Abstract: A process gas extraction device (10) for an axial compressor, having a high degree of adaptability to changes in the operating characteristics of the compressor; a casing (14) of the axial compressor is provided with a volute (15) for collecting process gas and the extraction device (10) comprises collecting structures (12) connected to this collecting volute (15).

Abstract: A device used as a chemical reactor or heat exchanger in general, with a thin tube plate, of the type in which at least one pipe is connected to a tube plate, this tube plate being closed by a chamber with a container function, wherein this chamber is produced by a section with any shape, with a base which is joined to the plate by a lateral portion; connection elements are also provided between the tube plate and the base of the chamber.

Abstract: A simplified support device (110) for nozzles (112) of a gas turbine stage, of the type in which the support device (110) is interposed in a rotor of the gas turbine, between an upstream blading disc (122) and a downstream blading disc (124) of the nozzles (112), and is provided with honeycomb-type alveolar seals (120); the nozzles (112) of the gas turbine stage comprise an annular body which is divided into nozzle segments (112) and the honeycomb-type alveolar seals (120) are anchored directly to these nozzle segments (112).

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 flame-passage device (10) for non-annular gas turbine combustion chambers comprises a tubular body (11), which is provided with a plurality of cooling holes (12), for cooling on the swirl-cooling type. The tubular body (11) is inserted in a flanged pipe (27), which connects the cases (31, 32) of two successive combustion chambers (17, 18), and has a first end (13) with a cylindrical shape, and a second end (14) with an oval shape, wherein the second, oval end (14) is provided with three rings (23, 24, 25), for anchorage of the corresponding combustion chamber (17) to the case (31).

Abstract: A main liquid fuel injection device (20) for a single combustion chamber (10), having a premixing chamber (12), of a gas turbine with low emission of pollutants, comprising a set of injection channels (42) for the liquid fuel distributed within the premixing chamber (12); the injection device (20) has a set of blades (32) extending radially about the axis of symmetry of the combustion chamber (10), each of which is provided with at least one of the injection channels (42).

Abstract: A scraper device for a reciprocating compressor piston rod that comprises at least one scraper ring, provided with at least one lip which faces the surface of the said rod, and a box to contain the scraper ring and for centering on the rod, wherein this scraper ring is produced by means of mechanical processing of deformable plastics materials and wherein this container box is accommodated in support elements with radial play.

Abstract: An improved liquid fuel injector (10) for burners of gas turbines, of the type comprising a tube (16) which supplies the liquid fuel to an injector head (12), an external tube (24) being provided around the tube (16) to form an annular cavity (26) where pressurized air is supplied, and a covering element (28) being provided around the head (12) to form a cavity (32); a turbulence element (18) comprising blading (22) is provided before the head (12).

Abstract: Balancing piston for centrifugal compressors, to control and damp subsynchronous vibrations, comprising a cylindrical body which is secured onto the rotor and a cylindrical structure which contains the body on the stator side with interposition of a seal with small cells wherein the play between the rotor and the stator increased in the direction of the flow of gas through the play.

Abstract: A structure for separating the high and low pressure turboexpanders of a gas turbine comprises a diaphragm (31) having the function of supplying flows of cooling air, a pair of shaped plates (50′, 50″) fixed to the diaphragm (31) and forming a gap (52) into which is blown cooling air which is drawn from a turbocompressor (11) and is then sent to hot areas of the turboexpanders, and a sealing ring (60) supported by the shaped plates (50′, 50″), designed to isolate the high pressure (12) and low pressure (13) turboexpanders and to receive and distribute the cooling air obtained from the gap (52).

Abstract: The inner barrel of a turbine has a plurality of holes for receiving compressor discharge air and flowing such air within the inner barrel. A plurality of replaceable nozzles having internal bores of different diameters are selectively screw threaded into the openings of the inner barrel body enabling, with different diameters, a variation in the flow of compressor discharge air entering the inner barrel.

Abstract: An anti-condensation device for a flame sensor (10) of a combustion chamber (12), wherein the sensor (10) is disposed outside the combustion chamber (12) and determines the presence of the combustion flame by means of an aperture (14) provided in a wall of the chamber (12); the device comprises at least two tubular structures (22, 24), one of which (24) surrounds the other (22) at least partially, an annular space in which air flows being provided between these two structures (22, 24).

Abstract: An improved diffuser (10) for a centrifugal compressor which comprises blading with blades (12).

Abstract: A centrifugal compressor for high pressure (10) with improved efficiency, of the type comprising a rotor (12), an inner case (14), diffusers (16) and diaphragms (18), wherein the surfaces which are subjected to passage of the flow of gas have been subjected to burnishing working.

Abstract: The present invention relates to a cobalt-based alloy for the coating of organs subject to erosion by liquid comprising chromium 28-32% by weight, tungsten 6-8% by weight, silicon 0.1-2% by weight, carbon 1.2-1.7% by weight, nickel 3-6% by weight, molybdenum 1-3%, cobalt the complement to 100%. The invention also relates to an application method of the alloy on organs subject to erosion by liquid, in particular vapour turbine blades, to reduce the metal erosion rate following impact with liquids.

Abstract: A system (10) for sealing and pressurisation for the support cushion (24) of a gas turbine (20), wherein the gas turbine (20) is provided with a compressor (21), with which there is associated an inner barrel (23), and the support cushion (24) is in turn provided with seals (38, 39) relative to the axis of the compressor (21), and has at least one pipe (33) for the venting discharge. The air is fed into the inner barrel (23), using the venting piping (33) of the support cushion (24), such as to create a flow of air, which starts from an intermediate stage of the compressor (21), and goes towards the inner barrel (23).

Abstract: An improved connection of blades (12) on a rotor disc (22) of a gas turbine, of the type in which a root (10) of each blade (12) is inserted in a seat (20) of the disc (22) which is complementary to the blade, wherein the root (10) is in the shape of an overturned isosceles triangle, with the two sides which converge at the base each having a grooved profile such as to form a series of teeth (14) and with a lower end (16) of the root (10) which is formed by the joined connection of the two lower teeth (14) of the two sides of the root (10), the teeth (14) of the root (10) corresponding to grooves (24) in the seat (20) and the lower end (16) of the root (10) corresponding to an end groove (26) in the seat (20).

Abstract: A safety device for a washing system for liquid fuel burners in gas turbines, in which these turbines are provided with separate injectors for the combustion of liquid fuel or gaseous fuel, wherein the washing system comes into use when gaseous fuel is used and comprises a feed pipe for washing gas, a manifold from which liquid fuel is distributed to the burners, and a drainage pipe in order to discharge deposits of liquid; on the feed pipe there is inserted a closed tank in which there are provided apertures both for an intake pipe and for an outlet pipe for the washing gas, for the drainage pipe and for at least two liquid level sensors.

Abstract: An improved method for production of a rotor (10) of a centrifugal compressor, wherein the rotor (10) is produced from a monolithic disc; this disc is worked in a radial direction by at least one tool (20) of a numerical control machine, such as to remove shavings, so as to produce radial cavities (12) in the rotor (10).

Abstract: A simplified piston (14), slidable in a cylinder (16), moved by magnetic coupling to an external magnetic element (20) which moves along the cylinder (16).