Abstract: The turbomachine assembly includes a first turbomachine having an inlet, an outlet and a rotary shaft, a second turbomachine having an inlet, an outlet and a rotary shaft, a transfer duct fluidly connecting the outlet of the first turbomachine to the inlet of the second turbomachine, and a casing housing the turbomachines and the transfer duct; the turbomachines are located adjacent to each other so that the outlet of the second turbomachine is close to the outlet of the first turbomachine and the inlet of the second turbomachine is remote from the outlet of the first turbomachine; the outlet of the second turbomachine has an end portion shaped like a cochlea (i.e. a spiral duct); the transfer duct has an annular shape, and surrounds the end portion of the outlet of the second turbomachine.

Abstract: A compressor unit for processing a working fluid comprising a compressor inside a housing to compress the working fluid wherein a collection chamber is fluidly coupled with a working fluid inlet of said housing.

Abstract: A motor-compressor includes a compressor, an electric motor directly connected to the compressor, magnetic bearings and one gas support located adjacent to a magnetic bearing to seal and support an end of the compressor's rotor. The compressor and the electric motor are integrated in a single unit, being housed in a single box or casing.

Abstract: A compressor unit for processing a working fluid comprising a compressor inside a housing to compress the working fluid wherein a collection chamber is fluidly coupled with a working fluid inlet of said housing.

Abstract: Motor-compressor comprising a compressor, an electric motor directly connected to said compressor, wherein the compressor and the electric motor are integrated in a single unit, housed in a single box or casing.

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 system for connecting a low-pressure jet to a transition duct in a gas turbine, in which the said low-pressure jets are arranged in sectors of two or three stator blades and are filled on to the ring of the jets. The platforms of the jets are provided with a channel inside which the transition duct is positioned by means of an edge. Furthermore, centering between the transition duct and the ring of the jets is achieved directly using centering means at three or more points.

Abstract: A draining and cooling system for gas turbine cushions where the above-mentioned gas turbine has its own drain unit (11), which consists of two essentially concentric rings connected to each other by means of a number of spokes (12, 13). In the draining system described, the lubricating and cooling oil is fed into the gas turbine's drain unit (11) by means of at least a first pipe (14), located inside one of the spokes (12) and is drained by means of at least a second pipe (20), located inside one of the spokes (13).

Abstract: A system for connecting a low-pressure jet (12) to a transition duct (149 in a gas turbine, in which the said low-pressure jets (12) are arranged in sectors of two or three stator blades and are filled on to the ring of the jets. The platforms (11) of the jets (12) are provided with a channel (13) inside which the transition duct (14) is positioned by means of an edge (15). Furthermore, centring between the transition duct (14) and the ring of the jets (12) is achieved directly using centring means at three or more points on the rings of the jets (12).

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 draining and cooling system for gas turbine cushions where the above-mentioned gas turbine has its own drain unit (11), which consists of two essentially concentric rings connected to each other by means of a number of spokes (12, 13). In the draining system described, the lubricating and cooling oil is fed into the gas turbine's drain unit (11) by means of at least a first pipe (14), located inside one of the spokes (12) and is drained by means of at least a second pipe (20), located inside one of the spokes (13).

Abstract: A device for securing blades of the first stage of a gas turbine wherein the blades having cooling passages for flowing cooling air from the blade roots towards the blade airfoils. A plurality of plates, each of which has at least one U-shaped projection, engages a corresponding U-shaped groove in the surface of a rotor disc of the first stage. Each plate is interposed between two adjacent first stage blades to secure the blades axially. Second stage turbine blades are secured against axial movement by a plurality of plates, each of which is interposed between the end portion of the foot of a corresponding blade and the turbine disc. Each of the latter plates is provided with ends to secure the blade axially.

Abstract: A device for positioning of nozzles of a stator stage and for cooling of rotor discs in gas turbines, of the type including nozzle segments consisting of several airfoils. Each nozzle segment is connected at its top to an outer ring to define a chamber containing cooling air and is positioned at its base on an inner ring. The nozzle segments form a circumferential array about the axis of the gas turbine. In each airfoil of the nozzle segment, there is provided at least one tube, which is inserted in a corresponding duct inside the airfoil for delivering cooling air to the first and second stage discs.

Abstract: A device for keeping the annular outlet mouth of the gas volute always centered about the nozzle assembly in a gas turbine, consisting of two diametrically divided retaining rings embracing said annular mouth, the lower half-ring having an inner radius greater than that of the upper half-ring, this latter forming predetermined radial gap with said annular mouth.

Abstract: A system for the rapid balancing of revolving shafts, in particular, the revolving shaft of a gas turbine. The system comprises two mutually adjacent bores provided in the stator of the turbine, which can be closed by relevant plugs, and which are collimated on the screw-threaded bores of the rotor. The system also comprises a special rigid rod for elastically holding a screw-threaded balancing mass, and for causing it to rotate.