Abstract: A system for analyzing layer thickness of a multilayer component is provided. The system includes: an opening forming device configured to create an opening having a predefined geometry partially into the multilayer component at a selected location on a surface of the multilayer component, where the multilayer component includes a plurality of material layers including a substrate and a bond coat and the opening exposes each of the plurality of material layers, and an imaging device configured to create an image of the exposed plurality of material layers in the opening. The system is configured to calculate at least a thickness of the bond coat of the exposed plurality of material layers from the image and based on the predefined geometry of the opening. The system may also include a repairing device configured to repair the opening, allowing the multilayer component to be used for an intended purpose.

Abstract: An automated system is provided. The system includes: a manipulator coupled to: an opening forming device configured to create an opening having a predefined geometry partially into a multilayer component at a selected location on a surface of the multilayer component, where the multilayer component includes a plurality of material layers including at least a substrate and a bond coat, and where the opening exposes each of the plurality of material layers; and an imaging device configured to create an image of the exposed plurality of material layers in the opening; and a processor configured to calculate at least a thickness of the bond coat of the exposed plurality of material layers from the image and based on the predefined geometry of the opening. Methods of using the system to analyze layer thickness of a multilayer component and repair a multilayer component are also provided.

Abstract: A method of analyzing layer thickness of a multilayer component is provided. The method includes: creating an opening having a predefined geometry partially into the multilayer component at a selected location on a surface of the multilayer component. The multilayer component includes a plurality of material layers including a substrate and a bond coat. The opening exposes each of the plurality of material layers including the substrate. Contrast of the exposed plurality of material layers can be increased. An image is created of the exposed layers in the opening using a digital microscope, and thickness of a bond coat, thickness of a depletion layer\ and/or thickness of an oxide layer is calculated from the image and based on the predefined geometry of the opening. Repairing the opening, allows the multilayer component to be used for an intended purpose after testing, e.g., re-installed and reused in a gas turbine.

Abstract: A method of analyzing layer thickness of a multilayer component is provided. The method includes: creating an opening having a predefined geometry partially into the multilayer component at a selected location on a surface of the multilayer component. The multilayer component includes a plurality of material layers including a substrate and a bond coat. The opening exposes each of the plurality of material layers including the substrate. Contrast of the exposed plurality of material layers can be increased. An image is created of the exposed layers in the opening using a digital microscope, and thickness of a bond coat, thickness of a depletion layer\ and/or thickness of an oxide layer is calculated from the image and based on the predefined geometry of the opening. Repairing the opening, allows the multilayer component to be used for an intended purpose after testing, e.g., re-installed and reused in a gas turbine.

Abstract: A method for generating coatings is disclosed. The method involves applying a flame spray technique. A metallic powder material is provided to the flame, and the process parameters of the flame spray process are chosen such as to achieve a metallic coating layer with a distinct surface roughness. In a subsequent process phase, a non-metallic material may be disposed on the rough metallic layer by flame spraying. The non-metallic layer effectively interlocks with the roughness of the metallic layer. The method may be carried out with hand-held equipment.

Abstract: A method for reconditioning a hot gas path part of a gas turbine to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of the hot gas path part, resulting in a cutout at the hot gas path part; and manufacturing a coupon for insertion into the cutout to replace the removed area of the hot gas path part. The method further includes inserting the coupon into the cutout; and joining the hot gas path part with the coupon. The coupon is manufactured by a selective laser melting method resulting in a fine grain sized material with significantly improved low cycle fatigue lifetime. The hot gas path part is coated, at least in an area including the inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue and oxidation lifetime.

Abstract: The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system.

Abstract: The invention relates to a high temperature protective coating based on MCrAlY coating, with M at least one element out of the group of Ni, Co and Fe, for a component of a turbo machine, especially a gas turbine, the coating containing at least at least 1.75 vol.-% chromium borides and the coating consisting of the following chemical composition (in wt.-%): 10-27 Cr; 3-12 Al; 1-4 Si; 0.1-3 Ta; 0.01-3 Y; 0.1-3 B; 0-7 M, with M being a different element out of said group compared to the remainder, and the remainder being M and inevitable impurities. A preferred embodiment is a coating with the following chemical composition: 10-27 Cr; 3-12 Al; 1-4 Si; 0.1-3 Ta; 0.01-3 Y; 0.1-3 B; 0-7 Co and the remainder being Ni and inevitable impurities.

Abstract: A method for reconditioning a hot gas path part of a gas turbine in order to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals is disclosed. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of said hot gas path part, resulting in a cutout at said hot gas path part; and manufacturing a coupon for being inserted into said cutout to replace said removed area of said hot gas path part. The method further includes inserting said coupon into said cutout; and joining said hot gas path part with said inserted coupon. The coupon is manufactured by a selective laser melting (SLM) method resulting in a fine grain sized material with significantly improved low cycle fatigue (LCF) lifetime. The hot gas path part is coated, at least in an area comprising said inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue (TMF) and oxidation lifetime.

Abstract: The invention relates to compounds of the formula: or their racemic, enantiomeric or diastereoisomeric isomers, or pharmaceutically acceptable salts of the compounds of formula I or the racemic, enantiomeric or diasteroisomeric isomers.

Abstract: The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system.

Abstract: The invention relates to a product of formula (I) where R1, R2, R3, and R4 are as defined herein, the therapeutic use of the product, a process to make the product, and a pharmaceutical composition comprising the product.

Abstract: The invention relates to the novel materials of formula (I), where: R1 is an optionally substituted L-aryl or L-heteroaryl, such that L is a single bond, alkyl, CO, or CO-alk, or L-X, with L? being an alkyl and X being O or S; R2 is H or alkyl; R3 is an alkyl optionally substituted by Hal; and R4 is Hou Hal, wherein said materials are in any isomeric form and the salts thereof, to be used as drugs.

Abstract: A plastic molding material contains at least one filler and a polymer resin, selected from the group made up of cyanate ester resins, epoxy novolac resins, multifunctional epoxy resins, bismaleimide resins and their mixtures. The proportion of filler in the plastic molding material is in the range of 65 to 92 wt. %, with reference to the overall mass of the plastic molding material.

Abstract: The invention relates to the novel materials of formula (I), where R1 is an optionally substituted L-aryl or -heteroaryl, such that L is: an alkyl or CO, or LX, with Lbeing an alkyl and X being O or S; R2 is H or an alkyl; R3 is an alkyl optionally substituted by Hal; and R4 is Hou Hal, wherein said materials are in any isomeric form and the salts thereof, to be used as drugs.

Abstract: The invention relates to methods of treating or preventing malaria which comprises administering to a patient in need thereof, an effective amount of a 1H-indazole-3-carboxamide derivative of general formula (I), in the form of a base or of an addition salt with an acid, or in the form of a hydrate or of a solvate of said base or acid addition salt.

Abstract: The invention relates to methods of treating or preventing malaria which comprises administering to a patient in need thereof, an effective amount of a 1H-indazole-3-carboxamide derivative of general formula (I), in the form of a base or of an addition salt with an acid, or in the form of a hydrate or of a solvate of said base or acid addition salt.

Abstract: Compound corresponding to general formula (I): in which, R1 represents a hydrogen or halogen atom, an NH2, NHR2, NHCOR2, NO2, CN, CH2NH2 and CH2NHR2; or alternatively R1 represents an optionally substituted phenyl or an optionally substituted heteroaromatic group; Ar represents an optionally substituted phenyl group or an optionally substituted heteroaromatic group; n represents 0, 1, 2 or 3; in the form of a base, of an addition salt with an acid, of a hydrate or of a solvate. Application in therapy.

Abstract: The invention relates to fusion proteins comprising at least three domains, where a first domain facilitates membrane localization of the fusion protein in a cellular context, and a second domain has or presumably has a ligand-binding function of a nuclear receptor, a third domain has an activity able to activate a signal pathway connected to a Ras protein in a cell, characterized in that when there is a lack of binding or, alternatively, when there is binding of ligand to the second domain the third domain cannot exert its activity to activate a signal pathway connected to a Ras protein in a cell, despite membrane localization. It additionally comprises inter alia cells which comprise such fusion proteins, assay methods using such cells, which are used inter alia for detecting specific interactions between ligand-binding sections of nuclear receptors and ligands, and kits for use in these assays.

Abstract: The invention relates to methods of treating or preventing malaria which comprises administering to a patient in need thereof, an effective amount of a 1H-indazole-3-carboxamide derivative of general formula (I), in the form of a base or of an addition salt with an acid, or in the form of a hydrate or of a solvate of said base or acid addition salt.