Abstract: A moving blade of a low pressure turbine includes a foot and a vane having an upper surface and a lower surface, the foot having a stilt linking the vane to the foot, wherein the stilt is formed such that the transverse section of the stilt has: a first straight portion, a second curved portion and a third straight portion, the curved portion having an outer face matching the profile of the upper surface of the vane and an inner face matching the profile of the lower surface of the vane.

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 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 moving blade of a low pressure turbine includes a foot and a vane having an upper surface and a lower surface, the foot having a stilt linking the vane to the foot, wherein the stilt is formed such that the transverse section of the stilt has: a first straight portion, a second curved portion and a third straight portion, the curved portion having an outer face matching the profile of the upper surface of the vane and an inner face matching the profile of the lower surface of the vane.

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).