FIELD: engines and pumps.
SUBSTANCE: gas turbine engine fan blade includes aerodynamic surface (12) in the first direction (14) between front edge (16) and rear edge and in the second direction which is essentially perpendicular to the first direction, between root and head of the blade. Aerodynamic surface is made from composite material. Blade includes solid reinforcing metal element (32) bonded to front edge (16) of the blade aerodynamic surface. Reinforcing element is located in the first direction (14) beyond the front edge of the blade aerodynamic surface and in the second direction between the blade root and head. Reinforcing element includes at least one cavity (34a) intended for absorption at least of some part of energy when the foreign object collides with blade front edge.
EFFECT: improving blow energy dissipation and reducing the blade damages.
10 cl, 9 dwg
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