Patent ID: 11920494
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A rotary turbomachine fan blade, the blade comprising:
a body made of a composite material, having an upstream edge and a downstream edge, between which the body extends along a first longitudinal direction, an extrados and an intrados, between which the body extends along a second thickness direction, which is transverse to the first longitudinal direction, a blade root and a blade head edge, between which the body extends along a third height direction, transverse to the first longitudinal direction and to the second thickness direction, the blade root having a function of attachment on a longitudinal rotary fan hub,
a metallic reinforcement part comprising an upstream metallic nose, which forms a leading edge of the blade and which is fixed to the upstream edge, a first metallic fin, which is connected downstream of a first extrados flank of the upstream metallic nose and which is fixed to an upstream portion of the extrados, and a second metallic fin, which is connected downstream of a second intrados flank of the upstream metallic nose and which is fixed to an upstream portion of the intrados, the upstream metallic nose having a metallic blade head portion, located upstream of the blade head edge,
wherein
the upstream metallic nose comprises at least on the metallic blade head portion at least one recess, which is of longitudinally elongated thickness and which is opening out along the third height direction on the metallic blade head portion,
the at least one recess delimiting on the metallic blade head portion over a determined non-zero height along the third height direction at least one metallic prescribed wear protrusion, which is of longitudinally elongated thickness over a major portion of a length of the upstream metallic nose along the first longitudinal direction and which is configured to be detached at least partially in the presence of tangential friction in the second thickness direction against the metallic blade head portion,
the at least one recess and the at least one metallic prescribed wear protrusion being situated in the first longitudinal direction upstream, the first metallic fin and/or upstream of the second metallic fin and/or upstream of the upstream edge of the body made of a composite material.