Assembly for a turbine engine

A turbomachine (1) comprising, from upstream to downstream with respect to the direction of gas flow within the turbomachine (1);

• a fan (2);
• a high-pressure compressor (3);
• a low-pressure compressor (4);
• a combustion chamber;
• a high-pressure turbine (5);
• a low-pressure turbine (6);
• and
• an assembly extending about an axis (X), comprising:
• a radially outer shaft (7) rotatably coupled to the low-pressure turbine (6);
• a radially inner shaft (8) rotatably coupled to the fan (2), said shafts (7, 8) being coaxial and extending along the axis (X);
• means (11, 15) for coupling the inner and outer shafts (7, 8) in terms of rotation;
• means (22) for axially holding the inner shaft (8) with respect to the outer shaft (7);
• and
• means for centering the inner shaft (8) with respect to the outer shaft (7);
• wherein the means of centering comprise a frustoconical radial centering and axial positioning wedge (14) inserted between a frustoconical centering surface (13) of the inner shaft (8) and a complementary frustoconical centering surface (10) of the outer shaft (7),
• wherein said frustoconical radial centering and axial positioning wedge (14) is separate from the inner shaft and outer shaft and comprises two parallel frustoconical surfaces respectively in contact with the complementary frustoconical centering surface (13) of the inner shaft (7) and in contact with the complementary frustoconical centering surface (10) of the outer shaft (8),
• wherein the axial positioning wedge (14) has at least one mainly axially extending slot (17), and
• wherein the at least one mainly axially extending slot (17) comprises:
• a first end (18) opening axially at the level of a downstream axial end (19) of the axial positioning wedge (14);
• and
• a second end (20) situated axially between the downstream axial end (19) and a second end (21) of the axial positioning wedge (14).