Abstract: The invention concerns a fixed flow distribution blading (10) in a turbomachine, comprising two coaxial annular platforms that are internal (12) and external respectively, linked to each other by a plurality of radial blades (11), in which the internal annular platform (12) comprises an annular radial partition (120) and a blade support ring (121) extending to each side of an outer radial end of said partition (120), the blading (10) further comprising an annular sealing plate (20) mounted on the internal annular platform (12), on the upstream side of the radial partition relative to an airflow in the blading, the blading (10) being characterized in that the sealing plate (20) is mounted on the blade support ring (121), and in that it comprises a circumferential groove. The invention also concerns a method for producing such a blading and a turbomachine comprising such a blading.

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract: The invention concerns a fixed flow distribution blading (10) in a turbomachine, comprising two coaxial annular platforms that are internal (12) and external respectively, linked to each other by a plurality of radial blades (11), in which the internal annular platform (12) comprises an annular radial partition (120) and a blade support ring (121) extending to each side of an outer radial end of said partition (120), the blading (10) further comprising an annular sealing plate (20) mounted on the internal annular platform (12), on the upstream side of the radial partition relative to an airflow in the blading, the blading (10) being characterised in that the sealing plate (20) is mounted on the blade support ring (121), and in that it comprises a circumferential groove. The invention also concerns a method for producing such a blading and a turbomachine comprising such a blading.

Abstract: A part of a turbomachine distributor, including an outer platform, an inner platform, at least one blade interspaced circumferentially about a longitudinal axis of the part, radial ends of the at least one blade being respectively fixed to the inner platform and to the outer platform, and a fastening element extending from the outer platform, for fastening the part to a casing of the turbomachine. The fastening element includes, on ends thereof arranged on either side of the longitudinal axis, two separate fastening tabs for fastening the part to the casing, the cumulated sum of lengths of the two fastening tabs in relation to length of the fastening element according to a transverse axis of the part being between 25% and 35%.