Abstract: A turbine stage in a turbomachine including ring sectors arranged about a turbine impeller, and an annular support supporting the ring sectors and attached to a turbine casing is disclosed. The annular support is able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Abstract: A turbine ring sector is disclosed. The turbine ring sector includes a wall bounding an aerodynamic flowpath in which gases flow from the upstream region toward the downstream region, and a multiperforated plate, situated on the opposite side of the aerodynamic flowpath with respect to the wall. The multiperforated plate includes a bottom and side walls. The distance between the wall of the ring sector and the bottom of the multiperforated plate defines a gap which is progressive in an axial direction, from the upstream region toward the downstream region. The value of the gap situated at the upstream region is below the value of the gap situated at the downstream region.

Abstract: A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract: A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.

Abstract: Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring (22) held by a casing (24) of the turbine, and an annular thermal protection sheet mounted between the casing (24) and the ring (22), wherein the annular thermal protection sheet is formed by a plurality of curved plates (54, 56) mounted end-to-end and attached by pins (70) to the casing (24).

Abstract: High-pressure turbine of a turbomachine A high-pressure turbine (10) of a turbomachine, comprising at least one upstream guide vane element (16) and an impeller (18) mounted so as to rotate inside ring sectors (20) attached to an annular support (24) which is suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means of attachment to an inner casing and, at its radially outer end, means (102, 104) for pressing axially on a fixed element (90) of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract: A turbine stage in a turbomachine comprising ring sectors (20) arranged about a turbine impeller (18), and an annular support (50) supporting the ring sectors and attached to a turbine casing (22), this annular support being able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Abstract: The present invention concerns the field of turbomachines, in particular the cooling of the ring sectors (1) of a turbine (8) of a turbomachine (9). It more specifically concerns a turbine ring sector (1) comprising: a wall (11) bounding an aerodynamic flowpath (5) in which gases flow from the upstream region (52) toward the downstream region (53), and a multiperforated plate (2), situated on the opposite side of the aerodynamic flowpath (5) with respect to the wall (11), said multiperforated plate (2) comprising a bottom (21, 121, 221, 321) and side walls (22, 23), the distance between the wall (11) of the ring sector (1) and the bottom (21, 121, 221, 321) of the multiperforated plate (2) defining a gap (7) which is progressive in an axial direction, from the upstream region (52) toward the downstream region (53). According to the invention, the value of the gap situated at the upstream region (52) is below the value of the gap situated at the downstream region (53).