Abstract: The invention relates to a motor vane for a turbine engine, comprising a body (170) locally defining a blade provided at the radially outer end with a root (33), characterised in that it also comprises at least one sealing element (39) extending beyond the radially outer end of the root and connected to an area of the root by means of a movable mechanical link (37).

Abstract: A nozzle sector for a turbine engine. The nozzle sector includes a radially outer platform, a radially inner platform, a first end blade, a second end blade and at least one first central blade between the end blades in a circumferential direction of the platforms. The blades extend radially between the platforms in the direction of the span of said blades. The sector includes means for cooling the blades, configured to cool each of the blades by circulating cooling air over same. The cooling means are configured to cool the one or more central blades more than at least one of the end blades.

Abstract: A vane (54) for a turbomachine, comprises an aerodynamic profile (61) formed from a body (70) made from a first material, and an add-on part (74) fixed to the body (70) by brazing and made from a second material. The add-on part (74) is housed in a recess (72) formed in a median part of an end part (73) of the body (70), between extreme parts (73A, 73B) of the end part, such that the add-on part (74) forms a median portion of the leading edge (62) of the aerodynamic profile (61). The second material has a coefficient of linear thermal expansion along the direction of the leading edge greater than that of the first material, at a normal operating temperature of the vane (54), which reduces risks of cracks appearing in the aerodynamic profile (61).

Abstract: The invention relates to a motor vane for a turbine engine, comprising a body (170) locally defining a blade provided at the radially outer end with a root (33), characterised in that it also comprises at least one sealing element (39) extending beyond the radially outer end of the root and connected to an area of the root by means of a movable mechanical link (37).

Abstract: A blade sector of a turbine distributor to be carried by a turbine casing of an aeronautical turbine engine, including a front connection mechanism and a rear connection mechanism, wherein the front connection mechanism is adapted so as to bear against a holder carried by the turbine casing. The sector further includes an anti-wear device formed by a piece of a metal material surrounding the front end of the front connection mechanism and provided between the front connection mechanism and the holder to ensure a sliding contact between the two parts. The anti-wear device is axially maintained in position on the blade sector using an attachment mechanism engaging with the front connection mechanism.

Abstract: A turbine nozzle sector that includes an outer platform segment and an inner platform segment between which there extends one or more hollow vanes is disclosed. Each vane presents a trailing edge cavity for feeding with cooling air and communicating with a plurality of vents distributed along the trailing edge of the vane, these vents serving to exhaust a fraction of the cooling air. The cavity communicates with an air outlet hole situated level with the outer platform and enabling a fraction of the cooling air to be exhausted.

Abstract: A blade sector of a turbine distributor to be carried by a turbine casing of an aeronautical turbine engine, including a front connection mechanism and a rear connection mechanism, wherein the front connection mechanism is adapted so as to bear against a holder carried by the turbine casing. The sector further includes an anti-wear device formed by a piece of a metal material surrounding the front end of the front connection mechanism and provided between the front connection mechanism and the holder to ensure a sliding contact between the two parts. The anti-wear device is axially maintained in position on the blade sector using an attachment mechanism engaging with the front connection mechanism.

Abstract: The present invention relates to an impeller blade for turbomachine formed by molding, comprising a blade, at one end of which is provided a heel formed of a single piece with the blade, to which it is joined at the level of a connection area, the heel comprising a platform on which is provided at least one sealing plate, a first bath being provided in the platform, characterized in that a second bath is provided in the first bath, at the level of the connection area between the blade and the heel.

Abstract: An assembly includes a vane and a cooling liner for cooling the vane, the vane having a central cavity with at least one first opening into which the liner extends, the liner having a flange fixed to the rim of the opening. This assembly includes, near the flange, a peripheral insert inserted between the wall of the liner and the wall of the opening.

Abstract: The present invention relates to an impeller blade for turbomachine formed by molding, comprising a blade, at one end of which is provided a heel formed of a single piece with the blade, to which it is joined at the level of a connection area, the heel comprising a platform on which is provided at least one sealing plate, a first bath being provided in the platform, characterized in that a second bath is provided in the first bath, at the level of the connection area between the blade and the heel.

Abstract: A turbine nozzle sector that comprises an outer platform segment and an inner platform segment between which there extend one or more hollow vanes. Each vane presents a trailing edge cavity for feeding with cooling air and communicating with a plurality of vents distributed along the trailing edge of the vane, these vents serving to exhaust a fraction of the cooling air. Said cavity communicates with an air outlet hole situated level with the outer platform and enabling a fraction of the cooling air to be exhausted.

Abstract: The assembly of the invention is comprised of a vane (2) and of a cooling liner (6) for cooling the vane (2), the vane (2) comprising a central cavity (5) with at least one first opening (7) into which the liner (6) extends, the liner (6) comprising a flange (13) fixed to the rim (14) of the opening (7). This assembly is one which comprises, near the flange (13), a peripheral insert (16) inserted between the wall of the liner (6) and the wall (7?) of the opening (7). Thus the joint at the flange (13) is sealed.