Fluid structure for a turbocompressor

The flow structure for the compressor of especially a gas turbine has at least one toroidal chamber (18) installed concentrically to an axis (17) of the compressor in the region of the free blade ends of a blade ring (15,16). An opening (30) is located in the region of at least one of the walls (19-21) of the toroidal chamber and enable a flow passage from the toroidal chamber. At least one compression chamber (31) is provided to receive this emerging flow. Independent claims are also included for the following: (A) a turbo-compressor in axial, diagonal and/or radial design style, with at least one flow structure; (B) an aviation jet engine with the aforesaid compressor; and (C) a stationary gas turbine with the proposed flow structure.