Turbomachine axial compressor with flow splitting device and assembly method for this device

The gas turbine axial by-pass flow compressor has at least one high-pressure section with a compressor, combustion chamber and turbine, surrounded by a low-pressure section and made with alternating compression (3) and rectifying (4) stages between concentric outer and inner rings. The outer ring acts as a separator between primary and secondary gas flows, and its external wall (11) has at least one self-centering thrust point (12) in contact with the ring fixing flange (13). The thrust point is in the form of a thickened portion of the ring wall which also acts as a reinforcing element.