Abstract: A manufacturing method for obtaining improved components (110) for gas turbines, which includes at least one process involving powder sintering or powder metallurgy with homogeneous/heterogeneous dispersion of powders; the invention also relates to the improved components obtained with this method.

Abstract: A manufacturing method for obtaining high-temperature components (10) for gas turbines, which comprises at least incorporation of an element or insert (14) in a main body (12) of the component (10), this element or insert (14) having mechanical properties able to withstand stresses to which said component (10) is subject in a zone where the said element or insert (14) is arranged; the invention also relates to a high temperature component thus obtained.

Abstract: A system (10) for sealing and pressurization 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: 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 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: 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: 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: 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 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 transition piece (10) for non-annular gas turbine combustion chambers has a projecting connection arm (22) for support on the turbine stator, wherein the projecting connection arm (22) makes it possible to obtain a lead-in axis with an angle of between 5° and 7° relative to an axis, which is parallel to the axis of the machine, and is perpendicular to the plane on which there lies the frame for interfacing of the transition piece (10) with the ring of nozzles of the first stage of the gas turbine.

Abstract: A device (10) for controlling the cooling flows of gas turbines (20), where the aforementioned gas turbine (20) is provided with a compressor (21) with which an inner barrel (23) and a load-bearing bolster (24) are associated, the device (10) envisaging the arrangement of a plurality of replaceable nozzles (11) which have an internal bore (51) with different diameters and which can be mounted in suitable holes (14) formed in the substantially cylindrical body (50) of the inner barrel (23) so as to allow variation in the flow of air entering into the inner barrel (23), by means of the selection and replacement of at least some of these nozzles (11) with other nozzles (11) having an internal bore (51) with suitable diameters.