Patent ID: 11939937
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Other special machines (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 0:
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.