US 12,410,718 B2
Method for preparing a root of a turbomachine blade
Antoine Hubert Marie Jean Masson, Moissy Cramayel (FR); and Geneviève Mougey, Moissy Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/694,821
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Aug. 26, 2022, PCT No. PCT/FR2022/051613
§ 371(c)(1), (2) Date Mar. 22, 2024,
PCT Pub. No. WO2023/047030, PCT Pub. Date Mar. 30, 2023.
Claims priority of application No. 2110098 (FR), filed on Sep. 24, 2021.
Prior Publication US 2024/0287910 A1, Aug. 29, 2024
Int. Cl. F01D 5/28 (2006.01); F01D 5/00 (2006.01); F01D 5/30 (2006.01)
CPC F01D 5/282 (2013.01) [F01D 5/005 (2013.01); F01D 5/30 (2013.01); F05D 2230/80 (2013.01); F05D 2300/603 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A method for preparing a root of a vane, the vane being a turbomachine vane made of composite material and to be mounted in a root support, the method comprising:
a first step of positioning on a side wall of the root of the vane an anti-wear layer including synthetic fibres coated or impregnated with an adhesive agent;
a second step of polymerising the adhesive agent so that said anti-wear layer adheres to the side wall of the root of the vane, and
after the second step, a third step of machining a free external surface of said anti-wear layer for being in contact with the root support, so as to obtain a ground external surface that forms at least a portion of the external surface of the root of the vane, the third step of machining decreasing a thickness of the anti-wear layer so as to shift from an initial thickness greater than 1 millimetre to a final thickness, the initial thickness of the anti-wear layer corresponding to the thickness of the anti-wear layer during the first step of positioning.