| 摘要 |
The invention aims to provide a rotor for a turbine engine comprising: a disc having cavities on the periphery thereof, referred to as primary cavities; a plurality of blades (100) each having a root (110) consisting of, at the bottom portion thereof, a bulb (120) locked axially in said primary cavities; a plurality of added platforms (300, 400), each being arranged between two consecutive blades (100); said rotor being characterised in that said platforms (300, 400) have: a substantially straight plate (301, 401) and a bulb (302, 402) extending radially under the plate (301, 401), said bulb (302, 402) being locked axially in secondary cavities made in the periphery of the disc, the secondary cavities being positioned between two consecutive primary cavities; a spoiler (310, 410) extending substantially axially, said spoiler (310, 410) forming an annular sector arranged opposite at least two consecutive blades. |
