Abstract: The compressor is used for processing a CO2 flow; a first compressor stage has a first row of blades with a first number of blades and a second compressor stage, downstream the first compressor stage, has a second row of blades with a second number of blades; the number of blades of the first compressor stage is less than the number of blades of the second compressor stage; there is an annular gap between the first row of blades and the second row of blades; the first compression stage (200) is designed so to assure that the CO2 flow is in supercritical condition, preferably close to CO2 critical point, at its outlet, and so that the second compressor stage process CO2 in supercritical condition.

Abstract: A novel diffuser for a centrifugal turbomachine to reduce or prevent stall. The diffuser includes diffuser vanes arranged around a diffuser axis. Each diffuser vane includes: a leading edge, a trailing edge, a suction side facing radially inwardly, and a pressure side facing radially outwardly. A respective flow passage is defined between the suction side of a first diffuser vane and the pressure side of a second diffuser vane of each pair of adjacently arranged diffuser vanes. The diffuser vanes are arranged with a non-constant pitch around the diffuser axis. The pitch between each pair of adjacently arranged first diffuser vane and second diffuser vane defining a respective flow passage there between is correlated to a chord of one of said first diffuser vane and second diffuser vane.

Abstract: A return channel for a centrifugal turbo machine. The return channel includes a plurality of return channel vanes, arranged around a return channel axis. Each return channel vane includes: a leading edge at a first distance from the return channel axis, a trailing edge at a second distance from the return channel axis, the second distance being smaller than the first distance. A respective flow passage is defined between each pair of adjacently arranged return channel vanes. The return channel vanes are arranged with a non-constant pitch around the return channel axis.

Abstract: A turbomachine airfoil component is disclosed, having a leading edge and a trailing edge. The airfoil component comprises a hole extending from an inlet positioned at the leading edge towards the interior of the airfoil component and forming a total pressure probe. The hole is fluidly connected to a pressure measuring device.

Abstract: A turbomachine airfoil component is disclosed, having a leading edge and a trailing edge. The airfoil component comprises a hole extending from an inlet positioned at the leading edge towards the interior of the airfoil component and forming a total pressure probe. The hole is fluidly connected to a pressure measuring device.