Patent ID: 11898466
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 4:
5. A turbomachine guide vane comprising a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, wherein:
at least one of the extrados and intrados faces is completely covered with a continuous polymer coating comprising:
a grooved zone of thickness (e1),
a non-grooved zone of thickness (e2) less than the thickness (e1) of the grooved zone, said continuous polymer coating forming said grooved zone and said non-grooved zone,

a coat of paint, of thickness (e3), covers the non-grooved zone such that the thickness of the coat of paint superimposed on the non-grooved zone is equal to the thickness (e1) of the grooved zone.