Turbomachine centre blade comprising a curved portion
A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.
1. A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine, the blade comprising:
a radially internal root portion;
a radially external tip portion;
a radially intermediate portion;
a curved portion perpendicularly to a main axial plane of the blade in a direction; and
at least one straight portion on at least one of the root portion and the tip portion,
wherein a tangential amplitude of the curved portion is between 1% and 5% of a radial length of the blade, and
wherein, when the blade is at rest, the straight portion is inclined by a non-zero angle less than or equal to 30° with respect to a main radial direction of the blade.
2. A blade as claimed in claim 1 , wherein a radial length of the curved portion is between 30% and 60% of the radial length of the blade.
3. A blade as claimed in claim 1 , wherein the curved portion is positioned radially on the root portion.
4. A blade according to 1 , wherein the curved portion is positioned radially on the tip portion.
5. A blade according to claim 1 , wherein the curved portion is positioned radially on the intermediate portion.
6. A blade as claimed in claim 1 , wherein the curved portion is tangentially curved in a direction of intrados of the blade.
7. A turbomachine compressor stator comprising:
radial blades distributed around the main axis of the turbomachine,
wherein each blade is a blade as claimed in claim 1 .
8. A turbomachine comprising a stator that comprises blades as claimed in claim 7 .