| 摘要 |
<p>An assembly for an aircraft turbine engine comprises an integral element 42 consisting of a disk 44 and a plurality of blades 48. Each blade has a connection zone 64 connecting it to the disk 44, the connection zone 64 comprising a first part 64a arranged at the external flowpath delimitation surface 50 provided on the disk 44, and at least one second end part 64b arranged at a recess 72 formed in the disk 44 along the axial extension of the external surface 50. The average fillet radius (R2, fig.7) defined by the second end part 64b is larger than the fillet radius (R1, fig.6) defined by said first end part 64a. The assembly also comprises a flowpath reconstruction part 52 formed in the aerodynamic continuity of the external flowpath delimitation surface 50, so as to cover said recess 72. The assembly may be for a fan, compressor or turbine. The ratio (R2/R1) may be between 1 and 5.</p> |
