Abstract: A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).

Abstract: A rotary assembly of an aviation turbine engine, includes a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk. The tooth of the fan disk includes a tab extending the tooth axially upstream, and the platform includes a locking ring at its upstream end for receiving the tab of the tooth of the fan disk. The assembly further includes a spacer positioned inside the locking ring so as to block the platform on the tab of the tooth of the fan disk.

Abstract: A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).

Abstract: A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).

Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.

Abstract: A rotary assembly of an aviation turbine engine, includes a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk. The tooth of the fan disk includes a tab extending the tooth axially upstream, and the platform includes a locking ring at its upstream end for receiving the tab of the tooth of the fan disk. The assembly further includes a spacer positioned inside the locking ring so as to block the platform on the tab of the tooth of the fan disk.

Abstract: A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).

Abstract: A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).

Abstract: A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).

Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.