Abstract: A process for energy storage comprises carrying out a cyclic thermodynamic transformation wherein, in a charge phase, a condensation of a working fluid is executed by means of heat absorption by a heat carrier in order to store the working fluid in the liquid or supercritical phase; in a discharge phase, an evaporation of the working fluid is executed starting from the liquid or supercritical phase and by transfer of heat from the heat carrier; provision is made for actively adjusting at least one parameter of the working fluid related to the condensation and/or to the evaporation, in order to control at least one temperature of the heat carrier and uncouple it from the ambient temperature without the aid of systems outside the cyclic thermodynamic transformation.

Abstract: A process for energy management includes actuating a closed cyclic thermodynamic transformation, first in one direction in a charge configuration/phase and then in the opposite direction in a discharge configuration/phase, between a casing for the storage of a working fluid other than atmospheric air, in gaseous phase and in equilibrium of pressure with the atmosphere, and a tank for the storage of the working fluid in liquid or super-critical phase with a temperature close to its own critical temperature. In the charge phase, the process accumulates heat and pressure. In the discharge phase, the process generates energy. The process includes actuating, with at least one part of the working fluid, at least one closed thermodynamic cycle, even at the same time as the charge phase or as the discharge phase; and heating the working fluid by means of at least one oxy-combustion within the closed thermodynamic cycle.

Abstract: A process for energy storage comprises carrying out a cyclic thermodynamic transformation wherein, in a charge phase, a condensation of a working fluid is executed by means of heat absorption by a heat carrier in order to store the working fluid in the liquid or supercritical phase; in a discharge phase, an evaporation of the working fluid is executed starting from the liquid or supercritical phase and by transfer of heat from the heat carrier; provision is made for actively adjusting at least one parameter of the working fluid related to the condensation and/or to the evaporation, in order to control at least one temperature of the heat carrier and uncouple it from the ambient temperature without the aid of systems outside the cyclic thermodynamic transformation.

Abstract: A plant for energy storage, comprises: a basin (2) for a work fluid having a critical temperature (Tc) lower than 0°; a tank (3) configured to store the work fluid in at least partly liquid or super-critical phase with a storage temperature (Ts) close to the critical temperature (Tc); an expander (4); a compressor (5); an operating/drive machine (6) operatively connected to the expander (4) and to the compressor (5); a thermal store (8) operatively interposed between the compressor (5) and the tank (3) and between the tank (3) and the expander (4). The plant (1) is configured for actuating a Cyclic Thermodynamic Transformation (TTC) with the work fluid, first in a storage configuration and then in a discharge configuration. The thermal store (8), in the storage configuration, is configured for absorbing sensible heat and subsequently latent heat from the work fluid and, in the discharge configuration, it is configured for transferring latent heat and subsequently sensible heat to the work fluid.

Abstract: A process for energy management includes actuating a closed cyclic thermodynamic transformation, first in one direction in a charge configuration/phase and then in the opposite direction in a discharge configuration/phase, between a casing for the storage of a working fluid other than atmospheric air, in gaseous phase and in equilibrium of pressure with the atmosphere, and a tank for the storage of the working fluid in liquid or super-critical phase with a temperature close to its own critical temperature. In the charge phase, the process accumulates heat and pressure. In the discharge phase, the process generates energy. The process includes actuating, with at least one part of the working fluid, at least one closed thermodynamic cycle, even at the same time as the charge phase or as the discharge phase; and heating the working fluid by means of at least one oxy-combustion within the closed thermodynamic cycle.

Abstract: Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions.

Abstract: A set of turbines, including: a first turbine including a first shaft supported in an overhung manner in a first case, a first rotor provided with first rotor blades and joined to a distal end of the first shaft; a second turbine including a second shaft supported in an overhung manner in a second case, and a second rotor provided with second rotor blades and joined to a distal end of the second shaft. A first front face of the first rotor faces a second front face of the second rotor. The set of turbines further includes a connection element connected to the first front face and to the second front face to transmit rotation from the first shaft to the second shaft or vice versa. The connection element includes at least one elastic joint configured to minimize the rotordynamic influence of the first and second turbine on each other.

Abstract: A method for the assembly of a counter-rotating radial turbine includes: preparing a central case; pre-assembling a first turbine unit and a second turbine unit, each including: a half-case delimiting a housing; a rotating unit with a shaft housed and rotatably supported in the housing and that is free to rotate about an axis of rotation with respect to said housing; a rotor disc joined to and overhanging a distal end of the shaft and having a front bladed face facing the opposite side with respect to the half-case. The method includes coupling the first pre-assembled turbine unit and the second pre-assembled turbine unit to the central case so as to arrange the front bladed face of the first rotor disc in front of the front bladed face of the second rotor disc, wherein, following the coupling process, the first half-case and the second half-case laterally close the central case.

Abstract: Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions.

Abstract: A radial turbomachine with axial thrust compensation includes a rotor disc with main bladed rings. The main bladed rings together with auxiliary bladed rings delimit a plurality of concentric front main chambers at different pressures. A plurality of concentric rear annular main chambers, each in fluid communication with a respective front main chamber and at the same pressure as the respective front main chamber, is delimited between a rear face of the rotor disc and a fixed casing. The concentric front main chambers are delimited by front areas of the rotor disc and concentric rear annular main chambers are delimited by rear annular areas of the rotor disc. All the rear annular areas are identical to the respective front areas except for one, which is a compensation area configured to compensate, at least in part, for the thrust of external pressure acting on the shaft.

Abstract: The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different diameters. Preparing the disc (6, 14) comprises: realizing annular sets of blades (20) in one piece with the disc (6, 14), said sets (20) being concentric and coaxial with a central axis (X-X) and arranged on the front face (7), wherein each blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X); and/or preparing a plurality of reinforcement rings (23) comprises: realizing in one piece with each one of the reinforcement rings (23) an annular set of auxiliary blades (20?) arranged around a central axis (X-X), wherein each auxiliary blade (20?) has a leading edge (21?) and a trailing edge (22?) substantially parallel to the central axis (X-X).

Abstract: Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions.

Abstract: A method for the construction of bladed rings for radial turbomachines, including: preparing an annular block; roughing the annular block by removing material to define a first, second, third and fourth axial section, wherein the first axial section defines a reinforcement ring, wherein the third axial section defines a base ring; roughing the second axial section by removing material to delimit a plurality of separate elements, wherein the separate elements axially connect the base ring to the reinforcement ring; finishing each of the separate elements by removing material to provide the separate element with the shape of an airfoil blade, wherein a leading edge of the blade and a trailing edge of the blade develop substantially parallel to a central axis of the bladed ring; roughing the fourth axial section by removing material for delimiting an annular anchoring appendage of the base ring to a radial turbomachine.

Abstract: A method for the assembly of a counter-rotating radial turbine includes: preparing a central case; pre-assembling a first turbine unit and a second turbine unit, each including: a half-case delimiting a housing; a rotating unit with a shaft housed and rotatably supported in the housing and that is free to rotate about an axis of rotation with respect to said housing; a rotor disc joined to and overhanging a distal end of the shaft and having a front bladed face facing the opposite side with respect to the half-case. The method includes coupling the first pre-assembled turbine unit and the second pre-assembled turbine unit to the central case so as to arrange the front bladed face of the first rotor disc in front of the front bladed face of the second rotor disc, wherein, following the coupling process, the first half-case and the second half-case laterally close the central case.

Abstract: A set of turbines, including: a first turbine including a first shaft supported in an overhung manner in a first case, a first rotor provided with first rotor blades and joined to a distal end of the first shaft; a second turbine including a second shaft supported in an overhung manner in a second case, and a second rotor provided with second rotor blades and joined to a distal end of the second shaft. A first front face of the first rotor faces a second front face of the second rotor. The set of turbines further includes a connection element connected to the first front face and to the second front face to transmit rotation from the first shaft to the second shaft or vice versa. The connection element includes at least one elastic joint configured to minimize the rotordynamic influence of the first and second turbine on each other.

Abstract: The present invention relates to a radial turbomachine with axial thrust compensation, comprising: a fixed casing (3); a plurality of main concentric bladed rings (9?,9?,9??,9??) arranged in the fixed casing (3) around a central axis (X-X); a plurality of concentric auxiliary bladed rings (15?, 15?, 15??) arranged in the fixed casing (3) around the central axis (X-X) and radially alternated with the main bladed rings (9?,9?,9??,9??). A rotor (2, 2?) comprising a rotor disc (6, 6?) and a rotation shaft (4, 4?, 4?) integral with the rotor disc (6, 6?) is rotatable in the fixed casing (3) around the central axis (X-X) and carries, on a front face (7, 7?), the main bladed rings (9?,9?,9??,9??). The main (9?,9?,9??,9??) and auxiliary (15?, 15?, 15??) bladed rings delimit, with the rotor disc (6, 6?), a plurality of concentric front main chambers (30, 33, 35, 36) at different pressures.

Abstract: The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different diameters. Preparing the disc (6, 14) comprises: realizing annular sets of blades (20) in one piece with the disc (6, 14), said sets (20) being concentric and coaxial with a central axis (X-X) and arranged on the front face (7), wherein each blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X); and/or preparing a plurality of reinforcement rings (23) comprises: realizing in one piece with each one of the reinforcement rings (23) an annular set of auxiliary blades (20?) arranged around a central axis (X-X), wherein each auxiliary blade (20?) has a leading edge (21 ‘) and a trailing edge (22’) substantially parallel to the central axis (X-X).

Abstract: A method for manufacturing bladed rings for radial turbomachines, including: assembling a first support ring with a second support ring, with a plurality of blades, with a first and second connecting ring, to make a bladed ring including the first and second support ring coaxial and axially spaced and the plurality of blades disposed equidistant from a central axis and interposed between the rings. The method includes joining a first end of each blade to the first connecting ring, joining a second end of each blade to the second connecting ring, fixing the first connecting ring to the first support ring and fixing the second connecting ring to the second support ring. The first support ring, second support ring, plurality of blades, first and second connecting rings are finished elements before assembling, meaning they present their final geometry and need no further machining and/or plastic deformations during and/or after assembly.

Abstract: A method for the construction of bladed rings for radial turbomachines, including: preparing an annular block; roughing the annular block by removing material to define a first, second, third and fourth axial section, wherein the first axial section defines a reinforcement ring, wherein the third axial section defines a base ring; roughing the second axial section by removing material to delimit a plurality of separate elements, wherein the separate elements axially connect the base ring to the reinforcement ring; finishing each of the separate elements by removing material to provide the separate element with the shape of an airfoil blade, wherein a leading edge of the blade and a trailing edge of the blade develop substantially parallel to a central axis of the bladed ring; roughing the fourth axial section by removing material for delimiting an annular anchoring appendage of the base ring to a radial turbomachine.

Abstract: An ORC binary cycle geothermal plant, including at least one ORC closed-cycle system and a geothermal system. The geothermal system includes at least one intake line of a geothermal fluid connected to at least one geothermal production well, wherein the fluid includes non-condensable gases; one interface line connected to the intake line, coupled to the ORC system in an interface zone, wherein the fluid exchanges heat with the organic working fluid; one reinjection line connected to the interface line and to at least one geothermal reinjection well. Further at least one separator device configured to separate at least the gases from the fluid; one expander connected to an outlet of the gases by the separator device; and one auxiliary generator connected to the expander. The expander is for interfacing with the system to receive and expand at least the gases after they have exchanged heat with the organic working fluid.