US 11,939,937 B2
Method for manufacturing a composite platform for a fan of an aircraft turbine engine
Matteo Minervino, Moissy-Cramayel (FR); Didier Fromonteil, Moissy-Cramayel (FR); Hervé Grelin, Moissy-Cramayel (FR); and Damien Bruno Lamouche, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/908,500
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Mar. 1, 2021, PCT No. PCT/FR2021/050340
§ 371(c)(1), (2) Date Aug. 31, 2022,
PCT Pub. No. WO2021/176167, PCT Pub. Date Sep. 10, 2021.
Claims priority of application No. 2002122 (FR), filed on Mar. 3, 2020.
Prior Publication US 2024/0060460 A1, Feb. 22, 2024
Int. Cl. F02K 3/06 (2006.01); B29C 70/72 (2006.01); B29K 705/00 (2006.01); B29L 31/08 (2006.01)
CPC F02K 3/06 (2013.01) [B29C 70/72 (2013.01); B29K 2705/00 (2013.01); B29L 2031/08 (2013.01); F05D 2220/36 (2013.01); F05D 2240/80 (2013.01); F05D 2300/603 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A method for manufacturing a composite platform for an aircraft turbine engine fan, this platform comprising a wall of elongated shape and configured to extend between two fan vanes, this wall comprising an aerodynamic external face and an internal face on which is located an attachment tab configured to be attached to a fan disc,
characterised in that it comprises the steps of:
a) preparing fabrics or sheets pre-impregnated with a resin,
b) depositing the fabrics or sheets in a mould,
c) positioning a metallic framework in the mould, on the fabrics or sheets, the framework being formed in one part with said attachment tab,
d) depositing fabrics or sheets on a portion of the framework, and
e) closing and heating the mould in order to solidify the assembly formed by the fabrics or sheets and the framework.