Patent ID: 8414256

Claim:
A compressor drum rotor stage for an axial turbo-machine, comprising: a hollow body in the form of a shell, generally symmetrical in revolution about an axis of revolution corresponding to the axis of the turbo-machine; and a plurality of vanes arranged at the periphery of the body; wherein each vane of the plurality of vanes at its root comprises: an attachment platform housed in a corresponding opening made in the shell, each platform being housed in a corresponding opening in such a way that the outer surface of each platform is essentially flush with the outer surface of the hollow body at the edge of the corresponding opening; and each platform is attached to the hollow body by welding between the outer edge of the platform and the inner edge of the corresponding opening; wherein the shell comprises two outer side-plates, each generally in a plane perpendicular to the axis, one being upstream and the other downstream from the row of openings, and a generally cylindrical part formed as an integral part of the downstream side-plate and having at least one circular rib around the circumference of the shell intended to engage by friction with a ferrule of a guide vane, forming with the row of rotor stage vanes a compressor stage.