| 摘要 |
Wheel (10) of a turbine engine such as an airplane turbojet, including a disk (12) having blades (14) and at least one ring of a metal matrix composite material (20, 22) mounted on the disk (12) in order to take up centrifugal forces during operation, the wheel further including at least one annular flange (28, 30) formed by sections arranged end-to-end and each including a radially internal annular portion applied on a flank (36, 38) of the disk (12) and a radially external portion coming into contact with the ring (20, 22) in order to ensure the axial holding of the latter on the disk (12), and means (32, 34, 40, 42) for radially holding flange sections on the disk.
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