Abstract: A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.

Abstract: A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.

Abstract: Assembly system (10) for a thermocouple (16) for a gas turbine equipped with a supporting element (12) in which the thermocouple (16) is housed, the supporting element (12) has a series of holes (45) for the inlet of the discharge gases of the gas turbine and a cavity (50) in which they are mixed before flowing through an opening (14) of the supporting element (12).

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: 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 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: 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 (28, 30) for washing gas, a manifold (14) from which liquid fuel is distributed to the burners, and a drainage pipe (26) in order to discharge deposits of liquid; on the feed pipe (28, 30) there is inserted a closed tank (20) in which there are provided apertures both for an intake pipe (28) and for an outlet pipe (30) for the washing gas, for the drainage pipe (26) and for at least two liquid level sensors (32, 34).

Abstract: A combustion chamber for gas turbines comprises an inner liner (12) and an outer liner (11), wherein the inner liner (12) is substantially concentric relative to the outer liner (11), such as to define an annular inner space (30), and wherein a shield (13) is provided at the output of each of the burners. The specific feature of the invention consists in the fact that each of the shields (13) comprises a single metal plate part, and that the liners (11, 12) have a plurality of holes (20, 21), in sections adjacent to the longitudinal development of the shield (13), such as to define gaps (60, 61) for the circulation of air.

Abstract: A device (31) for connection of a nozzle (23) of a pre-mixing chamber (11) of a gas turbine, to a housing (12) of the pre-mixing chamber (11) comprises a flange (33) which clasps and retains the nozzle (23). The flange (33) is connected in a detachable manner to the housing (12) of the pre-mixing chamber (11), so as to render the nozzle (23) integral with the housing (12) of the pre-mixing chamber (11).

Abstract: A pre-mixing chamber (10) for gas turbines, wherein the gas turbine is of the type which comprises at least one compressor connected to the turbine, and a combustion chamber, wherein the combustion chamber has a converging portion (12), positioned such as to give rise to combustion inside the combustion chamber, and wherein the pre-mixing chamber (10) has a plurality of pipes (19) provided with holes (20), which open into the combustion chamber on a front portion of the body of the pre-mixing chamber (10), in order to generate a series of pilot flames, which are appropriately regulated, in order to stabilise a main flame, which is primed inside the combustion chamber, in which a front area of the converging portion (12) of the pre-mixing chamber (10) has at least one circular groove (28) provided at the holes (20) which belong to the pies (19).

Abstract: The present invention relates to a liquid fuel injector (10) for burners in gas turbines, of the type used inside burners which are provided with a pre-mixing chamber (62) and an element (13) to create turbulence in the flow of compressed air obtained from the compressor of the gas turbine. The injector (10) comprises a body (11) which ends in a tip (12) and is provided with at least one duct (25) for passage of the fuel, and ducts (48, 58) for the inflow of compressed air from the compressor of the turbine, wherein the duct (25) for the fuel and the ducts (48, 58) for the compressed air end in respective outlet holes. The tip (12) of the injector (10) ends at the median part of the converging portion (61) of the pre-mixing chamber (62).