Abstract: The turbine (12) for a turbine engine (100) extends around a major axis (X-X) and comprises: —a casing (4) comprising an annular hook (38), —a movably mounted impeller (16), —a ring (30) extending opposite the impeller in a direction radial to the major axis (XX), —a distributor (14) comprising a blade provided with a platform (11), the platform being extended radially outwards by a spoiler (22, 24), the spoiler (22, 24) being radially mounted on the hook (38), and —foils (40) each having a profiled trough shape in a direction circumferential to the axis, the foils extending in succession in the circumferential direction, each foil (40) extending between the spoiler (22, 24) and the hook (38). The turbine comprises stops (162) to prevent the foils (40) from moving in the circumferential direction. Each foil (40) comprises a protrusion (162) arranged so as to extend circumferentially opposite another protrusion (162) of another adjacent foil (40).

Abstract: The turbine (12) for a turbine engine (100) extends around a major axis (X-X) and comprises: - a casing (4) comprising an annular hook (38), - a movably mounted impeller (16), - a ring (30) extending opposite the impeller in a direction radial to the major axis (XX), - a distributor (14) comprising a blade provided with a platform (11), the platform being extended radially outwards by a spoiler (22, 24), the spoiler (22, 24) being radially mounted on the hook (38), and - foils (40) each having a profiled trough shape in a direction circumferential to the axis, the foils extending in succession in the circumferential direction, each foil (40) extending between the spoiler (22, 24) and the hook (38). The turbine comprises stops (162) to prevent the foils (40) from moving in the circumferential direction. Each foil (40) comprises a protrusion (162) arranged so as to extend circumferentially opposite another protrusion (162) of another adjacent foil (40).

Abstract: Assembly (2) comprising an annular turbine distributor (3) for turbomachinery (1), an annular structural element (4) of the turbomachinery (1), coaxial with the distributor (3) and at least one device (5) for attaching the annular distributor (3) with the annular structural element (4), characterised in that: —the annular distributor (3) is crossed by at least two axial passages, and —the or each attachment device (5) comprises: at least two pins (15), rigidly connected to the annular structural element (4) and passing through one of said passages of the distributor (3), a first transverse stop (16) for stopping the distributor (3) axially and passing through two consecutive pins (15), and two second stops (17) rigidly connected to the structural element (4) to retain, in the pins (15), the first transverse stop (16) for stopping the distributor (3) radially.

Abstract: The present invention relates to an assembly (10) comprising: an annular nozzle (4) of a turbine of a turbine engine, a structural annular element (6) of the turbine engine, the nozzle (4) and the structural annular element (6) each comprising a radial flange (16, 18), the flanges being applied axially onto one another, and at least one member (12) for axially retaining the flange (16) of the nozzle (4) with the flange (18) of the structural annular element (6), with the member being applied to one of the flanges and being able to axially retain the two flanges one on top of the other.

Abstract: Assembly (2) comprising an annular turbine distributor (3) for turbomachinery (1), an annular structural element (4) of the turbomachinery (1), coaxial with the distributor (3) and at least one device (5) for attaching the annular distributor (3) with the annular structural element (4), characterised in that: —the annular distributor (3) is crossed by at least two axial passages, and —the or each attachment device (5) comprises: at least two pins (15), rigidly connected to the annular structural element (4) and passing through one of said passages of the distributor (3), a first transverse stop (16) for stopping the distributor (3) axially and passing through two consecutive pins (15), and two second stops (17) rigidly connected to the structural element (4) to retain, in the pins (15), the first transverse stop (16) for stopping the distributor (3) radially.

Abstract: The present invention relates to an assembly (10) comprising: an annular nozzle (4) of a turbine of a turbine engine, a structural annular element (6) of the turbine engine, the nozzle (4) and the structural annular element (6) each comprising a radial flange (16, 18), the flanges being applied axially onto one another, and at least one member (12) for axially retaining the flange (16) of the nozzle (4) with the flange (18) of the structural annular element (6), with the member being applied to one of the flanges and being able to axially retain the two flanges one on top of the other.

Abstract: The turbine (1) has a rotor (2) with blades (4) arranged on a periphery of disks (5) in radial planes (3), and a tie rod (6) extending along slots (7) in the disks. An annular spacer (15, 15?) fixes a position of the tie rod relative to a center line (M) of the disks, and is arranged in a channel (10, 11). The spacer has through-openings, which are arranged radially relative to the tie rod or to its center line, and extend coaxially. The channel carries a cooling medium and is limited by a separating pipe (13, 14) radially outwards. The through-openings serve for flow of the medium.

Abstract: The invention relates to a turbomachine (30) comprising: a compressor stage and a turbine stage, each stage comprising at least one disk (42); and a tubular shaft (31) sleeve (33) extending along the axis (32) of the turbomachine, wherein the sleeve (33) comprises at least one tab (40) extending from an outer radial surface (41) of the sleeve and facing the disk (42), the tab (40) being designed to come into contact with the disk (42) when the sleeve (33) is in rotation about the axis (32) of the turbomachine.