US 12,000,307 B2
Blade for a turbine engine, and associated turbine engine
Pierre-Marie Fonts, Moissy-Cramayel (FR); Marc Maurice Dijoud, Moissy-Cramayel (FR); Hélène Clech, Moissy-Cramayel (FR); Michel Nin, Moissy-Cramayel (FR); and Lorenzo Huacan Hernandez, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/763,027
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Sep. 23, 2020, PCT No. PCT/EP2020/076620
§ 371(c)(1), (2) Date Mar. 23, 2022,
PCT Pub. No. WO2021/058599, PCT Pub. Date Apr. 1, 2021.
Claims priority of application No. 1910503 (FR), filed on Sep. 24, 2019.
Prior Publication US 2022/0341336 A1, Oct. 27, 2022
Int. Cl. F01D 5/28 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/288 (2013.01) [F01D 5/143 (2013.01); F05D 2240/80 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A blade for a turbine engine, comprising:
an aerodynamic airfoil extending radially outwards,
a blade tip,
a blade root, and
a platform connected to the root by an upper end, a maximum radial distance between the blade tip and the platform defining a maximum extent of the bearing surface of the airfoil, wherein the blade is partially covered by a protective strip configured to combat oxidation and corrosion, said strip extending between a lower limit situated on at least one portion of the platform and an upper limit situated on the blade root, the blade tip not being covered with the protective strip or any other coating, wherein the protective strip is made of material selected from the group consisting of aluminum, iron, nickel, cobalt, yttrium, rare earths or precious metals.