| 摘要 |
A subsonic rotor and/or stator blade profile (22, 24) of an axial turbomachine compressor, such as a turbojet. The blade has a leading edge (26) with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost part of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called "sweep" profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses. |
