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A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by thre

A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.

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1. A method of manufacturing a composite material casing of varying thickness for a gas turbine, the method comprising: forming a woven fiber texture of varying thickness, the woven fiber texture having a plurality of layers of warp yarns and a plurality of layers of weft yarns woven together by thr

1. A method of manufacturing a composite material casing of varying thickness for a gas turbine, the method comprising: forming a woven fiber texture of varying thickness, the woven fiber texture having a plurality of layers of warp yarns and a plurality of layers of weft yarns woven together by three-dimensional weaving,forming a fiber preform of varying thickness and of shape corresponding to the shape of the casing to be made by winding said woven fiber texture into a plurality of superposed turns on a mandrel having a profile corresponding to the profile of the casing to be made, anddensifying the preform with a matrix. 2. A method according to claim 1, wherein the fiber texture is woven with its warp yarns being taken up on a drum having a profile that is determined as a function of the profile of the casing to be made, the drum being distinct from said mandrel. 3. A method according to claim 1, for manufacturing a casing having at least one fastening or connection flange, wherein the preform is made as a single part with a preform portion corresponding to the flange of the casing. 4. A method according to claim 1, wherein the fiber texture is woven with thickness that increases progressively from its longitudinal ends in zones that are adjacent to the longitudinal ends. 5. A method according to claim 1, wherein the preform is formed by three-dimensional weaving with an interlock weave. 6. A fan retention casing for a gas turbine, the casing being made of composite material with a fiber reinforcement densified by a matrix, wherein the fiber reinforcement comprises a woven fiber texture of varying thickness having a plurality of layers of warp yarns and a plurality of layers of weft yarns woven together by three-dimensional weaving, the woven fiber texture being wound into superposed layers. 7. A casing according to claim 6, including at least one flange, wherein the fiber reinforcement is made as a single part including a flange-reinforcing portion. 8. A gas turbine aeroengine including a fan retention casing according to claim 6 or claim 7. 9. A gas turbine aeroengine including a fan retention casing according to claim 7. 10. A gas turbine aeroengine including a fan retention casing manufactured by the method of claim 1. 11. A gas turbine aeroengine including a fan retention casing manufactured by the method of claim 2. 12. A gas turbine aeroengine including a fan retention casing manufactured by the method of claim 3.