Abstract: An axial thrust balancing system for a centrifugal compressor, having improved safety characteristics, the centrifugal compressor comprising a rotor having impellers adjacent to each other and connected by a shaft, the rotor rotating in a stator, the centrifugal compressor additionally including a balancing piston, a balancing line being provided between an intake of a first compression stage and an area downstream of the balancing piston; this system comprises an intake mechanical gas seal around the shaft upstream of the first compression stage and an outlet mechanical gas seal downstream of the balancing piston, the balancing line being closable by blocking elements.

Abstract: A drainage system for gas turbine supporting cushions or bearings, in particular for the second supporting bearing, consisting of a central shaft (20), surrounded by a series of supporting studs (21), which result, in their turn, with connection to a container housing (22) for studs (21), a sleeve (23) for containing the second supporting bearing of the turbine and a series of pipes (24, 25), respectively for the entry and drainage of the lubrication and cooling oil; the system consists of, in addition, a series of lateral seals (26), provided in positions facing the second supporting bearing, which create a pressure difference which permits the oil to pass under pressure within the drainpipes (25) at a well sustained speed.

Abstract: A cylindrical blade for a rotor of the purely radial type of a centrifugal compressor with a medium-high flow coefficient comprises a first surface (3) of the pressure side and a second surface (5) of the suction side of equal curvature with generatrices parallel to the axis (Z) of rotation of the rotor, the lines of curvature of the said surfaces (3, 5) being defined, in a system of Cartesian coordinates (X, Y, Z) by the ratio between the coordinates of a discrete set of points (10) belonging to them and the outer radius (R) of the rotor (20).