A turbine guide apparatus, having multiple guide blades. Each guide blade has a first shroud and a second shroud formed on radial ends of a blade leaf having a first carrier for the guide blades. Each guide blade is fastened to the first carrier via a first shroud projection having a second carrier for the guide blades and is fastened on the second carrier via a second shroud projection. The first shroud projection is inserted into a groove of the first carrier in the radial direction and fastened in this groove via a bolt extending in the axial direction through the projection of the first shroud with radial mobility in this groove. The second shroud projection of the guide blade is fastened in the circumferential and radial direction via a pin extending in the axial direction into the projection of the second shroud and the second carrier.

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

A compressor section includes a compressor casing that has an upper casing portion coupled to a lower casing portion such that a split-line is defined between the upper casing portion and the lower casing portion. A split-line stator vane assembly includes a first split-line stator vane that has a first shank with a first platform portion and a first mounting portion extends radially outward of the first platform portion. A first airfoil extends radially inward of the platform portion. The first platform portion includes a protrusion that extends circumferentially beyond the split-line. A second split-line stator vane having second shank with a second platform portion and a second mounting portion extends radially outward of the second platform portion. A second airfoil extends radially inward of the second platform portion. The second platform portion includes a recess that extends circumferentially away from the split-line.

The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).

An assembly for a turbomachine turbine includes a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) including at least one radial bearing surface of an oblong hole capable of cooperating with support pins (13, 14) of the housing (1), at least one of the sides (17, 18) including means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.

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.

Methods of manufacturing a bladed stator element for a turbomachine include mounting a tool on a circumferential zone of an annular shell prior to welding vanes in the circumferential zone, welding radially outer ends of the vanes to the annular shell, dismantling the tool after welding the vanes in the circumferential zone, and repeatedly mounting and dismounting the tool on different circumferential zones of the annular shell so as to fix the vanes all around the annular shell.

A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.

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.