Turbomachine centre blade comprising a curved portion
AssigneeSafran Aircarft Engines
InventorsDamien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
Life of this patent
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Abstract
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.
Claims8
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.
A blade according to 1, wherein the curved portion is positioned radially on the tip portion.
Dependencies are inferred from the claim text.