Abstract: The invention relates to an assembly which includes: two rotationally symmetrical components (10, 20) for supporting the blades of a turbine engine, arranged one inside the other concentrically about a turbine engine axis, and a system (30) for locking the components (10, 20) such as to prevent the relative translation of same in the axial and radial directions relative to said axis, the system including a slotted ring (40) comprising a U-shaped cross-section suitable for receiving one end of the components (10, 20), the assembly being characterized in that the ring (40) and one of the components (10, 20) are shaped such as to allow the ring to be interlocked on the component, and in that the locking system (30) also includes a member for stopping the rotation of the ring relative to the component with which the latter is interlocked. The invention further relates to a method for assembling such an assembly.

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract: A device for connecting a fixed turbine engine portion and a distributor foot of a turbine engine turbine is provided. The device includes a ring-shaped body adapted so as to be connected and secured to the fixed turbine engine portion, and two ring-shaped upstream and downstream brackets secured to the body, both brackets being adapted so as to clamp the foot of the distributor. At least one bracket is interrupted by forming an expansion or retraction slot, the slot allowing an expansion of the bracket tending to close the slot or retraction of the bracket tending to further open the slot, under the effect of a difference in internal temperatures of the device.

Abstract: The invention relates to an assembly which includes: two rotationally symmetrical components (10, 20) for supporting the blades of a turbine engine, arranged one inside the other concentrically about a turbine engine axis, and a system (30) for locking the components (10, 20) such as to prevent the relative translation of same in the axial and radial directions relative to said axis, the system including a slotted ring (40) comprising a U-shaped cross-section suitable for receiving one end of the components (10, 20), the assembly being characterised in that the ring (40) and one of the components (10, 20) are shaped such as to allow the ring to be interlocked on the component, and in that the locking system (30) also includes a member for stopping the rotation of the ring relative to the component with which the latter is interlocked. The invention further relates to a method for assembling such an assembly.

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract: A device (1) for connecting a fixed turbine engine portion (2) and a distributor (3) foot (31) of a turbine engine turbine, comprising a ring-shaped flange (111), the flange (111) being adapted so as to be connected and secured to the fixed turbine engine portion (2) and to the foot (31) of the distributor, the device being characterized in that it further comprises a ring-shaped screen (9), the screen (9) being connected and secured to the flange (111) so as to be positioned in an upstream chamber (4) made between the fixed turbine engine portion (2) and the flange (111) so as to at least partly block heat radiation from the fixed turbine engine portion (2) and directed towards the flange (111).

Abstract: A device (1) for connecting a fixed turbine engine portion (2) and a distributor (3) foot (31) of a turbine engine turbine, comprising: a ring-shaped body (11) adapted so as to be connected and secured to the fixed turbine engine portion (2), and two ring-shaped upstream (12) and downstream (13) brackets secured to the body (11), both brackets (12, 13) being adapted so as to clamp the foot (31) of the distributor, characterized in that at least one bracket (12, 13) is interrupted by forming an expansion or retraction slot (121, 131), the slot (121, 131) allowing an expansion of the bracket (12, 13) tending to close the slot (121, 131) or retraction of the bracket (12, 13) tending to further open the slot (121, 131), under the effect of a difference in internal temperatures of the device.