Turbine unit for aircraft turbine engine with improved disc-cooling circuit

摘要

A turbine unit for an aircraft turbine engine comprises a rotor disc 17 axially continued by a rim 36 and carrying rotary blades 18. A root 21 of each of the blades and a cell (23, fig 3) in the disc define together channels for air flow 43. An annular flange 33 including a bearing end 34 defines together with the rim an air passage 42 communicating with the channels. A member 32 for axially retaining the blades is applied against the disc by the bearing end. At least one of the retaining member and the flange comprises a groove 44 formed facing the other of the retaining member and the flange, into which a sealing joint 45 is inserted to prevent leakage of air. The retaining member may be formed by an alternation of first and second segments (46, 47, fig 7). An aircraft turbine engine comprises a turbine having the turbine unit.