Abstract: A moulding device (1) for moulding a material around a core (2), comprising a hollow moulding enclosure (3) suitable for receiving the core (2), and means for controlling the shape of the core (2) in the hollow enclosure (3), the control means comprising means for deforming the core (2). The control means further comprise force control means and a control unit (8) suitable for actuating the deformation means in accordance with information provided by the force control means.

Abstract: A compression bandage in the form of a knit obtained with warp knit technology, formed of synthetic yarns and composed of two textile surfaces having the same or different textile structure, linked together by spacer threads, each surface has elastic yarns, and the spacer threads of the knit are multifilaments. The knit has longitudinal elongation measured as per standard EN 14704-1 of between 30 and 160% and threshold shear stress equal to or higher than 2800 Pa and/or conformability equal to or lower than 65 mm.

Abstract: A compression bandage in the form of a knit obtained by warp stitch technology on the basis of synthetic yarns and comprising two textile surfaces of respective textile structures that may be identical or different, the surfaces being interconnected by spacer yarns, each surface including elastic yarns, the bandage being characterized in that said knit presents: longitudinal stretch measured in compliance with the standard EN 14704-1 lying in the range 30% to 160%; and threshold shear stress greater than or equal to 2800 Pa.

Abstract: A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.

Abstract: A compression bandage formed by a knit obtained by warp stitch technology, based on synthetic yarns which is made up of two textile surfaces whose textile structure is identical or different connected to each other by spacer yarns. Each textile surface has elastic yarns and the spacer yarn being a monofilament. The knit has a longitudinal elongation measured according to standard EN 14704-1 of between 30 and 160%. The textile surface which comes into contact with the skin has synthetic multifilament yarns, the filaments of which have a count of between 1.2 and 5 dtex and the number of filaments is between 15 and 150, and a dynamic coefficient of friction measured according to standard EN ISO 8295 greater than or equal to 0.25 and less than or equal to 1.2.

Abstract: The invention relates to a moulding device (1) for moulding a material around a core (2), comprising a hollow moulding enclosure (3) suitable for receiving the core (2), and means for controlling the shape of the core (2) in the hollow enclosure (3), the control means comprising means for deforming the core (2). The control means further comprise force control means and a control unit (8) suitable for actuating the deformation means in accordance with information provided by the force control means.

Abstract: A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.

Abstract: A compression bandage in the form of a knit obtained with warp knit technology, formed of synthetic yarns and composed of two textile surfaces having the same or different textile structure, linked together by spacer threads, each surface has elastic yarns, and the spacer threads of the knit are multifilaments. The knit has longitudinal elongation measured as per standard EN 14704-1 of between 30 and 160% and threshold shear stress equal to or higher than 2800 Pa and/or conformability equal to or lower than 65 mm.

Abstract: A refractory core (12) for fabricating a hollow turbine engine airfoil (10) using the lost-wax casting technique, the core comprising a main body (14) and at least one shell (16) connected to the main body (14) and defining a cavity (18) between the main body and the shell, the shell (16) being configured to come into contact with the airfoil (10) during fabrication.

Abstract: A ceramic material mold for use in molding a turbine engine blade from a molten metal, the blade including a root, an inner platform, an airfoil, and an outer platform, and the mold including a cavity having the shape of the blade, and an auxiliary grain duct including a first segment and a second segment that is an extension of the first segment, the first segment opening out at one end into a first portion of the cavity forming the root of the blade, and at another end into a second portion of the cavity forming a lip of the inner platform of the blade, the second segment opening out at one end into the second portion of the cavity, and at another end into a third portion of the cavity forming a lip of the outer platform of the blade.

Abstract: An installation for manufacturing a part by implementation of a Bridgman method includes in particular a mold intended to receive a melted material and a thermal screen movable with respect to the mold intended to be positioned in front of the solidification front during the directional solidification.

Abstract: A feed system for conveying a molten metal that is to make a casting, the system including a feed channel made of ceramic material that is configured to enable the molten metal to flow by gravity inside the feed channel, the feed channel having a first portion extending in a first direction, and at least one second portion extending in a second direction different from the first direction, the second portion being arranged downstream from the first portion and being connected to the first portion by a junction. The system further includes a damping channel having a first end opening out into the junction and a second end that is closed, the damping channel extending the first portion of the feed channel.

Abstract: A ceramic material mold for use in molding a turbine engine blade from a molten metal, the blade including a root, an inner platform, an airfoil, and an outer platform, and the mold including a cavity having the shape of the blade, and an auxiliary grain duct including a first segment and a second segment extending the first segment, the first segment opening out at one end into a first portion of the cavity forming the root of the blade, and at another end into a second portion of the cavity forming a lip of the inner platform of the blade, the second segment opening out at one end into the second portion of the cavity, and at another end into a third portion of the cavity forming a lip of the outer platform of the blade.

Abstract: A feed system for conveying a molten metal that is to make a casting, the system including a feed channel made of ceramic material that is configured to enable the molten metal to flow by gravity inside the feed channel, the feed channel having a first portion extending in a first direction, and at least one second portion extending in a second direction different from the first direction, the second portion being arranged downstream from the first portion and being connected to the first portion by a junction. The system further includes a damping channel having a first end opening out into the junction and a second end that is closed, the damping channel extending the first portion of the feed channel.

Abstract: A refractory core (12) for fabricating a hollow turbine engine airfoil (10) using the lost-wax casting technique, the core comprising a main body (14) and at least one shell (16) connected to the main body (14) and defining a cavity (18) between the main body and the shell, the shell (16) being configured to come into contact with the airfoil (10) during fabrication.

Abstract: A compression bandage in the form of a knit obtained by warp stitch technology on the basis of synthetic yarns and comprising two textile surfaces of respective textile structures that may be identical or different, the surfaces being interconnected by spacer yarns, each surface including elastic yarns, the bandage being characterized in that said knit presents: longitudinal stretch measured in compliance with the standard EN 14704-1 lying in the range 30% to 160%; and threshold shear stress greater than or equal to 2800 Pa.

Abstract: An installation for manufacturing a part by implementation of a Bridgman method includes in particular a mold intended to receive a melted material and a thermal screen movable with respect to the mold intended to be positioned in front of the solidification front during the directional solidification.