Abstract: A variable section nozzle includes an ejection casing and a plurality of internal flaps arranged in a ring downstream from the ejection casing. Each internal flap is connected to the ejection casing by a movable lever pivotally mounted to the downstream end of the ejection casing. Each lever is movable between a first position in which the internal flaps are in a high position and a second position in which the internal flaps are in a folded-down position. The nozzle includes a plurality of rigid movement transmission parts distributed circumferentially around the ejection casing. Each rigid movement transmission part is connected to two adjacent levers by connecting rods, and to a control actuator. Each rigid movement transmission part can move in a direction corresponding to the axial direction of the nozzle under the action of the control actuator to move the adjacent levers between the first and second positions.

Abstract: A variable section nozzle includes an ejection casing and a plurality of internal flaps arranged in a ring downstream from the ejection casing. Each internal flap is connected to the ejection casing by a movable lever pivotally mounted to the downstream end of the ejection casing. Each lever is movable between a first position in which the internal flaps are in a high position and a second position in which the internal flaps are in a folded-down position. The nozzle includes a plurality of rigid movement transmission parts distributed circumferentially around the ejection casing. Each rigid movement transmission part is connected to two adjacent levers by connecting rods, and to a control actuator. Each rigid movement transmission part can move in a direction corresponding to the axial direction of the nozzle under the action of the control actuator to move the adjacent levers between the first and second positions.

Abstract: An acoustic protection device for a fan casing of an aircraft turbomachine, including an acoustic protection panel forming a ferrule sector centered on a center axis, and one or more vibration damping strips pressed on a first side to an external surface of the panel and on a second side to an internal surface of the casing, each damping strip including two opposite edges each including an upstream end and a downstream end spaced from each other along a direction of the center axis. At least one of both opposite edges of at least one of the damping strips is shaped such that liquid present on this edge can flow by gravity towards either or both of its upstream and downstream ends.

Abstract: A method of repairing a flange of a casing, or a casing made of aluminum, for a turbine engine or an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment. The method includes: forming a spot face in the flange around the hole for passing the bolt; anodizing the bottom surface of the spot face; placing a washer on the spot face; and fastening the washer to the flange using adhesive.

Abstract: A method for inspecting impacts present on an internal face of a fan casing, the method including: spotting a first impact present on the internal face of the fan casing; delimiting an inspection area containing the first impact; spotting the various impacts present in the delimited inspection area, the various spotted impacts forming a set of impacts to be considered; measuring, for each impact that is to be considered, the depth of length of the impact; for each impact to be considered, determining a harmfulness value, using at least one chart relating the depth and length of each impact to be considered to a level of harmfulness; determining, for the inspection area containing the first impact, a total harmfulness value by adding together the harmfulness level determined for each impact to be considered.

Abstract: An acoustic protection device for a fan casing of an aircraft turbomachine, including an acoustic protection panel forming a ferrule sector centered on a center axis, and one or more vibration damping strips pressed on a first side to an external surface of the panel and on a second side to an internal surface of the casing, each damping strip including two opposite edges each including an upstream end and a downstream end spaced from each other along a direction of the center axis. At least one of both opposite edges of at least one of the damping strips is shaped such that liquid present on this edge can flow by gravity towards either or both of its upstream and downstream ends.

Abstract: A vibration-damping shim configured to be interposed between a platform of a fan blade and a fan disk, including a radially external surface fitted with plates in contact with the fan blade platform, and a radially internal surface formed by an upstream surface, configured to be facing the disk, and a downstream surface separated from the upstream surface by a break in alignment. The upstream surface includes a zone protruding radially towards the interior, initiated at some distance from its upstream end.

Abstract: A shim configured to be inserted between a fan blade root of a turbojet and a bottom of a compartment in which this root is housed, the compartment being delimited by a fan disk. The shim includes a metal stiffener including at least one external element made of an elastomer material, and including a support surface of the external element. The support surface includes at least one corrugated zone.

Abstract: A method of repairing a flange of a casing for an airplane turboprop or turbojet, in which the flange includes at least one through hole for passing a bolt for fastening equipment, and the hole opens out in a face of the flange that is worn by friction against the equipment, disclosed. The method includes mounting a bearing member on the flange. The bearing member includes a radial wall covering the worn face of the flange. The wall includes a hole that comes into register with the hole in the flange and having thickness for compensating the wear of the face of the flange. The member further includes an abutment for bearing against the periphery of the flange, and being fastened to the flange by adhesive.

Abstract: A method for inspecting impacts present on an internal face of a fan casing, the method including: spotting a first impact present on the internal face of the fan casing; delimiting an inspection area containing the first impact; spotting the various impacts present in the delimited inspection area, the various spotted impacts forming a set of impacts to be considered; measuring, for each impact that is to be considered, the depth of length of the impact; for each impact to be considered, determining a harmfulness value, using at least one chart relating the depth and length of each impact to be considered to a level of harmfulness; determining, for the inspection area containing the first impact, a total harmfulness value by adding together the harmfulness level determined for each impact to be considered.

Abstract: A method of repairing a flange of a casing, or a casing made of aluminum, for a turbine engine or an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment. The method includes: forming a spot face in the flange around the hole for passing the bolt; anodizing the bottom surface of the spot face; placing a washer on the spot face; and fastening the washer to the flange using adhesive.

Abstract: A vibration-damping shim configured to be interposed between a platform of a fan blade and a fan disk, including a radially external surface fitted with plates in contact with the fan blade platform, and a radially internal surface formed by an upstream surface, configured to be facing the disk, and a downstream surface separated from the upstream surface by a break in alignment. The upstream surface includes a zone protruding radially towards the interior, initiated at some distance from its upstream end.

Abstract: A shim configured to be inserted between a fan blade root of a turbojet and a bottom of a compartment in which this root is housed, the compartment being delimited by a fan disk. The shim includes a metal stiffener including at least one external element made of an elastomer material, and including a support surface of the external element. The support surface includes at least one corrugated zone.

Abstract: The invention relates to a method of repairing a flange of a casing for an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment, the hole opening out in a face of the flange that is worn by friction against the equipment. The method consists in mounting a bearing member on the flange, the bearing member comprising a radial wall covering the worn face of the flange, said wall including a hole that comes into register with the hole in the flange and having thickness for compensating the wear of the face of the flange, said member further including an abutment for bearing against the periphery of the flange, and being fastened to the flange by adhesive.