US 11,898,466 B2
Method for coating a turbomachine guide vane, associated guide vane
Célia Iglesias Cano, Moissy Cramayel (FR); Vincent Marie Jacques Rémi De Carné-Carnavalet, Moissy Cramayel (FR); and Antoine Hubert Marie Jean Masson, Moissy Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/619,505
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 18, 2020, PCT No. PCT/FR2020/051055
§ 371(c)(1), (2) Date Dec. 15, 2021,
PCT Pub. No. WO2020/254764, PCT Pub. Date Dec. 24, 2020.
Claims priority of application No. 1906647 (FR), filed on Jun. 20, 2019.
Prior Publication US 2022/0235666 A1, Jul. 28, 2022
Int. Cl. F01D 9/04 (2006.01); F01D 5/28 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 5/282 (2013.01); F01D 5/288 (2013.01); F05D 2230/31 (2013.01); F05D 2230/90 (2013.01); F05D 2240/121 (2013.01); F05D 2240/122 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A method for coating 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, the method comprising:
completely covering one of the extrados and intrados faces of the vane with a polymer coating of first thickness (e1) provided with grooves,
removing the grooves from a part of the polymer coating in such a way that the polymer coating comprises a grooved zone and a non-grooved zone, and
coating the non-grooved zone with a coat of paint of thickness (e3) 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.