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: A cascade process for the production of power from variable temperature heat sources, includes: circulating a main working fluid selected from perfluorinated compounds (like Perfluoro-2-methylpentane/Perfluoro-i-hexane) in a main circuit according to a main supercritical organic Rankine cycle, operatively coupling in a boiler a variable temperature heat source with the main working fluid of the main circuit to heat and vaporize the main working fluid; circulating an auxiliary working fluid in an auxiliary circuit according to an auxiliary Rankine cycle; thermally coupling in cascade the expanded main working fluid of the main Rankine cycle with the auxiliary working fluid of the auxiliary Rankine cycle, in order to cool the main working fluid and heating the vaporizing the auxiliary working fluid by heat transfer from the main Rankine cycle to the auxiliary Rankine cycle before the expansion of the auxiliary working fluid in an auxiliary expander.

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 Rankine cycle plant for the regasification of liquefied gas, includes: a Rankine closed loop system; a source of liquefied gas at a cryogenic temperature operatively coupled to a condenser to receive heat from a working fluid from an expansion turbine to take the liquefied gas to the gaseous state; a source of a heating fluid at a temperature higher than the cryogenic temperature operatively coupled to an evaporator to transfer heat to the working fluid coming from the condenser. The expansion turbine is radial centrifugal with at least one auxiliary outlet interposed between successive stages. The condenser is multilevel and has at least two condensing chambers, wherein a lower chamber being connected to an outflow opening of the expansion turbine and an upper chamber connected to the auxiliary outlet of the expansion turbine.

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.

Abstract: A method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the stop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.

Abstract: A radial centrifugal turbomachine with an adjusting device operatively active at the axial inlet of the turbomachine fixed casing, including: an annular member delimiting at least one radially inner passage at the axial inlet, wherein the member front surface and abutment surface of the casing delimit a radial annular passage. An actuator is connected to the member and to move axially and/or rotate according to a predefined angle to vary the radial annular passage and/or passage sections delimited between stator blades of the turbomachine first radial stage. A transmission shaft coaxial with the rotation axis and integral with the member is operatively connected to the actuator. The adjusting device allows adjusting the mass flow rate at the inlet to better adapt the performances of the turbomachine to the loading of the process/cycle and to implement a safety system dedicated to stopping the turbomachine in case of an urgent stop request.

Abstract: A radial turbomachine has: a fixed casing; at least one rotor disc installed in the casing and rotatable in the casing around a respective rotation axis; a plurality of annular rotor elements coaxial with the rotation axis, axially projecting from a front face of the rotor disc and/or from a rear face of the rotor disc; a plurality of annular fixed elements coaxial with the rotation axis, axially projecting from the casing and each positioned in a radially external position with respect to a respective annular rotor element; a plurality of sealing devices radially interposed between at least some of said annular rotor elements and the respective annular fixed elements.

Abstract: A centrifugal radial turbine includes at least one support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path. The disc has through induction channels situated in a position radially external with respect to a respective shaft and radially internal with respect to the radial rotor stage. At the respective through induction channels, the disc includes a plurality of induction rotor blades of at least one respective axial rotor stage.

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: An ORC system for generation of energy by Organic Rankine Cycle comprises a turbo-expander (40) of a radial centrifugal type formed by a single rotor disc (108) and provided with an auxiliary opening (40c). The auxiliary opening (40c) is interposed between an inlet (40a) and an outlet (40b) of the turbine (40) and is in fluid connection with an auxiliary circuit (1000, 2000), such as to extract from the turbo-expander (40) or inject into the turbo-expander (40) the organic working fluid at an intermediate pressure between an injection pressure and a discharge pressure.