US 11,891,913 B2
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. 17/908,037
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Feb. 19, 2021, PCT No. PCT/FR2021/050298
§ 371(c)(1), (2) Date Aug. 30, 2022,
PCT Pub. No. WO2021/176161, PCT Pub. Date Sep. 10, 2021.
Claims priority of application No. 2002128 (FR), filed on Mar. 3, 2020.
Prior Publication US 2023/0108760 A1, Apr. 6, 2023
Int. Cl. F01D 5/02 (2006.01); F01D 11/00 (2006.01)
CPC F01D 5/021 (2013.01) [F01D 11/008 (2013.01); F05D 2220/36 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A composite platform for a fan of an aircraft turbine engine, said composite platform comprising:
a wall of elongated shape and configured to extend between two fan vanes, the wall comprising an aerodynamic external face and an internal face, the wall having a first longitudinal dimension;
a metallic framework configured to be attached to a fan disc;
the metallic framework formed of a single part including:
a first portion forming an attachment tab;
a second portion forming a plate, said plate having an elongated shape and a second longitudinal dimension which represents at least 50% of said first longitudinal dimension and at most 100% of said first longitudinal dimension,
wherein said wall is produced by over-moulding a resin onto said plate such that the wall wraps around the plate, and wherein the attachment tab extends inwardly from the wall.