US 12,409,615 B2
Method for manufacturing a composite part for a turbomachine
Matthieu Patrick Jean Roger Perlin, Moissy-Cramayel (FR); Arthur Bouchaud, Moissy-Cramayel (FR); and Romain Plante, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/001,769
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 10, 2021, PCT No. PCT/FR2021/051042
§ 371(c)(1), (2) Date Dec. 14, 2022,
PCT Pub. No. WO2021/255368, PCT Pub. Date Dec. 23, 2021.
Claims priority of application No. 2006391 (FR), filed on Jun. 18, 2020.
Prior Publication US 2023/0311428 A1, Oct. 5, 2023
Int. Cl. B29C 70/24 (2006.01); B29C 37/00 (2006.01); B29C 70/44 (2006.01); B29C 70/54 (2006.01); B29L 31/08 (2006.01)
CPC B29C 70/24 (2013.01) [B29C 37/0025 (2013.01); B29C 70/443 (2013.01); B29C 70/545 (2013.01); B29L 2031/082 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A method for manufacturing a part made of composite material for a turbomachine, comprising the steps of:
b) arranging a preform made by weaving fibers in three dimensions in a mold,
c) injecting the polymerizable resin into the mold to impregnate the preform so as to form the part after solidification,
d) machining the part,
e) visually checking the part by an operator to validate at least one compliance criterion,
wherein step b) is preceded by a step a) during which at least one compliance coating is deposited in the mold, the compliance coating having a calibrated thickness (X) and at least one visual aspect identifiable by an operator, the compliance coating being configured to cover at least one area of the preform and to be secured thereto by the resin at the end of the step c),
and wherein step e) comprises verifying by the operator of the presence of said aspect in said area, so as to validate said compliance criterion, and said coating comprises at least one polymerizable compound and the polymerization of which is initiated before the step b).