Abstract: The invention relates to an aeronautical part, such as, for example, a turbine blade or a distributor vane, which is used in aeronautics, comprising at least one reactive layer adapted to react with at least one CMAS compound, the reactive layer at least partially covering the environmental barrier, characterized in that the material of the reactive layer comprises at least one oxide of the formula A?4-xA?xB?2-yB?yO11-?, A? being selected from a rare earth, yttrium and scandium, A? being selected from a rare earth, yttrium, scandium and aluminum, B? being selected from tantalum and niobium, B? being selected from tantalum, niobium, titanium, zirconium, hafnium, aluminum and cesium, wherein x and y are real numbers between 0 and 2 and 6 is a real number between ?1 and 2 and preferably between ?1 and 1.

Abstract: A method for manufacturing a real component, enabling at least one acceptance criterion to be displayed by targeting a point on the real component with a pointer of an augmented reality device. The method includes the steps of determining a transfer matrix for converting coordinates of a real point located in a second reference frame into coordinates of a virtual point located in a first reference frame and corresponding to the real point, determining the coordinates in the first reference frame of a virtual point associated with the pointer, using the transfer matrix, determining whether the virtual point associated with the pointer belongs to a criterion area of the virtual component, and, if so, displaying at least one acceptance criterion of the criterion area to which the virtual point associated with the pointer belongs, and addressing the non-conformance according to the acceptance criterion, to make the real component acceptable.

Abstract: A method for locating at least one point of a real part on a virtual part defined in a first coordinate system by targeting the point of the real part with a pointer of an augmented-reality device. The method includes determining a transfer matrix for converting between a coordinate system in which the pointer moves and a coordinate system in which the virtual part corresponding to the real part is defined, and determining the coordinates in the first coordinate system of the point be located by converting, by virtue of the transfer matrix, the coordinates in the second coordinate system of the pointer pointed at the point to be located.

Abstract: A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate CMAS protection layer present on the substrate. The layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material and a second phase including particles of an anti-wetting material dispersed in the first phase.

Abstract: The present invention relates to a turbine part, comprising a substrate, an environmental barrier comprising at least one layer selected from a thermally insulating layer, a sub-layer adapted to promote adhesion between the substrate and a thermally insulating layer, and a protective layer adapted to protect the substrate from oxidation and/or corrosion, the environmental barrier at least partially covering the substrate, at least one reactive layer being adapted to react with at least one CMAS compound, the reactive layer covering at least part of the environmental barrier. The invention is characterized in that the material of the reactive layer comprises an oxide of formula A?A?BO5-?, A? being selected from a rare earth and yttrium, A? being selected from a rare earth yttrium and aluminum, B being selected from titanium, zirconium, lufnium, tantlum and niobium, wherein ? is a real number between 0 and 0.5.

Abstract: The invention relates to an aeronautical part, such as, for example, a turbine blade or a distributor vane, which is used in aeronautics, comprising at least one reactive layer adapted to react with at least one CMAS compound, the reactive layer at least partially covering the environmental barrier, characterized in that the material of the reactive layer comprises at least one oxide of the formula A?4-xA?xB?2-yB?yO11-?, A? being selected from a rare earth, yttrium and scandium, A? being selected from a rare earth, yttrium, scandium and aluminum, B? being selected from tantalum and niobium, B? being selected from tantalum, niobium, titanium, zirconium, hafnium, aluminum and cesium, wherein x and y are real numbers between 0 and 2 and ? is a real number between ?1 and 2 and preferably between ?1 and 1.

Abstract: A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate (CMAS) protection layer present on the substrate. The protection layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material capable of forming an apatite or anorthite phase in the presence of calcium-magnesium-alumino-silicates CMAS and a second phase including particles of at least one rare-earth REa silicate dispersed in the first phase.

Abstract: The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.

Abstract: A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate CMAS protection layer present on the substrate. The layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material and a second phase including particles of an anti-wetting material dispersed in the first phase.

Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.

Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, comprising: an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element, an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ and a connection zone between the airfoil and said airfoil end face, said connection zone forming a fattening of the airfoil, is characterized in that said connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.

Abstract: For carrying out an interrogation a position modulated laser light wave is used. A key word is displayed in an interrogator and coded in accordance with a cyclic code, for example Golay's code. This coded key word is used for modulating the laser wave. In the responder the same key word is displayed and coded in the same way. After reception and demodulation each message is compared in a correlation circuit with the local reference word. The correlation method used allows parasite pulses to be taken into account and the word received to be validated with a given security threshold.