Abstract: A turbine ring assembly having ring segments made of ceramic matrix composite material and each having first and second attachment tabs and a cavity for the circulation of air flow, a metal support having a first bracket and a second bracket bearing axially upstream against the second tab, a first metal flange arranged upstream of the first bracket and having an inner periphery bearing axially downstream against the first tab and an outer periphery fastened to the first bracket, and air passage orifices formed in the inner periphery of the first flange and/or in the second bracket, the orifices configured to ensure that the air flow passes from the cavity to the outside of the assembly.

Abstract: A high-pressure gas turbine for a turbomachine includes a nozzle guide vane assembly, an annular array of movable blades mounted downstream of the nozzle guide vane assembly, a bleed cavity, an upstream sealing element mounted on the nozzle guide vane assembly and a downstream sealing element mounted on the annular array of movable blades, a double baffle being formed by said upstream and downstream sealing elements, an external upstream cavity being formed in the upstream sealing element.

Abstract: A turbine including a casing and a nozzle including an outer metallic shroud secured to the casing, an inner metallic shroud, and a plurality of nozzle segments made of CMC forming a crown extending between the outer shroud and the inner shroud, each segment including a strut, an inner platform, an outer platform and at least one airfoil having a hollow profile traversed by the strut, wherein for each airfoil, the outer platform includes an axial stop extending in outward radial protrusion from the outer platform, and the outer metallic shroud comprises a complementary axial stop extending in inward radial protrusion from the outer metallic shroud, the axial stop being upstream and axially bearing against the complementary axial stop, and machined with an angle of machining chosen to adjust the orientation of said at least one blade of the segment with respect to the axial direction.

Abstract: A high-pressure gas turbine for a turbomachine includes a nozzle guide vane assembly, an annular array of movable blades mounted downstream of the nozzle guide vane assembly, a first recirculation cavity, a second recirculation cavity, and a bleed cavity. An upstream sealing element is mounted on the nozzle guide vane assembly and a downstream sealing element is mounted on the annular array of movable blades.

Abstract: A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

Abstract: A turbine ring assembly extending around a longitudinal axis and comprises: a plurality of ring angular sectors made of CMC material circumferentially arranged in such a way as to form a turbine ring, each sector comprising a base from which an upstream leg and a downstream leg extend radially, a ring support structure comprising: a spacer extending around the sectors and comprising a downstream flange in such a way that the downstream leg of each sector is held against the downstream flange, a upstream force-absorbing plate extending circumferentially around the longitudinal axis in such a way as to be in contact with the upstream leg of each sector and fixed to an upstream area of the spacer which extends in extension of the upstream leg.

Abstract: A turbine comprising a casing and a nozzle including an outer metallic shroud (9) secured to the casing, an inner metallic shroud, and a plurality of nozzle segments (20) made of CMC forming a crown extending between the outer shroud (9) and the inner shroud, each segment including a strut (6), an inner platform, an outer platform and at least one airfoil having a hollow profile traversed by the strut (6). For each airfoil (20), the outer platform (26) comprises an axial stop (260) extending in outward radial protrusion from the outer platform (26), and the outer metallic shroud (9) comprises a complementary axial stop (96) extending in inward radial protrusion from the outer metallic shroud (9), the axial stop (260) being upstream and axially bearing against the complementary axial stop (96), and machined with an angle of machining chosen to adjust the orientation of said at least one blade of the segment with respect to the axial direction (DA).

Abstract: A turbine ring assembly having ring segments made of ceramic matrix composite material and each having first and second attachment tabs and a cavity for the circulation of air flow, a metal support having a first bracket and a second bracket bearing axially upstream against the second tab, a first metal flange arranged upstream of the first bracket and having an inner periphery bearing axially downstream against the first tab and an outer periphery fastened to the first bracket, and air passage orifices formed in the inner periphery of the first flange and/or in the second bracket, the orifices configured to ensure that the air flow passes from the cavity to the outside of the assembly.

Abstract: A turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition —a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.

Abstract: A turbine ring assembly extending around a longitudinal axis and comprises: a plurality of ring angular sectors made of CMC material circumferentially arranged in such a way as to form a turbine ring, each sector comprising a base from which an upstream leg and a downstream leg extend radially, a ring support structure comprising: a spacer extending around the sectors and comprising a downstream flange in such a way that the downstream leg of each sector is held against the downstream flange, a upstream force-absorbing plate extending circumferentially around the longitudinal axis in such a way as to be in contact with the upstream leg of each sector and fixed to an upstream area of the spacer which extends in extension of the upstream leg.

Abstract: A turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition ?a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.

Abstract: A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.