RU2776401C1 - Configuration of a multi-stage turbomachine (expander-compressor) - Google Patents

Abstract

FIELD: energy industry.

SUBSTANCE: invention is intended for use in the field of energy. A turbomachine 1 containing a body structure and a shaft supported in it with the possibility of rotation is proposed. The shaft is supported with the possibility of rotation by the first and second blocks 25, 27 of bearings. The first and second sections of the compressor 5A, 5B are installed in the housing structure. The first section of the compressor contains the first impeller of the compressor mounted on the shaft with the possibility of rotation with it, and the second section of the compressor contains the second impeller of the compressor mounted on the shaft with the possibility of rotation with it. The turbomachine additionally contains the first turbo expander and the second turbo expander 13, 15, mounted on a shaft with the possibility of rotation together with it in the body structure. The impellers of the turbo expanders 13, 15 and compressor sections 5A, 5B are made as a whole with the corresponding section of the shaft. The sections of the shaft are placed sequentially one after another, and their ends are connected to each other to form a shaft.

EFFECT: invention makes it possible to increase the efficiency and reliability of the turbomachine.

18 cl, 12 dwg

Description

FIELD OF THE INVENTION

[0001] This description relates to turbomachines. In particular, the embodiments disclosed herein relate to integral compressor-expander systems.

BACKGROUND OF THE INVENTION

[0002] In some industrial applications, there is a need to increase the pressure of the gas stream. Dynamic compressors, such as in particular centrifugal compressors, are often used to compress a gas stream. The compressor is driven by mechanical energy supplied by a drive such as an electric motor. In some industrial plants, compressed gas flows need to be expanded. To recover mechanical energy, the expansion is performed in an expander. In some known configurations, the expander and compressor are combined into an integral compressor-expander system, which may also include an electric machine. When the mechanical energy generated by the expander is balanced by the mechanical energy required to drive the compressor, this configuration is a so-called expander-compressor. The electric machine is configured to operate as an electric generator when the energy generated by the expander exceeds the energy required to drive the compressor and the excess mechanical energy is converted into electrical energy. If the energy generated by the expander is less than the energy required to drive the compressor, the electric machine is driven in motor mode to provide the additional energy required to drive the compressor.

[0003] An integral expander-compressor of this type is described, for example, in US 2013/0091869.

[0004] An important design aspect of combined compressor-expander system configurations is efficient energy recovery and optimal operation of the compressor stages. Developers are constantly looking for ways to improve the efficiency and reliability of these machines.

SUMMARY OF THE INVENTION

[0005] In the embodiments described herein, a turbomachine is provided that includes a housing structure and a shaft rotatably supported in the housing structure. The shaft is rotatably supported by at least a first bearing unit and a second bearing unit configured to rotatably support the shaft in the housing structure. The first section of the compressor and the second section of the compressor are installed in the casing structure. The first compressor section contains the first compressor impeller mounted on the shaft to rotate with it, and the second compressor section contains the second compressor impeller mounted on the shaft to rotate with it. The turbomachine also contains the first turbo-expander and the second turbo-expander mounted on the shaft with the possibility of rotation together with it in the housing structure and configured to generate mechanical energy by expanding the gas flow passing through them and actuating the first compressor section and the second compressor section.

[0006] In highly preferred embodiments, the turbo expanders provide all the power required to drive the compressor sections so that an external electric machine is not required and the shaft can be hermetically housed within the housing structure. It does not require gaskets or seals on the machine's rotor components to reduce leakage to the environment. Thus, the body is completely sealed.

[0007] In some embodiments, the turbo expanders are arranged in series such that the partially expanded gas from the upstream turbo expander is further expanded in the downstream turbo expander. Thus, the enthalpy reduction in a turbomachine is divided into two stages. This allows the use of a turbomachine with limited rotational speeds. To ensure more reliable operation, the impellers of the turbo expanders and compressor sections can be configured in a multi-stage configuration rather than in an interference fit configuration, thereby ensuring safer operation even at high rotor speeds. In this way, high power ratings can be achieved without being limited by the risk of loosening the impeller-shaft connection due to centrifugal forces. The combination of successive turbo-expanders and a shaft consisting of a plurality of sections arranged one after the other makes it possible to create turbomachines with a high power rating, in which significant pressure drops in the turbo-expanders are tolerable. This allows efficient energy recovery.

BRIEF DESCRIPTION OF GRAPHICS

[0008] The described embodiments of the invention and many of its attendant advantages can be more fully appreciated and understood in the course of studying the following detailed description, considered in connection with the accompanying drawings, and:

in Fig. 1 is a cross-sectional view of an embodiment of a turbomachine according to the present disclosure;

in Fig. 2 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 3 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 4 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 5 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 6 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 7 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 8 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 9 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 10 is a diagram of a further embodiment of a turbomachine according to the present disclosure;

in Fig. 11 is a diagram of a further embodiment of a turbomachine according to the present disclosure; and

in Fig. 12 is a diagram of a further embodiment of a turbomachine according to the present disclosure.

DETAILED DESCRIPTION

[0009] The turbomachine in accordance with the present description contains one shaft, on which several impellers are mounted. The impellers include two turbo expander impellers and two compressor impellers. The turbo expanders provide all the power required to drive the compressor impellers so that the rotating components of the compressor sections and turbo expanders can be housed in a sealed housing structure without the need to extend the rotating shaft outside the housing, thus eliminating the need for seals and leakage prevention. In some embodiments, the implementation of the shaft consists of many sections located one after the other, thus, due to the absence of a connection formed by an interference fit, higher rotational speeds can be achieved.

[0010] In FIG. 1, a cross-sectional view along a sectional plane containing the rotation axis AA of the turbomachine 1 shows a first embodiment of the turbomachine 1 having the configuration of an integral compressor-expander system.

[0011] The turbomachine 1 includes a housing structure 3. In the context of this document, the term "hull structure" means a single housing containing a rotating shaft, or a plurality of compartments connected to each other by a rotating shaft passing through these compartments. In the embodiment shown in FIG. 1, the body structure 3 includes a first center compartment 3A and side compartments 3B, 3C. The central compartment 3A accommodates the compressor sections of the turbomachine 1. The compressor sections, collectively referred to as 5, may include a first compressor section 5A and a second compressor section 5B. In the embodiment shown in FIG. 1, each of the first compressor section 5A and the second compressor section 5B comprises one compressor stage with one impeller. Other embodiments may include more sections and/or one section, some or all of the compressor sections may include more than one impeller.

[0012] In the embodiment shown in FIG. 1, the first compressor section 5A includes a compressor impeller 7A, and the second compressor section 5B includes a compressor impeller 7B.

[0013] As shown in FIG. 1, the compressor sections 5A, 5B are arranged in line such that one gas stream entering the upstream compressor section 5A is compressed therein and the partially compressed gas stream is fed to the second downstream compressor section 5B. for extra compression. Thus, the casing structure 3 has one compressor inlet 9 and one compressor outlet 11.

[0014] The turbomachine 1 also includes a first turboexpander 13 housed in compartment 3B and a second turboexpander 15 housed in compartment 3C. Each turbo expander 13, 15 has, respectively, an inlet 13.1, 15.1 for gas and an outlet 13.2, 15.2 for gas. The turbo expander 13 includes a turbo expander impeller 19, and the turbo expander 15 includes a turbo expander impeller 21.

[0015] In preferred embodiments, one or both impellers 19, 21 of the turboexpander are placed in a cantilevered configuration, i.e., they are supported on respective first and second ends of a rotating shaft 23 that protrudes freely from the respective bearing blocks 25, 27. The cantilever configuration of the turboexpanders facilitates the flow of the expanded gas. In addition, access to the impellers 19, 21 of the turboexpander is simplified, for example, for their maintenance or repair.

[0016] The bearing units 25, 27 may include active magnetic bearings. Typically, bearing blocks 25, 27 provide radial and axial support for shaft 23. For example, each bearing block 25, 27 may include a radial bearing 25.1 and 27.1, respectively. At least one of the bearing blocks 25, 27 may additionally comprise an axial bearing, as shown by way of example at 25.2. If a single axial bearing is used, it is a bi-directional axial bearing. In other embodiments, each bearing assembly may include a side bearing, with each of the two side bearings providing axial support in only one direction.

[0017] In the embodiment shown in FIG. 1, the turbo expanders 13, 15 are centripetal turbo expanders, i.e. the gas flow enters the respective impeller radially from the impeller inlet and exits the impeller axially into the impeller outlet. The inlets of the impellers 19, 21 of the turboexpander are shown at 19.1 and 21.1, respectively, and the outlets of the impeller of the turboexpander are shown at 19.2 and 21.2, respectively. The gas flows radially inward from the inlet towards the axis of rotation AA and is deflected by the impeller in a substantially axial direction at the outlet of the turboexpander. Adjustable inlet guide vanes (IGV), shown schematically at 13.5 and 15.5, can be installed between the respective inlet chamber 13.4 and 15.4 and the impeller 19, 21 of the turboexpander. Adjustable inlet guide vanes increase the flexibility of the turbomachine, since the angle of deflection of the gas flow entering the corresponding impeller 19, 21 of the turboexpander can be adapted depending on the operating conditions, in particular on the speed of rotation of the turbomachine.

[0018] The turbomachine 1 may have a multi-stage configuration in which both impellers 19, 21 of the turboexpander and both impellers 7A, 7B of the compressor are integral with the corresponding section of the shaft 23, and the sections of the shaft are placed in series with each other to form the shaft 23. More Specifically, as shown in FIG. 1, shaft 23 includes six shaft sections, designated 23.1, 23.2, 23.3, 23.4, 23.5 and 23.6. Plot 23.1 shaft is integral with the impeller 19 of the turboexpander. The shaft section 23.2 passes through the first bearing block 25 and is rotatably connected at one end to the first shaft section 23.1 and at the opposite end to the first end of the third shaft section 23.3. The third section of the shaft is integral with the first impeller 7A of the compressor. The second end of the third shaft section 23.3 is rotatably connected to the first end of the fourth shaft section 23.4, which in turn is integral with the second compressor impeller 7B. The second end of the fourth shaft section 23.3 is rotatably connected to the first end of the fifth shaft section 23.5 which passes through the second bearing block 27 . The second end of the fifth section 23.5 of the shaft is rotatably connected to the sixth section 23.6 of the shaft, which is integral with the impeller 21 of the turboexpander.

[0019] By forming each impeller in a single unit, i.e., monolithically, with the corresponding section of the shaft, a turbomachine rotor is obtained that is capable of rotating at higher rotation speeds than a rotor in which the impellers are installed by an interference fit.

[0020] Each two of the rotatably coupled shaft sections are connected to each other by a tie rod and a pair of intermeshing front teeth, such as a V-tooth connection comprising tapered teeth that engage with each other at the end faces of each from two interlocking sections of the shaft. The tie rods connecting the various sections of the shaft are shown schematically at 31.1, 31.2 and 31.3.

[0021] Various sections of the turboexpander and compressor of the turbomachine 1 may be fluidly connected in accordance with various configurations. Continuing with references to FIG. 1 in FIG. 2 schematically shows a first hydraulic connection configuration. In this embodiment, the turbo expanders 13, 15 are arranged in series such that the compressed gas flow is partially expanded in the first turbo expander 13 and then further expanded in the second turbo expander 15. The gas outlet 13.2 of the first turbo expander 13 is fluidly connected to the inlet 15.1 for gas of the second turboexpander 15. This configuration is particularly advantageous because the enthalpy reduction is divided into two successive turboexpanders 13, 15 and lower speeds of the shaft 23 can be maintained.

[0022] The compressor sections 5A, 5B are also arranged one behind the other, i.e. in series, so that the same gas stream is sequentially processed in the first compressor section 5A and in the second compressor section 5B.

[0023] In other embodiments, the turbo expanders 13, 15 may be arranged in parallel rather than in series. This may be advantageous, for example, if the pressure drop of the gas expanded in the turbo expanders is relatively small, but the gas flow rate is high. Continuing with references to FIG. 1 in FIG. 3 schematically shows an embodiment with turbo expanders 13, 15 arranged in parallel. To indicate the same parts or components in FIG. 3 uses the same reference numbers as in FIG. 1. In the configuration shown in FIG. 3, the compressed gas stream to be expanded in the turbo-expanders 13, 15 is divided into two partial streams, which are expanded in two turbo-expanders 13, 15 arranged in parallel. The compressor sections 5A, 5B shown in FIG. 3 are arranged in series as shown in FIG. 1 and 2.

[0024] In some embodiments, compressor sections 5A, 5B may be intercooled. Continuing with references to FIG. 1 in FIG. 4 schematically shows a turbomachine 1 with an intercooled compressor. Like reference numerals designate the same elements, parts or components already described with reference to FIG. 1. In the embodiment schematically shown in FIG. 4, the casing structure 3 includes a first compressor inlet 9A in fluid communication with the first compressor section 5A. Partially pressurized gas is supplied from the discharge side of the first compressor section 5A through the first compressor outlet 11A, which is fluidly connected to the inlet side of the intercooler heat exchanger, having the general designation 12. The outlet side of the heat exchanger is fluidly connected to the second gas inlet 9B, through which the partially compressed and cooled gas is supplied to the second compressor section 5B. The housing structure also includes a second compressor outlet 11B through which pressurized gas is supplied.

[0025] The turbo expanders 13, 15 of the turbomachine 1 shown in FIG. 4 may be arranged in series or in parallel in accordance with any of the system configurations described above.

[0026] Although the diagram shown in FIG. 4, compressor sections 5A, 5B are arranged in series, in other embodiments compressor sections 5A, 5B may be arranged in parallel.

[0027] The compressor and turbo expander sections of turbomachine 1 may be arranged in other possible configurations, some of which are described herein with reference to FIG. 5–12. The main components of the turbomachine 1 shown in FIG. 5-12 are designated by the same reference numbers as those used in FIG. 1. The various components of the machine may be configured as described above with reference to FIG. 1 unless otherwise noted in the description below.

[0028] In FIG. 5 is a diagram of a further configuration of turbomachine 1 in which two compressor sections 5A, 5B are arranged in parallel. The gas flow to be compressed is divided into two partial flows, which are supplied to the suction side of the two compressor sections 5A, 5B through the first and second compressor inlets 9A, 9B. Each compressor section 5A, 5B is fluidly connected to a respective compressor outlet 11A, 11B. Similar to that shown in FIG. 1-4, in the embodiment shown in FIG. 5, compressor sections 5A, 5B also have a configuration between bearings, namely two bearing blocks 25 and 27. The turbo expanders are located on the outer sides of the turbomachine, with the respective impellers of the turbo expanders in a cantilever configuration, as detailed in FIG. 1 are supported on the free ends of the shaft 23 which extend beyond the bearing blocks 25, 27. In the diagram shown in Fig. 5, the compressor sections 5A, 5B are arranged in a back-to-back configuration, i.e., the two pressure sides (compressor outlets 11A, 11B) of the compressor sections 5A, 5B face each other and are located between the suction sides (compressor outlets 11A, 11B). 9A, 9B compressor) compressor sections.

[0029] In FIG. 6 shows a configuration that is different from the configuration shown in FIG. 5, a sealing system 40 located between two compressor sections 5A, 5B. Thus, the two compressor sections 5A, 5B are configured to process different gas streams supplied separately from each other. By way of example, the compressor sections 5A, 5B are arranged in reverse from the arrangement shown in FIG. 5, that is, the suction sides (compressor inlets 9A, 9B) face each other, and the discharge sides (compressor outlets 11A, 11B) face away from each other. The compressor sections 5A, 5B are again in an inter-bearing configuration, while the turbo expanders 13, 15 are cantilevered, with the respective impellers supported by the ends of the shaft, cantilevered beyond the respective bearing blocks 25, 27.

[0030] Continuing with references to FIG. 1-6 in FIG. 7 shows a further configuration of a turbomachine 1 in accordance with the present invention. Like reference numbers designate the same or equivalent parts already described above. Turbomachine 1 shown in FIG. 7 comprises two compressor sections 5A, 5B which may be front to front or back to back and between the bearings. On FIG. 7 shows a front-to-front configuration, but compressor sections can be arranged back-to-back as shown in FIG. 5, with or without an intermediate sealing system 40. In the configuration shown in FIG. 7, compressor sections 5A, 5B are arranged in series. The gas flow processed by the compressor 5 is sucked in by the first compressor section 5A through the first compressor inlet 9A and supplied through the first compressor outlet 11. In the exemplary embodiment shown in FIG. 7, the first compressor outlet 11A is fluidly connected to the second compressor inlet 9B by means of an intercooler, again indicated at 12. The final pressure gas is supplied through the second compressor outlet 11B. The first and second turbo expanders 13, 15 may be cantilevered, with the respective impellers of the turboexpanders being cantilevered at the ends of a shaft 23 which cantileveredly protrudes from the bearing systems 25, 27. The two turbo expanders 13, 15 may be arranged in series, with the component supplying the first turbo expander 13 being fluidly connected to the inlet of the second turbo expander 15 so that the pressurized gas stream is sequentially expanded in two steps.

[0031] In FIG. 8 shows the same system as in Fig. 7, but in this case, the turbo expanders 13, 15 have a parallel configuration of mutual arrangement.

[0032] In the embodiments described above, the turbo expanders are located on the sides of the turbomachine 1, and the compressor sections 5A, 5B are located between the bearings in the intermediate section of the turbomachine. This configuration is particularly advantageous in terms of both the availability of the turbo expander components and the dynamic efficiency of the fluid. Essentially, on the one hand, access to the impellers 19, 21 of the turboexpanders is facilitated. In addition, access to the adjustable inlet guide vanes 13.5 and 15.5 and the associated actuators is facilitated. On the other hand, since the impellers 19, 21 of the turboexpanders are usually centripetal impellers, providing an outlet (expanded) gas flow is easier if there is free space in the axial direction on the supply side of the impeller. No additional diffusers are required to deflect the flow direction. Dynamic fluid loss is minimized.

[0033] However, in currently less preferred embodiments, another system of turbo expanders and compressor sections may be used. Continuing with references to FIG. 1 in FIG. 9 shows an embodiment in which the compressor sections 5A, 5B are located at the terminal ends of the turbomachine 1 and the turboexpanders 13,15 are configured between bearings in the central region of the turbomachine 1 between the compressor sections 5A, 5B. The gas treated in the compressor sections 5A, 5B enters the turbomachine 1 through the first compressor inlet 9A and is partially compressed by the first compressor section 5A, from which the partially compressed gas is fed through the first compressor outlet 11A towards the second compressor inlet 9B. The gas entering the second compressor inlet 9B is further compressed in the second compressor section 5B and supplied through the second compressor outlet 11B. An intercooler 12 may be provided between the first compressor outlet 11A and the second compressor inlet 9B to remove heat from the partially compressed gas before it is further compressed in the second compressor section 5B.

[0034] The compressor impellers 7A, 7B may be supported in a cantilever configuration on the ends of the shaft 23 which cantilever the first and second bearing blocks 25, 27.

[0035] The impellers 19, 21 of the turboexpander may be configured to be located between bearings on the central portion of the shaft 23 between the bearing blocks 25, 27. The two turbo expanders 13, 15 may be arranged in series or in parallel, as described above with reference to FIG. 1–8.

[0036] Continuing with references to FIG. 1-9 in FIG. 10 shows an additional embodiment. Turbomachine 1 shown in FIG. 10 also includes first and second turbo expanders 13, 15, first and second compressor sections 5A, 5B, and a common shaft 23 rotatably supported in a housing structure 3 (not shown in FIG. 10). The shaft 23 may be a shaft consisting of a plurality of sections located one after the other, as described above with reference to FIG. 1. Such a multi-stage configuration can preferably be used in the embodiments shown in FIG. 2–9.

[0037] Unlike shown in FIG. 1-9 in FIG. 10 shows that both compressor impellers 7A, 7B and turbo expanders 19, 21 are in an inter-bearing configuration since both compressor sections 5A, 5B and turbo expanders 13, 15 are located between bearing blocks 25, 27.

[0038] The fluid connection between the compressor sections 5A, 5B can be provided such that the compressor sections 5A, 5B are arranged in series or in parallel. In addition, although the circuit shown in FIG. 10, the compressor sections 5A, 5B are shown in an in-line configuration, in other embodiments, the compressor sections 5A, 5B may be front to front or back to back, for example, as shown in FIG. 5 or 6. Any of these various configurations may be preferred depending on various factors. In particular, a front-to-front or back-to-back configuration may be more advantageous in terms of hydraulic pressure balancing because the axial forces generated during operation by the two compressor impellers on shaft 23 are oriented in opposite directions. directions and thus at least partially balanced. An in-line configuration may be preferred in terms of facilitating the provision of channels for flow, as seen in FIG. 1. If intercooling is not required, an in-line configuration may eliminate the need for dual inlet and outlet connections in the housing.

[0039] Although in FIG. 10 shows that the compressor sections 5A, 5B are located adjacent to each other and, similarly, the turbo expanders 13, 15 are arranged in a back-to-back configuration one next to the other, other configurations are possible when the compressor sections and turbo expanders are located in interleaved configurations, i.e. one compressor section is placed between two turbo expanders. In addition, the turbo expanders can be arranged in line rather than in a back-to-back configuration.

[0040] Continuing with references to FIG. 1-10 in FIG. 11 shows yet another further embodiment of the turbomachine 1. In this embodiment, the second turboexpander 15 and the first compressor section 5A are in an inter-bearing configuration, namely between bearing blocks 25, 27. The first turbo expander 13 is cantilevered at one end of the shaft 23 which cantilevered out of the bearing block 25, and the second compressor section 5B is cantilevered at the other end of the shaft 23 which cantilevered out of the bearing block 27. As an example, two turboexpanders 13, 15 are arranged in series. In other embodiments, the turbo expanders 13, 15 may be arranged in parallel. Compressor sections 5A, 5B can be operated in parallel or in series with or without intercooling.

[0041] Finally, continuing with reference to FIG. 1-11 in FIG. 12 shows another further embodiment of a turbomachine 1 in accordance with the present description. The embodiment shown in FIG. 12 is different from the embodiment shown in FIG. 11, mainly in that the turboexpanders 13, 15 are arranged in parallel. The compressor sections 5A, 5B are arranged in series with an intercooler 12 in between.

[0042] In all embodiments described herein, the shaft may be supported by two radial bearings and one or two thrust bearings. In particular, in the case of using two thrust bearings, so-called half thrust bearings can be used, each of which supports the axle in only one direction. Thus, in some embodiments, two bearing blocks can be used: each bearing block functions as a radial bearing, and both of these blocks also function as an axial bearing (thrust bearing), however, each of them is only in one direction. In other embodiments, each bearing block functions as a radial bearing and only one of them functions as a thrust bearing (thrust bearing) in both directions.

[0043] In preferred embodiments, each bearing assembly may comprise one or more active magnetic bearings.

[0044] While the present invention has been described with reference to various specific embodiments, it will be apparent to those skilled in the art that many modifications, changes, and omissions are possible without departing from the spirit and scope of the claims. In addition, unless otherwise indicated, the order or sequence of any process or method steps may be varied or reordered in accordance with alternative embodiments. In particular, in each of the configurations described above, the two compressor sections may be arranged either in series or in parallel, unless otherwise indicated. In addition, the two turbo expanders may alternatively be operated in series or in parallel, unless otherwise indicated.

Claims (24)

1. Turbomachine, containing: body structure; a shaft rotatably supported in said housing structure; at least a first bearing unit and a second bearing unit configured to rotatably support the shaft in the housing structure; the first section of the compressor and the second section of the compressor in the specified housing structure, and the first section of the compressor contains at least the first compressor impeller mounted on the specified shaft to rotate with it, and the second compressor section contains at least the second compressor impeller mounted on the specified shaft with the possibility of rotation with it; and the first turbo-expander and the second turbo-expander mounted on the shaft with the possibility of rotation with it in the specified housing structure and configured to generate mechanical energy by expanding the gas flow passing through them and actuating the first compressor section and the second compressor section, moreover, the impellers of the turboexpanders and compressor sections are integral with the corresponding shaft section, and these shaft sections are placed sequentially one after the other, and their respective ends are connected to each other to form said shaft. 2. The turbomachine of claim. 1, in which the first turboexpander and the second turboexpander are configured to generate all the mechanical energy required to drive the first compressor section and the second compressor section. 3. A turbomachine according to claim 1 or 2, wherein the first turboexpander is positioned in a cantilever configuration at the first end of the shaft. 4. The turbomachine of claim 3, wherein the second turboexpander is positioned in a cantilever configuration at the second end of the shaft. 5. A turbomachine according to any one of the preceding claims, wherein the first compressor section and the second compressor section are configured between bearings, namely between the first bearing block and the second bearing block. 6. A turbomachine according to any one of the preceding claims, wherein said shaft is a shaft consisting of a plurality of sections arranged one after the other. 7. A turbomachine according to any one of the preceding claims, wherein the first turboexpander is a centripetal turboexpander. 8. The turbomachine according to claim 7, wherein the second turboexpander is a centripetal turboexpander. 9. A turbomachine according to any one of the preceding claims, wherein the first turboexpander and the second turboexpander are arranged in series, wherein the outlet of one of said first turboexpander and the second turboexpander is fluidly connected to the inlet of the other of said first turboexpander and the second turboexpander so that in the process operation, the gas flow is first partially expanded in one of said first turbo-expander and second turbo-expander, and then further expanded in the other of said first turbo-expander and second turbo-expander. 10. Turbomachine according to any one of paragraphs. 1-8, in which the first turbo-expander and the second turbo-expander are arranged in parallel in such a way that during operation the compressed gas stream is separated and fed partly into the first turbo-expander and partly into the second turbo-expander for expansion therein. 11. A turbomachine according to any one of the preceding claims, wherein the first compressor section and the second compressor are arranged in series. 12. The turbomachine of claim. 11, in which the intercooler is located between the first compressor section and the second compressor section. 13. Turbomachine according to any one of paragraphs. 1-10, in which the first compressor section and the second compressor section are arranged in parallel. 14. A turbomachine according to any one of the preceding claims, wherein the shaft is hermetically housed in a housing structure. 15. A turbomachine according to any of the preceding claims, wherein the housing structure comprises separate housing compartments for each of said first turboexpander, second turboexpander, first compressor section, and second compressor section, wherein the housing compartments are separated from each other by sealing systems along the shaft. 16. A turbomachine according to any one of the preceding claims, wherein at least one of said first bearing block and said second bearing block comprises an active magnetic bearing. 17. A turbomachine according to any one of the preceding claims, wherein said first bearing assembly and second bearing assembly each comprise a respective half thrust bearing. 18. A turbomachine according to any one of the preceding claims, wherein the ends of said shaft sections are connected to each other by means of a tie rod and interlocking teeth on the end faces of each of the two interconnected shaft sections.

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