Patent ID: 11891913
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC F

Claim 0:
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.