Abstract: The invention relates to a blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, the blade having a profile which can be identified by having a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, the blade also comprising a thickening, substantially parallel to a base portion of the blade itself, fixable to said rotor, said thickening being substantially situated half-way up the blade and being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.

Abstract: Method for laterally replacing a heavy component of a plant assembly, the method including disconnecting the heavy component from other components of the plant assembly and from a base plate to which the heavy component is fixed; lifting the heavy component above the base plate with a lifting system provided within the base plate; connecting at least a pair of rails to the base plate, under the lifted heavy component, such that the at least a pair of rails extends at substantially a right angle relative to a longitudinal axis of the heavy component; lowering the heavy component on crawling mechanisms disposed on the at least a pair of rails; and laterally replacing the heavy component from the base plate and the other components of the plant assembly by actuating the crawling mechanisms.

Abstract: A method and apparatus are described for controlling the combustion in a gas turbine. The method includes measuring, with one or two calorimeters, the temperature, calorific value and relative density of a gaseous fuel in order to determine the Wobbe index, comparing the Wobbe index value measured with a predefined Wobbe index value for the gaseous fuel and regulating the temperature of the gaseous fuel with at least one heat exchanger in order to reach the predefined Wobbe index value. The method may also include using a second gaseous fuel, having a different Wobbe index from the gaseous fuel, or a fuel obtained by mixing the gaseous fuel and the second gaseous fuel, according to arbitrary proportions and variable with time.

Abstract: Resting element (10) for a compressor or turbine comprising a first cantilever resting portion (20) and a second fixing portion (30) to a case of the compressor or turbine by means of a series of screws (60), the second fixing portion (30) comprises a third end portion (32) externally axial symmetrical and also a fourth counter-portion (36) situated between the third portion (32) and the first resting portion (20) to prevent the disengagement of a hauling rope.

Abstract: Protection device for a stator of a turbine comprising a series of annular sectors (12) which can be coupled by connection means, each sector (12) comprising a first side surface (13) which has at least one cavity (14) equipped with a bottom (15), each bottom (15) of the at least one cavity (14) is convex and each sector (12) comprises at least one stiffening rib (16) positioned inside the at least one cavity (14) and having a variable section in a longitudinal direction to modulate the rigidity of each sector (12).

Abstract: Movement system (10) for the inspection of a turbine (40) of the type equipped with a shaft (42) having a series of blades, which is coupled with a shaft (72) of a compressor (70) by means of a loading joint (80), the system (10) comprises a crank rotation mechanism (20) in turn comprising a reducer group (24) for rotating the shaft (42) of the turbine (40) to allow the inspection of the series of blades by means of a boroscope, avoiding the necessity of decoupling the turbine (40) from the compressor (70).

Abstract: Vapor turbine operating with geothermal vapors containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of sealing laminas made of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapors, maintaining a high useful life of the series of sealing laminas and vapor turbine.

Abstract: Vapor turbine operating with geothermal vapors containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of stator blades made of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapors, maintaining a high useful life of the series of stator blades and vapor turbine.

Abstract: Blade (1) of a rotor for a first phase of a gas turbine having a profile identified by means of a series of closed intersection curves (20) between the profile itself and planes (X,Y) lying at distances (Z) from the central axis, each closed curve (20) has a first rounded end (21) and a second rounded end (22), which connect the trace of the first surface (3) with the trace of the second surface (5) in depression, the first end (21) first meets a gas flow of the turbine, each closed curve (20) has an axial chord (40) defined as the maximum distance of the first end (21) from the second end (22) along the axis (X), each closed curve (20) has a thickness (30) of the first end (21) defined as the maximum diameter of the circle inscribed in the first end (21); said dimensionless thickness (30), i.e. divided by the axial chord (40), has a quadric distribution according to a curve of the fourth order along the axis (Z).

Abstract: Vapor turbine operating with geothermal vapors containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of rotor blades made of a nickel alloy containing a quantity of nickel ranging from 55% to 59% by weight to avoid the washing of the geothermal vapors, maintaining a high useful life of the series of rotor blades and vapor turbine.

Abstract: A rotor for the second phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y,Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat single ranges from 54.9° to 57.9°.

Abstract: A stator for the second phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade is identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 57.8° to 60.8°.

Abstract: A rotor for the first phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y,Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade is identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 54.9° to 57.9°.

Abstract: A stator for the first phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z) wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade is identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 57° to 60°.

Abstract: Vapour turbine operating with geothermal vapours containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of rotor blades made of a nickel alloy containing a quantity of nickel ranging from 55% to 59% by weight to avoid the washing of the geothermal vapours, maintaining a high useful life of the series of rotor blades and vapour turbine.

Abstract: Vapour turbine operating with geothermal vapours containing corrosive agents or aggressive substances such as chlorides and/or sulfides in particular. The turbine comprises a series of stator blades and a series of rotor blades, each stator blade of the series of stator blades comprises a surfacing consisting of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapours, at the same time maintaining a high useful life of the series of stator blades and vapour turbine.

Abstract: Vapour turbine operating with geothermal vapours containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of sealing laminas made of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapours, maintaining a high useful life of the series of sealing laminas and vapour turbine.

Abstract: Vapour turbine operating with geothermal vapours containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of stator blades made of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapours, maintaining a high useful life of the series of stator blades and vapour turbine.

Abstract: Blade (1) of a rotor for a first phase of a gas turbine having a profile identified by means of a series of closed intersection curves (20) between the profile itself and planes (X,Y) lying at distances (Z) from the central axis, each closed curve (20) has a first rounded end (21) and a second rounded end (22), which connect the trace of the first surface (3) with the trace of the second surface (5) in depression, the first end (21) first meets a gas flow of the turbine, each closed curve (20) has an axial chord (40) defined as the maximum distance of the first end (21) from the second end (22) along the axis (X), each closed curve (20) has a thickness (30) of the first end (21) defined as the maximum diameter of the circle inscribed in the first end (21); said dimensionless thickness (30), i.e. divided by the axial chord (40), has a quadric distribution according to a curve of the fourth order along the axis (Z).

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).