Abstract: A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams.

Abstract: A material comprising an encapsulated component within a shell, a rupture initiator associated with the encapsulated component, and a polymeric matrix material, wherein the encapsulation is adapted to fail upon activation of the rupture initiator allowing the encapsulated component to be liberated to initiate a reaction or increase the reactivity of the material.

Abstract: A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams.

Abstract: A turbomachine blade that includes an airfoil that includes an intrados wall, an extrados wall, a leading edge, a trailing edge, an internal cavity and a plurality of cooling holes made in the walls and leading and trailing edges, each cooling hole connecting the internal cavity to the exterior, one end of each cooling hole opening up into the cavity, the other end of each cooling hole opening to the exterior through an outlet, wherein the cooling holes are distributed in at least one first alignment and a second alignment made in a wall of the airfoil, wherein this outlet of at least one of the cooling holes belonging to at least the second alignment is an oblong shape with its long dimension along the principal direction of said second alignment.

Abstract: A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.

Abstract: A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

Abstract: A method for producing a rotor vane (10) for a turbomachine, including producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the axis.

Abstract: A turbine engine blade includes an airfoil connected by a platform to a middle radial wall extending axially and prolonged radially inwards by a blade root that is mountable in a slot of a disk, and the platform and the middle radial wall defining two lateral cavities situated on either side of the middle radial wall and opening out circumferentially to receive scaling members. The cavities are open downstream with two fins projecting on either side of the middle radial wall at downstream end of the middle radial wall, the fins coming to bear against two adjacent teeth of the disk between which the slot is formed. The downstream end of the middle radial wall includes a setback extending between at least one rib of the platform and the fins.

Abstract: A turbomachine vane for cooperating with a vane retention disk including a plurality of peripheral teeth, the vane including a shank including a neck and a bulb for cooperating with a socket of the disk so as to radially hold the shank in the socket, the socket being a space bounded by two successive teeth of the disk, a pole on top of the neck, including two side walls facing the active surface side of the vane and two side walls facing the passive surface side of the vane, each wall having a rib at a lower end of the pole, the rib extending in the direction of the side wall facing the wall and providing a function of holding the vane when the vane is retained in the disk.

Abstract: The invention relates to a blade preform (46) including a strut connecting a plat-form (16) to a blade root portion (14) extending longitudinally in an upstream-downstream direction, an upstream web (26) and a downstream (28) web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream (26) and downstream (28) webs connect the upstream and downstream ends of the plat-form (16) to the upstream and downstream ends of the blade root (14). According to the invention, the blade root (14) extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs (26, 28) and the side edges (40) of each web (26, 28) are extended by walls that converge (44) at the flanks of the blade root.

Abstract: The invention relates to a method for producing a rotor vane (10) for a turbomachine, comprising a step consisting in producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to the above-mentioned axis, said method comprising an additional step of machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the above-mentioned axis.

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 turbomachine vane for cooperating with a vane retention disk including a plurality of peripheral teeth, the vane including a shank including a neck and a bulb for cooperating with a socket of the disk so as to radially hold the shank in the socket, the socket being a space bounded by two successive teeth of the disk, a pole on top of the neck, including two side walls facing the active surface side of the vane and two side walls facing the passive surface side of the vane, each wall having a rib at a lower end of the pole, the rib extending in the direction of the side wall facing the wall and providing a function of holding the vane when the vane is retained in the disk.

Abstract: The invention relates to a turbine engine blade (1) comprising an airfoil (2) connected by a platform (3) to a middle radial wall (4) extending axially and prolonged radially inwards by a blade root (5) for mounting in a slot (6) of a disk (7), the platform (3) and said middle wall (4) defining two lateral cavities (16) situated on either side of said middle wall (4) and opening out circumferentially for the purpose of receiving sealing members. Said cavities (16) are open downstream with two fins (21) projecting on either side of said middle wall (4) at its downstream end, said fins (21) coming to bear against two adjacent teeth (19) of the disk (7) between which the slot (6) is formed. The downstream end (22) of the middle wall (4) including a setback (24) extending between said rib (20) and the fins (21).