BLADE COMPRISING A METAL BODY AND AN OUTER CASING COVERING AN OPENWORK AND / OR LATTICE STRUCTURE OF THE METAL BODY

Abstract

The invention relates to a blade (7) for a turbomachine, in particular for an aircraft, said blade comprising a blade (70) connected to a root (76), said blade (70) comprising a leading edge (73), a trailing edge (74), a lower surface (71) and an upper surface (72) connected to the lower surface by the leading edge and the trailing edge, wherein the blade comprises a metal body (8) and at least one outer casing (10), the metal body defining the root of the blade, as well as first (83) and second (84) edges at the leading and trailing edges of the blade respectively, the metal body further comprising an openwork structure (SA) and / or the lattice structure (ST) extending between the first and second edges, and the outer casing covering at least the openwork structure and / or the lattice structure so as to define the lower surface and the upper surface of the blade. Figure for abstract: Figure 10

Claims

8. Blade according to the preceding claim, characterized in that the light (80) of the openwork structure (SA) and / or the orifices (81) of the lattice structure (ST) are empty or entirely filled with a non-metallic material (9) for example chosen from a composite, a plastic, a polymer, a resin, fibers and a foam.

9. Blade according to any one of the preceding claims, characterized in that the openwork structure (SA) comprises at least two or more independent lights (80) separated from each other by one or more partitions (800) of the metal body (8), each partition (800) extending in a parallel, perpendicular, transverse and / or inclined direction relative to an axis of elongation (A) of the blade.

10. Blade according to the preceding claim, characterized in that the metal body (8) comprises at least one weight (86) located on the partition(s) (800).

11. Blade according to the preceding claim, characterized in that the lattice structure (ST) is formed by the partition(s) (800) and / or by the at least one weight (86).

12. A blade according to any one of the preceding claims, characterized in that the metal body (8) further comprises at least one serration element (88) on the leading edge (73) or the trailing edge (74).

13. Turbomachine (100), in particular for an aircraft, comprising at least one blade (7) according to any one of the preceding claims. [Fig. 5] 75 t [Fig. 6] [Fig. 8]

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