element with at least one measuring and front face, a first electrically non-conductive isolator element, and a first partial element of a first shield. The measuring and front face, the first isolator element, and the first partial element of the first shield are adhesively connected to one another and configured as a multilayer, where the first isolator element is disposed between the measuring element with its measuring and front face and the first partial element.

Abstract: A method for repairing a sealing segment of a gas turbine is provided. The sealing segment includes a radially outer holding portion for a radially inner abradable portion. The method includes the steps of providing a sealing segment to be repaired; removing a damaged, radially inner abradable portion of the sealing segment along a circumferentially extending parting plane, such that the abradable portion is completely removed from the holding portion; making a replacement part for the separated abradable portion of the sealing segment; and joining the replacement part to the holding portion of the sealing segment.

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 circulation structure for a turbo compressor, in particular for a compressor of a gas turbine, is disclosed. The circulation structure includes at least one annular chamber that can be traversed in a circumferential direction, is concentric with a shaft of the turbo compressor in the region of the free blade ends of a blade ring, and radially borders a main flow channel. Several chambers that can be traversed in an axial direction are situated upstream of the or each annular chamber, when viewed from the main flow direction of the main flow channel.

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. The filament or wire end is arranged in a mounting recess of a housing. A free end of the filament or wire bundle protrudes from the housing and is opposite from the filament or wire end. At least one projection is formed on an inner contour of the mounting recess in such a manner that the filament or wire bundle is clamped by the projection at a predefined distance from the filament or wire end.

Abstract: A device is for adjusting guide blades of a gas turbine. The guide blades are each connected to an adjusting ring via an adjusting lever, so as to be able to swivel, a first end of the, or each, adjusting lever engaging with the adjusting ring, and a second end of the, or each, adjusting lever, opposite to the first end, engaging with an end of a shaft or shank of the respective guide blade. The adjusting ring is assigned a rotor of a torque motor, a stator of the torque motor concentrically surrounding the rotor of the torque motor.

Abstract: An apparatus and method for machining of components, namely for rotary machining of rotationally symmetrical components on radially interior machining surfaces of a component, is disclosed. The device has a drill rod extending essentially axially and has a tool mount extending essentially radially, carrying a lathe tool. The drill rod has a projection that extends essentially radially and can be coupled to the tool mount that extends essentially radially, where the radial dimensions of the projection of the drill rod and of the tool mount are adapted to the dimensions of a hub bore of the component to be machined, such that the drill rod and the tool mount in the uncoupled state can be inserted into the hub bore, and, in the coupled state, the lathe tool mounted in the tool mount can be brought into contact with the radially interior machining surfaces of the component.

Abstract: A method for producing a cast part from metal, a metal alloy or from plastic, with at least one complex internal structure, in particular with at least one hollow space, by at least one casting mold, is disclosed. The method includes the following steps: a) providing at least one core element, wherein the core element peripherally reproduces the complex internal structure and has a metallic layer on its outer periphery; b) forming a first casting mold or negative mold for producing a positive mold reproducing the cast part, with one or more cast-in core elements; c) casting an enclosure around the positive mold to form a second casting mold or negative mold of the cast part and removing the positive mold; d) filling the casting mold or negative mold with casting material and cooling the casting material down; and e) removing the enclosure and removal of the cast part.

Abstract: The present technology relates to the problem that during diverse machining steps of application to the production or reconditioning of internally cooled gas turbine blades, an undesired effect may be had on sections of the gas turbine blades and proposes, as an improvement, to inject the cavity of the gas turbine blades before the machining steps with a plastic material which can be removed without trace, such as polystyrene, which can be subsequently removed again, in particular by heat.

Abstract: A method for remelting metallic surfaces of components using the effect of a stable high pressure plasma jet, includes melting the surface in localized areas, the surface having a structure refinement after solidification. The plasma jet action is generated by the microwave impact on a carrier gas, the pressure of the high pressure plasma jet being above the atmospheric pressure. In addition, a plasma torch for generating a directed high pressure plasma jet includes a gas supply, a device for generating a plasma, and an outlet nozzle for a plasma jet. The device for generating the plasma includes a magnetron and a resonator in which the supplied pressurized carrier gas is transferred into a plasma under the effect of microwaves, causing the plasma to exit through the outlet nozzle at a pressure above 0.1 MPa.

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: In a milling method for producing a structural component from a raw material by chip-cutting, a milling tool is moved along at least one defined tool path for the milling. In addition to the at least one tool path, at least one collision contour is also defined. The position or orientation of the milling tool relative to the collision contour(s) is monitored. The position or orientation of the milling tool is changed and/or an error message is generated if at least one of the collision contours is damaged, i.e. intersected, by the milling tool.