FIELD: engine building.
SUBSTANCE: invention provides blade (16) comprising body (30) of blade made from organic binder composite material, and front edge screen (32) made of material, which resists pinpoint impacts better than composite material of blade body (30). Blade 16 comprises blade end 26. Front edge shield (32) is assembled on vane body (30) and includes plate (34) of the trough and back plate (36). Plate (34) of the trough includes a trough flap, and back plate (36) includes a back flap. Trough flap and back flap are bent one on another and attached to each other so that they form partial coating (48) of blade end (26). Invention also provides a turbojet engine including a fan having a plurality of such blades, as well as a method of making such a blade.
EFFECT: thus, probability of blade damage is reduced.
10 cl, 11 dwg
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