Composite spacer ring and production method thereof

A method for manufacturing a spacer ring made of composite material for a turbine engine fan, said spacer ring comprising an upstream skin delimiting an upstream face of the spacer ring when it is mounted on the turbine engine, a downstream skin delimiting a downstream face of the spacer ring when it is mounted on the turbine engine, and an annular insert housed between the upstream and downstream skins, the manufacturing method comprising the following steps:

• preparing an upstream skin preform,
• preparing a downstream skin preform,
• preparing an insert preform,
• inserting the insert preform between the upstream skin preform and the downstream skin preform so as to form a spacer ring preform, and
• baking the spacer ring preform,
• wherein at least one of preparing the upstream skin preform and/or preparing the downstream skin preform comprises drape forming prepreg tows over a skin mould by automatic fibre placement,
• wherein preparing-the insert preform comprises drape forming-prepreg tows over an insert mould by automatic fibre placement, the insert mould having a disc shape the prepreg tows being drape formed over a rim of said disc,
• wherein the disc is rotationally symmetric about a central axis, a cylindrical reference frame is associated with the insert mould with, at each point, an axial direction parallel to the central axis, a radial direction joining the central axis to said point and a circumferential direction orthogonal to the axial and radial directions, and each prepreg tow is drape formed substantially parallel to the circumferential direction.
• wherein drape forming prepreg tows over the insert mould comprises:
• producing at least one stack of layers of prepreg tows stacked in the radial direction, said stack having an axial edge defined by drape forming which has an axial extension, and
• machining a machined axial edge of the stack, opposite the axial edge defined by drape forming, by clean cutting of the stack.