Turbomachinery

Abstract

To create a new-model turbo-machine arrangement.SOLUTION: A turbo-machine arrangement comprises: a compressor section including a compressor shaft; an electric machine including a shaft extending co-axially to and connected to the compressor shaft, the electric machine and the respective compressor section being mounted in a common hermetically sealed housing via bearings in such a manner that the respective compressor section, the electric machine and the bearings are altogether washed by the working medium; a supply line for uncompressed working medium; a discharge line for compressed working medium; an ejector, which can be supplied via a first connection with working medium at a first pressure level as propellant for sucking in working medium at a lower second pressure level via a second connection, and in which a mixture formed in the ejector, of the working medium at the first pressure level and the working medium at the second pressure level can be supplied to the electric machine and / or to at least one other assembly to be cooled via a third connection, as cooling medium.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present invention relates to a turbomachine device. Background Art

[0002] Patent Document 1 discloses a turbomachine device comprising a multi-stage compressor section and an electric machine, wherein the electric machine drives the compressor section to increase the pressure of a working medium. A compressor shaft of the compressor section extends coaxially with respect to a shaft of the electric machine and is connected to the shaft of the electric machine. The electric machine and the compressor section are arranged in a common housing and mounted within the housing via bearings. The compressed working medium can be extracted from a stage of the compressor section as a cooling gas and used for cooling the electric machine.

[0003] A turbomachine device comprising at least one single-stage or multi-stage compressor section and an electric machine that drives the or each compressor section is also referred to as an integrated motor compressor.

[0004] Patent Document 2 discloses a turbocharger comprising a plurality of compressor sections. The compressor section and the electric machine that drives the compressor section are arranged in an airtight housing and attached to the housing via bearings. The shaft of each compressor section and the shaft of the electric machine extend coaxially with respect to each other and are connected without using a gear device. The compressed working medium branched from the compressor section is used for cooling the electric machine.

[0005] Patent Document 3 further discloses a turbo compressor. In order to extract the working medium compressed in a region of a compressor stage of a compressor section of the turbomachine and supply the working medium to an assembly to be cooled, it is disclosed that the working medium is guided starting from a gear side space so as to pass through an end of the gear side space, and the working medium is guided through an extraction path to a collection chamber.

[0006] In particular, when using compressed working fluid from the compressor section to cool a turbomachinery assembly, there is a drawback: the overall efficiency of the turbomachinery is reduced. In addition, the compressed working fluid is already heated as a result of the compression, which reduces its cooling capacity.

[0007] There is a need to cool the electromechanical components of turbomachinery systems more efficiently, taking advantage of the high overall thermodynamic efficiency of turbomachinery systems. [Prior art documents] [Patent Documents]

[0008] [Patent Document 1] International Publication No. 2013 / 139568 [Patent Document 2] European Patent No. 1074746 [Patent Document 3] German Patent Application Publication No. 102007019264 [Overview of the project] [Problems that the invention aims to solve]

[0009] Based on this need, the objective of the present invention is to create a new type of turbomachinery device. This objective is solved by the turbomachinery device described in claim 1. [Means for solving the problem]

[0010] The turbomachinery system comprises at least one single-stage or multi-stage compressor section for increasing the pressure of a working medium such as a process gas, and each compressor section includes a compressor shaft. Furthermore, the turbomachinery system comprises an electromechanical unit including a shaft. The compressor shaft of each compressor section extends coaxially with the shaft of the electromechanical unit.

[0011] Preferably, the compressor shafts of each compressor section are directly connected to the shafts of the electromechanical unit without the use of gear mechanisms.

[0012] The electromechanical unit and each compressor section are housed in a common, enclosed, one-piece or multi-part housing, and are mounted within the housing via bearings so that each compressor section, electromechanical unit, and bearing is flushed together by the working fluid. Uncompressed working fluid can be supplied to the turbomachinery unit via a supply conduit. Compressed working fluid can be discharged from the turbomachinery unit via a discharge conduit.

[0013] Furthermore, the turbomachinery apparatus according to claim 1 comprises at least one ejector, the ejector being supplied via a first conduit or first connection to a working medium at a first pressure level as a propellant, i.e., to draw in a working medium at a lower second pressure level via a second conduit or second connection, and a mixture of the working medium at the first pressure level and the working medium at the second pressure level formed within at least one ejector being supplied via a third conduit or third connection as a cooling medium to an electromechanical and / or at least one other assembly to be cooled, particularly a bearing.

[0014] In the present invention, the turbomachinery device includes at least one ejector to which a working medium at a first pressure level, preferably at least partially compressed, may be supplied as a propellant, thereby drawing in the working medium at the lower second pressure level due to the pressure difference between the working medium at the first pressure level and a working medium at a lower second pressure level, preferably uncompressed, the working medium at the second pressure level is mixed with the working medium at the first pressure level, and the mixture is supplied for cooling to an electromachine and / or at least one other assembly to be cooled.

[0015] Since only one portion of the cooling medium guided to pass through or via the electromechanical device and / or at least one other assembly to be cooled consists of a working medium at a first pressure level, preferably at least partially compressed, and the other portion of the working medium consists of a working medium at a lower second pressure level, preferably uncompressed, the cooling medium has a lower temperature on one side, thereby increasing the overall thermodynamic efficiency of the turbomechanical device on the other. With the high overall thermodynamic efficiency of the turbomechanical device, more efficient cooling of the electromechanical device can be supplied.

[0016] Preferably, at least one ejector is connected via a first conduit or first connection to one compressor section or one of the compressor sections, or to a discharge conduit or a first leak point of the turbomachinery. Preferably, at least one ejector is connected via a second conduit or second connection to a supply conduit or a second leak point of the turbomachinery, or to a return conduit of the turbomachinery for a cooling medium that is guided to pass through or via an electromechanical and / or at least one other assembly to be cooled.

[0017] According to a first further development of the present invention, a return conduit for a cooling medium, which is guided to pass through or via an electromechanical and / or at least one other assembly to be cooled, is connected to the turbomachinery supply conduit such that the opening point of the return conduit for the cooling medium to the turbomachinery supply conduit is located downstream of a branch point of a second conduit or second connection of the turbomachinery supply conduit, viewed in the direction of flow through the turbomachinery supply conduit. The branch point of the second conduit or second connection is used to extract a working medium that is at a smaller or lower pressure to be supplied to at least one ejector.

[0018] This first further development of the present invention is particularly preferred. The opening point of the return conduit to the supply conduit is located downstream of the branching point of the second conduit or second connection of the supply conduit, so that a cryogenic working medium that is not exclusively compressed is drawn in through the second conduit or second connection via an ejector that does not contain the returned cooling medium.

[0019] According to an alternative second further development of the present invention, a return conduit for a cooling medium guided to pass through or via an electromechanical and / or at least one other assembly to be cooled is connected to a second conduit leading to at least one ejector, or to a second connection of an ejector for supplying propellant to at least one ejector. This second further development may provide a closed cooling circuit for the cooling medium guided through the electromechanical.

[0020] Preferably, a heat exchanger or cooler is incorporated into each return conduit for the cooling medium to increase efficiency. Incorporating a heat exchanger into the return conduit for the cooling medium is particularly preferable with respect to efficient cooling of the electromechanical and / or at least one other assembly to be cooled.

[0021] Preferably, to further increase efficiency, at least one ejector is connected to one compressor section or one of the compressor sections via a first conduit or first connection, and at least one ejector is connected to a supply conduit of the turbomachinery via a second conduit or second connection. This connection of the turbomachinery ejector to the compressor section and to the supply conduit is particularly preferred to provide efficient cooling of the electromechanical and / or at least one other assembly to be cooled, such as bearings, with the high overall thermodynamic efficiency of the turbomachinery.

[0022] Preferred further developments of the present invention can be derived from the dependent claims and the following description.

[0023] Exemplary aspects of the present invention will be described in more detail with reference to the drawings, without being limited thereto. The drawings are as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] [Figure 1] FIG. 1 is a very schematic diagram showing a first turbomachine device according to the present invention. [Figure 2] FIG. 2 is a very schematic diagram showing a second turbomachine device according to the present invention. [Figure 3] FIG. 3 is a very schematic diagram showing a third turbomachine device according to the present invention. [Figure 4] FIG. 4 is a very schematic diagram showing a fourth turbomachine device according to the present invention. [Figure 5] FIG. 5 is a very schematic diagram showing a fifth turbomachine device according to the present invention. [Figure 6] FIG. 6 is a very schematic diagram showing a sixth turbomachine device according to the present invention. [Figure 7] FIG. 7 is a very schematic diagram showing a seventh turbomachine device according to the present invention. DESCRIPTION OF EMBODIMENTS

[0025] The present invention particularly relates to a turbomachine device 10 embodied as an integrated motor compressor.

[0026] Figure 1 shows a first exemplary embodiment of a turbomachinery device 10 according to the present invention, formed as an integrated motor compressor, which includes a compressor section 11 for compressing a process gas, preferably to increase the pressure of a working medium. The compressor section 11 according to Figure 1 comprises a plurality of compressor stages 12 and a compressor shaft 13, to which uncompressed working medium may be supplied via a supply conduit 14 of the turbomachinery device 10, and compressed working medium may be discharged from the compressor section 11, and therefore from the turbomachinery device 10, via a discharge conduit 15 of the turbomachinery device 10. The turbomachinery device 10 according to Figure 1, formed as an integrated motor compressor, further comprises an electromachine 16 having a shaft 17, which is used to drive the compressor section 11. The compressor shaft 13 and the shaft 17 of the electromachine 16 extend coaxially with respect to each other. Furthermore, the compressor shaft 13 and the shaft 17 of the electric machine 16 are preferably connected directly to each other without the use of a gear mechanism.

[0027] The electromechanism 16 and the compressor section 11 are housed in a sealed, and therefore airtight, common housing 18, and are rotatably mounted within the housing 18 via bearings 19. The airtight housing 18 may be formed as a single unit or may consist of multiple parts. Here, the compressor section 11, the electromechanism 16, and the bearings 19 are all cleaned with a working fluid, particularly a process gas.

[0028] The turbomachinery apparatus 10 according to the present invention comprises at least one ejector 20. The ejector 20 shown in Figure 1 may be supplied with a working medium at a first pressure level as a propellant, i.e., to draw in a working medium at a lower second pressure level via a second conduit 23 or second connection 24, via a first conduit 21 or first connection 22, and the mixture of the working medium at the first pressure level and the working medium at the second pressure level formed in the ejector 20 may be supplied as a cooling medium to at least one other assembly to be cooled, such as an electromachinery 16 and / or a bearing 19, via a third conduit 25 or third connection 26.

[0029] In Figure 1, the ejector 20 may be supplied with at least partially compressed working medium as a propellant for drawing in uncompressed working medium via a second conduit 23 or second connection 24, through a first conduit 21 or first connection 22, and the mixture of at least partially compressed and uncompressed working medium formed in the ejector 20 may be supplied as a cooling medium to at least one other assembly to be cooled, such as the electromechanism 16 and / or bearings 19, via a third conduit 25 or third connection 26.

[0030] Here, the ejector 20 comprises a mixing chamber 20a and a diffuser 20b, where the mixing chamber 20a supplies a first connection 22 and a second connection 24, and the diffuser 20b supplies a third connection 26. First Partially compressed working medium guided through connection 22 acts as a propellant, preferably via an adjustable drive nozzle, to form a pulsed jet of working medium entering the mixing chamber 20a. The ejector 20 may be supplied with at least partially compressed working medium via a first conduit 21 starting from the compressor section 11 and via the first connection 22 in the mixing chamber 20a, which corresponds to working medium at a first pressure level in Figure 1, and in Figure 1, the partially compressed working medium branches off from the compressor section 11 and is guided toward the ejector 20.

[0031] The partially compressed working medium introduced into the ejector 20 via the first conduit 21 or the first connection 22 corresponds to the working medium at a lower second pressure level in Figure 1 and has a higher pressure than the uncompressed working medium introduced into the ejector 20 via the second conduit 23 or the second connection 24. As a result of this pressure difference, the uncompressed working medium can be drawn into the mixing chamber 20a of the ejector 20, starting from the supply conduit 14 of the turbomachinery unit 10 and via the second conduit 23 or the second connection 24, preferably via an adjustable drive nozzle, and the uncompressed medium is mixed with at least the partially compressed working medium in the region of the mixing chamber 20a.

[0032] This mixture of at least partially compressed working medium or working medium at a first pressure level and uncompressed working medium or working medium at a second pressure level is supplied for cooling to the electromechanical unit 16 and / or at least one other assembly to be cooled, such as a bearing 19, via the diffuser 20b of the ejector 20, a third connection 26 supplied by the diffuser 20b, and a third conduit 25.

[0033] In Figure 1, the mixing ratio of the partially compressed working medium corresponding to the working medium at the first pressure level and the uncompressed working medium corresponding to the working medium at the second pressure level depends on the ejector structure on the one hand, and on the other hand, on the pressure difference between the uncompressed working medium or the working medium at the second pressure level and the partially compressed working medium or the working medium at the first pressure level. The larger the proportion of the uncompressed working medium or the working medium at the second pressure level drawn in through the second conduit 23, the larger the pressure difference between the partially compressed working medium or the working medium at the first pressure level and the uncompressed working medium or the working medium at the second pressure level.

[0034] In Figure 1, because a mixture of at least partially compressed and uncompressed working fluid is guided through the electromechanism 16 and / or at least one other assembly to be cooled, such as the bearing 19, the cooling fluid has a lower temperature than in the prior art where only at least partially compressed working fluid is branched from the compressor section 11 and guided through the electromechanism 16 for cooling. This makes it possible to improve the cooling force and further contributes to the improved overall thermodynamic efficiency of the turbomechanical device 10.

[0035] In the exemplary embodiment shown in Figure 1, the ejector 20, i.e., the mixing chamber 20a of the ejector 20, is appropriately connected to the compressor section 11, i.e., the compressor stage 12 of the compressor section 11, via a first conduit 21 or a first connection 22. Furthermore, the ejector 20, i.e., the mixing chamber 20a of the ejector 20, is connected to the supply conduit 14 of the turbomachinery unit 10 via a second conduit 23 or a second connection 24, as shown in Figure 1. In addition, the ejector 20, i.e., the diffuser 20b of the ejector 20, is connected to the electromachinery 16 via a third conduit 25 or a third connection 26.

[0036] In Figure 1, the electromachine 16 is connected to the supply conduit 14 of the turbomachinery 10 via a return conduit 27 for the cooling medium which is guided through the electromachine 16. Specifically, the opening point 27a of the return conduit 27 to the supply conduit 14 of the turbomachinery 10 is located downstream of the branching point 23a of the second conduit 23 of the supply conduit 14, when viewed in the direction of flow through the supply conduit 14 of the turbomachinery 10. This ensures that only fresh working medium is taken out of the conduit 23 via the second conduit 23.

[0037] Figure 2 shows a further development of the turbomachinery 10 shown in Figure 1, which differs from the turbomachinery 10 shown in Figure 2 only in that a heat exchanger 28 or cooler is incorporated in the return conduit 27 to cool the cooling medium before it returns to the supply conduit 14 of the turbomachinery 10. This is also used to increase the overall thermodynamic efficiency. In other respects, the turbomachinery 10 shown in Figure 2 corresponds to the turbomachinery 10 shown in Figure 1, so to avoid unnecessary repetition, the same reference numerals are used for the same assemblies and the description of the turbomachinery 10 shown in Figure 1 is referenced.

[0038] Figure 3 shows a modification of the turbomachinery device 10 according to Figure 1. The turbomachinery device 10 according to Figure 3 has two compressor sections 11a and 11b, each comprising compressor stages 12a and 12b and compressor shafts 13a and 13b, respectively. These compressor sections 11a and 11b differ from those in Figure 1 in that they are located on opposite sides of the electric machine 16. The two compressor shafts 13a and 13b are preferably located on opposite sides of the electric machine 16 and preferably directly connected to the shaft 17 of the electric machine 16 without the use of a gear mechanism.

[0039] In Figure 3, the two compressor sections 11a and 11b are connected in series. The working medium compressed in compressor section 11a is further compressed in compressor section 11b. Alternatively, the compressor sections 11a and 11b can be connected in parallel, and the first conduit 21 is connected to the discharge conduit of one of the two compressor sections 11a and 11b, as well as to the return conduit 27 to the supply conduit 14 of one of the two compressor sections 11a and 11b for the cooling medium.

[0040] In Figure 3, the compressor sections 11a and 11b can each include multiple compressor stages.

[0041] In Figure 3, the partially compressed working medium, i.e., the working medium partially compressed by the first compressor section 11a, is also supplied to the second compressor section 11b and the ejector 20 for further compression via the overflow conduit 29 and the first conduit 21 branching from the overflow conduit 29. The ejector 20 then draws in the uncompressed working medium from the supply conduit 14 of the turbomachinery unit 10 due to the pressure difference between at least the partially compressed working medium and the uncompressed working medium, and mixes this working medium with the partially compressed working medium in the region of the mixing chamber 20a of the ejector 20. This mixture resulting from the ejector 20 is then supplied again for cooling to the electromachinery unit 16 and / or at least one other assembly to be cooled, such as the bearings 19. In Figure 3, the discharge conduit 15 of the turbomachinery unit 10 for the compressed working medium extends away from the second compressor section 11b.

[0042] Figure 4 shows a modification of the turbomachinery unit 10 according to Figure 3, which differs from the exemplary embodiment in Figure 3 only in that the heat exchanger 28 is incorporated into the return conduit 27 for the cooling medium, which returns the cooling medium, which is guided to pass through or via the electromachinery 16, towards the supply conduit 14 of the turbomachinery unit 10. Alternatively or additionally, coolers may be incorporated into conduits 21, 23 and 25.

[0043] Except for the number and arrangement of the compressor components, the exemplary embodiments in Figures 3 and 4 correspond to the exemplary embodiments in Figures 1 and 2; therefore, to avoid unnecessary repetition, the same reference numerals are used for the same assemblies.

[0044] In Figures 3 and 4, the compressor sections 11a and 11b may also be connected in parallel. In this case, the supply conduit 14 of the turbomachinery unit 10 may lead to both compressor sections 11a and 11b. Using the parallel connection of the compressor sections 11a and 11b, the first conduit 21 may preferably be connected to the discharge conduit of one of the two compressor sections 11a and 11b, as well as to the return conduit 27 to the supply conduit 14 of one of the two compressor sections 11a and 11b for the cooling medium.

[0045] Figure 5 shows a modification of the turbomachinery 10 according to Figure 3, in which, as a propellant supplied to the ejector 20 via the first conduit 21 or first connection 22, partially compressed working medium is not used in the first compressor section 11a, but fully compressed working medium is used in the second compressor section 11b. Therefore, according to Figure 5, the first conduit 21 does not branch off from the overflow conduit 29 but branches off from the discharge conduit 15 of the turbomachinery 10. Consequently, in Figure 5, there is a significantly larger pressure difference between the compressed working medium used as a propellant and the uncompressed working medium drawn in from the supply conduit, and in Figure 5, the mixture of uncompressed and compressed working medium formed in the ejector 20 preferably contains a larger proportion of uncompressed working medium than in Figure 3. All other details are as follows: the exemplary embodiments of Figure 5 correspond to the exemplary embodiments of Figure 3, so to avoid unnecessary repetition, the same reference numerals are used for the same assemblies.

[0046] Alternatively, using a multi-stage compressor structure, the propellant can be taken from an intermediate stage similar to that shown in Figure 1. Furthermore, conduits 23 and 27 can be terminated at an overflow conduit 29 instead of the supply conduit 14 of the turbomachinery unit 10, thereby ensuring that the cooling medium is taken only downstream of the compressor section 11b and returned to the overflow conduit 29.

[0047] Figure 6 shows a modification of an exemplary embodiment relating to Figure 5, which differs from Figure 5 only in that the heat exchanger 28 is incorporated into a return conduit 27 for a cooling medium that is guided to pass through or via at least one other assembly to be cooled, such as the electromechanical unit 16 or the bearing 19.

[0048] Figure 7 shows one embodiment of the turbomachinery device 10 according to the present invention, representing a modification of the turbomachinery device 10 shown in Figure 4. In Figure 4, the second conduit 23 branches off from the supply conduit 14 of the turbomachinery device 10, and the return conduit 27 for the cooling medium opens into the supply conduit 14 of the turbomachinery device 10. In contrast, in Figure 7, a closed circuit for the cooling medium exists, namely the second conduit 23, which is connected to the return conduit 27 for the cooling medium. Accordingly, in Figure 7, the working medium partially compressed in the first compressor section 11a is also appropriately used as a propellant, and this working medium branches off from the overflow conduit 29 and is supplied to the ejector 20 via the first conduit 21, while in Figure 7, the uncompressed working medium is not drawn in by the ejector 20, but rather drawn in, which is guided to pass through or via at least one other assembly to be cooled, such as the electromechanism 16 and / or the bearing 19, and this cooling medium is discharged from at least one other assembly to be cooled, such as the electromechanism 16 and / or the bearing 19, via the cooling medium return conduit 27. Thus, the second conduit 23 and the return conduit 27 for the cooling medium form a closed cooling circuit for the cooling medium in Figure 7, and according to Figure 7, the cooling circuit incorporates a heat exchanger 28.

[0049] In Figure 7, the ejector 20 may be supplied with a working medium at a first pressure level as a propellant via a first conduit 21 or first connection 22, i.e., to draw in a working medium at a lower second pressure level via a second conduit 23 or second connection 24, and the mixture of the working medium at the first pressure level and the working medium at the second pressure level formed in the ejector 20 may be supplied as a cooling medium to at least one other assembly to be cooled, such as the electromechanism 16 and / or the bearing 19, via a third conduit 25 or third connection 26. In Figure 7, the working medium at the first pressure level is the working medium partially compressed in the compressor section 11a, while the working medium at the second pressure level in Figure 7 is the cooling medium that is guided to pass through or via the electromechanism 16 and / or the bearing 19, and the cooling medium is supplied via a cooling medium return conduit 27 and heat exchanger 28 It is supplied to the second conduit 23, and therefore to the second connection 24, via the first conduit 21 or the first connection 22, thereby compensating for any loss of the cooling medium in the circuit.

[0050] The present invention enables effective cooling of at least one other assembly to be cooled, such as the electromachine 16 and / or the bearings 19 of the turbomachine 10, with high overall thermodynamic efficiency of the turbomachine 10.

[0051] The present invention makes it possible to use an electric machine 16 having a high output range in a turbomachinery device 10.

[0052] The flow rate through the ejector 20 can preferably be controlled using an adjustable drive nozzle (not shown). However, in order to ensure the greatest simplicity and robustness of the turbomachinery unit 10, such a preferably adjustable drive nozzle is optional, and the ejector 20 operates in an uncontrolled state.

[0053] In the exemplary embodiments of the turbomachinery unit 10 shown in Figures 1 to 7, the ejector 20 is located outside the housing 18 in each case, and at least some of the conduits 21, 25, and 29 extend outside the housing 18, or at least partially through the housing 18. Alternatively, the ejector 20 may be located inside the housing 18. [Explanation of Symbols]

[0054] 10 Turbomachinery 11 Compressor section 11a Compressor section 11b Compressor section 12 Compressor Stages 12a Compressor stage 12b Compressor stage 13 Compressor shaft 13a Compressor shaft 13b Compressor shaft 14 Supply conduit 15 Discharge conduit 16 Electrical machinery 17 Shaft 18 Housing 19 battalions 20 ejectors 20a Mixing room 20b Diffuser 21 First conduit 22 First connection 23 Second conduit 23a Branch point 24 Second connection 25 The third conduit 26 Third Connection 27 Return conduit 27a Opening point 28 Heat exchanger 29 Overflow conduit

Claims

1. A turbomachinery (10), Each of the compressor sections (11, 11a, 11b) comprises at least one single-stage or multi-stage compressor section (11, 11a, 11b) for increasing the pressure of the working medium, wherein each of the compressor sections (11, 11a, 11b) includes a compressor shaft (13, 13a, 13b), An electrical machine (16) including a shaft (17), Each of the compressor shafts (13, 13a, 13b) extends coaxially with respect to the shaft (17) of the electrical machine (16). Each of the compressor shafts (13, 13a, 13b) is connected to the shaft (17) of the electrical machine (16). The electrical machinery (16) and the compressor sections (11, 11a, 11b) are each housed in a common, sealed, integrated or multi-part housing (18), and the compressor sections (11, 11a, 11b), the electrical machinery (16), and the bearings (19) are mounted within the housing (18) via the bearings (19) so that they are all cleaned by the working fluid. Electrical machinery (16) and, A supply conduit (14) through which an uncompressed working medium can be supplied to the turbomachinery device (10), A discharge conduit (15) through which the working medium compressed by the turbomachinery device (10) can be discharged, The ejector (20) comprises at least one ejector (20) wherein a working medium at a first pressure level may be supplied via a first conduit (21) or first connection (22) as a propellant, i.e., to draw in a working medium at a lower second pressure level via a second conduit (23) or second connection (24), and a mixture of the working medium at the first pressure level and the working medium at the second pressure level formed within at least one of the ejector (20) may be supplied as a cooling medium to the electromechanical unit (16) and / or at least one other assembly to be cooled via a third conduit (25) or third connection (26), A turbomachinery (10) is connected to the supply conduit (14) of the turbomachinery, such that a return conduit (27) for a cooling medium, which is guided to pass through or via the electromachinery (16) and / or at least one other assembly to be cooled, is located downstream of the branching point (23a) of the second conduit (23) or the second connection (24) of the supply conduit (14) of the turbomachinery, when viewed in the direction of flow through the supply conduit (14).

2. The turbomachinery apparatus according to claim 1, wherein at least one of the ejectors (20) may be supplied via the first conduit (21) or the first connection (22) with at least partially compressed working medium as a propellant for drawing in uncompressed working medium via the second conduit (23) or the second connection (24), and a mixture of the at least partially compressed working medium and the uncompressed working medium formed within at least one of the ejectors (20) may be supplied as a cooling medium to the electromachinery (16) and / or at least one other assembly to be cooled via the third conduit (25) or the third connection (26).

3. The turbomachinery according to claim 1, characterized in that at least one of the ejectors (20) is connected via the first conduit (21) or the first connection (22) to the compressor portion (11) or one of the compressor portions (11a, 11b), or to the discharge conduit (15) of the turbomachinery, or to a first leak point of the turbomachinery.

4. The turbomachinery according to claim 1, characterized in that at least one of the ejectors (20) is connected via the second conduit (23) or the second connection (24) to the supply conduit (14) of the turbomachinery, or to one of the compressor sections (11) or the compressor sections (11a, 11b), or to a second leak point of the turbomachinery, or to the electromachinery (16) and / or at least one other assembly to be cooled, to a return conduit (27) of the turbomachinery for a cooling medium guided to pass through or via the electromachinery (16) and / or at least one other assembly to be cooled.

5. The turbomachinery apparatus according to claim 1, characterized in that at least one of the ejectors (20) is connected to the electromachine (16) and / or at least one other assembly to be cooled via the third conduit (25) or the third connection (26).

6. The turbomachinery apparatus according to claim 1, characterized in that a heat exchanger (28) or cooler is incorporated into the return conduit (27) for the cooling medium.

7. The turbomachinery apparatus according to claim 1, characterized in that a separate compressor section (11) has at least one compressor stage (12) arranged coaxially with respect to the electric machine (16) on the side surface of the electric machine (16).

8. The turbomachinery device according to claim 1, characterized in that two compressor sections (11a, 11b), each having at least one compressor stage (12a, 12b), are arranged coaxially with respect to the electric machine (16) on opposite sides of the electric machine (16).

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