Patent ID: 8524026

Claim:
A method of fabricating a composite material casing for a gas turbine engine using a former comprising: two cheekplates; an annular wall having an outside surface of profile that corresponds to a profile of an inside surface of the casing that is to be fabricated; a removable fastener plate for fastening a layer of fiber texture, the plate being designed to be received in a recess of complementary shape passing through the annular wall of the former, an outside surface of the plate, when in position, reconstituting a profile of the outside surface of the annular wall, and presenting a plurality of spikes projecting radially outwards and designed to hold only the first layer of the fiber texture mechanically while the fiber texture is being wound on the former; and a shutter free of spikes that replaces the removable fastener plate and is designed to be received in the recess of complementary shape passing through the annular wall of the former, the outside surface of the plate, when in position, reconstituting the profile of the outside surface of the annular wall, the method comprising: mounting and securing the removable fastener plate in the recess in the annular wall of the former; winding layers of fiber texture on the former with an end thereof being positioned over the fastener plate; penetrating between fibers of the first layer of the fiber texture wound on the former with the spikes of the plate so as to hold only the first layer mechanically; exerting a traction force on each layer of the fiber texture while each layer is being wound on the former; removing the fastener plate from the former; replacing the fastener plate with the shutter; securing the shutter in the recess in the annular wall of the former; and subjecting the wound fiber texture to resin impregnation and to polymerization of the resin, wherein a height of the spikes is less than a thickness of the first layer of the fiber texture.