Stator ring for an aircraft turbine engine and aircraft turbine engine fitted with same

A stator ring for an aircraft turbine engine, said stator ring comprising an internal shroud coaxial with an external shroud, wherein the internal shroud and the external shroud are connected together by vanes which are each solid and integral with the shrouds, the external shroud comprising an external annular surface connected to at least one attachment catch configured to attach the stator ring, and the internal shroud comprising an internal annular surface connected to a support for an abradable coating, wherein at least one of said internal and external annular surfaces comprises recesses which are located in line with the vanes and which are configured so that the vanes are connected to the corresponding shroud, at a level of the recesses, by webs of material which have a thickness less than that of said shroud,

• and wherein said at least one attachment catch is arranged between two series of recesses in the external shroud, and/or said support is arranged between two series of recesses in the internal shroud.