| 摘要 |
The invention relates to a compressor blade for a rotary disk of a turbine engine, the blade presenting orthogonal axes that are longitudinal, tangential, and radial, said blade extending radially between a root and a tip, and longitudinally between a leading edge and a trailing edge, said blade being for rotating inside an outer stator shroud having its surface covered in an abradable material. In the invention the tip of the blade presents at least one chamfer in order to reduce the area of contact that can exist between the tip of the blade and the abradable material.
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