Abstract: A Controller, a gas turbine, and a method for auto-tuning a combustion system of a gas turbine are provided. The method includes selecting a first tuning curve from a set of tuning curves for the gas turbine; unbalancing a stable operating point of the gas turbine by modifying one or more operational parameters based on a predefined recipe; determining tuning parameters and storing them while a current operating point of the gas turbine is brought back on the first tuning curve; and generating a backup of tuning parameters to recover the stable operating point.

Abstract: Combustion system (10) for a gas turbine equipped with a premixing chamber (12) for air which is mixed with the fuel injected from a series of holes (11) creating a main central flame which is formed in a flame tube (14), the premixing chamber (12) is convergent towards a connection end with a combustion chamber comprising the flame tube (14), the combustion system (10) comprises a series of pilot devices (20) with premixing of the fuel gas, which create a series of corresponding pilot flames suitable for stabilizing the main central flame itself, at the same time reducing the polluting emissions.

Abstract: System for estimation and control of the concentrations of pollutant gases at the discharge of a gas turbine comprising a unit (3) for acquisition of the data relating to the operating state of the turbine, the said data being detected by a control panel (2) of the turbine. The system also comprises a local processing unit (4), which processes the said data in association with the said acquisition unit and makes the data available for consultation by the latter.

Abstract: Combustion system (10) for a gas turbine equipped with a premixing chamber (12) for air which is mixed with the fuel injected from a series of holes (11) creating a main central flame which is formed in a flame tube (14), the premixing chamber (12) is convergent towards a connection end with a combustion chamber comprising the flame tube (14), the combustion system (10) comprises a series of pilot devices (20) with premixing of the fuel gas, which create a series of corresponding pilot flames suitable for stabilizing the main central flame itself, at the same time reducing the polluting emissions.

Abstract: An improved flame tube or “liner” (112) for a combustion chamber (110) of a gas turbine with low emission of pollutants, of the type comprising a cylindrical structure connected to the outlet of a premixing chamber (114) by means of a truncated conical end (120), in which the premixing chamber (114) is supplied with air which is guided by a cavity (116) which is located between the flame tube (112) and outer walls (118) of the combustion chamber (110), this air circulating in the opposite direction to the flow of combustion products; a first cylindrical region (122) of the flame tube (112) is surrounded by a cylindrical casing (136) which creates an annular chamber (138).

Abstract: An improved combination (110) of a premixing chamber (112) and a combustion chamber (111), with low emission of pollutants, for gas turbines running on liquid and/or gas fuel, in which the combustion chamber (111) has a truncated conical end (111a) and is surrounded by a cavity (115) for cooling air (120), the cavity (115) carrying combustion air (120a) to the premixing chamber (112), which has at its inlet apertures or ports (126) which can be constricted according to the quantity of fuel used, and at its outlet a circumferential set of burners (134) to create a corresponding set of additional flames; gas fuel supply means (125) fuel and liquid fuel injection devices (119) are provided in the premixing chamber (112), and a set of liquid fuel injectors (140) is present on the end (111a).

Abstract: An improved combination (110) of a premixing chamber (112) and a combustion chamber (111), with low emission of pollutants, for gas turbines running on liquid and/or gas fuel, in which the combustion chamber (111) has a truncated conical end (111a) and is surrounded by a cavity (115) for cooling air (120), the cavity (115) carrying combustion air (120a) to the premixing chamber (112), which has at its inlet apertures or ports (126) which can be constricted according to the quantity of fuel used, and at its outlet a circumferential set of burners (134) to create a corresponding set of additional flames; gas fuel supply means (125) fuel and liquid fuel injection devices (119) are provided in the premixing chamber (112), and a set of liquid fuel injectors (140) is present on the end (111a).

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: 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: 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: 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: An improved flame tube or “liner” (112) for a combustion chamber (110) of a gas turbine with low emission of pollutants, of the type comprising a cylindrical structure connected to the outlet of a premixing chamber (114) by means of a truncated conical end (120), in which the premixing chamber (114) is supplied with air which is guided by a cavity (116) which is located between the flame tube (112) and outer walls (118) of the combustion chamber (110), this air circulating in the opposite direction to the flow of combustion products; a first cylindrical region (122) of the flame tube (112) is surrounded by a cylindrical casing (136) which creates an annular chamber (138).

Abstract: Combustion system with low polluting emissions for gas turbines, of the pre-mixing type, wherein a series of parallel burners, autonomously fed with additional fuel, is circumferentially arranged around the conjunction choke of the pre-mixing chamber with the combustion chamber, to create in the combustion zone immediately before the choke a corresponding series of additional flames for the stabilization of the main flame, the combustion air for the burners deriving from the cooling air of the tapered head of the combustion chamber, which is sent to the burners through twirled blades to give a substantially helicoidal movement to the air.

Abstract: A combustion system with low pollutant emission, of the pre-mixing type for gas turbines, in which the combustion air passes from the interspace to the pre-mixing chamber via apertures in this latter, their degree of opening being varied, in accordance with the fuel quantity used, by corresponding apertures in a rotatable drum, and in which a series of small holes fed with additional fuel is provided in the interspace. Further flame stabilization expedients and differential cooling of the combustion chamber are also provided.

Abstract: A gripper tape drive device for a shuttleless loom, in which a circular disc is mounted coaxial but not perpendicular to the main loom shaft, its outer circular edge rotatably engaging a circular collar, of which two opposing pins spaced 180.degree. apart cooperate with the ends of a fork rigid with the control shaft of the gripper tape sprocket. Adjustment means are also provided for varying the amplitude of the oscillatory motion of said control shaft.