Abstract: An aft aerodynamic fairing of an aircraft engine pylon including at least two side panels, wherein each side panel is made of titanium or of titanium alloy and wherein at least one anti-oxidation protective layer, including a layer composed of a chemically inert ceramic material is deposited on the external faces of each side panel that, when the aircraft engine pylon is in use, are in contact with an aerodynamic flow.

Abstract: Calibration methods use a calibration target for obtaining the intrinsic and extrinsic camera parameters of one or more cameras are. The methods can include acquiring, with each camera, a sequence of target images representing the calibration target in different target poses and at different acquisition times. The methods can include identifying reference images from the target images, and defining volume bins, angle bins and multi-camera bins into which the reference images are stored. The reference images can be used to determine the intrinsic and extrinsic parameters of the one or more cameras. In some implementations, the calibration methods can enable a user to monitor the progress of the calibration process, for example by providing an interactive calibration target including an input/output user interface to guide the user in real-time during the acquisition of the target images and/or sensors to provide positional information about the target poses.

Abstract: Calibration methods use a calibration target for obtaining the intrinsic and extrinsic camera parameters of one or more cameras are. The methods can include acquiring, with each camera, a sequence of target images representing the calibration target in different target poses and at different acquisition times. The methods can include identifying reference images from the target images, and defining volume bins, angle bins and multi-camera bins into which the reference images are stored. The reference images can be used to determine the intrinsic and extrinsic parameters of the one or more cameras. In some implementations, the calibration methods can enable a user to monitor the progress of the calibration process, for example by providing an interactive calibration target including an input/output user interface to guide the user in real-time during the acquisition of the target images and/or sensors to provide positional information about the target poses.

Abstract: A component, especially contrived and designed for being used in a turbomachine, includes a high-temperature coating being arranged above a base of the component. The base has at least one structural element for connecting it to the high-temperature coating, with the cross-section of the at least one structural element having at least three different widths, i.e. a base width at the lower end of the at least one structural element, a center width above it, and a tip width above that, where on average the center width is greater than or equal to the base width, but less than four times the base width, in particular less than or equal to three times the base width.

Abstract: A method for forming a protective coating containing aluminum and zirconium on the surface of a metal part. The part is put into contact with a cement made of aluminum alloy, at a treatment temperature, with an atmosphere containing an active gas which reacts with the cement to form a gaseous aluminum halide, which decomposes in contact with the part depositing metallic aluminum thereon, the active gas containing ZrOCl2 that decomposes in contact with the part depositing Zr metal thereon, and being formed by vaporizing granules of ZrOCl2 that are solid at ambient temperature. The part, the cement, and ZrOCl2 granules are then progressively heated together in a chamber from ambient temperature to the treatment temperature with a plateau at 400° C.±200° C.

Abstract: A fabrication method of fabricating a thermal barrier covering a superalloy metal substrate, the thermal barrier including at least an underlayer and a ceramic layer, the method including: smoothing a surface state of the underlayer by at least one physicochemical and/or mechanical process prior to depositing the ceramic layer such that a number of defects presenting a peak-to-peak difference lower than or equal to 2 ?m is at most five over any distance of 50 ?m, and then depositing the ceramic layer. The method can be applied to turbine blades.

Abstract: The present invention relates to a method for forming a protective coating containing aluminium and zirconium on the surface of a metal part, wherein said part is put into contact with a cement made of aluminium alloy, at a treatment temperature, with an atmosphere containing an active gas which reacts with the cement to form a gaseous aluminium halide, which decomposes in contact with the part depositing metallic aluminium thereon, the active gas containing ZrOCl2 that decomposes in contact with the part depositing Zr metal thereon, and being formed by vaporizing granules of ZrOCl2 that are solid at ambient temperature. The method is characterized in that the part, the cement and ZrOCl2 granules are progressively heated together in a chamber from ambient temperature to the treatment temperature with a plateau at 400° C.±200° C.