Abstract: A turbine ring assembly extending about an axis, includes a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure held by a turbine casing, each ring sector including a base from which an upstream lug and a downstream lug spaced axially from each other extend radially outwardly, the ring support structure including a spacer having a clamp against which the downstream lug of the ring sectors is held, a first upstream flange against which the upstream lug of the ring sectors is held, and upstream of the first upstream flange, a second upstream flange for absorbing forces against which the first upstream flange is held.

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 ring assembly includes ring segments forming a turbine ring and a ring support structure, each segment having a part forming an annular base with, in the radial direction, an inner face and an outer face from which project a first and a second hooking tab, the structure including a shroud from which project a first and a second radial flange between which are retained the first and second tabs, a first annular flange made of one part and a second annular flange disposed upstream of the ring. The first flange includes an annular shoulder and the second flange includes an annular recess forming an axial stop cooperating with the shoulder.

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 turbine ring assembly includes ring segments forming a turbine ring and a ring support structure, each segment having a part forming an annular base with, in the radial direction, an inner face and an outer face from which project a first and a second hooking tab, the structure including a shroud from which project a first and a second radial flange between which are retained the first and second tabs, a first annular flange made of one part and a second annular flange disposed upstream of the ring. The first flange includes an annular shoulder and the second flange includes an annular recess forming an axial stop cooperating with the shoulder.

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 ring assembly includes adjacent ring sectors forming a turbine ring, each ring sector having a platform with an inner face defining the inner face of the turbine ring and an outer face from which an upstream lug and a downstream lug extend along the radial direction. Each ring sector includes a first groove present in the platform in the vicinity of the inner face of the platform, a second groove present in the platform in the vicinity of the outer face of the platform, an upstream groove extending into the upstream lug and a downstream groove extending into the downstream lug. A first sealing tab extends into the first groove. A second sealing tab extends into the second groove. An upstream sealing tab extends into the upstream groove. A downstream sealing tab extends into the downstream groove. The second sealing tab includes at least one opening.

Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each sector having, along a cutting plane defined by an axial direction and a radial direction of the ring, a portion forming an annular base with, in the radial direction, an inner face and an outer face from which a first and a second lug protrude, the structure including a shroud from which protrude a first and a second radial clamp from which the first and second lugs are held. The turbine ring includes an annular flange having a first portion bearing against the first lug, and a second portion removably fixed to the first radial clamp, the first portion including radial slits open on a free end of the annular flange and delimiting first-portion sectors.

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.

Abstract: A turbine ring assembly includes adjacent ring sectors forming a turbine ring, each ring sector having a platform with an inner face defining the inner face of the turbine ring and an outer face from which an upstream lug and a downstream lug extend along the radial direction. Each ring sector includes a first groove present in the platform in the vicinity of the inner face of the platform, a second groove present in the platform in the vicinity of the outer face of the platform, an upstream groove extending into the upstream lug and a downstream groove extending into the downstream lug. A first sealing tab extends into the first groove. A second sealing tab extends into the second groove. An upstream sealing tab extends into the upstream groove. A downstream sealing tab extends into the downstream groove. The second sealing tab includes at least one opening.

Abstract: A sector of a sectorized annular nozzle of a turbine of a turbomachine comprises an outer platform having an outer wall connected to a coaxial inner wall via at least one straightening fixed blade. The outer platform includes hooking means that hook the outer platform to a turbine fixed casing. The outer platform includes an outer circular shell, axially offset with respect to the outer wall and integrally formed with the outer wall, and the outer shell is intended to surround an angular portion of a rotor wheel. The hooking means includes an upstream circular edge and a downstream circular edge extending axially, said upstream and downstream edges being respectively configured to attach to an upstream hook and a downstream hook of said turbine casing, and said upstream and downstream edges being oriented in the downstream direction.

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 turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each sector having, along a cutting plane defined by an axial direction and a radial direction of the ring, a portion forming an annular base with, in the radial direction, an inner face and an outer face from which a first and a second lug protrude, the structure including a shroud from which protrude a first and a second radial clamp from which the first and second lugs are held. The turbine ring includes an annular flange having a first portion bearing against the first lug, and a second portion removably fixed to the first radial clamp, the first portion including radial slits open on a free end of the annular flange and delimiting first-portion sectors.

Abstract: A sector of a sectorized annular nozzle of a turbine of a turbomachine comprises an outer platform having an outer wall connected to a coaxial inner wall via at least one straightening fixed blade. The outer platform includes hooking means that hook the outer platform to a turbine fixed casing. The outer platform includes an outer circular shell, axially offset with respect to the outer wall and integrally formed with the outer wall, and the outer shell is intended to surround an angular portion of a rotor wheel. The hooking means includes an upstream circular edge and a downstream circular edge extending axially, said upstream and downstream edges being respectively configured to attach to an upstream hook and a downstream hook of said turbine casing, and said upstream and downstream edges being oriented in the downstream direction.