Abstract: The invention relates to a method for optically detecting surfaces wherein strip patterns are projected onto the surface, images are captured, and the three-dimensional contour thereof is determined from the reproduction of the strip pattern on the surface of the object. The aim of the invention is to prevent reflections that interfere with the images and as a result, the surface of the object is covered with a layer of a fluorescent material, is then radiated with ultraviolet radiation, and the radiation emitted by the fluorescent material in the visible light is detected.

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 joining element, for example, an adapter, for connecting a rotor blade to a rotor disc or a rotor ring, or a rotor blade per se of an aircraft engine is disclosed. The joining element has a base body and a joining surface, with the joining surface formed by a fusion weldable coating made of a compressed powder that is connected in a positive fit to a contour of the base body. A method for the production of such a joining element, as well as an integrally bladed rotor, is also disclosed.

Abstract: A method and apparatus for surface hardening a component, particularly an aircraft construction component, is disclosed. A force is applied to the surface of the component, which is made of an intermetallic compound at least in the region of the surface to be hardened. The component is heated at least in the region that is made of the intermetallic compound to a temperature higher than the standard temperature. The temperature is set such that a ductility of the intermetallic compound at the temperature is increased compared to a ductility of the intermetallic compound at the standard temperature. The apparatus includes a hardening tool and a heating device where the component is heated to a temperature higher than the standard temperature and the temperature is set such that a ductility of the intermetallic compound at the temperature is increased compared to a ductility of the intermetallic compound at the standard temperature.

Abstract: A method for welding two components is disclosed. In an embodiment, the method includes the following process steps. The two components are positioned such that the joining surfaces are opposite each other, at a short distance from each other. A high-frequency electrical current is conducted through the two components, heating the components at least in the region of the joining surfaces. The two components are pressed against each other such that the two joining surfaces are welded together.

Abstract: A method for joining at least two components by inductive high-frequency pressure welding is disclosed. The first component has a first material structure with a first hardness and the second component has a second material structure with a second hardness which is smaller than the first hardness. Both components are inductively heated in the region of the joining surfaces and are subsequently pressed together by a compressive force. The joining surface of the first component with the first hardness, which is greater than the second hardness of the second component, is pre-contoured in a spherical, conical or convex manner prior to joining the two components.

Abstract: A gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade and a vane footing. The blade is defined by a flow inlet edge or a front edge, a flow outlet edge or a rear edge, and a blade surface extending between the front edge and the rear edge and forming a suction side and a pressure side. The suction side of the blade includes at least one microprofiled or microstructured region for optimizing the flow around the blade.

Abstract: The invention relates to a method for optically detecting surfaces wherein strip patterns are projected onto the surface, images are captured, and the three-dimensional contour thereof is determined from the reproduction of the strip pattern on the surface of the object. The aim of the invention is to prevent reflections that interfere with the images and as a result, the surface of the object is covered with a layer of a fluorescent material, is then radiated with ultraviolet radiation, and the radiation emitted by the fluorescent material in the visible light is detected.

Abstract: The invention relates to a method for joining two components (10, 12) made of a metal material, which are connected on two mutually associated joining surfaces (14, 16) by means of a joined connection, wherein at least one of the components (10) is strengthened in at least a partial region of the joining surface (14) thereof prior to joining. The invention further relates to a joined connection of two components (10, 12) made of a metal material.

Abstract: A process for producing a join between a first component and a second component is disclosed. The second component contains a single-crystal or directionally solidified material. A polycrystalline layer is produced on a joining surface of the second component for joining the second component to the first component. The joining surface of the second component is joined to the first component by friction welding.

Abstract: A method for producing a blisk (bladed disk) or a bling (bladed ring) of a gas turbine is disclosed. The method includes the following steps: a) producing a turbine blade by joining a blade to an adapter element consisting of a metal material that is suitable for fusion welding, the adapter element being used to form a blade root of the turbine blade, and b) joining the turbine blade to a rotor disk consisting of a metal material that is suitable for fusion welding or to a rotor ring consisting of a metal material that is suitable for fusion welding in such a manner that the turbine blade is arranged on the outer periphery of the rotor disk or of the rotor ring. A component of a gas turbine or of a high-pressure or low-pressure compressor, especially a blisk or bling, and a turbine blade are also disclosed.

Abstract: Two structural components, such as a gas turbine rotor hub and a rotor blade, are integrally joined to each other by friction welding, particularly linear friction welding. For this purpose, each component is provided with a joining surface and at least one of the two components is provided with a groove next to the respective joining surface. The groove extends fully or partly around the respective joining surface and serves for reducing stress in a normal and radial direction of the respective joining surface, whereby a more uniform heating of the joining zone is achieved and joining faults are avoided or at least reduced during the friction welding.

Abstract: A method and a device are for testing the detectability of at least one flaw in a component, or for evaluating ultrasonic signals of the flaw. The method provides for an electronic specification of the flaw to be generated, which includes a two-dimensional or three-dimensional point pattern. This specification predefines the number, position, shape, orientation, and dimensions of flaws to be deliberately generated. A test specimen is produced, where for each point of the point pattern, a microcrack is generated at the position of this point. An ultrasonic image of the test specimen is recorded and evaluated. The test specimen may be made out of a material transparent to visible light, e.g., crown glass, optical glass, borosilicate glass, or quartz glass. The microcracks may be produced, using internal laser engraving.

Abstract: A method and apparatus for surface hardening parts is disclosed. To harden a surface of a part, a relative movement, or advancing motion, is established between the part and at least one sonotrode-like tool which is excited in the ultrasonic frequency range. The tool is aligned during the surface hardening in such a way to the surface of the part to be hardened that a tool axis running in the effective direction of the tool runs at an angle to the surface of the part to be hardened.

Abstract: An induction coil for inductive heating of at least one metallic component having at least one lateral face and at least one face to be heated is provided. The induction coil includes a meandering pattern section shaped around the at least one component in such a way that the section extends over at least a partial area of the at least one lateral face of the at least one component to be heated in the area of the at least one face to be heated. A device and method for inductive heating of at least one metallic component are also provided.

Abstract: A method for joining components, in particular for joining a rotor blade to a rotor base body in the manufacture and/or repair of an integrally bladed gas turbine rotor, is disclosed. The method includes the following steps: a) providing two components that are to be connected, i.e., joined together; b) providing a joining part; c) aligning the two components and the joining part that are to be joined together such that the joining part is arranged as an insert between the two components that are to be joined together; d) connecting the two components with the intermediate arrangement of the joining part by moving the joining part with respect to the two stationary components that are to be joined together and in particular by exerting a compression force on the joining zones between the two stationary components and the joining part via the two stationary components.

Abstract: A method for joining components is described, in particular, for joining a rotor blade to a rotor base member when manufacturing and/or repairing an integrally bladed gas turbine rotor. The method includes the following steps: providing two components to be assembled, respectively joined to one another; providing a joining part; mutually aligning the two components to be assembled and the joining part such that the joining part is positioned as an insert between the two components to be assembled; driving the two components being assembled with the joining part being interposed therebetween in that the joining part to execute a linear, reciprocating motion in opposition to the two stationary components to be assembled in order to generate the frictional motion, further comprising exerting an upsetting force via the joining part on the joint zones between the two stationary components and the joining part, namely in a direction that extends essentially perpendicularly to the frictional motion.

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: 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 and a device are for testing the detectability of at least one flaw in a component, or for evaluating ultrasonic signals of the flaw. The method provides for an electronic specification of the flaw to be generated, which includes a two-dimensional or three-dimensional point pattern. This specification predefines the number, position, shape, orientation, and dimensions of flaws to be deliberately generated. A test specimen is produced, where for each point of the point pattern, a microcrack is generated at the position of this point. An ultrasonic image of the test specimen is recorded and evaluated. The test specimen may be made out of a material transparent to visible light, e.g., crown glass, optical glass, borosilicate glass, or quartz glass. The microcracks may be produced, using internal laser engraving.