Abstract: A threaded spindle module includes a threaded spindle which extends along a longitudinal axis and has an external thread at an output-side end and, offset with respect to the external thread, a drive-side end with a peg for rotationally fixed coupling to an actuator interface, and with a threaded nut which is screwed onto the external thread, and a joint-like curved support point of the threaded nut is provided as a pivot joint of the threaded spindle module, with a pivot joint center relative to an associated receiver.

Abstract: In a method for the generative production of a component (3), in particular of a turbo-engine component, wherein material (4) is bonded layer-by-layer selectively to a layer disposed therebeneath or to a substrate (6), according to the invention a laser (1A; 1B; 2) additionally acts on the material (4) before, during and/or after the bonding.

Abstract: The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit.

Abstract: Selective laser solidification apparatus is described that includes a powder bed onto which a powder layer can be deposited and a gas flow unit for passing a flow of gas over the powder bed along a predefined gas flow direction. A laser scanning unit is provided for scanning a laser beam over the powder layer to selectively solidify at least part of the powder layer to form a required pattern. The required pattern is formed from a plurality of stripes or stripe segments that are formed by advancing the laser beam along the stripe or stripe segment in a stripe formation direction. The stripe formation direction is arranged so that it always at least partially opposes the predefined gas flow direction. A corresponding method is also described.

Abstract: A method for evaluating the quality of a component produced by means of an additive laser sintering and/or laser melting method, in particular a component for an aircraft engine comprises at least the steps of providing a first data set, which comprises spatially resolved color values, which each characterize the temperature of the component at an associated component location during the laser sintering and/or laser melting of the component, providing a second data set, which comprises spatially resolved color values corresponding to the first data set, which color values each characterize the temperature of a reference component at an associated reference component location during the laser sintering and/or laser melting of the reference component.

Abstract: A dispersible, nonwoven multistrata wipe material is provided that is stable in a wetting liquid and flushable in use. More particularly, multilayered structures including, but not limited to, two, three, or four layers are provided to form the dispersible nonwoven wipe material. The layers contain combinations of cellulosic and noncellulosic fibers, and optionally a binder or additive.

Abstract: Selective laser solidification apparatus is described that includes a powder bed onto which a powder layer can be deposited and a gas flow unit for passing a flow of gas over the powder bed along a predefined gas flow direction. A laser scanning unit is provided for scanning a laser beam over the powder layer to selectively solidify at least part of the powder layer to form a required pattern. The required pattern is formed from a plurality of stripes or stripe segments that are formed by advancing the laser beam along the stripe or stripe segment in a stripe formation direction. The stripe formation direction is arranged so that it always at least partially opposes the predefined gas flow direction. A corresponding method is also described.

Abstract: A method for manufacturing a turbine casing part having a bearing chamber system including a shell (1) and at least one bearing receptacle (2) and further having a protective heat shield (30) that at least partially encompasses the shell (1) radially outwardly, the protective heat shield (30) being additively manufactured integrally with the bearing chamber system by selectively solidifying layer-by-layer a feedstock material (5) is provided.

Abstract: The invention relates to a device and a method for the additive manufacture of components through the layered bonding of powder particles to one another and/or to a semi-finished product or substrate already produced, using selective interaction of the powder particles with a high-energy beam, wherein, during the bonding of the powder particles into a layer made of powder particles with the aid of the high-energy beam, a gas flow, which has a flow direction having a directional component directed at least partially parallel to the layer of powder particles, is provided across the layer of powder particles and/or the bonding region in the layer of powder particles, wherein the directional component of the gas flow directed at least partially parallel to the layer of powder particles during the bonding of the powder particles in a layer is generated in at least two directions, which have oppositely directed directional components.

Abstract: A leaf seal for sealing off a shaft rotating around an axis, particularly in a gas turbine, is disclosed. The leaf seal includes a plurality of leaves arranged spaced apart from one another, where the leaves are produced integrally with a basic element supporting the leaves by a generative production process. A process for producing a leaf seal for sealing off a shaft rotating around an axis is also disclosed.

Abstract: A method for producing a three-dimensional object (2) by applying layers of a pulverulent construction material (11) and by selectively solidifying said material by the action of energy comprises the steps: a layer of the pulverulent construction material (11) is applied to a support (6) or to a layer of the construction material that has been previously applied and at least selectively solidified; an energy beam (14) from an energy source (13) sweeps over points on the applied layer corresponding to a cross-section of the object (2) to be produced in order to selectively solidify the pulverulent construction material (11); and a gas flow (18) is guided in a main flow direction (RG) over the applied layer during the sweep of the energy beam (14). The main flow direction (RG) of the gas flow (G) and the sweep direction (RL) of the energy beam (14) are adapted to one another at least in one region of the cross-section to be solidified.

Abstract: Disclosed is a method for generatively producing components by layer-by-layer building from a powder material by selective material bonding of powder particles by a high-energy beam. An eddy current testing is carried out concurrently with the material bonding. Also disclosed is an apparatus which is suitable for carrying out the method.

Abstract: A method for evaluating the quality of a component produced by means of an additive laser sintering and/or laser melting method, in particular a component for an aircraft engine, includes at least the steps of providing a first data set, which comprises spatially resolved color values, which each characterize the temperature of the component at an associated component location during the laser sintering and/or laser melting of the component, providing a second data set, which comprises spatially resolved color values corresponding to the first data set, which color values each characterize the temperature of a reference component at an associated reference component location during the laser sintering and/or laser melting of the reference component.

Abstract: A dispersible, nonwoven multistrata wipe material is provided that is stable in a wetting liquid and flushable in use. More particularly, multilayered structures including, but not limited to, two, three, or four layers are provided to form the dispersible nonwoven wipe material. The layers contain combinations of cellulosic and noncellulosic fibers, and optionally a binder or additive.

Abstract: The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (1-3) connected to one another in the circumferential direction (U), wherein shells adjacent in the axial direction have cross sections opened counter to a throughflow direction (A) and/or a thread axis inclined counter to the throughflow direction.

Abstract: A method for producing a three-dimensional object (2) by applying layers of a pulverulent construction material (11) and by selectively solidifying said material by the action of energy comprises the steps: a layer of the pulverulent construction material (11) is applied to a support (6) or to a layer of the construction material that has been previously applied and at least selectively solidified; an energy beam (14) from an energy source (13) sweeps over points on the applied layer corresponding to a cross-section of the object (2) to be produced in order to selectively solidify the pulverulent construction material (11); and a gas flow (18) is guided in a main flow direction (RG) over the applied layer during the sweep of the energy beam (14). The main flow direction (RG) of the gas flow (G) and the sweep direction (RL) of the energy beam (14) are adapted to one another at least in one region of the cross-section to be solidified.

Abstract: Equipment for the generative manufacture and/or repair of components, in particular of gas turbines, includes a solidifying means for the layer-by-layer, local, particularly optical, thermal, and/or chemical solidification of particularly powdered, granular, and/or fluid material, and an electrodeposition means for the electrostatic deposition of particles and/or gas from a region between a layer of material, which is to be solidified or is solidified, and the solidifying means, as well as a method for the generative manufacture and/or repair of components, in particular of gas turbines, by means of such equipment.

Abstract: A method is provided for operating a trace procedure, which traces execution of a computer program, where the program uses different callable modules. A program stack is used to store trace buffer information and an error state, and the modules include calls of the trace procedure. The method includes: (i) when entering execution of a module, storing the current write position of the trace buffer and a cleared error flag in the current frame of the stack; (ii) in case of an error condition during execution of the program, setting the error flag in the current frame; and (iii) when leaving execution of a module, determining if the error flag is set, and if not, then rewinding the trace buffer to the write position stored in the current frame, and deleting the current write position of the trace buffer and the error flag from the stack.

Abstract: The invention relates to a guide vane ring with at least one guide vane ring segment for a turbomachine, including a plurality of guide vanes arranged radially around an axis of rotation, an outer shroud arranged radially on the outer side of the guide vanes, and an inner shroud arranged radially on the inner side of the guide vanes, wherein the outer shroud or the inner shroud has at least one expansion joint, wherein the guide vane ring segment is formed in one piece with the guide vanes, the outer shroud, and the inner shroud and the at least one expansion joint is sealed in each case by at least one sealing device arranged in the respective expansion joint.

Abstract: A serial bus is provided with a device (sometimes herein referred to as an I2C serializer device) including circuitry and machine logic that operates as follows: when one of the master devices is using the bus for data communication, then the other master(s) will receive a wait signal until the bus becomes available again. This wait signal allows the master devices to wait as a “hardware response,” rather than requiring the master devices to be equipped with software and/or firmware to control the operation of waiting until the serial bus is available. In some embodiments, the use of the I2C serializer device allows a bus operating under a bus serialization protocol (for example, I2C) to be simultaneously connected to multiple master devices even in the case that one, or more, master device(s) do not include any currently conventional form of multi-master support.