Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.

Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.

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 nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.

Abstract: A device for cooling a turbine shroud comprising at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream, with respect to a circulation direction of an air flow, of the turbine shroud, and comprising at least one cooling air circulation channel, a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject on a radially external face of the shroud, via the injection holes, the cooling air originating in the intake channel, and a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings.

Abstract: A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.

Abstract: The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.

Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.

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: The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.

Abstract: Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there extend in a projecting manner an upstream attachment lug (14) and a downstream attachment lug (16), the support structure comprising a collar (31), from which there radially extend in a projecting manner towards the shroud an upstream radial flange (32) and a downstream radial flange (36), by which the lugs of each section of the shroud are retained, the shroud (1) being retained by axial pins (119, 120) which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (33, 34), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.

Abstract: An assembly for a turbomachine turbine includes at least one ring sector made of CMC material and a support casing including an upstream flange and a downstream flange between which each ring sector is disposed, each ring sector including a base that has a radially external face from which radially extend two lugs, the lugs of each ring sector being retained between the two flanges of the support casing by axial pins each engaged in one of the flanges of the ring support casing and in the lug of the ring sector facing said flange, the assembly further including, for each ring sector, at least one radial retaining pin screwed into the support casing and coming to radially bear against a lug of the at least one ring sector to retain it in position, and anti-rotation system for rotationally locking the radial retaining pin.

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 method for assembling/disassembling a turbine ring assembly including a turbine ring of ceramic matrix composite material and a ring support structure of metal equipped with a central shroud and with at least one single-piece annular plate positioned upstream of the ring with respect to the direction of an air flow passing through the assembly, the plate having in the radial direction a first free end and a second end opposite to the first end, the second end being removably attached to the first radial flange and shrink-fit to the central shroud, is disclosed. The method for assembling/disassembling includes, before the assembling/disassembling of the plate, a step of deformation of the central shroud and/or of the at least one annular plate.

Abstract: A turbine shroud sector made of ceramic matrix composite, of longitudinal axis X and which includes a base with a radially internal face, a radially external face from which there extend upstream and downstream tabs for attachment to a shroud support structure. The base includes a first slot and a second slot, which is arranged radially on the outside of the first slot. The slots are formed in the lateral face. A first and a second sealing strip rest against a radially internal wall of the first and second slots. The first strip has the overall shape of an omega and the shroud sector exhibits a first clearance which is defined radially between a central part of the first strip and the radially internal wall of the first slot, and a second clearance which is defined radially between this central part and a radially external wall of the first slot.

Abstract: A turbine of a turbo engine includes a casing and a nozzle stage including an outer metal shroud secured to the casing, an inner metal shroud, and a plurality of ring sectors made of ceramic-matrix composite material each having an internal platform, an external platform and at least one blade extending between the external platform and the internal platform and secured thereto. The internal platform of each sector includes a first and a second tab protruding radially inwardly from respectively an upstream end and a downstream end of the internal platform, and the inner shroud includes a shoulder protruding radially outwardly and being in abutment upstream against the first tab, and a clamp downstream of the shoulder including two jaws extending radially outwardly and held under stress towards each other against the second tab.

Abstract: A device for cooling a turbine shroud comprising at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream, with respect to a circulation direction of an air flow, of the turbine shroud, and comprising at least one cooling air circulation channel, a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject on a radially external face of the shroud, via the injection holes, the cooling air originating in the intake channel, and a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings.

Abstract: Turbine comprising a casing and a nozzle including a metal outer shroud integral with the casing, a metal inner shroud, and a plurality of nozzle sectors of CMC forming a ring extending between the metal outer shroud and the metal inner shroud, each sector including a mast, an inner platform, an outer platform and at least one airfoil having a hollow profile defining an inner recess, each of the inner and outer platforms having an opening communicating with said inner recess, and the mast passing through said openings and the inner recess and being attached to said casing and connected with said nozzle sector. The mast comprises at least one fastening projection having at least one portion extending from a radially outer end of the mast in a direction opposite to the center of the mast and in a plane orthogonal to the radial direction.

Abstract: A turbine of a turbo engine including a casing and a turbine nozzle stage, the turbine nozzle stage including an outer metal shroud secured to the casing, an inner metal shroud, and a plurality of ring sectors made of ceramic-matrix composite material forming a crown extending between the outer metal shroud and the inner metal shroud and having an internal shroud and an external shroud, each ring sector having an internal platform forming a portion of the internal shroud, an external platform forming a portion of the external shroud, and at least one blade extending between the external platform and the internal platform and secured thereto. Each sector is fixed to the outer metal shroud using at least one assembly including a screw and a nut, the screw passing through the outer platform of the sector and the outer metal shroud.