Turbomachine and device having said turbomachine

Abstract

The turbomachine comprises a case (2) and a rotor (4) arranged in the case (2) so as to rotate about its longitudinal axis (XX) relative to the case (2). The rotor (4) has a blade arrangement for passing a first working fluid arranged on the rotor (4) and in each passing volume (11) partitioned between the rotor (4) and the case (2), and a helical conduit (14) extending in a loop around the longitudinal axis (XX) and between an inlet (15) and an outlet (16) for passing a second working fluid. The helical conduit (14) is radially inward relative to the blade arrangement and has a loop whose radial dimension gradually increases or decreases from the inlet (15) to the outlet (16).

Description

[Technical field]

[0001] The present invention is directed to a turbomachine and to a device comprising said turbomachine. The invention is in the technical field of turbomachines, at least in part, for example one or more stages, of the "bladeless" type, i.e. without vanes. Preferably, the invention is in the technical field of turbomachines, used in the field of devices for energy conversion, for example, but not necessarily, devices arranged for realizing a refrigeration cycle. [Background technology]

[0002] Vaneless (bladeless) turbomachines are known which use a rotor with a spiral channel through which a working fluid passes, obtaining energy exchange between said working fluid and said rotor.

[0003] For example, document CN201610943536 shows a steam turbine having a spiral channel integrally connected to the rotor.

[0004] Document US 2,655,868 shows a centrifugal pump having a rotor in which is formed a spiral channel having at least a helical spiral.

[0005] Document US 2,544,154 shows a tubular turbine having a variable diameter conduit with a number of helically arranged lobes.

[0006] Document ES 2365663 A1 shows a turbine with radial ridges between which the openings of the inclined passages obtained in the turbine are formed.

[0007] Document US 4,603,549 A shows a turbine motor with a helical tube. Summary of the Invention [Problem to be solved by the invention]

[0008] In this field, the applicant has set himself the goal of proposing a "bladeless" turbomachine, which, taking advantage of the "bladeless" principle, is more compact and more efficient and can be used in various fields for energy conversion.

[0009] The Applicant has set himself in particular the objective of proposing a turbomachine that integrates different stages and / or functions (for example an expander and a compressor, or different stages of expansion and / or compression).

[0010] The applicant has also set himself the objective of proposing a turbomachine that is compact and moreover easily deployable in an apparatus for energy conversion.

[0011] The Applicant has also set himself the objective of proposing a turbomachine which is structurally simple and which is also relatively cheap and reliable. [Means for solving the problem]

[0012] The Applicant has found that these aims and objectives are obtained by realising a turbomachine according to the invention of the type as claimed in the accompanying claims and / or as described in the following aspects.

[0013] In particular, the turbomachine according to the present invention integrates a conventional bladed turbomachine into a vane-free or "bladeless" type turbomachine.

[0014] According to a first aspect, the present invention relates to a turbomachine comprising: Case and a rotor disposed in the case so as to be rotatable about its longitudinal axis relative to the case; Equipped with The rotor is at least one blade arrangement attached to the rotor and arranged in a respective passage volume defined between the rotor and the case for passage of a first working fluid; at least one helical conduit extending in a loop about the longitudinal axis and between at least one inlet and at least one outlet for a flow path of a second working fluid, the at least one helical conduit being radially inward of the at least one blading and having a loop with a radial dimension gradually increasing or decreasing from the inlet to the outlet; It has.

[0015] The through volume is the passage occupied by the blading and through which the first working fluid passes while interacting with the blading and stator components of the turbomachine.

[0016] According to a second aspect, there is provided an apparatus for energy conversion, comprising a turbomachine according to the preceding first aspect and / or according to one or more of the second aspects described below.

[0017] In this specification and the appended claims, the term "blading" generally intends an assembly of elements or suitably shaped elements that rotate with a rotor and interact with a working fluid to convert the energy of the fluid into mechanical energy of rotation of the rotor, or vice versa. Thus, unless otherwise specified, blading may include vanes, blades, lobes, screw profiles, scroll shapes, etc., and may function as an expander / turbine or compressor / pump.

[0018] The applicant has determined that by integrating a bladeless turbomachine with a conventional bladed turbomachine in accordance with the invention as set forth in the claims and described embodiments, it is possible to achieve multiple expansion and / or compression functions with minimal overall dimensions.

[0019] The applicant has determined that the compactness of the turbomachine according to the invention allows it to be easily installed in various types and sizes of energy conversion equipment.

[0020] The Applicant has also determined that the turbomachine according to the invention, apart from being compact, is furthermore structurally simple, reliable and relatively inexpensive.

[0021] The applicant has further determined that a turbomachine according to the invention makes it possible to increase the efficiency of the equipment in which it is installed.

[0022] Further aspects of the invention are set out below.

[0023] In one aspect, the at least one blade and the at least one helical conduit are integral with one another and rotate together about a longitudinal axis.

[0024] In one aspect, the at least one blade is disposed on a radially outer surface of the rotor.

[0025] In one aspect, the at least one helical conduit is radially inward relative to the at least one blading.

[0026] In one aspect, the at least one helical conduit is radially inward relative to the radially outer surface.

[0027] In one aspect, the rotor is a solid body and the at least one helical conduit is formed in the solid body.

[0028] In one aspect, the rotor is realized from metals, such as steel, stainless steel (eg, martensitic, austenitic), nickel alloys, aluminum, or plastics, composites, or organic materials, depending on the application.

[0029] In one aspect, the rotor is realized by 3D printing, casting, machining, such as milling or EDM (electrical discharge machining), depending on the material selected for its formation.

[0030] In one aspect, the rotor has at least two portions that are rigidly joined together, for example by welding, or diffusion bonding, or mechanical connection.

[0031] In one aspect, each section has at least one bundle of at least one helical conduit formed therein.

[0032] In one aspect, the at least one inlet is located in a radially outer surface of the rotor.

[0033] In one aspect, a turbomachine has a shaft integral with a rotor.

[0034] In one aspect, the shaft is rotatably supported within and / or by the case.

[0035] In one aspect, a bearing is interposed between the case and the shaft to allow the rotor to rotate within the case.

[0036] In one aspect, the rotor is located at the end of a shaft and is therefore supported overhanging within the case.

[0037] In one aspect, the rotor is located between opposite ends of a shaft, with each end supported within a case.

[0038] In one aspect, the shaft is connected to an electric motor and / or to a generator.

[0039] In one aspect, the shaft supporting the rotor is a motor and / or generator shaft that passes through the case.

[0040] In one aspect, the shaft is rotatably supported by a bearing in the motor or generator.

[0041] In one aspect, the rotor has a first portion that supports the blading and a second portion that is defined by, constitutes, or is attached to the shaft.

[0042] In one aspect, the first and second portions are separate elements, optionally connected to one another via screws, welds, or Hirth teeth.

[0043] The two-part realization allows for optimisation of production and costs.

[0044] For example, the second part can be realized by 3D printing and the first part by milling. The first and second parts can be realized in the same or different materials, for example in such a way as to optimize their strength according to the different loads and temperature conditions. By realizing a rotor with a first and a second part, the two parts can be thermally decoupled. For example, in the case of a turbopump for space propulsion, the second part (inner) is at -200 °C, whereas the first part (outer) is at 600 °C. Moreover, in this way it is also possible to intervene (perform upgrades) in existing turbomachines, for example refrigeration compressors, by directly adding a "bladeless" part by modifying an already functioning compressor.

[0045] The two separated parts can move freely, one relative to the other in a limited manner, for example along the hearth, and such relative movement makes it possible to avoid breakage of the two due to thermal stresses associated with deformations that would be prevented if a solid body were realized.

[0046] The two-part realisation of the rotor allows optimisation of maintenance, as the two parts can be replaced independently.

[0047] In one aspect, at least one helical conduit is provided in the first portion or the second portion, or in both the first portion and the second portion.

[0048] In one aspect, the first part is attached to the shaft.

[0049] In one aspect, multiple first portions are mounted on a common shaft to provide multiple turbomachines.

[0050] In one aspect, the helical conduits of the turbomachine are connected to each other in series or parallel.

[0051] In one aspect, the passing volumes of the turbomachines are connected to one another in series or in parallel.

[0052] In one aspect, the rotor has at least one void to reduce the weight of the rotor.

[0053] In one aspect, the at least one gap portion is internal to the rotor or formed in an exterior surface of the rotor.

[0054] In one aspect, the rotor, or at least a portion thereof, has a honeycomb structure, for example achieved by 3D printing.

[0055] In one aspect, the at least one outlet is located in a top surface of the rotor.

[0056] In one aspect, the at least one inlet is located near a first end of the rotor.

[0057] In one aspect, the at least one outlet is located near a second end of the rotor opposite the first end.

[0058] In one aspect, the rotor has a plurality of helical conduits.

[0059] In one aspect, the rotor has multiple inlets for the helical conduits, one for each conduit or multiple inlets for each conduit.

[0060] In one aspect, the rotor has multiple outlets for the helical conduits, one for each conduit, or also multiple outlets for each conduit.

[0061] In one aspect, different helical conduits are disposed in different axial regions of the rotor.

[0062] In one aspect, the different helical conduits are disposed in the same axial region of the rotor.

[0063] In one aspect, the at least one helical conduit has constant or variable portions of a path along its progression.

[0064] In one aspect, the cross section of the at least one helical conduit has a circular or triangular or elongated or T-shape.

[0065] In one aspect, the different helical conduits have respective inlets or outlets located near the axial center of the rotor and respective outlets or inlets located at opposite ends of the rotor or shaft.

[0066] In one aspect, the rotor has an inlet series of helical conduits.

[0067] In one aspect, each series has a number of outlets circumferentially arranged around the rotor.

[0068] In one aspect, each series is in fluid communication with a respective helical conduit, at least some of which join together or remain separate until said at least one outlet.

[0069] In one aspect, the series are disposed at different axial positions.

[0070] In one aspect, the rotor has circumferential surfaces of differing diameters, and each series is disposed on one of the circumferential surfaces.

[0071] In one aspect, the at least one blading comprises a plurality of vanes.

[0072] In one aspect, the at least one inlet and / or the at least one outlet are disposed between vanes of a blading arrangement to modify a boundary layer of the first working fluid.

[0073] In one aspect, the at least one blading defines at least one profile of the screw.

[0074] In one aspect, the at least one blading within the passing volume defines or is part of one of a compressor or a pump, for example of the blade, lobe, screw, spiral, or scroll type.

[0075] In one aspect, the at least one blading in the passing volume defines or is part of one of the bladed expanders.

[0076] In one aspect, the at least one helical conduit is a vaneless (bladeless) expander, such as a vaneless turbine.

[0077] In one aspect, the at least one helical conduit is a vaneless (bladeless) compressor or pump.

[0078] In one aspect, the bladed expander is a turbine, optionally an axial flow turbine, a radial flow turbine, or a radial / axial turbine, or a mixed axial / radial flow turbine.

[0079] In one aspect, the bladed compressor is a radial compressor, an axial compressor, or a radial / axial compressor, a mixed axial / radial flow compressor.

[0080] In one aspect, the at least one blading and the at least one helical conduit located within the passing volume are part of the same circuit, and the first working fluid and the second working fluid are the same working fluid.

[0081] In one aspect, the at least one blading and the at least one helical conduit located within the passing volume are part of separate circuits, and the first working fluid and the second working fluid may be different fluids.

[0082] In one aspect, the first working fluid is a gas, vapor, or liquid, such as a coolant, oxygen, or hydrogen.

[0083] In one aspect, the second working fluid is a gas, vapor, or liquid, such as liquid oxygen, hydrogen, or liquid hydrogen.

[0084] In one aspect, the case has a diffuser disposed about the rotor and in fluid communication with an outlet of the passage volume.

[0085] In one aspect, the case has a diffuser disposed about the rotor and in fluid communication with an outlet of the at least one helical conduit.

[0086] In one aspect, the case has a distributor disposed about the rotor and in fluid communication with the inlet of the passing volume.

[0087] In one aspect, the case has a distributor disposed about the rotor and in fluid communication with the inlet of the at least one helical conduit.

[0088] In one aspect, the diffuser and distributor are side-by-side and separated from each other by a bulkhead in the case.

[0089] In one aspect, the distributor has a plurality of directional blades, optionally the blades being directional, and the turbomachine is adapted to operate at partial or variable loads.

[0090] In one aspect, the distributor is configured to channel the second working fluid through one or more inlet series depending on the load (eg, to operate at partial or variable load).

[0091] In one aspect, the case has a plurality of stationary vanes that cooperate with the at least one blading within the passing volume.

[0092] In one aspect, the device for energy conversion is a refrigeration device or a heat pump.

[0093] In one aspect, the turbomachine is used as a turbocharger in the gas cycle (gas turbine or turbogas) or steam cycle (as a turbopump).

[0094] In one aspect, the turbomachine is a turbine, or a compressor, or a turbocharger, or a turbopump.

[0095] In one aspect, the refrigeration apparatus comprises: At least one condenser; At least one evaporator; at least one turbomachine, i.e. a turbocharger, according to the preceding aspect; an electric motor connected to a rotor of the turbomachine; a duct connecting the at least one condenser, the at least one evaporator, and the at least one turbomachine to form a refrigeration circuit; Equipped with A duct connects the at least one condenser and the at least one evaporator to the at least one turbomachine to compress a working fluid circulating in the refrigeration circuit before entering the at least one condenser and to expand the working fluid before entering the at least one evaporator.

[0096] In one aspect related to the preceding aspect, the at least one evaporator has an inlet and an outlet, the at least one condenser has an inlet and an outlet, the vane arrangement in the passing volume defines or is a part of a compressor, the at least one helical conduit is an expander, the condenser outlet is connected to the inlet of the at least one helical conduit, the condenser inlet is connected to the outlet of the passing volume, the evaporator outlet is connected to the inlet of the passing volume, and the evaporator inlet is connected to the outlet of the at least one helical conduit.

[0097] The applicant has determined that by applying the turbomachine (turbocharger) according to the present invention to a refrigeration system, it is possible to reduce consumption and / or increase the refrigeration capacity (heat generation capacity when used as a heat pump), i.e. improve efficiency.

[0098] The applicant has also determined that when the turbomachine is a turbopump for an aerospace propulsion system, the vaneless pump according to the invention allows for savings in size (it is more compact) and weight, and, taking into account the presence of liquid, has a better performance than a conventional bladed pump.

[0099] Other features and advantages will become apparent from the detailed description of preferred, but non-exclusive, embodiments of the turbomachine according to the invention and of an apparatus comprising said turbomachine. [Brief description of the drawings]

[0100] The description will now be made with reference to the accompanying drawings, which are for illustrative purposes only and are therefore non-limiting. [Figure 1] FIG. 1 is a cross-sectional view of a turbomachine according to the present invention. [Diagram 2] FIG. 2 is a three-dimensional view of the turbomachine of FIG. [Diagram 3] FIG. 3 is an exploded view of the turbomachine of FIGS. 1 and 2 at an assembly step. [Figure 4] FIG. 4 is a rear view of the rotor of the turbomachine of the preceding figures. [Diagram 5] FIG. 5 shows a schematic diagram of a refrigeration device according to the present invention. [Figure 6] FIG. 6 shows the refrigeration cycle performed by the device of FIG. 5 in comparison with a conventional refrigeration cycle. [Figure 7] FIG. 7 is a cross-sectional view of a modified turbomachine according to the present invention. [Figure 8] FIG. 8 is a sectional view of another modified example of the turbomachine according to the present invention. [Figure 9] FIG. 9 is a sectional view of another modified example of the turbomachine according to the present invention. [Figure 10] FIG. 10 is a sectional view of another modified example of the turbomachine according to the present invention. [Figure 11] FIG. 11 shows a schematic representation of an embodiment of a rotor for a turbomachine according to the invention. [Figure 12] FIG. 12 shows a schematic representation of an embodiment of a rotor for a turbomachine according to the invention. [Figure 13] FIG. 13 shows a schematic representation of an embodiment of a rotor for a turbomachine according to the invention. [Figure 14] FIG. 14 shows a schematic representation of an embodiment of a rotor for a turbomachine according to the invention. [Figure 15] FIG. 15 is a schematic rear view of a rotor of a turbomachine according to the present invention. [Figure 16] FIG. 16 shows another variant of the turbomachine of FIG. [Figure 17]FIG. 17 shows another variant of the rotor which can be implemented in the turbomachine according to the invention. [Figure 18] FIG. 18 shows another variant of the rotor which can be implemented in the turbomachine according to the invention. [Figure 19] FIG. 19 shows another variant of the rotor which can be implemented in the turbomachine according to the invention. [Figure 20] FIG. 20 shows another variant of the rotor which can be implemented in the turbomachine according to the invention. [Figure 21] FIG. 21 shows another variant of the rotor which can be implemented in the turbomachine according to the invention. [Figure 22] FIG. 22 shows another variant of the rotor which can be implemented in the turbomachine according to the present invention. [Figure 23] FIG. 23 shows another variant of the rotor which can be implemented in the turbomachine according to the invention. [Figure 24] FIG. 24 shows another variant of the rotor which can be implemented in the turbomachine according to the present invention. [Diagram 25] FIG. 25 shows another variant of the rotor which can be implemented in the turbomachine according to the present invention. [Figure 26] FIG. 26 shows another variant of the rotor which can be implemented in the turbomachine according to the present invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0101] With reference to the accompanying drawings, at 1 there is shown generally a turbomachine according to the present invention.

[0102] In the embodiment shown in Figures 1 to 3, the turbomachine 1 is a turbocharger that integrates a mixed axial / radial flow centrifugal compressor and a turbine without vanes, i.e., a "bladeless" type turbine.

[0103] The turbomachine 1 has a case 2 having a central portion 3 defining a housing for a rotor 4 and a sleeve 5 extending and overhanging from a side of the central portion 3. The tubular body 6 extends and overhangs from the side of the central portion 3 opposite to the side connected to the sleeve 5.

[0104] The rotor 4 has a cylindrical base 7 with a larger diameter circular portion which tapers to a distal portion 8 with a smaller diameter circular portion. The radially outer surface 9 of the rotor 4 turns from the distal end 8 towards the cylindrical base 7, resulting in a blading defined by a number of vanes 10 that decrease in height from the distal end 8 towards the cylindrical base 7. The vanes 10 are curved and follow the profile of the radially outer surface 9.

[0105] The wall of the case 2 is located near the vanes 10 and defines, together with the radially outer surface 9 of the rotor 4, a passage volume 11 for passing a first working fluid. A portion of said passage volume decreases from the distal end 8 towards the cylindrical base 7, i.e. starting from the inlet 12 of the passage volume 11 towards the outlet 13 of said passage volume.

[0106] The rotor 4 is a solid body and further has a helical conduit 14 obtained therein. The helical conduit 14 extends in a loop around the longitudinal axis "XX" or axis of rotation of the rotor 4. The helical conduit 14 has a number of inlets 15 defined by respective holes formed in the radially outer surface of the rotor 4 near the cylindrical base and an outlet 16 formed in the head surface of the distal portion 8 of the rotor 4. For example, but not necessarily, the outlets 16 are axial, i.e., parallel to the longitudinal axis "XX".

[0107] The helical conduit 14 unfolds in loops around the longitudinal axis "XX" and extends between a number of inlets 15 and an outlet 16 according to a number of loops of gradually decreasing radial dimensions starting from the inlets 15 towards the outlet 16. The inlets 15 are all connected to a first loop of larger dimensions, as for example shown in FIG.

[0108] The helical conduit 14 is radially inward relative to the radially outer surface 9 of the blading and rotor 4 and is configured to allow the passage of a second working fluid.

[0109] The helical conduit 14 also utilizes frictional forces exchanged between the inner surface of the helical conduit 14 and the second working fluid to transmit power / force between said fluid and the rotor 4 .

[0110] The turbomachine 1 has a shaft 17 which is integral with the rotor 4 and extends from the cylindrical base 7 coaxially with the longitudinal axis "XX". The shaft 17 is mounted in the sleeve 5 of the case 2 via bearings 18 so as to be rotatable about the longitudinal axis "XX". The bearings 18 support the shaft 17 and overhang the rotor 4 within the case 4, being located only on one side of the rotor 4, whereas the distal portion 8 is not supported by the case 4 but overhangs and projects. In a variant of the embodiment, the rotor 4 can be connected to a motor and / or a generator.

[0111] In these variants, the shaft 17 may also be the shaft of a motor / generator which passes through an opening in the case 2 and supports the rotor 4. In these variants, the shaft is supported by a bearing of the motor / generator instead of the bearing 18 arranged in the case 4.

[0112] The rotor 4 is a solid body, and the vanes 10 and the helical conduits 14 are integral with each other and rotate together about a longitudinal axis "XX" when the rotor 4 rotates.

[0113] The central part 3 of the case 2 defines a diffuser 19 and a distributor 20 arranged around the cylindrical base 7. The diffuser 19 surrounds the outlet 13 of the passing volume 11 and is in fluid communication with the outlet 13. The distributor 20 surrounds the inlet 15 of the helical conduit 14 and is in fluid communication with the inlet 15. The diffuser 19 and the distributor 20 are formed in a loop 21 arranged around the cylindrical base 7 and are separated from each other by a partition 22. The partition 22 is connected to the radial circumferential wall of the loop 21 and its radial inner edge is arranged near the cylindrical base 7. The edges are provided with a gasket or mechanical seal to prevent leakage between the diffuser 19 and the distributor 20. Optionally, the diffuser 19 is arranged with fixed blades 23 and the distributor 20 is arranged with directional blades 24. The directing blades 24 can be oriented as a function of the flow rate, and the turbomachine 1 is adapted to operate at part load or variable load.

[0114] A radial support 25 arranged within the tubular body 6 supports an inner tubular body 26 arranged forward of the distal portion 8 and coaxial with the longitudinal axis "XX" of the rotor 4, and receives the second working fluid exiting the outlet 16 of the helical conduit 14 and allows it to leak out of the case 2 through a first outlet 27 from said case 2.

[0115] The first inlet 28 of the case 2 is bounded between the tubular body 6 and the inner tubular body 26 and allows the first working fluid to enter from the inlet 12 of the passing volume 11. The loop 21 has a respective second inlet 29 in the case 2 flowing into the distributor 20 and a second outlet 30 for the first working fluid to escape from the diffuser 19. Furthermore, the first working fluid enters axially into the case 2 from the first inlet 28, passes through the passing volume 11 with the vanes 10, flows in the diffuser 19 and exits from the second outlet 30. The second working fluid enters from the second inlet 29 of the case 2 along a direction substantially perpendicular to the longitudinal axis "XX", passes through the distributor 20, flows through the helical conduit 14 and exits axially from the first outlet 27.

[0116] As will become more apparent hereinafter, the vanes 10 of the passing volume define a mixed axial / radial flow centrifugal compressor, while the helical conduit 14 defines a "bladeless" turbine.

[0117] In the embodiment shown in Figures 1 to 4, the case 2 is formed by a first body and a second body. The first body has a tubular body 6, an inner tubular body 26, radial supports 25, a central portion 3 having a loop 21, and a partition wall 22. The second body has a sleeve 5 and a rear wall 31 that allows the sleeve 5 to project and closes the first body.

[0118] The turbomachine 1 may be mounted by inserting the shaft 17 with bearings 18 into the sleeve 5, axially approximating the first body with the rotor 4 therebetween to the second body, and joining the rear wall 31 to the first body, as shown in FIG. 3.

[0119] In a possible variant, not shown, the case 2 can alternatively be divided into two halves according to a plane containing the longitudinal axis "XX".

[0120] Figure 5 shows diagrammatically a refrigeration system 32 in which the above-mentioned turbomachine 1 is used. In this figure, the turbomachine 1 is shown diagrammatically. Said turbomachine 1 is a turbocharger. The blading of the passing volume 11 defines the compressor, and the helical duct 14 is a "bladeless" expander or turbine.

[0121] The refrigeration system 32 comprises a turbomachine 1, an evaporator 33 and a condenser 34. The shaft 17 of the rotor 4 of the turbomachine 1 is connected to an electric motor 35. Conduits connect between the turbocharger 1, the evaporator 33 and the condenser 34 to define a refrigeration circuit and the refrigeration system 32 configured to operate the refrigeration circuit, and contain a cooling fluid, which is a working fluid.

[0122] The first and second working fluids, which are designated by different names in the detailed description of the turbomachine 1 of Figures 1 to 4, are identical, i.e. only one working fluid circulates through the refrigeration circuit of Figure 5, then through the mixed axial / radial flow centrifugal compressor and through the helical conduit 14 that defines the "bladeless" turbine.

[0123] In FIG. 5, evaporator 33 has an inlet 36 and an outlet 37 , and condenser 34 has an inlet 38 and an outlet 39 .

[0124] The outlet 39 of the condenser 34 is connected to the second inlet 29 of the case 2 and further to the inlet 15 of the helical conduit 14, the inlet 38 of the condenser 34 is connected to the second outlet 30 of the case 2 and further to the outlet 13 of the passing volume 11. The outlet 37 of the evaporator 33 is connected to the first inlet 28 of the case 2 and further to the inlet 12 of the passing volume 11, and the inlet 36 of the evaporator 33 is connected to the first outlet 27 of the case 2 and further to the outlet 16 of the helical conduit 14. The working fluid circulating in the refrigeration circuit is compressed in a compressor operated by an electric motor 35 before entering the condenser 34 and expanded in a "bladeless" expander / turbine before entering the evaporator 33.

[0125] The accompanying FIG. 6 shows a refrigeration cycle operated by the device 32 according to the invention described in this specification (continuous line) and a refrigeration cycle operated by a conventional device (dashed line), in which the turbocharger 1 of the invention is replaced by a compressor and a lamination / expansion valve, i.e. instead of the turbine according to the invention the working fluid is expanded via a lamination / expansion valve.

[0126] According to a conventional cycle, the working fluid is compressed from A to B in a compressor, cooled and condensed in a condenser from B to C, expanded in a lamination valve from C to D, and evaporated in an evaporator from D to A.

[0127] According to the cycle operated by the device 32 of the invention, the working fluid is compressed in the compressor from A to B, cooled and condensed in the condenser 34 from B to C, expanded in a "bladeless" turbine from C to D', and evaporated in the evaporator 33 from D' to A.

[0128] As can be seen, the two cycles are substantially overlapped except for the expansion zones / steps CD, C-D', so that the area enclosed by the refrigeration cycle operated by the device 32 according to the invention is larger than the area enclosed by the conventional cycle, and therefore involves a larger specific work in absolute values, and is also closest to the ideal cycle.

[0129] The Applicant has already confirmed that in small-scale domestic applications, when using turbines with a performance of 60% or more, the invention makes it possible to increase the refrigeration capacity by a few percent (up to 15-20%), as well as to reduce consumption by about 20-25%. These advantages are greater the higher the turbine performance and the greater the temperature difference between the hot and cold sources.

[0130] Figure 7 shows a cross-sectional view of a variant of the turbomachine 1 according to the invention, which differs from the turbomachine shown in figures 1 to 4 because the rotor 4 is not supported overhanging. Indeed, the shaft 17 further has an end 40 extending from the distal part 8 of the rotor 4 and is supported in the case 2 by a bearing 18 housed in a body 41 supported by a radial support 42 arranged in the tubular body 6. The helical conduit 14 also extends into said end 40 of the shaft 17 and ends at the end side of said end 40 arranged in the inner tubular body 26.

[0131] FIG. 8 is a cross-sectional view of another variant of the turbomachine 1 according to the invention, which differs from the turbomachine shown in FIGS. 1 to 4 because the compressor is of the axial type, i.e. the vanes 10 develop radially starting from the distal part 8 of the rotor 4 with a decreasing height from the inlet 11 towards the outlet 13 of the passing volume 11.

[0132] Another variant, not shown, has the compressor construction of FIG. 8, in which the end 36 of the shaft 17 is supported by a bearing 18 as in FIG.

[0133] The variants of Figures 7 and 8 can also have the case 2 divided as in Figure 3 or divided according to a plane containing the longitudinal axis "XX".

[0134] 9 is a cross-sectional view of another variant of the turbomachine 1 according to the present invention, which differs from the turbomachine shown in FIGS. 1 to 4 in the arrangement of the second inlet 29 and the second outlet 30 on the case 2. The second inlet 29 is arranged diametrically opposite to the second outlet 30, such that the flow of the inlet working fluid at the inlet of the second inlet 29 and the flow at the outlet from the second outlet 30 are substantially radial to the longitudinal axis "XX". In another variant, not shown, the second inlet 29 and the second outlet 30 are aligned such that the flow is always radial.

[0135] Figure 10 is a cross-sectional view of another variant of the turbomachine 1 according to the invention, which differs from the turbomachine shown in Figures 1 to 4 by the presence of a passage 43 for atmospheric air formed between two different loops, one defining a diffuser 19 surrounding and in fluid communication with the outlet 13 of the passing volume 11, and the other defining a distributor 20 surrounding and in fluid communication with the inlet 15 of the helical conduit 14. The same passage 43 is obtained between the second inlet 29 and the second outlet 30, aligned so that the inlet and outlet flows are radial.

[0136] In other embodiments within the scope of the present invention, the arrangement and shape of the blading within the passing volume 11, as well as the number and arrangement of the helical conduits 14, may differ from those described above.

[0137] For example, the blading in the passing volume defines an expander instead of a compressor, and the helical channel defines a compressor or a pump instead of an expander, where the diffuser is in fluid communication with an outlet of the helical conduit and the distributor is in fluid communication with an inlet in the passing volume.

[0138] For example, the blading can be subdivided into different parts with different functions, each constituting one or more stages (see FIG. 11 showing two turbines with vanes 10 and a "bladeless" compressor defined by a helical conduit 14). Case 2 can have several fixed vanes 44 cooperating in the passing volume 11 (e.g. as in FIG. 11). Instead of having several different vanes, the blading can define at least one profile of a screw.

[0139] When the helical channel is used as a compressor, the loops gradually increase in radial dimension from the inlet or inlets 15 to the outlet or outlets 16 (see FIG. 11).

[0140] The rotor 4 may also have multiple helical conduits 14 extending in the same axial zone of the rotor 4, i.e. extending along the entire axial development of the rotor 4, as in FIG. 13 for example (which shows a compressor with vanes 10 and two "bladeless" turbines defined by respective helical conduits 14), or extending in different axial zones of the rotor 4 (see FIG. 12 which shows a turbine with vanes 10 and a "bladeless" turbine defined by respective helical conduits 14).

[0141] Each helical conduit 14 may have one inlet 15 or multiple inlets 15 and / or one outlet 16 or multiple outlets 16. The inlet 15 or multiple inlets 15 may be located at a first end of the rotor 4 or in an intermediate zone thereof, for example as in Fig. 12. Similarly, the outlet 16 or multiple outlets 16 may be located at a second end of the rotor 4 or in an intermediate zone thereof.

[0142] The outlet or outlets 16 may be oriented parallel to the longitudinal axis "XX" (axial outlet) or may have an inclined angle relative to said longitudinal axis "XX".

[0143] The rotor 4 can also be lightened by removing unnecessary material, both externally and internally. For example, the parts of the rotor 4 that are located radially inward of the loops of the helical conduit 14 (or of the helical conduits), i.e. where there are no loops, can be lightened by removing material to obtain one or more voids. The rotor, or at least a part of it, can further have a honeycomb structure in order to reduce weight and at the same time ensure sufficient rigidity.

[0144] Regardless of the particular shape adopted, the material from which the turbomachine 1 is realized is chosen according to the particular requirements: for example, the rotor 4 is realized in a metal, such as steel, martensitic or austenitic stainless steel, nickel alloy, aluminum, or in a plastic, composite, or organic material.

[0145] If the rotor is made of metal, it is preferably realized by casting, machining, such as milling or electroerosion (EDM - Electrical Discharge Machining), or by 3D printing. If the rotor is made of plastic material, it can be realized, for example, by 3D printing.

[0146] The rotor 4 may be realised in a solid body, as shown diagrammatically in figure 14, or in several joined parts 45, each of which obtains a channel or a bundle of helical channels 14. Each part 45 may be manufactured by casting, by machining, such as milling or electroerosion, by 3D printing. If realised in metal, these parts 45 are joined, for example, by welding, or diffusion bonding, or by other mechanical connections.

[0147] Furthermore, the rotor 4 may be geometrically studied and the inlet or inlets 15 and / or the outlet or outlets 16 may be optimized. For example, as shown in FIG. 15, the outer surface of the rotor 4 forms a step at least at the inlets 15 such that the inlets 15 are formed on a surface of the rotor 4 that is not coaxial with the longitudinal axis "XX". The inlets 15 are not oriented along a radial direction, but form a non-zero angle with respect to the radial direction passing through the respective inlet points. Furthermore, the passage portions of each helical channel 14 may have different dimensions and shapes (e.g., circular, triangular, elongated, T-shaped, etc.) and may be constant or may vary along its development.

[0148] Figure 16 shows another variant of the turbomachine of Figure 1, which differs from that of Figure 1 in that the case 2 has an auxiliary loop 46 arranged at the end of the tubular body 6. The first inlet 28 is obtained on said auxiliary loop 46 and there is no radial support 25. In this way, the case 2 is simpler (no radial support 25) and completely prevents the flow entering the compressor from mixing with the fluid leaving the turbine.

[0149] The turbomachine 1 according to the invention can also be used in devices other than the refrigeration devices described above, for example as a turbocharger in a gas cycle (gas turbine or turbogas) or in a steam cycle (turbopump).

[0150] For example, in a possible embodiment, the blading located in the passing volume 11 and the helical conduit 14 are part of a separate circuit, and a first working fluid and a second working fluid are different fluids circulating in said separate circuit. The first working fluid can be used to rotate a turbine defined by the blading located in the passing volume 11, which in turn drives a compressor defined by the helical channel 14, compressing a second working fluid. Depending on the specific application, the shaft of the turbomachine 1 according to the invention can be connected to an electric motor as indicated above, or to an electric generator or motor-generator.

[0151] The turbomachine 1 according to the present invention can furthermore be adapted to handle different types of fluids, for example viscous fluids (i.e. 10 -1 having a dynamic viscosity higher than Pa·s), can be used with Newtonian or non-Newtonian fluids, hydroelectric, gas or steam or liquid.

[0152] FIG. 17 shows another variant of the rotor 4 with three inlet series 15. The rotor has three circumferential surfaces with different diameters aligned axially. Each series is located on one of the three circumferential surfaces. The inlets 15 of each series are connected to a respective helical conduit 14. A distributor 20, not shown in FIG. 17, is constructed and arranged to admit the second working fluid through the inlets of one, two or all three series as a function of the flow rate. The turbomachine 1 is further adapted to operate at variable load.

[0153] Figures 18, 19 and 20 show a variant in which the rotor 4 is formed by a first part 47 supporting the blading and by a second part 48. The first part 47 and the second part 48 are separate elements and are connected to each other, for example via screws and / or welding and / or hearth teeth.

[0154] In FIG. 18, the second portion 48 is the shaft 17 and the first portion 47 is attached to the second portion 48. Furthermore, the helical conduit 14 is formed entirely in the first portion 47 and around the shaft 17. The rotor 4 in FIG. 19 differs from that in FIG. 18 because the helical conduit 14 is formed partly in the first portion 47 and partly in the shaft 17. The inlet 15 is in the first portion 47 and the outlet 16 is at the end of the shaft 17. In an embodiment not shown, a single shaft 17 can support multiple first portions 47 to realize multiple turbomachines 1. For example, the helical conduits 14 of the turbomachines 1 are connected to each other in series or in parallel and / or the passing volumes 11 of the turbomachines 1 are connected to each other in series or in parallel.

[0155] The second part 48 of the rotor 4 (turbopump) of FIG. 20 has a larger diameter part in which the outlet 16 is located and from which the shaft 17 extends in an overhanging manner. The helical conduit 14 is entirely formed in the second part 48 and defines the pump. The inlet 15 is located at the tip of the shaft 17. The first part 47 supports the vanes 10 that define the turbine and has a central passage that accommodates the shaft 17 of the second part 48. The first part 47 rests against the larger diameter part and is connected via hearth teeth 50 (a toothed ring obtained in the first part 47 and a toothed ring provided in the larger diameter part). Furthermore, a plate 51 with a toothed ring is screwed onto the end of the shaft 17. The plate 51 engages with a toothed ring (another hearth tooth 50) formed in the first part 47 and closes the first part between the larger diameter part and the above-mentioned plate 51.

[0156] In an alternative embodiment not shown, the outlet 16 is located on the side of the larger diameter portion opposite the side that overhangs from the shaft 17, instead of at the periphery of the larger diameter portion. The outlet 16 of the pump defined by the helical conduit 14 is axial, but could also be axial / radial. In this way, a better separation of the first and second working fluid flows can be achieved when these flows are at very different temperatures.

[0157] In another variation, not shown, first part 47 is similar to that of FIG. 20 and second part 48 is similar to that of FIG. 20 but does not have shaft 17, and second part 48 is attached to a shaft.

[0158] Figures 21 and 22 show an example of a lightened rotor 4, i.e. with a void portion 49. The rotor 4 of Figure 21 is similar to that of Figures 1 and 3, but further includes recesses 49 in the portions not occupied by the helical conduits 14.

[0159] The rotor 4 of Figure 22 is double (helical conduits 14 are present but not shown) like those of Figures 11 and 12, and each blade arrangement is similar to that of the rotor 4 shown in Figures 1 and 3. The central portion of the rotor 4 is diamond shaped in cross section, with the central inner portion being empty.

[0160] FIG. 23 shows a rotor 4 (two turbomachines 1 with vanes 10) similar to that of FIG. 12. Unlike FIG. 12, there is only one spiral conduit 14, with an inlet 15 located between the vanes 10 of the subsequent stage of the first turbomachine 1 and an outlet 16 located between the vanes 10 of the subsequent stage of the second turbomachine 1. FIG. 24 shows a close-up of the outlet 16, showing the velocity of the first fluid in the vicinity of the radially outer surface of the rotor 4. FIG. 25 shows a close-up of the inlet 15, showing the velocity of the first fluid in the vicinity of the radially outer surface of the rotor 4. In this case, the first and second fluids are the same fluid and may be mentioned, but the withdrawal or pouring of the fluid at the base of the vanes 10 activates or entrains the boundary layer so as to limit the formation of vortices and improve the performance of the turbomachine 1.

[0161] 26 shows a rotor 4 with only one blading, where the helical conduit 14 has an axial inlet 15 and an outlet 16 located between the vanes 10 of the subsequent stage. In this case, the second fluid passing through the helical conduit 14 is used to energize the boundary layer of the first fluid. For example, the first fluid is natural gas and the second fluid is hydrogen. [Explanation of symbols]

[0162] 1. Turbomachinery 2 Cases 3 Center of case 4 Rotors 5 Sleeve 6 Tubular body 7 Cylindrical base 8 Distal part 9 Radial outer surface 10 Vane 11 Passage volume 12 Inlet of passing volume 13. Exit volume of passing 14 Spiral conduit 15 Entrance to the spiral conduit 16 Spiral conduit outlet 17 Shaft 18 Bearings 19 Diffuser 20 Distributor 21 Loop 22 Bulkhead 23 Fixed Blade 24 Oriented Blades 25 Radial Support 26 Inner tubular body 27 Exit 1 28 First Entrance 29 Second Entrance 30 2nd exit 31 Back wall 32 Refrigeration equipment 33 Evaporator 34 Capacitor 35 Electric Motor 36 Condenser inlet 37 Condenser outlet 38 Evaporator inlet 39 Evaporator outlet 40 Shaft End 41 Main unit 42 Radial Support 43 Atmospheric passage 44 Fixed Vane 45 portions 46 Auxiliary Loop 47 Part 1 48 Part 2 49 Void part 50 Haas teeth 51 Plate

Claims

1. Case (2) and a rotor (4) arranged within the case (2) so as to be rotatable relative to the case (2) about its longitudinal axis (X-X); Equipped with The rotor (4) at least one blade arrangement attached to the rotor (4) and arranged in each passing volume (11) defined between the rotor (4) and the case (2) for passing a first working fluid; at least one helical conduit (14) extending in a loop around the longitudinal axis (X-X) and between at least one inlet (15) and at least one outlet (16) for passing a second working fluid, the at least one helical conduit (14) being radially inward of the at least one blade arrangement and having loops with a gradually increasing or decreasing radial dimension from the inlet (15) to the outlet (16); A turbomachine having

2. the at least one blade arrangement is disposed on a radially outer surface (9) of the rotor (4), and the at least one helical conduit (14) is radially inward relative to the radially outer surface (9); The turbomachine of claim 1 .

3. The rotor (4) is a solid body, and the at least one helical conduit (14) is formed in the solid body. A turbomachine according to claim 1 or 2.

4. the at least one inlet (15) is located on the radially outer surface (9) of the rotor (4), and the at least one outlet (16) is located on the top surface of the rotor (4); The turbomachine of claim 2 .

5. The at least one inlet (15) is located near a first end of the rotor (4), and the at least one outlet (16) is located near a second end of the rotor (4) opposite the first end. The turbomachine of claim 2 .

6. The at least one blading has a plurality of vanes (10) or defines at least one profile of a screw. A turbomachine according to claim 1 or 2.

7. the at least one blading located in the passing volume (11) defines a compressor or a pump or defines part of a compressor or a pump, or the blading in the passing volume (11) defines an expander or defines part of an expander, and the at least one helical conduit (14) is a bladeless expander, or the at least one helical conduit (14) is a bladeless compressor or pump; A turbomachine according to claim 1 or 2.

8. the at least one blade arrangement and the at least one helical conduit (14) located in the passing volume (11) are part of the same circuit, and the first working fluid and the second working fluid are the same working fluid; A turbomachine according to claim 1 or 2.

9. the case (2) having a distributor (20) disposed around the rotor (4) and in fluid communication with the inlet (15) of the at least one helical conduit (14), optionally the distributor (20) having a plurality of orientable directional blades (24); A turbomachine according to claim 1 or 2.

10. the rotor (4) has inlet series (15) of the helical conduits (14), each series having a plurality of inlets (15) arranged circumferentially around the rotor (4), the series being arranged at different axial positions, and the distributor (20) arranged around the rotor (4) is configured to channel the second working fluid through one or more of the inlet series (15) depending on load. The turbomachine of claim 9.

11. the rotor (4) has a first part (47) supporting the blade arrangement (10) and a second part (48) defined by or having a shaft (17), the first part (47) and the second part (48) being separate elements connected to each other, and the at least one helical conduit (14) being formed in the first part (47) or in the second part (48) or in both the first part (47) and the second part (48), A turbomachine according to claim 1 or 2.

12. The rotor (4) has at least a gap portion (49) for reducing the weight of the rotor (4). A turbomachine according to claim 1 or 2.

13. the at least one inlet (15) and / or the at least one outlet (16) are arranged / located between the vanes (10) of the blading so as to modify the boundary layer of the first working fluid; A turbomachine according to claim 1 or 2.

14. The turbomachine (1) is a turbopump. A turbomachine according to claim 1 or 2.

15. The turbomachine (1) is a turbocharger. A turbomachine according to claim 1 or 2.

16. at least one capacitor (34); at least one evaporator (33); At least one turbomachine according to claim 15; an electric motor connected to the rotor (4) of the turbomachine; a duct connecting the at least one condenser (34), the at least one evaporator (33), and the at least one turbomachine to form a refrigeration circuit; Equipped with The duct connects the at least one condenser (34) and the at least one evaporator (33) to the at least one turbomachine so as to compress the working fluid circulating in the refrigeration circuit before it enters the at least one condenser (34) and expand the working fluid before it enters the at least one evaporator (33).

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