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 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 turbine ring assembly including ring sectors forming a turbine ring and a ring support structure, each sector having, in a section plane defined by an axial direction and a radial direction of the ring, a first and a second attachment tabs extending in the radial direction, and the structure including a central shell ring from which extend as projections a first and a second radial flanges between which are retained the first and second attachment tabs of each sector. Each sector includes rectilinear seatings mounted on the faces of the first and second attachment tabs in contact, respectively, with the second annular flange and the annular ring-flange and including, along a tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second ends of the sector and a maximum thickness in a median portion of the rectilinear seating.

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 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 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 ring assembly including ring sectors forming a turbine ring and a ring support structure, each sector having, in a section plane defined by an axial direction and a radial direction of the ring, a first and a second attachment tabs extending in the radial direction, and the structure including a central shell ring from which extend as projections a first and a second radial flanges between which are retained the first and second attachment tabs of each sector. Each sector includes rectilinear seatings mounted on the faces of the first and second attachment tabs in contact, respectively, with the second annular flange and the annular ring-flange and including, along a tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second ends of the sector and a maximum thickness in a median portion of the rectilinear seating.

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 including a ring support structure and a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, each sector presenting in a first section plane defined by an axial direction and a radial direction of the ring a portion forming an annular base having, in the radial direction, an inner face and an outer face from which there extend two attachment tabs defining between them a circumferentially-open annular cavity, the structure including two radial tabs between which the attachment tabs are held, and at least one injection orifice for injecting a stream of cooling air into the annular cavity. In a second section plane containing the axial direction and a direction orthogonal to the first section plane, the orifice forms a first feed angle relative to the direction orthogonal to the first section plane, the first feed angle lying in the range ?80° to +80°.

Abstract: A turbine ring assembly including ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section 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 defining the inner face of the ring and an outer face from which a first and a second attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the first and second attachment tabs of each ring sector are maintained. It includes a first and a second annular flanges removably fastened to the first radial clamp of the central shroud and separated from each other by a contact abutment.

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 ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section 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 attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the attachment tabs of each ring sector are maintained. The turbine ring assembly includes a first and a second annular flanges removably fastened to the first radial clamp, the second annular flange including a bearing shroud protruding upstream in the axial direction and having a radial bearing in contact with the central 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 turbine ring assembly including ring sections forming a turbine ring and a ring support structure, each ring section having, along a section plane defined by an axial direction and a radial direction of the ring, a part forming an annular base with, in the radial direction, an inner face and an outer face, from which a first and a second fastening lug project, the structure including a central shroud, from which a first and a second radial clamp project, between which the fastening lugs of each ring section are maintained. It includes a first and a second annular flange detachably fixed to the first radial clamp, the second annular flange including a support shroud projecting upstream in the axial direction and having a radial support in contact with the central shroud.

Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section 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 attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the attachment tabs of each ring sector are maintained. The turbine ring assembly includes a first and a second annular flanges removably fastened to the first radial clamp, the second annular flange including a bearing shroud protruding upstream in the axial direction and having a radial bearing in contact with the central shroud.

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.