Abstract: An assembly for gas turbine, includes a first part and a second part installed circumferentially around a longitudinal axis of the turbine, where the first part has a first side face adjacent to a second side face of the second part, and where a first aperture made in first side face is facing a second aperture made in second side face, a sealing plate fitted inside the first aperture and the second aperture, at least one longitudinal face of the sealing plate includes at least two projections made either side of a longitudinal central area of the sealing plate, wherein each projection is of a height chosen so as to reduce a clearance between the sealing plate and the first and second apertures.

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: An assembly for gas turbine, includes a first part and a second part installed circumferentially around a longitudinal axis of the turbine, where the first part has a first side face adjacent to a second side face of the second part, and where a first aperture made in first side face is facing a second aperture made in second side face, a sealing plate fitted inside the first aperture and the second aperture, at least one longitudinal face of the sealing plate includes at least two projections made either side of a longitudinal central area of the sealing plate, wherein each projection is of a height chosen so as to reduce a clearance between the sealing plate and the first and second apertures.

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.