Abstract: A method for creating a computer-implemented data system, includes: providing a virtual 3D engine model of an engine including a plurality of components; providing component-specific data associated with said each of the plurality of components; and virtually linking the virtual 3D engine model to the component-specific data by creating virtual data markers in the virtual 3D engine model at a coordinate of each of the plurality of components, and associating each virtual data marker with the component-specific data of its corresponding one of the plurality of components. In this regard, the component specific data may include, for example, part number, name, inspection intervals, etc. The engine may be an aircraft engine, and may further be an aircraft engine casing. Further, in addition to the virtual 3D engine model, the method may include providing 2D images of the plurality components, and the step of virtually linking may further include linking the 2D images to the component specific data.

Abstract: A method for producing a weakening line in a surface of a component. The method comprises a guiding step and a skipping step. In the guiding step, a removal apparatus for removing a material of the surface is guided over a plurality of segments of a predefined line-shaped contour by means of an activated laser beam in order to produce a desired wall thickness for at least one of the segments so as to produce the weakening line. In the skipping step, the segment is skipped if the segment has the desired wall thickness.

Abstract: The invention relates to a method for producing at least in regions an oxidation protection coating on a component of a thermal gas turbine. In accordance with the invention, the method comprises the steps of coating the component at least in regions with a lacquer, which comprises at least one UV-curable binder and metal particles, curing the lacquer by exposure to UV light, and thermal treatment of the component at least in the region of the cured lacquer for production of the oxidation protection coating.

Abstract: A method for correcting an alignment of a cutting layer made up of stacked, sheet-format product in the form of sheets in relation to a cutting plane of a cutting blade of a cutting machine, and a cutting machine. The cutting machine has a feed saddle for displacing the cutting layer in the direction of the cutting plane of the cutting blade, wherein the feed saddle is adjustable in its alignment in relation to the cutting plane to change the alignment of the cutting layer pressing against the feed saddle in relation to the cutting plane. The respective sheet is provided with at least one cutting test mark, wherein the respective cutting test mark has a coloration changing in the feed direction of the feed saddle.

Abstract: A method for contour punching an output stack consisting of sheet-like material and a punching device for carrying out the method Includes providing at least two punching procedures. A large proportion of an unprinted region is separated from a printed region in a first punching procedure and a first punching waste produced thereby is collected separately, whereby the quantity of the second punching waste which is formed in a second punching procedure is significantly less than if only a single punching procedure were to be carried out. By collecting the first punching waste and the second punching waste separately, it is possible to provide this waste in each case for appropriate disposal or appropriate recycling.

Abstract: The present invention relates to a method for inspecting a component, in particular a component of a turbomachine (1), including the steps of: capturing (S2) at least one X-ray or CT image of the component (10) using an image-capturing device (20); providing (S21) metadata about the component (10), the metadata including, in particular, a component type, a running time of the component (10), a number of remaining life cycles, and/or a repair history; classifying, by a machine learning system (30), the component (10) into a “serviceable” category or a “non-serviceable” category based on the image captured by the image-capturing device (20) and the provided metadata.

Abstract: A method for producing a weakening line in a surface of a component. The method comprises a guiding step and a skipping step. In the guiding step, a removal apparatus for removing a material of the surface is guided over a plurality of segments of a predefined line-shaped contour by means of an activated laser beam in order to produce a desired wall thickness for at least one of the segments so as to produce the weakening line. In the skipping step, the segment is skipped if the segment has the desired wall thickness.

Abstract: Provided is a method for detecting defects, in particular cracks and/or pores, in a component, in particular in a component of a turbomachine, preferably in a component of an engine, the method including the following steps: applying penetrant to at least a sub-region of the component such that the penetrant penetrates into any defects, in particular cracks and/or pores, present in the component; cleaning the surface of the component of penetrant that has not penetrated into defects, in particular cracks and/or pores, of the component; capturing an image, in particular a complete image, of the component; inputting the captured image into a machine learning system trained to detect defects, in particular cracks and/or pores; and detecting defects, in particular cracks and/or pores, in the component by machine learning system on the basis of light emitted and/or reflected by the penetrant in the defects, in particular cracks and/or pores.

Abstract: The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

Abstract: Disclosed is a thermal barrier coating system for components of a turbomachine, especially for high temperature-stressed or hot gas-stressed components of a turbomachine, comprising a ceramic coating of fully or partially stabilized zirconium oxide, and an oxide cover coating which comprises aluminum and at least one element from the group lanthanum, magnesium, silicon, calcium and sodium. The aluminum oxide exists at least partially as free ?-Al2O3. Also disclosed is a method for producing a corresponding thermal barrier coating system.

Abstract: A method for contour punching an output stack consisting of sheet-like material and a punching device for carrying out the method Includes providing at least two punching procedures. A large proportion of an unprinted region is separated from a printed region in a first punching procedure and a first punching waste produced thereby is collected separately, whereby the quantity of the second punching waste which is formed in a second punching procedure is significantly less than if only a single punching procedure were to be carried out. By collecting the first punching waste and the second punching waste separately, it is possible to provide this waste in each case for appropriate disposal or appropriate recycling.

Abstract: A method and device for producing a tear line on a planar workpiece by material removal by means of a pulsed laser, wherein machining cycles are preceded by a method step for generating and storing a reference signal curve which is formed by reference signals, causing the pulse amplitude of the laser pulses, via removal locations along the contour of the tear line. The achievement of a respective predetermined percentage of the reference signal or of an absolute distance from the reference signal by a measurement signal is used as the space-resolved deactivation criterion for each removal location, which measurement signal is obtained from a transmitted part of the pulse amplitude at the respective removal location.

Abstract: A method for producing at least one patterned design having a plurality of pattern elements via a laser in a component that is at least partially transparent and is coated on a first surface. The component is coated on a first surface with at least one layer. The coated first surface of the component is surveyed with first co-ordinated. At least one patterned design is created with second coordinates. The second coordinates of the at least one patterned design are transformed into third coordinates. The coated first surface is irradiated with laser radiation via control coordinates. The laser radiation is measured on a second surface and the laser radiation received is compared via the sensor system with a reference value. The laser radiation is switched off when the reference value is reached.

Abstract: Disclosed is a method of repairing damage of an aircraft engine component made of or comprising weldable thermoplastic material, which method comprises welding of the weld filler material into an initially prepared damaged area. Also disclosed are the use of plastic welding technique for repairing damaged aircraft engine components made of weldable thermoplastic materials.

Abstract: The present invention relates to a method for transmitting device-specific data over a data transmission system to a plurality of devices connected to the data transmission system. In one step of the method, a broadcast announcement identified with a broadcast identifier is sent to the devices over the data transmission system. An individual device indicator and the broadcast identifier are assigned to each one of the devices. The individual devices are put in a state of readiness to receive the device-specific data after the broadcast announcement has been received. Data reception readiness confirmations are transmitted by the individual devices after the respective device has reached the state of readiness to receive the device-specific data. According to the invention, there is a joint transmission of the device-specific data over the data transmission system to the devices after the devices have transmitted the data reception readiness confirmations.

Abstract: The present invention relates to a method for transmitting device-specific data over a data transmission system to a plurality of devices connected to the data transmission system. In one step of the method, a broadcast announcement identified with a broadcast identifier is sent to the devices over the data transmission system. An individual device indicator and the broadcast identifier are assigned to each one of the devices. The individual devices are put in a state of readiness to receive the device-specific data after the broadcast announcement has been received. Data reception readiness confirmations are transmitted by the individual devices after the respective device has reached the state of readiness to receive the device-specific data. According to the invention, there is a joint transmission of the device-specific data over the data transmission system to the devices after the devices have transmitted the data reception readiness confirmations.

Abstract: The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

Abstract: A method and device for producing a tear line on a planar workpiece by material removal by means of a pulsed laser, wherein machining cycles are preceded by a method step for generating and storing a reference signal curve which is formed by reference signals, causing the pulse amplitude of the laser pulses, via removal locations along the contour of the tear line. The achievement of a respective predetermined percentage of the reference signal or of an absolute distance from the reference signal by a measurement signal is used as the space-resolved deactivation criterion for each removal location, which measurement signal is obtained from a transmitted part of the pulse amplitude at the respective removal location.

Abstract: An energy absorbing system that is adapted for absorbing energy of an object in a vehicle in a crash situation by decreasing acceleration and force acting on the object in the crash situation, the energy absorbing system comprising at least one plastically deformable energy absorber that is plastically deformable in the crash situation. A mass-dependent self-adjusting mechanism is provided, the mass-dependent self-adjusting mechanism being adapted for adjusting, on the basis of an underlying mass of the object, a required compensation force that is to be provided by the energy absorbing system in the crash situation for plastically deforming the at least one plastically deformable energy absorber in order to decrease the acceleration and force acting on the object.

Abstract: Disclosed is a repair method for guide blades of a gas turbine. The method comprises: providing at least one guide blade to be maintained; capturing the actual geometry of the guide blade to be maintained with application of at least one measuring method; comparing the actual geometry captured by the contactless measuring method to a predetermined desired geometry for a corresponding guide blade type; calculating a target geometry for the guide blade to be maintained, which corresponds as much as possible to the desired geometry, such that using optimization parameters, the desired geometry of the guide blade to be maintained is approximated at least in sections along its flow contour; applying material and removing material by machine on the guide blade, such that the calculated target geometry is produced.