Abstract: A blade for a turbomachine bladed wheel, the blade comprising a root, an airfoil, and a tip. The root and the tip have respective platforms, each presenting a surface (15) on a side toward the airfoil, which surfaces are referred to respectively as the root platform wall and the tip platform wall. Each of these platform walls is constituted by a pressure side portion and a suction side portion situated respectively pressure side and on the suction side and meeting at a crest curve (45, 65). Fabrication of the blade is facilitated in particular by the fact that every point of a first surface selected from the pressure side and the suction side and every point of the root and tip platform wall portions situated on the same side as the first surface presents a normal forming an acute angle or a right angle relative to a direction referred to as the first fabrication direction. A method of modeling the blade.

Abstract: The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-side wall in pressure-side cavities, and radially toward the inside along the suction-side wall in a suction-side cavity that is separated from the pressure-side cavities by an internal wall of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-side and suction-side walls thereby limiting the inhomogeneity.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: The invention relates to a rotary mold for centrifugal casting of an alloy. The mold comprises liners (135a) housed in hollow exoskeletons (137a). The exoskeletons retain the liners against the centrifugal force, during the casting, while the mold is spinning.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: A blade for a turbomachine bladed wheel having N blades. At one end, the blade presents a platform that is formed integrally with an airfoil of the blade. Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil. Each of these segments forms an angle of 90°-180° /N relative to the radial direction on either side of the airfoil.

Abstract: A turbine nozzle for a turbomachine, the nozzle including two coaxial platforms interconnected by radial vanes, an inner platform being connected to an annular partition that is festooned or crenellated and on which there is fastened an annular support carrying elements made of abradable material. The support is capable of sliding circumferentially over the partition between a mounting-and-dismounting position and a position for locking the support on the partition.

Abstract: A method for manufacturing a metal component using the lost-wax casting method is provided. The component is made of nickel alloy, with a columnar or monocrystalline structure with at least one cavity of elongate shape. The method includes creating a wax model of the component with a ceramic core corresponding to said cavity, the ceramic core comprising a first land for holding at one longitudinal end and a second land for holding at the opposite end, creating a shell mold around the model, the mold comprising a base and the first land of the core being at the same end as the base, placing the mold in a furnace, with the base standing on the sole of the furnace, pouring the said molten alloy into the shell mold, solidifying the poured metal by gradual cooling from the sole in a direction of propagation.

Abstract: A method of fabricating at least one metal part for a turbine engine, the method including the steps of casting a metal alloy by centrifuging into a permanent metal mold for making a blank; obtaining a cast blank of elongate shape and of section that is circular or polygonal; and machining the blank to make the part.

Abstract: A turbomachine rotor blade presenting an outer part (314) at its distal end (310B), the outer part comprising a platform (320) defining the outside surface of the passage for gas passing through the turbomachine and presenting first (351) and second opposite side edges; and upstream and downstream sealing wipers (331, 332) extending outwards from said platform (320), each wiper extending between two lateral faces (331L, 332L) situated respectively at the first (351) and second side edges. The lateral faces (331L, 332L) of the upstream and downstream wipers (331, 332) are covered at least in part in an anti-wear material (360).

Abstract: A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold.

Abstract: A casting method for obtaining a part that includes a tapering portion, and also a turbine engine blade obtained by casting and including a tapering trailing edge. According to the invention, the method comprises the following steps: providing an insert element having a tapering portion; making a shell around the insert element; and casting a molten material into said shell including the insert element.

Abstract: The invention relates to a sectored distributor (112) for a turbomachine, including two coaxial platforms mutually connected by radial blades, the inner platform (130) being connected to an annular partition (138) for suspending an annular mounting (140) carrying elements (136) made of material subject to abrasion, this mounting sliding circumferentially on the partition and comprising a means engaging with means corresponding to the inner periphery of the partition to ensure radial restraint of the mounting on this partition.

Abstract: The turbomachine blade has ribs formed in the vicinity of the trailing edge. Over the major fraction of the trailing edge (42), in zones where the temperature in operation is particularly high, the ends (53) of the ribs are closer to the trailing edge and/or the sections of the ribs (F) are greater. Thereby, the design of the blade is optimized and the lifetime thereof is increased.

Abstract: A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold.

Abstract: The invention relates to a sectored distributor (112) for a turbomachine, including two coaxial platforms mutually connected by radial blades, the inner platform (130) being connected to an annular partition (138) for suspending an annular mounting (140) carrying elements (136) made of material subject to abrasion, this mounting sliding circumferentially on the partition and comprising a means engaging with means corresponding to the inner periphery of the partition to ensure radial restraint of the mounting on this partition.

Abstract: A turbine nozzle for a turbomachine, the nozzle including two coaxial platforms interconnected by radial vanes, an inner platform being connected to an annular partition that is festooned or crenellated and on which there is fastened an annular support carrying elements made of abradable material. The support is capable of sliding circumferentially over the partition between a mounting-and-dismounting position and a position for locking the support on the partition.

Abstract: The turbomachine blade has ribs formed in the vicinity of the trailing edge. Over the major fraction of the trailing edge (42), in zones where the temperature in operation is particularly high, the ends (53) of the ribs are closer to the trailing edge and/or the sections of the ribs (F) are greater. Thereby, the design of the blade is optimized and the lifetime thereof is increased.

Abstract: A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk. The air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.