Compressor system

Abstract

A compressor system according to the present disclosure includes: a compressor provided with a rotor and a stator that forms a flow path for a fluid to be compressed by covering the rotor; and a sacrificial member disposed in a receiving space that communicates with the flow path. The sacrificial member has a portion to be measured, which is disposed in the receiving space and is stressed by changes in fluid pressure.

Description

Technical area

[0001] The present disclosure relates to a compressor system. This application claims priority based on JP 2022-156117, filed on September 29, 2022, the contents of which are incorporated herein by reference. State of the art

[0002] In turbomachinery, such as centrifugal compressors, the material forming a rotor, stator, or the like can deteriorate through contact with a working fluid. Examples of material wear include embrittlement and corrosion caused by components of the working fluid.

[0003] For example, Patent Document 1 discloses a method in which a coupled multi-electrode array sensor (CMAS) probe is capable of detecting an increase in electrical resistance over time, which is arranged within a compressor so as to be exposed to a working fluid, thereby measuring and monitoring the erosion and corrosion state of materials. Citation listPatent literature

[0004] Patent Document 1: JP 2019-82165 A Brief description of the inventionTechnical problem

[0005] A compressor rotor rotating at high speed is subjected to stress caused by centrifugal force, and the stress acting on the rotor is greater than the stress acting on the stator. Thus, wear, such as embrittlement, corrosion, or the like, is more likely to occur in the rotor than in the stator. This can lead to a case where a defect such as stress corrosion cracking occurs in the rotor due to stress and corrosion. Therefore, there is a need for technology capable of detecting wear, defects, and the like in a wider variety of modes.

[0006] The present disclosure has been made to solve the above problems, and an object of the present disclosure is to provide a compressor system capable of detecting wear, defects, and the like in a wider variety of modes. Solution to the problem

[0007] To solve the above-mentioned problems, a compressor system according to the present disclosure includes: a compressor provided with a rotor and a stator that forms a flow path for a fluid to be compressed by covering the rotor; and a sacrificial member disposed in a receiving space in communication with the flow path. The sacrificial member includes a portion to be measured, which is disposed in the receiving space and is stressed by a pressure of the fluid. Advantageous effects of the invention

[0008] The present disclosure may provide a compressor system capable of detecting wear, defects, and the like in a wider variety of modes. Brief description of the drawings Fig. 1 is a diagram illustrating a schematic configuration of a compressor system according to a first embodiment, a second embodiment, and a third embodiment of the present disclosure. Fig. 2 is an enlarged diagram of a main section in Fig. 1 for explaining a configuration of a sacrificial member according to the first embodiment of the present disclosure. Fig. 3 is an enlarged diagram of a main section in Fig. 1 for explaining a configuration of a sacrificial member according to the second embodiment of the present disclosure. Fig. 4 is an enlarged diagram of a main section in Fig. 1 for explaining a configuration of a sacrificial member according to the third embodiment of the present disclosure. Fig. 5 is a diagram illustrating a schematic configuration of a compressor system according to a fourth embodiment of the present disclosure. Fig. 6 is a diagram illustrating a schematic configuration of a compressor system according to a sixth embodiment of the present disclosure. Fig. 7 is an enlarged diagram of a main section in Fig. 6 for explaining a configuration of a sacrificial member and an inspection cover according to the fifth embodiment of the present disclosure. Fig. 8 is a diagram for explaining a configuration of a sacrificial member and an inspection cover according to a sixth embodiment of the present disclosure, and is a diagram similar to that shown in Fig. 7 illustrated section. Fig. 9 is a diagram for explaining a configuration of a sacrificial member and an inspection cover according to a seventh embodiment of the present disclosure. Fig. 10 is a diagram illustrating a schematic configuration of a compressor system according to another embodiment of the present disclosure. Fig. 11 is a diagram illustrating a schematic configuration of a compressor system according to another embodiment of the present disclosure. Description of embodiments

[0009] Hereinafter, embodiments for implementing a compressor system according to the present disclosure will be described with reference to the accompanying drawings. First embodiment compressor system

[0010] A compressor system detects wear, defects, and the like of a compressor operating in a facility. A compressor system according to the present embodiment detects wear, defects, and the like of a rotor of a compressor.

[0011] As in Fig. 1, a compressor system 1 includes a compressor 10, a sacrificial member 20, a voltage tester 30, and an inspection cover 40. compressor

[0012] The compressor 10 is arranged, for example, within a building or the like in a chemical plant. The compressor 10 is arranged in an atmospheric environment within the building. The compressor 10 compresses, for example, a process gas generated in a chemical plant as a working fluid and supplies the compressed process gas to a reaction device (not illustrated) or the like arranged in the chemical plant.

[0013] The compressor 10 of the present embodiment is a single-shaft multi-stage centrifugal compressor (multi-stage centrifugal compressor) that compresses hydrogen gas (H2) as the process gas. For convenience, a process gas to be compressed by the compressor 10 is hereinafter referred to simply as "Gas G."

[0014] The compressor 10 includes a rotor 11, a stator 12, a bearing portion 13 and a seal portion 14. rotor

[0015] The rotor 11 is a part of the compressor 10 that is configured to rotate when the compressor 10 is driven.

[0016] The rotor 11 includes a rotor shaft 110 and an impeller 111.

[0017] The rotor shaft 110 is formed in a cylindrical shape centered on a virtual axis Ar extending in a direction along a horizontal direction. In the present embodiment, for convenience, a direction in which the axis Ar extends is referred to as an “axial direction Da.” Of both sides in the axial direction Da, one side (left side in Fig. 1) simply called “one side Dal”, and the opposite side (right side in Fig. 1) is called “the other side of Dar”.

[0018] A circumferential direction of the rotor shaft 110 extending centrally along the axis Ar is simply referred to as the "circumferential direction Dc." A direction perpendicular to the axis Ar is referred to as the "radial direction." The rotor shaft 110 is formed from a metal material, for example, in the present embodiment.

[0019] The impeller 111 is integrally fixed to the rotor shaft 110 on an outer surface 110s of the rotor shaft 110, and a plurality of stages of the impellers 111 are arranged at intervals in the axial direction Da. In the present embodiment, a case where the impellers 111 of five stages are arranged at intervals in the axial direction Da will be described as an example.

[0020] Hereinafter, for the sake of simplicity, the idler wheel 111 arranged on the leftmost side Dal among the plurality of idler wheels 111 is referred to as “front-stage idler wheel 111f,” and the idler wheel 111 arranged on the rightmost side Dar among the plurality of idler wheels 111 is referred to as “rear-stage idler wheel 111e.”

[0021] The impeller 111 of each stage compresses the gas G flowing into the interior of the impeller 111 from one side Dal and directs the gas G radially outward using a centrifugal force generated by its rotation around the axis Ar together with the rotor shaft 110. Accordingly, the impeller 111 of each stage is exposed to the gas G.

[0022] Each impeller 111 includes a disk 111a, a blade 111b, and a cover 111c. The impeller 111 of the present embodiment is a so-called closed impeller. The impeller 111 is formed, for example, from a metal material.

[0023] The disc 111a is tubular in shape, gradually extending toward the other side Dar, with the center located on the axis Ar when attached to the rotor shaft 110. Accordingly, a side surface (reference numeral omitted) is formed on the disc 111a, facing one side Dal and extending toward the other side Dar. The disc 111a is integrally attached to the rotor shaft 110 by attaching an inner surface (reference numeral omitted) of the disc 111a to the outer surface 110s of the rotor shaft 110.

[0024] The moving blade 111b is integrally formed with the side surface of the disk 111a. A plurality of moving blades 111b are arranged to be aligned at equal intervals in the circumferential direction Dc. For example, the moving blade 111b extends such that it is twisted in one rotational direction Dr of the rotor shaft 110 while extending toward the other side Dar.

[0025] The rotation direction Dr of the rotor shaft 110 in the present embodiment is a direction in which the rotor shaft 110 rotates clockwise when the rotor shaft 110 is viewed from the one side Dal.

[0026] The cover 111c faces the disk 111a from one side Dal in a state where the moving blade 111b is inserted together with the disk 111a in the axial direction Da. The cover 111c is tubular and gradually widens toward the other side.

[0027] The cover 111c is formed integrally with the moving blade 111b. Since the cover 111c is formed integrally with the moving blade 111b, a compression flow path 111p is defined between the cover 111c and the disk 111a, in which the gas G is compressed by the moving blade 111b. stator

[0028] The stator 12 is a part of the compressor 10 that is configured to remain stationary when the compressor 10 is driven. The stator 12 covers the rotor 11 from the outside in the radial direction.

[0029] The stator 12 includes a housing 120, a diaphragm 121, an inlet nozzle 122 and an outlet nozzle 123.

[0030] The housing 120 is an outer shell of the compressor 10 and houses various devices comprising the compressor 10. In the present embodiment, the housing 120 is formed, for example, in a tubular shape with both ends closed in a state extending in the axial direction Da. An outer surface 120s of the housing 120 facing the outside of the compressor 10 is exposed to the atmosphere. The housing 120 is formed, for example, from a metal material.

[0031] In the housing 120, a housing inlet flow path 120a through which the gas G flows in from the outside of the housing 120 to the inside, and a housing outlet flow path 120b through which the gas G flows out from the inside to the outside of the housing 120 are formed.

[0032] The housing inlet flow path 120a and the housing outlet flow path 120b are formed to extend through an outer wall of the housing 120. The housing inlet flow path 120a and the housing outlet flow path 120b are arranged to be separated from each other in the axial direction Da. More specifically, the housing inlet flow path 120a is arranged on one side Dal relative to the housing outlet flow path 120b.

[0033] The diaphragm 121 is arranged to cover the impeller 111 of the rotor 11 from the outside in the radial direction and to cover the rotor shaft 110 from the outer peripheral side with a gap from the outer surface 110s of the rotor shaft 110. The diaphragm 121 is tubular in shape, the center of which is the axis Ar and extends outward.

[0034] The diaphragm 121 is housed in the housing 120 and is integrally secured to an inner surface 120i of the housing 120. The diaphragm 121 is secured to the inner surface 120i of the housing 120, for example, by a fastening member (not illustrated), such as a screw. The diaphragm 121 is formed, for example, from a metal material.

[0035] The diaphragm 121 has an opposing surface 121s on the inside, which faces the outer surface 110s of the rotor shaft 110 as an inner surface. The diaphragm 121 is formed with a receiving recessed portion 121r that is recessed radially outward from the opposing surface 121s to accommodate the impeller 111 therein. In the axial direction Da, the same number of receiving recessed portions 121r as the number of impellers 111 are arranged side by side.

[0036] A plurality of flow paths through which the gas G flows are formed in the diaphragm 121. More specifically, a first flow path 121a for allowing the gas G to flow into the compression flow path 111p of the front-stage impeller 111f (intake), a second flow path 121b for allowing the gas G to flow out of the compression flow path 111p of the rear-stage impeller 111e (exhaust), and a plurality of intermediate flow paths 121c for connecting the compression flow paths 111p of the impellers 111 adjacent to each other between the first flow path 121a and the second flow path 121b are formed in the diaphragm 121.

[0037] The first flow path 121a is a flow path located on the leftmost side Dal among the plurality of flow paths formed in the diaphragm 121. The first flow path 121a is formed, for example, as an annular space centered on the axis Ar.

[0038] The first flow path 121a is connected to the casing inlet flow path 120a from the inner side (inside in the radial direction) of the casing 120. The first flow path 121a is connected to the compression flow path 111p of the front-stage impeller 111f from one side Dal.

[0039] The second flow path 121b is a flow path located on the far right of the other side Dar among the plurality of flow paths formed in the diaphragm 121. The second flow path 121b is formed, for example, as an annular space centered on the axis Ar.

[0040] The second flow path 121b is connected to the compression flow path 111p of the rearmost stage impeller 111e from the other side. The second flow path 121b is connected to the casing outlet flow path 120b from the inside (inner side in the radial direction) of the casing 120.

[0041] The plurality of intermediate flow paths 121c are arranged side by side in the axial direction Da and separated from each other between the first flow path 121a and the second flow path 121b. Each intermediate flow path 121c is a flow path that guides the gas G compressed in the compression flow path 111p of the impeller 111 arranged on one side Dal to the compression flow path 111p of the next-stage impeller 111 arranged on the other side Dar relative to the above-mentioned impeller 111.

[0042] In the present embodiment, the intermediate flow path 121c consists of a diffuser flow path 121d and a return flow path 121e.

[0043] The diffuser flow path 121d is a flow path that guides the gas G compressed in the compression flow paths 111p of the impeller 111, except for the rearmost stage impeller 111e among the plurality of impellers 111, to the outside in the radial direction. One end of the diffuser flow path 121d is open to the inner surface of the receiving recessed portion 121r. One end of the diffuser flow path 121d is arranged so that the opening portion faces the outlet of the compression flow path 111p of the impeller 111 in the radial direction.

[0044] The return flow path 121e is a flow path connected to the other end opposite to one end of the diffuser flow path 121d, guides the gas G that has flowed through the diffuser flow path 121d to the inside in the radial direction, and guides the gas G to the compression flow path 111p of the impeller 111 of the subsequent stage.

[0045] Thus, in the flow path of gas G, between the first flow path 121a and the second flow path 121b, the compression flow path 111p of the impeller 111 and the intermediate flow path 121c, consisting of the diffuser flow path 121d and the return flow path 121e, are alternately arranged. For convenience of description, the flow path of gas G consisting of the compression flow path 111p of the impeller 111 and the intermediate flow path 121c will be referred to as the "compression section" hereinafter.

[0046] A portion of the gas G compressed by the rotation of the impeller 111 flows into the gap between the inner surface of the receiving recessed portion 121r and the disc 111a of the impeller 111 and into the gap between the inner surface of the receiving recessed portion 121r and the cover 111c of the impeller 111. Accordingly, these gaps communicate with the compression flow path 111p of the impeller 111.

[0047] The inlet nozzle 122 introduces the gas G supplied from the outside into the housing 120. Accordingly, the inlet nozzle 122 is an inlet portion of the gas G into the compressor 10. The inlet nozzle 122 is formed integrally with the housing 120. The inlet nozzle 122 is formed, for example, from a metal material.

[0048] An intake flow path 122a is formed within the intake nozzle 122. For example, gas G flows into the intake flow path 122a through a suction pipe 100 connected to the intake nozzle 122 and connecting the intake nozzle 122 and a device (not illustrated), such as a gas supply source outside the compressor 10.

[0049] The intake flow path 122a is connected to the housing inlet flow path 120a formed in the housing 120 from the outside (outside in the radial direction) of the housing 120. Thus, the gas G flowing through the intake pipe 100 flows through the intake flow path 122a and the housing inlet flow path 120a into the first flow path 121a.

[0050] In the present embodiment, the first flow path 121a of the diaphragm 121, the housing inlet flow path 120a of the housing 120, and the suction flow path 122a of the inlet nozzle 122 described above form an inlet flow path P1 through which the gas G flows before being compressed. The inlet flow path P1 is a flow path through which the gas G with the lowest pressure flows before being compressed by the compression section among the flow paths of the gas G in the compressor 10.

[0051] The outlet nozzle 123 causes the gas G compressed inside the housing 120 to flow out of the housing 120. Therefore, the outlet nozzle 123 is an outlet portion for the gas G in the compressor 10. The outlet nozzle 123 is formed integrally with the housing 120. The outlet nozzle 123 is arranged on the other side relative to the inlet nozzle 122. The outlet nozzle 123 is formed, for example, from a metal material.

[0052] A discharge flow path 123a is formed within the discharge nozzle 123. The discharge flow path 123a is connected to the housing outlet flow path 120b formed in the housing 120 from the outside (outside in the radial direction) of the housing 120. Thus, the compressed gas G flows through the second flow path 121b formed in the diaphragm 121 and through the housing outlet flow path 120b into the discharge flow path 123a.

[0053] A discharge pipe 200 connecting the discharge nozzle 123 to a device external to the compressor 10 is connected to the discharge flow path 123a. Accordingly, the gas G flowing through the discharge flow path 123a flows through the discharge pipe 200 toward the device external to the compressor 10 (is discharged).

[0054] In the present embodiment, the second flow path 121b of the diaphragm 121, the casing outlet flow path 120b of the casing 120, and the discharge flow path 123a of the discharge nozzle 123 described above constitute an outlet flow path P2 through which the gas G flows after compression. The outlet flow path P2 is a flow path through which the gas G compressed by the compression section and having the highest pressure flows in the flow path for the gas G in the compressor 10. Storage sections

[0055] The bearing portion 13 is housed in the housing 120. In the present embodiment, the bearing portion 13 includes a radial bearing 130, a thrust bearing 131, and a thrust ring 132.

[0056] The radial bearing 130 rotatably supports the rotor shaft 110 of the rotor 11. For example, a pair of radial bearings 130 are arranged spaced apart from each other in the axial direction Da. The pair of radial bearings 130 are arranged such that the diaphragm 121 is clamped therebetween in the axial direction Da.

[0057] The thrust bearing 131 prevents a situation in which the rotor shaft 110 of the rotor 11 is displaced in the axial direction Da due to the compression of the gas G by the impeller 111. The thrust bearing 131 prevents a situation in which the rotor shaft 110 is displaced in the axial direction Da by pressing the flange-shaped thrust ring 132, which is integrally connected to the rotor shaft 110, into a state in which the thrust ring 132 is supported in the axial direction Da.

[0058] Specifically, for example, a pair of thrust bearings 131 and a pair of thrust rings 132 are each arranged to be separated from each other in the axial direction Da. Each bearing of the pair of thrust bearings 131 and each ring of the pair of thrust rings is arranged between the diaphragm 121 and the radial bearing 130.

[0059] Of the pair of thrust bearings 131, the thrust bearing 131 arranged on one side Dal supports the thrust ring 132 arranged on one side Dal of the pair of thrust rings 132, while pressing on the thrust ring 132 from one side Dal.

[0060] On the other hand, of the pair of thrust bearings 131, the thrust bearing 131 arranged on the other side Dar supports the thrust ring 132 arranged on the other side Dar of the pair of thrust rings 132, while pressing the thrust ring 132 from the other side Dar. Sealing section

[0061] The sealing portion 14 prevents a situation in which air flows into the compression portion through the gap between the rotor shaft 110 of the rotor 11 and the diaphragm 121 of the stator 12. The sealing portion 14 is disposed between the rotor shaft 110 and the diaphragm 121. For example, a pair of sealing portions 14 are arranged to sandwich the plurality of impellers 111 aligned in the axial direction Da.

[0062] Of the pair of seal portions 14, the seal portion 14 disposed on one side Dal prevents a situation in which air flows from one side Dal through the gap between the rotor shaft 110 and the diaphragm 121 into the compression flow path 111p of the front-stage impeller 111f.

[0063] On the other hand, of the pair of seal portions 14, the seal portion 14 arranged on the other side Dar prevents a situation in which air from the other side Dar flows into the compression flow path 111p of the rearmost stage impeller 111e through the gap between the rotor shaft 110 and the diaphragm 121.

[0064] For the sake of simplicity of description, hereinafter, of the pair of sealing portions 14, the sealing portion 14 arranged on one side Dal is referred to as “first sealing portion 14a” and the sealing portion 14 arranged on the other side Dar of the pair of sealing portions 14 is referred to as “second sealing portion 14b”.

[0065] Although not illustrated in detail, the seal portions 14 (the first seal portion 14a and the second seal portion 14b) in the present embodiment are each, for example, a labyrinth seal configured as follows: a plurality of rotor-side ribs formed to extend outward in a flange shape in the radial direction from the outer surface 110s of the rotor shaft 110, and a plurality of stator-side ribs formed to extend inward in a flange shape in the radial direction from the opposing surface 121s of the diaphragm 121 are alternately arranged in the axial direction Da. For example, a part of the pressurized gas G flowing through the discharge pipe 200 is supplied to the seal portion 14 as a seal gas.

[0066] Although not illustrated in detail, a part of the compressed gas G flowing through the discharge pipe 200 is supplied toward the second sealing portion 14b, for example, from a position on the other side Dar relative to the second sealing portion 14b.

[0067] Thus, the compressed gas G flows through the gaps between the outer surface 110s of the rotor shaft 110 and the opposing surface 121s of the diaphragm 121 at a position Dal on one side relative to the first sealing portion 14a and a position Dar on the other side relative to the second sealing portion 14b. Therefore, the space of the gap between the diaphragm 121 and the rotor shaft 110 is maintained in a high-pressure state.

[0068] An example of a compression flow of the gas G through the compressor 10 is described below.

[0069] The rotor shaft 110 is rotated at high speed in the rotation direction Dr at a predetermined rotation speed by a drive source (not illustrated), such as an electric motor, in a state supported by the bearing portion 13. Due to the rotation of the rotor shaft 110, the impeller 111 integrated into the rotor shaft 110 rotates at high speed together with the rotor shaft 110.

[0070] The gas G supplied from the gas supply source located outside the compressor 10 through the suction pipe 100 to the compressor 10 is sucked into the casing 120 through the inlet nozzle 122 by the driving rotation of the rotor 11. The gas G flowing through the suction flow path 122a of the inlet nozzle 122 and the casing inlet flow path 120a of the casing 120 into the first flow path 121a of the diaphragm 121 is compressed by the moving blade 111b rotating in the compression flow path 111p of the subsequent front-stage impeller 111f. That is, before compression, the gas G flowing through the suction pipe 100 toward the compressor 10 is guided through the inlet flow path P1 (the suction flow path 122a, the casing inlet flow path 120a, and the first flow path 121a) of the compressors 10 to the compression flow path 111p of the front-stage impeller 111f.

[0071] The gas G compressed in the compression flow path 111p of the front-stage impeller 111f is passed through the subsequent diffuser flow path 121d and the return flow path 121e to the compression flow path 111p of the next-stage impeller 111, and is further compressed in the compression flow path 111p of the next-stage impeller 111. The gas G compressed in the compression flow path 111p of the impeller 111 flows through the subsequent intermediate flow path 121c (the diffuser flow path 121d and the return flow path 121e) and repeats a step of being recompressed in the next-stage impeller 111, whereby the gas G reaches the compression flow path 111p of the rear-stage impeller 111e.

[0072] The gas G compressed in the compression flow path 111p of the rearmost stage impeller 111e is discharged into the second flow path 121b of the subsequent diaphragm 121 and flows into the discharge pipe 200 through the casing outlet flow path 120b of the casing 120 and the discharge flow path 123a of the discharge nozzle 123. That is, the compressed gas G, after passing through the compression flow path 111p of the rearmost stage impeller 111e, is led into the discharge pipe 200 through the discharge flow path P2 (the second flow path 121b, the casing outlet flow path 120b, and the discharge flow path 123a) of the compressor 10. The gas G flowing into the discharge pipe 200 is introduced, for example, into a reaction device (not illustrated) arranged outside the compressor 10 and used as a reaction fluid.

[0073] In summary, the gas G sucked into the compressor 10 through the suction pipe 100 before compression is guided through the inlet flow path P1 (the intake flow path 122a, the casing inlet flow path 120a and the first flow path 121a) to the compression flow path 111p of the front-stage impeller 111f in the compression section. The gas G supplied to the compression flow path 111p of the front-stage impeller 111f is subjected to compression through multiple stages of the compression sections consisting of the compression flow paths 111p of the impellers 111 of the plurality of stages and the intermediate flow paths 121c connecting the compression flow paths 111p to each other, until the gas G reaches a predetermined high pressure state. The gas G compressed by the compression sections is discharged from the compression flow path 111p of the rearmost stage impeller 111e in its compression section through the outlet flow path P2 (the second flow path 121b, the casing outlet flow path 120b and the discharge flow path 123a) into the discharge pipe 200. sacrificial limb

[0074] The sacrificial member 20 can simulate a state of change over time / wear of the rotor 11 due to the stress of the driven compressor 10 acting on the rotor 11 and due to the fact that the rotor 11 is exposed to the gas G as the working fluid.

[0075] The sacrificial member 20 in the present embodiment is used, for example, to judge whether or not inspection and repair of the compressor 10 is required, and to determine the timing, duration, and the like of the inspection and repair.

[0076] As in Fig. 1, an accommodating space R for accommodating the sacrificial member 20 is formed in the casing 120 of the stator 12 of the above-described compressor 10. The accommodating space R, in the present embodiment, is a space defined by an inner surface of a recess 120d formed to be recessed from the outer surface 120s of the casing 120. In other words, the accommodating space R is open to the outer surface 120s of the casing 120. The accommodating space R, in the present embodiment, is located, for example, on the other side Dar relative to the outlet flow path P2.

[0077] The receiving space R is connected to the outlet flow path P2 through a connecting flow path 12p formed in the housing 120. In other words, the receiving space R is connected (communicates with) the outlet flow path P2 via the connecting flow path 12p, through which the gas G flows at the highest pressure after compression.

[0078] One end of the connecting flow path 12p is open to the accommodation space R. The other end of the connecting flow path 12p is open to the housing outlet flow path 120b of the outlet flow path P2. Accordingly, a portion of the gas G flowing through the outlet flow path P2 after being compressed by the compression section is sucked into the accommodation space R through the connecting flow path 12p.

[0079] The sacrificial member 20 is arranged in the receiving space R. That is, when the compressor 10 is in operation, the sacrificial member 20 is exposed to the gas G after being compressed by the compression section. Fig. 1, the sacrificial member 20 has a quadrangular shape indicated by a dotted line for ease of illustration. The configuration, shape, and the like of the sacrificial member 20 will be described with reference to Fig. 2 described in detail.

[0080] As in Fig. 2, the sacrificial member 20 in the present embodiment includes a C-ring portion 210 and a pressing and holding portion 21. C-ring section

[0081] The C-ring portion 210 is formed from a metal material having the same composition as the metal material constituting the rotor 11 of the compressor 10. In the present embodiment, the C-ring portion 210 is formed from a metal material having the same composition as the metal material constituting the impeller 111 of the rotor 11.

[0082] In this case, “same composition” means, for example, that it is the same material as that used to manufacture the rotor 11.

[0083] The C-ring portion 210 is formed with a portion 21x to be measured, which is stressed by pressurizing with the gas G sucked from the outlet flow path P2.

[0084] The C-ring portion 210 is a plate-like member and is convexly curved and arranged in a C-shape. In the present embodiment, the convex portion of the C-ring portion 210 is the 21x to be measured. The C-ring portion 210 is formed with one end 210a and the other end 210b that are close to each other due to the C-shape arrangement described above. Hereinafter, the one end 210a and the other end 210b of the C-ring portion 210 may be collectively referred to as "both ends." Pressing and holding section

[0085] The pressing and holding portion 21 holds both ends (one end 210a and the other end 210b) of the C-ring portion 210 in a pressing state to bring them close to each other. The pressing and holding portion 21 includes a bolt portion 22 and a pair of nut portions 23.

[0086] The bolt portion 22 is columnar, and the nut portion 23 can be screwed onto it. The bolt portion 22 extends through a portion of the C-ring portion 210 near one end 210a and a portion of the C-ring portion 210 near the other end 210b. For example, a stud bolt or the like that does not have a head portion is used as the bolt portion 22.

[0087] The pair of nut portions 23 are screwed to the bolt portion 22 in such a way that the C-ring portion 210 is clamped therebetween. The pair of nut portions 23 are screwed onto the bolt portion 22, thereby being held in a state where they press the C-ring portion 210 in a direction in which the C-ring portion 210 is clamped therebetween.

[0088] More specifically, each pair of the nut portions 23 is arranged outside the C-ring portion 210 in a direction in which the bolt portion 22 extends in a state screwed to the bolt portion 22, and applies such a pressure to the C-ring portion 210 that brings one end 210a and the other end 210b of the C-ring portion 210 close to each other.

[0089] At this time, the pair of nut portions 23 exerts a tension on the C-ring portion 210 that is higher than the maximum tension acting on the rotor 11 during the rated operation of the compressor 10 in the direction in which the C-ring portion 210 is clamped therebetween. The pair of nut portions 23 of the present embodiment exerts a tension on the C-ring portion 210 that is higher than the maximum tension acting on the impeller 111 during the rated operation of the compressor 10. In other words, the tightening torque of the pair of nut portions 23 is adjusted so that a tension higher than the maximum tension acting on the impeller 111 of the rotor 11 during the rated operation of the compressor 10 is applied to the portion to be measured 21x of the C-ring portion 210 during the rated operation of the compressor 10 is applied.

[0090] The term “maximum stress” as used herein means, for example, the maximum magnitude among the magnitudes of stresses acting on the rearmost stage impeller 111e during rated operation of the compressors 10. The magnitude and direction of the stress acting on the impeller 111 of the rotor 11, its distribution, and the like are detected in advance by performing, for example, an analysis using the finite element method (FEM analysis) or the like.

[0091] When the pair of nut portions 23 exert pressure on the C-ring portion 210, a peripheral portion of the portion to be measured 21x, including the portion to be measured 21x, is pulled toward one end 210a and the other end 210b while taking the portion to be measured 21x as the base point. That is, a tensile stress is generated in the portion to be measured 21x. Voltage tester

[0092] The tension detector 30 is a sensor configured to detect a strain of the section 21x to be measured. The tension detector 30 is attached (clamped) to the section 21x to be measured of the C-ring section 210. The tension detector 30 is electrically connected, for example, to a monitoring device (not illustrated) located outside the compressor 10.

[0093] The tension detector 30 detects the amount of strain of the section 21x to be measured and transmits a signal indicating the amount of strain to the aforementioned monitoring device. Accordingly, the monitoring device can, for example, monitor the amount of strain of the section 21x to be measured of the C-ring section 210 over time. Inspection cover

[0094] The inspection cover 40 is a cover member that closes the opening of the recess 120d formed in the housing 120 to make the receiving space R a closed space. The inspection cover 40 can be attached to and detached from the outer surface 120s of the housing 120. More specifically, the inspection cover 40 can be attached to and detached from the outer surface 120s of the housing 120 by a fastening member B, such as a bolt.

[0095] That is, the inspection cover 40 closes the opening of the receiving space R by being fixed to the outer surface 120s of the housing 120 with the fixing member B, and opens the receiving space R by being removed when the fixing member B is released. The inspection cover 40 is formed of, for example, a metal material.

[0096] The inspection cover 40 is attached to the outer surface 120s of the housing 120 during operation of the compressor 10. The inspection cover 40 is attached to the outer surface 120s of the housing 120 to hermetically isolate the receiving space R from the atmosphere. The inspection cover 40 is removed from the outer surface 120s of the housing 120 when the sacrificial member 20 is removed from the receiving space R by an operator, a maintenance technician, or the like of the compressor 10. Thus, the operator, maintenance technician, or the like of the compressor 10 can remove or observe the sacrificial member 20 from outside the compressor 10. Operational impact

[0097] In the configuration described above, a portion of the gas G (H2) compressed during operation (rated operation) of the compressor 10 is sucked into the receiving space R, and the sacrificial member 20 disposed in the receiving space R is exposed to the sucked gas G. Once the sacrificial member 20 is exposed to the gas G, the C-ring portion 210 enclosed in the sacrificial member 20 is stressed by absorbing the pressure of the gas G.

[0098] Thus, for example, by removing the sacrificial member 20 from the receiving space R while the compressor 10 is stopped, the amount of strain of the section to be measured 21x in the C-ring section 210 can be checked. In other words, it is possible to detect the amount of strain, which is an indicator of the degree of wear of the C-ring section 210, from the section to be measured 21x. The members constituting the compressor 10 are subject not only to wear, such as corrosion, caused simply by the properties of the gas G, but also to wear caused by the applied pressure because they are exposed to the high-pressure gas G while rotating like the rotor 11. To address this problem, since the sacrificial member 20 is stressed by the pressure of the gas G, it is possible to detect not only the influence of wear due to the properties of the gas G, but also the influence of wear due to the pressure of the gas G.

[0099] This makes it possible to check how much stress was exerted on the C-ring portion 210 when the pressure of the gas G acted on the C-ring portion 210. Consequently, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0100] In the configuration discussed above, the metal material forming the C-ring portion 210 is the same as the metal material forming the impeller 111 of the rotor 11. For example, when the compressor 10 is stopped, by removing the sacrificial member 20 from the receiving space R and observing the surface of the C-ring portion 210, it is possible to check the degree of progression of embrittlement (hydrogen embrittlement) caused by the gas G on the surface of the C-ring portion 210, the presence or absence of a defect, and the like. In other words, it is possible to determine the degree of progression of embrittlement, which is an indicator of the degree of wear of the C-ring portion 210, from the surface of the C-ring portion 210. Accordingly, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0101] In summary, by disposing the sacrificial member 20 in the receiving space R connected to the flow path of the fluid compressed by the compressor 10, it is possible to detect more wear, defects, and the like that may occur in the rotor 11 (impeller 111) of the compressor 10 than in a case of using, for example, a sacrificial member that does not include a portion to be measured or a sacrificial member that includes a portion to be measured that is not formed of a metal material having the same composition as the metal material constituting the rotor 11.

[0102] Furthermore, in the configuration described above, the accommodation space R in which the sacrificial member 20 is accommodated is connected to the outlet flow path P2 through which the gas G flows at the highest pressure after being compressed by the compression section. Accordingly, greater pressure is exerted by the gas G on the C-ring portion 210 than when the gas G is sucked into the receiving space R before compression or when the gas G is sucked into the receiving space R in the middle of compression. That is, it is possible to check the condition of the C-ring portion 210 that has deteriorated under more severe embrittlement conditions. In particular, when hydrogen gas is used as the process gas, members exposed to the hydrogen gas are significantly affected by hydrogen embrittlement. When higher pressure is applied, the possibility of hydrogen embrittlement is higher. Accordingly, by disposing the sacrificial member 20 in the receiving space R connected to the outlet flow path P2, through which the gas G flows at the highest pressure, it is possible to simulate a member of the compressor 10 that is most affected by hydrogen embrittlement with high accuracy through the sacrificial member 20. Therefore, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be better estimated.

[0103] In the configuration described above, a convex portion of the C-ring portion 210 serves as the section to be measured 21x, which is stressed by the pressure of the gas G. The bolt portion 22 passes through the portion near one end 210a and the portion near the other end 210b in the C-ring portion 210, and the pair of nut portions 23 screwed onto the bolt portion 22 exerts a stress on the C-ring portion 210 that is higher than the maximum stress generated in the rotor 11 (impeller 111) in the direction in which the C-ring portion 210 is sandwiched therebetween. Thus, during the operation of the compressor 10 (during rated operation), a stress continues to act on the C-ring portion 210 that is always higher than the maximum stress acting on the rotor 11.This makes it possible to check the condition of the C-ring portion 210, which has deteriorated under more severe embrittlement conditions compared to the environment of the compression flow path 111p in which the rotor 11 rotates while being exposed to the gas G. Therefore, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be better estimated.

[0104] In the configuration described above, the receiving space R in which the sacrificial member 20 is accommodated is formed in the stator 12 (housing 120) of the compressor 10. As a result, it is not necessary to additionally provide a member or the like for defining the receiving space R, for example, in the compressor 10. Thus, an increase in the number of components of the compressor 10 can be avoided.

[0105] In the configuration described above, the tension detector 30 is attached to the section 21x to be measured. This makes it possible, for example, to transmit a signal indicating the amount of strain detected by the tension detector 30 to the outside of the compressor 10, so that a change in the amount of strain over time of the section 21x to be measured in the C-ring section 210 can be monitored from the outside of the compressor 10 during operation of the compressor 10. Thus, it is possible to inspect and repair the rotor 11 of the compressor 10 at the appropriate time based on the amount of strain in the section to be measured 21x of the C-ring section 210 detected by the tension tester 30.

[0106] In the configuration described above, the opening of the receiving space R on the outer surface 120s of the housing 120 is closed by the attachable / detachable inspection cover 40. Thus, the sacrificial member 20 can be removed from the receiving space R by removing the inspection cover 40. By closing the inspection cover 40, the receiving space R can be hermetically sealed from the atmosphere. Accordingly, it is not necessary to disassemble the compressor 10 when, for example, removing the sacrificial member 20 from the receiving space R. Therefore, the condition of the worn C-ring section 210 can be easily checked. Second embodiment

[0107] In the following, using Fig. 3 describes a second embodiment of a sacrificial member according to the present disclosure. In the following description of the second embodiment, common components with the first embodiment are denoted by the same reference numerals in the drawings, and explanations thereof will be omitted. In the second embodiment, the configuration of a sacrificial member differs from the configuration of the sacrificial member described in the first embodiment.

[0108] An accommodation space R is formed as a cylindrical space in the present embodiment. That is, a recess 120d is formed to be recessed from an outer surface 120s of a housing 120 in a circular cross-sectional shape. An inspection cover 40 in the present embodiment is provided with an atmosphere opening hole 40h extending through the inspection cover 40 to allow the atmosphere outside a compressor 10 to communicate with the interior of the accommodation space R. sacrificial limb

[0109] A sacrificial member 20 includes a diaphragm plate 211 in the present embodiment. Diaphragm plate

[0110] The diaphragm plate 211 is disk-shaped and has a predetermined thickness. The diaphragm plate 211 has one surface 211a and another surface 211b facing away from the one surface 211a. The diaphragm plate 211 divides the receiving space R into two spaces.

[0111] That is, the diaphragm plate 211 divides the receiving space R into the following two spaces: a space located on the side of one surface 211a and a space located on the side of the other surface 211b, with the diaphragm plate 211 as a boundary. The diaphragm plate 211 is arranged in the receiving space R in a state where these two spaces are hermetically isolated from each other.

[0112] Specifically, the diaphragm plate 211 is fixed to the inner surface of the recess 120d. One of the two spaces defined by the diaphragm plate 211 (the space located on the side of one surface 211a) communicates with an exhaust flow path P2 via a connecting flow path 12p. The other of the two spaces defined by the diaphragm plate 211 (the space located on the side of the other surface 211b) is open to the atmosphere through the atmosphere opening hole 40h formed in the inspection cover 40.

[0113] For the sake of simplicity of description, of the two spaces defined by the diaphragm plate 211, the space communicating with the outlet flow path P2 is referred to below as the "first space R1." Of the two spaces defined by the diaphragm plate 211, the space open to the atmosphere is referred to as the "second space R2."

[0114] In the present embodiment, for example, the other surface 211b of the diaphragm plate 211 facing the second space R2 serves as the portion to be measured 21x. Since a compressed gas G is sucked through the connecting flow path 12p from the outlet flow path P2 to the first space R1, the first space R1 is in a higher pressure state than the second space R2 open to the atmosphere. That is, a differential pressure is generated between the first space R1 and the second space R2.

[0115] One surface 211a of the diaphragm plate 211 is convexly stressed toward the second space R2 in the first space R1 by the differential pressure. At the same time, the other surface 211b, as the section 21x to be measured, is pressed by the differential pressure in a direction in which one surface 211a is convex (toward the side of the second space R2) and is convexly stressed toward the second space R2. This means that during operation of the compressor 10, a compressive stress is generated in the section 21x to be measured of the diaphragm plate 211. Voltage tester

[0116] A voltage tester 30 in the present embodiment is attached (clamped) to a central portion of the surface 211b other than the portion 21x to be measured of the diaphragm plate 211. Operational impact

[0117] In the configuration described above, a portion of the gas G (H2) compressed during operation of the compressor 10 is sucked into the first space R1 of the receiving space R, and the diaphragm plate 211 of the sacrificial member 20 disposed in the receiving space R is exposed to the sucked gas G. The diaphragm plate 211 is stressed by absorbing the pressure of the gas G.

[0118] Thus, for example, by removing the sacrificial member 20 from the receiving space R while the compressor 10 is stopped, the amount of strain of the section 21x to be measured in the diaphragm plate 211 can be checked. In other words, it is possible to detect the amount of strain, which is an indicator of the degree of wear of the diaphragm plate 211, from the section 21x to be measured.

[0119] Since the pressure of the gas G acts on the diaphragm plate 211, it is possible to check how much stress has acted on the diaphragm plate 211. Consequently, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0120] In the configuration discussed above, the composition of a metal material constituting the diaphragm plate 211 is the same as the composition of a metal material constituting the impeller 111 of the rotor 11. Thus, for example, when the compressor 10 is stopped, by removing the sacrificial member 20 from the receiving space R and observing one surface 211a of the diaphragm plate 211, it is possible to check the degree of progression of embrittlement (hydrogen embrittlement) caused by the gas G on one surface 211a of the diaphragm plate 211, the presence or absence of a defect, and the like. In other words, it is possible to detect the degree of progression of embrittlement, which is an indicator of the degree of wear of the diaphragm plate 211, from one surface 211a of the diaphragm plate 211. Accordingly, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0121] In the configuration described above, the diaphragm plate 211 is pressed toward the second space R2 and bent by the differential pressure generated between the first space R1 and the second space R2. As a result, the section 21x to be measured is subjected to compressive stress. Thus, for example, the amount of strain caused by the compressive stress repeatedly generated in the diaphragm plate 211 during operation of the compressor 10, such as a daily start-and-stop (DSS) operation, can be detected with the stress detector 30. Accordingly, for example, compared with the configuration of the sacrificial member 20 described in the first embodiment, it is possible to detect not only the magnitude of the stress constantly generated in the rotor 11 during the rated operation of the compressor 10, but also a change in the magnitude of the stress repeatedly generated during start-and-stop operations of the compressor 10. As a result, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be better estimated.

[0122] In the configuration described above, the voltage tester 30 is arranged on the other surface 211b facing the second space R2 open to the atmosphere. Since the voltage tester 30 is not exposed to the gas G, the voltage tester 30 does not break apart due to the pressure of the gas G.

[0123] In the above-described configuration, the second space R2 is open to the atmosphere through the atmosphere opening hole 40h formed in the inspection cover 40. Therefore, for example, when the diaphragm plate 211 is damaged and, as a result, the first space R1 and the second space R2 communicate with each other, a situation in which the gas G excessively leaks from the accommodating space R to the outside of the compressor 10 at one time can be avoided, compared to a case where the compressor system 1 does not enclose the inspection cover 40. Accordingly, it is possible to prevent a pressure drop of the gas G flowing through the outlet flow path P2. Third embodiment

[0124] In the following, using Fig. 4, a third embodiment of a sacrificial member according to the present disclosure is described. In the following description of the third embodiment, common components with the first and second embodiments are denoted by the same reference numerals in the drawings, and explanations thereof will be omitted. The configuration of a sacrificial member described in the third embodiment is different from the configurations of the sacrificial members described in the first and second embodiments. sacrificial limb

[0125] A sacrificial member 20 in the present embodiment includes a piston ring portion 24, a fixed plate portion 25, and a rod portion 212. Piston ring section

[0126] The piston ring portion 24 is disc-shaped and has a predetermined thickness. The piston ring portion 24 has a first surface 24a and a second surface 24b facing away from the first surface 24a. The piston ring portion 24 divides a receiving space R into two spaces.

[0127] That is, the piston ring portion 24 divides the receiving space R into the following two spaces: a space located on the first surface 24a side and a space located on the second surface 24b side, with the piston ring portion 24 serving as a boundary. The piston ring portion 24 is disposed in the receiving space R in a state where these two spaces are hermetically isolated from each other.

[0128] Specifically, the piston ring portion 24 is arranged to be movable in a direction in which the receiving space R extends in a state of slidingly contacting the inner surface of a recess 120d. One of the two spaces defined by the piston ring portion 24 (the space located on the first surface 24a side) communicates with an exhaust flow path P2 via a communication flow path 12p. The other of the two spaces defined by the piston ring portion 24 (the space located on the second surface 24b side) is open to the atmosphere through an atmosphere opening hole 40h formed in an inspection cover 40.

[0129] For the sake of simplicity of description, of the two spaces defined by the piston ring portion 24, the space communicating with the exhaust flow path P2 is referred to below as the "first space R1." Of the two spaces defined by the piston ring portion 24, the space open to the atmosphere is referred to as the "second space R2."

[0130] Since a compressed gas G is sucked through the connecting flow path 12p from the outlet flow path P2 to the first space R1, the first space R1 is in a higher pressure state than the second space R2 open to the atmosphere. That is, a differential pressure is generated between the first space R1 and the second space R2. Fixed plate section

[0131] The fixed plate portion 25 is disc-shaped and has a predetermined thickness. The fixed plate portion 25 is arranged in the first space R1. The fixed plate portion 25 is immovably attached to the inner surface of the recess 120d.

[0132] The fixed plate portion 25 has a main surface 25a and a back surface 25b facing the first surface 24a of the piston ring portion 24 in a state facing in a direction away from the main surface 25a.

[0133] A plurality of communication holes 25h are formed in the fixed plate portion 25, extending from the main surface 25a to the rear surface 25b. The plurality of communication holes 25h are annular and arranged at equal intervals in a direction in which the main surface 25a and the rear surface 25b extend.

[0134] In the present embodiment, a case where four communication holes 25h are formed in the fixed plate portion 25 will be described as an example. The communication holes 25h allow a space on the first surface 24a side and a space on the second surface 24b side in the first space R1 to communicate with each other when the fixed plate portion 25 is taken as a boundary. Rod section

[0135] The rod portion 212 is formed in a cylindrical shape. One end of the rod portion 212 is fixed to a central portion of the rear surface 25b of the fixed plate portion 25. More specifically, one end of the rod portion 212 is fixed to a portion of the rear surface 25b on the inner side relative to the openings of the plurality of communication holes 25h. The other end of the rod portion 212 is fixed to a central portion of the first surface 24a of the piston ring portion 24.

[0136] That is, the rod portion 212 extends between the fixed plate portion 25 and the piston ring portion 24 in a state of connecting the fixed plate portion 25 and the piston ring portion 24. In the present embodiment, a side surface 212s of the rod portion 212 serves as a portion 21x to be measured.

[0137] The piston ring portion 24 moves such that a volume of the second space R2 is reduced by a differential pressure generated between the first space R1 and the second space R2. At the same time, the side surface 212s of the rod portion 212, as the portion 21x to be measured, is stressed to expand in the direction in which the rod portion 212 extends in response to the movement of the piston ring portion 24. This means that during operation of the compressor 10, a tensile stress is generated in the portion 21x to be measured. Voltage tester

[0138] A voltage tester 30 in the present embodiment is attached (clamped) to a center portion of the side surface 212s as the portion to be measured 21x of the rod portion 212. Operational impact

[0139] In the configuration described above, a part of the gas G (H2) compressed during operation of the compressor 10 is sucked into the first space R1 of the accommodation space R, and the sacrificial member 20 arranged in the accommodation space R is exposed to the sucked gas G. When the piston ring portion 24 of the sacrificial member 20 is pushed toward the second space R2 side by the gas G, the rod portion 212 of the sacrificial member 20 is stressed (pulled) in the direction in which the rod portion 212 extends.

[0140] For example, by removing the rod portion 212 from the receiving space R while the compressor 10 is stopped, the amount of elongation of the portion 21x to be measured in the rod portion 212 can be checked. In other words, it is possible to detect the amount of elongation, which is an indicator of the degree of wear of the rod portion 212, from the portion 21x to be measured.

[0141] This makes it possible to check how much stress was exerted on the rod portion 212 when the pressure of the gas G acted on the rod portion 212. Consequently, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0142] In the configuration discussed above, the composition of a metal material constituting the rod portion 212 is the same as the composition of a metal material constituting the impeller 111 of the rotor 11. Thus, for example, when the compressor 10 is stopped, by removing the rod portion 212 from the receiving space R and observing the side surface 212s of the rod portion 212, it is possible to check the degree of progression of embrittlement (hydrogen embrittlement) caused by the gas G on the side surface 212s of the rod portion 212, the presence or absence of a defect, and the like. In other words, it is possible to recognize the degree of progression of embrittlement, which is an indicator of the degree of wear of the rod portion 212, from the side surface 212s of the rod portion 212. Accordingly, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0143] In the configuration described above, compared to the configuration described in the first embodiment, the section to be measured 21x of the rod portion 212 is stressed due to the differential pressure generated between the first space R1 and the second space R2. At this time, the rod portion 212 expands and contracts due to a pressure change of the gas G flowing into the first space R1. As a result, the section to be measured 21x is stressed by tensile stress. Thus, for example, the amount of strain due to the tensile stress repeatedly generated in the rod portion 212 at the time of operation of the compressor 10, such as a daily start and stop (DSS) operation, can be detected with the tension tester 30.

[0144] In this case, during operation of the compressor 10, a tensile stress is generated in the rotor 11, accompanied by the action of centrifugal force. Therefore, according to the configuration described above, it is possible to test a change in the amount of strain while maintaining the same type of stress (tensile stress). As a result, the degree of wear of the rotor 11 (impeller 111) of the compressor 10 can be better estimated. Fourth embodiment

[0145] In the following, using Fig. 5 describes a fourth embodiment of a compressor system 1 according to the invention. In the following description of the fourth embodiment, common components with the first, second, and third embodiments are designated by the same reference numerals in the drawings, and explanations thereof will be omitted.

[0146] A gas G to be compressed by a compressor 10 in the present embodiment is not hydrogen gas (H2), but a corrosive gas. The gas G to be compressed by the compressor 10 in the present embodiment is, for example, hydrogen sulfide gas (H2S).

[0147] A receiving space R in the present embodiment is a space defined by an inner surface of a recess 120d formed to be recessed from an outer surface 120s of a housing 120. In other words, the receiving space R is open to the outer surface 120s of the housing 120. The receiving space R is arranged, for example, on a side Dal relative to an inlet flow path P1.

[0148] The receiving space R is connected to the inlet flow path P1 through a connecting flow path 12p formed in the housing 120. In other words, the receiving space R is connected (communicates with) the inlet flow path P1 via the connecting flow path 12p, through which the gas G flows before compression.

[0149] One end of the connecting flow path 12p of the present embodiment is open to the accommodation space R. The other end of the connecting flow path 12p is open to a casing inlet flow path 120a of the inlet flow path P1. Accordingly, a portion of the gas G flowing through the inlet flow path P1 before being compressed by a compression section is sucked into the accommodation space R through the connecting flow path 12p.

[0150] A sacrificial member 20 is arranged in the receiving space R. That is, when the compressor 10 is in operation, the sacrificial member 20 is exposed to the gas G before it is compressed by the compression section. In Fig. 5, the sacrificial member 20 has a square shape for ease of illustration, which is indicated by a dotted line.

[0151] Any of the sacrificial members 20 described in the first to third embodiments can be adopted as the sacrificial member 20 of the present embodiment. At this time, a voltage tester 30 is attached (clamped) to a portion 21x to be measured enclosed in the sacrificial member 20. Operational impact

[0152] In the configuration described above, a part of the gas G (H2S) is sucked into the receiving space R before being compressed during operation (rated operation) of the compressor 10, and the sacrificial member 20 arranged in the receiving space R is exposed to the sucked gas G. Once the sacrificial member 20 is exposed to the gas G, the portion 21x to be measured of the sacrificial member 20 is stressed by the pressure of the gas G. At the same time, since the composition of a metal material constituting the portion 21x to be measured is the same as the composition of a metal material constituting a rotor 11 of the compressor 10, the portion 21x to be measured is subjected to a corrosive action by the gas G in the same manner as the rotor 11 of the compressor 10.At this time, the section to be measured 21x is exposed to the gas G having a high concentration of corrosive components before compression, and thus the section to be measured 21x experiences a stronger corrosive effect from the gas G compared to a case where the section to be measured 21x is exposed to, for example, the gas G during compression or the gas G after compression. That is, it is possible to check the condition of the section to be measured 21x that has deteriorated under severe stress corrosion cracking conditions compared to the environment of a compression flow path 111p in which the rotor 11 rotates while being exposed to the gas G. Thus, the degree of wear of the rotor 11 of the compressor 10 can be better estimated. Fifth embodiment

[0153] In the following, using Fig. 6 and Fig. 7, a fifth embodiment of a compressor system 1 according to the invention is described. In the following description of the fifth embodiment, common components with the first, second, and third embodiments are designated by the same reference numerals in the drawings, and explanations thereof will be omitted. The configuration of a sacrificial member in the fifth embodiment differs from the configurations of the sacrificial members described in the first, second, and third embodiments.

[0154] The compressor system 1 in the fifth embodiment does not include a voltage detector 30. A gas G to be compressed by a compressor 10 in the present embodiment is, for example, a hydrogen gas (H2).

[0155] An accommodating space R in the present embodiment is a space defined by an inner surface of a recess 120d formed to be recessed from an inner surface of a receiving recessed portion 121r accommodating an impeller 111e of the rearmost stage of a diaphragm 121 to the other side Dar.

[0156] In other words, the accommodation space R is open to the inner surface of the accommodation recessed portion 121r configured to accommodate the rearmost stage impeller 111e, and is connected to a compression flow path 111p of the rearmost stage impeller 111e. The recess 120d is annular and surrounds a rotor shaft 110 of a rotor 11. That is, the accommodation space R is formed as an annular space surrounding the rotor shaft 110 of the rotor 11. sacrificial limb

[0157] As in Fig. 7, a sacrificial member 20 of the present embodiment includes a columnar portion 213. Columnar section

[0158] The columnar portion 213 is formed in a columnar shape and is integrally fixed to a disc 111a of the rearmost stage impeller 111e of the rotor 11. The columnar portion 213 extends from the disc 111a toward the other side Dar. That is, the columnar portion 213 orbits an axis Ar in the accommodation space R, and the rotation of the rearmost stage impeller 111e accompanies the operation of the compressor 10.

[0159] The columnar portion 213 has a recessed portion 213a that is recessed while being narrowed from its outer surface. The recessed portion 213a is located at a central portion in a direction in which the columnar portion 213 extends (axial direction Da). At the recessed portion 213a, a cross-sectional area of ​​the columnar portion 213 in a direction perpendicular to the direction in which the columnar portion 213 extends is smaller than a cross-sectional area at the portion other than the recessed portion 213a.

[0160] More specifically, in the depressed portion 213a, a cross-sectional area is gradually reduced from a starting portion located at the leftmost side on one side Dal toward the other side Dar, and a cross-sectional area is gradually reduced from a starting portion located at the rightmost side on the other side Dar toward the one side Dal, and then the cross-sectional areas are merged.

[0161] In this case, a sight hole 12h is formed in a stator 12, extending from the receiving space R to an outer surface 120s of a housing 120 and open to the outer surface 120s of the housing 120. Specifically, one end of the sight hole 12h is open to the inner surface of the recess 120d, and the other end of the sight hole 12h is open to the outer surface 120s of the housing 120. The sight hole 12h is formed as a through hole through the diaphragm 121 and the housing 120. Inspection cover

[0162] An inspection cover 40 is a cover member that hermetically isolates the receiving space R from the atmosphere by closing an opening 12h' of the inspection hole 12h in the outer surface 120s of the housing 120. The inspection cover 40 can be attached to and removed from the outer surface 120s of the housing 120.

[0163] More specifically, the inspection cover 40 can be attached to and detached from the outer surface 120s of the housing 120 by a fastening member B, such as a bolt. That is, the inspection cover 40 closes the opening 12h' of the inspection hole 12h in the outer surface 120s of the housing 120 by being attached to the outer surface 120s of the housing 120 with the fastening member B, and exposes the opening 12h' of the inspection hole 12h by being removed when the fastening member B is loosened.

[0164] The inspection cover 40 is attached to the outer surface 120s of the housing 120 during operation of the compressor 10. The inspection cover 40 is removed from the outer surface 120s of the housing 120 when the condition of the columnar portion 213 is to be inspected, for example, by an operator, a maintenance technician, or the like of the compressor 10. When the inspection cover 40 is removed from the outer surface 120s of the housing 120, the operator, the maintenance technician, or the like of the compressor 10 inspects the outer surface of the columnar portion 213, the condition of the recessed portion 213a, and the like using, for example, an industrial endoscope Bs (borescope). Operational impact

[0165] In the configuration described above, a part of the gas G (H2) compressed during operation (rated operation) of the compressor 10 is sucked into the receiving space R, and the columnar portion 213 disposed in the receiving space R is exposed to the sucked gas G. At the same time, the columnar portion 213 orbits the axis Ar in the receiving space R, which is formed as an annular space surrounding the rotor shaft 110, and the rotation of the impeller 111e of the rearmost stage of the rotor 11 is accompanied. The columnar portion 213 receives the pressure of the gas G while orbiting the axis Ar, thereby engaging the depressed portion 213a as the portion 21x to be measured of the columnar portion 213. Accordingly, the columnar portion 213 can more accurately simulate the stress acting on the rotor 11 than the configurations described in the above embodiments.

[0166] In the above configuration, the stator 12 is provided with the inspection hole 12h through which the columnar portion 213 arranged in the receiving space R can be accessed from outside the compressor 10, for example, using an industrial endoscope Bs. Furthermore, the inspection cover 40, which can be attached to and detached from the outer surface 120s of the housing 120, closes the opening 12h' of the inspection hole 12h in the outer surface 120s of the housing 120. This eliminates the need to disassemble the compressor 10, for example, when checking the condition of the columnar portion 213. Therefore, the condition of the worn columnar portion 213 can be easily checked. Sixth embodiment

[0167] In the following, using Fig. 8 describes a sixth embodiment of a compressor system 1 according to the invention. In the following description of the sixth embodiment, common components with the fifth embodiment are provided with the same reference numerals in the drawings, and explanations thereof are omitted.

[0168] A receiving space R in the present embodiment is a space defined by an inner surface of a recess 120d formed to be recessed from an opposite surface 121s of a diaphragm 121 in the radial direction toward an outside.

[0169] That is, the receiving space R is open to a space of a gap between the diaphragm 121 and a rotor shaft 110 of a rotor 11. The receiving space R is located on the other side Dar relative to a second sealing portion 14b. The recess 120d is annular and surrounds the rotor shaft 110 of the rotor 11. That is, the receiving space R is formed as an annular space surrounding the rotor shaft 110 of the rotor 11. sacrificial limb

[0170] A sacrificial member 20 of the present embodiment includes a columnar portion 213. Columnar section

[0171] The columnar portion 213 is formed in a columnar shape and is integrally fixed to the rotor shaft 110 of the rotor 11. The columnar portion 213 extends radially outward from an outer surface 110s of the rotor shaft 110. That is, the columnar portion 213 orbits an axis Ar during operation of the compressor 10, accompanying the rotation of the rotor shaft 110.

[0172] The columnar portion 213 has a recessed portion 213a that is recessed while being narrowed from its outer surface. The recessed portion 213a is located at a central portion in a direction in which the columnar portion 213 extends (radial direction). At the recessed portion 213a, a cross-sectional area of ​​the columnar portion 213 in a direction perpendicular to the direction in which the columnar portion 213 extends is smaller than a cross-sectional area at the portion other than the recessed portion 213a.

[0173] More specifically, at the recessed portion 213a, a cross-sectional area is gradually reduced from a starting portion at the innermost side toward the outer side in the radial direction, and a cross-sectional area is gradually reduced from a starting portion at the outermost side toward the inner side in the radial direction, and then the cross-sectional areas are merged. Operational impact

[0174] The same operational effects as the configuration described in the fifth embodiment can be achieved.

[0175] In the configuration described above, the columnar portion 213 is fixed to the rotor shaft 110 in a state extending in the radial direction. Thus, the direction of action of the centrifugal force caused by the rotation of the rotor 11 coincides with the direction of the tensile stress acting on the columnar section 213. Therefore, the columnar portion 213 can more accurately simulate the stress acting on the rotor 11 compared to the configuration described in the fifth embodiment. Seventh embodiment

[0176] In the following, using Fig. 9 describes a seventh embodiment of a compressor system 1 according to the invention. In the following description of the seventh embodiment, common components with the fifth embodiment are designated by the same reference numerals in the drawings, and explanations thereof are omitted.

[0177] A gas G to be compressed by a compressor 10 in the present embodiment is not hydrogen gas (H2), but a corrosive gas. The gas G to be compressed by the compressor 10 in the present embodiment is, for example, hydrogen sulfide gas (H2S).

[0178] An accommodating space R in the present embodiment is a space defined by an inner surface of a recess 120d formed to be recessed toward a Dal side from an inner surface of a receiving recessed portion 121r accommodating an impeller 111f of the frontmost stage of a diaphragm 121.

[0179] In other words, the accommodation space R is open to the inner surface of the accommodation recessed portion 121r configured to accommodate the front-stage impeller 111f, and is connected to a compression flow path 111p of the front-stage impeller 111f. The recess 120d is annular and surrounds a rotor shaft 110 of a rotor 11. That is, the accommodation space R is formed as an annular space surrounding the rotor shaft 110 of the rotor 11. sacrificial limb

[0180] A sacrificial member 20 of the present embodiment includes a columnar portion 213. Columnar section

[0181] The columnar portion 213 is formed in a columnar shape and is integrally fixed to a cover 111c of the front-stage impeller 111f of the rotor 11. The columnar portion 213 extends from the cover 111c toward one side Dal. That is, the columnar portion 213 orbits an axis Ar in the accommodation space R and accompanies the rotation of the front-stage impeller 111f during operation of the compressor 10.

[0182] The columnar portion 213 has a recessed portion 213a that is recessed while being narrowed from its outer surface. The recessed portion 213a is located at a central portion in a direction in which the columnar portion 213 extends (axial direction Da). At the recessed portion 213a, a cross-sectional area of ​​the columnar portion 213 in a direction perpendicular to the direction in which the columnar portion 213 extends is smaller than a cross-sectional area at the portion other than the recessed portion 213a.

[0183] More specifically, in the depressed portion 213a, a cross-sectional area is gradually reduced from a starting portion located at the leftmost side on one side Dal toward the other side Dar, and a cross-sectional area is gradually reduced from a starting portion located at the rightmost side on the other side Dar toward the one side Dal, and then the cross-sectional areas are merged. Operational impact

[0184] In the configuration described above, a part of the gas G (H2S) compressed by the front-stage impeller 111f during operation (rated operation) of the compressor 10 is sucked into the receiving space R, and the columnar portion 213 disposed in the receiving space R is exposed to the sucked gas G. Similar to the rotor 11 of the compressor 10, the columnar portion 213 is subjected to a corrosive action by the gas G. At this time, since the columnar portion 213 is exposed to the gas G compressed in the compression flow path 111p of the impeller 111f of the foremost stage, the columnar portion 213 receives a stronger corrosive action from the gas G compared to a case where it is exposed to the gas G compressed by the impeller 111 in a stage subsequent to the foremost stage of the impeller 111f.At the same time, the columnar portion 213 orbits the axis Ar in the receiving space R, which is formed as an annular space surrounding the rotor shaft 110, and the rotation of the front-stage impeller 111f of the rotor 11 accompanies this rotation. The columnar portion 213 receives the pressure of the gas G while orbiting the axis Ar, thereby stressing the recessed portion 213a as a portion 21x to be measured. Accordingly, compared with the configuration described in the fourth embodiment, the stress corrosion cracking conditions of the rotor 11 can be more accurately simulated. Other embodiment

[0185] Embodiments of the present disclosure have been described above in detail with reference to the drawings. However, specific configurations are not limited to the configurations of the above embodiments. Any configuration may be added, omitted, replaced, or otherwise changed without departing from the spirit of the present disclosure.

[0186] The receiving space R for receiving the sacrificial member 20 described in the above embodiments does not have to be formed in the stator 12. For example, the compressor system 1, as shown in Fig. 10, further include an inspection chamber 50 in which a receiving space R is defined. The inspection chamber 50 is fixed, for example, to an outer surface 120s of a housing 120. The inspection chamber 50 has, for example, the shape of a tube with one end open. The above-described inspection cover 40 is attached to the inspection chamber 50 so as to close the opening of the inspection chamber 50. In this case, the inspection cover 40 is attachable to and detachable from the inspection chamber 50. In this case, the accommodation space R within the inspection chamber 50 communicates with an outlet flow path P2 through a connecting flow path 12p formed in the stator 12. The accommodation space R within the inspection chamber 50 can communicate with an inlet flow path P1 through the connecting flow path 12p. This makes it unnecessary to form the accommodation space R in the stator 12. Therefore, it is possible to avoid a reduction in the degree of freedom in the design of the stator 12 when arranging the accommodation space R.

[0187] In addition, the compressor system 1, as for example in Fig.11, further include an introduction pipe 60 configured to connect a receiving space R within an inspection chamber 50 and the inside of an outlet pipe 200, and to guide a part of a gas G flowing in the outlet pipe 200 into the inspection chamber 50. At this time, it is desirable that a flow path length L between an introduction port as a connecting portion between the introduction pipe 60 and the outlet pipe 200 and a connecting portion between a second flow path 121b and a compression flow path 111p of a rearmost stage impeller 111e (a starting portion of the second flow path 121b) be equal to or less than 10 m, for example, in terms of the pressure loss of the gas G. The introduction port of the introduction pipe 60 is not limited to being connected to the outlet pipe 200, and may be connected to an outlet nozzle 123.That is, the introduction pipe 60 can introduce the compressed gas G flowing through an outlet flow path 123a of the outlet nozzle 123 into the inspection chamber 50.

[0188] Each of the nut portions 23 described in the first embodiment may be disposed within the C-ring portion 210 in the direction in which the bolt portion 22 extends when screwed to the bolt portion 22, and may apply such a pressure to the C-ring portion 210 that one end 210a and the other end 210b of the C-ring portion 210 are separated from each other.

[0189] The gas G to be compressed by the compressors 10 described in the first, second, third, fifth, and sixth embodiments is not limited to hydrogen gas (H2). The corrosive gas G to be compressed by the compressors 10 described in the fourth and seventh embodiments is not limited to hydrogen sulfide gas (H2S).

[0190] The other end of the connecting flow path 12p described in the first to third embodiments is not limited to the case where it is connected to the casing outlet flow path 120b, and may be connected to, for example, the exhaust flow path 123a or the second flow path 121b. The other end of the connecting flow path 12p described in the fourth embodiment is not limited to the case where it is connected to the casing inlet flow path 120a, and may be connected to, for example, the suction flow path 122a or the first flow path 121a. The other end of the connecting flow path 12p is not limited to the case where it is connected to the inlet flow path P1 and the outlet flow path P2, and may be connected to, for example, the intermediate flow path 121c.In this case, the intermediate flow path 121c can be used as an outlet flow path, and the gas G can be sucked into the accommodation space R through the connecting flow path 12p. Furthermore, in a case where, for example, a flow path to which the gas G is directly supplied is formed in the intermediate flow path 121c, this flow path can be used as an inlet flow path, and the gas G can be sucked into the accommodation space R through the connecting flow path 12p.

[0191] The compressor systems 1 described in the first to fourth embodiments do not necessarily include the voltage tester 30.

[0192] For example, a plurality of tension testers 30 described in the first to fourth embodiments may be attached to the section 21x to be measured. Thus, even if one of the tension testers 30 breaks, the strain amount of the section 21x to be measured can be measured by the other tension testers 30.

[0193] The voltage detectors 30 described in the second embodiment and the third embodiment are not necessarily attached to the central portion of the portion to be measured 21x.

[0194] The receiving spaces R described in the second and third embodiments are not limited to a cylindrical shape, but may also have a quadrangular prism shape, for example. In this case, the diaphragm plate 211 described in the second embodiment and the piston ring portion 24 and fixed plate portion 25 described in the third embodiment may be formed in a flat plate shape (rectangular plate shape).

[0195] A plurality of the columnar portions 213 described in the first embodiment and the fifth to seventh embodiments may be arranged in the accommodating space R. For example, in a case where a plurality of the sacrificial members 20 described in the fifth embodiment to the seventh embodiment are arranged in the accommodating space R, the plurality of sacrificial members 20 are attached to the rotor 11 so as to be arranged at equal intervals in the circumferential direction Dc of the rotor shaft 110. Thus, for example, the condition of each section 21x to be measured can be checked by removing the sacrificial members 20 one at a time or by removing the sacrificial members 20 each time after a predetermined period of time. Accordingly, it is possible to detect the change over time and the age-related wear of the section 21x to be measured, and consequently, to detect the change and age-related wear of the rotor 11 over time according to the length of the period.

[0196] The accommodation spaces described in the first to third embodiments need not be open to the outer surface 120s of the housing 120. In this case, the inspection hole 12h extending from the accommodation space R to the outer surface 120s of the housing 120 and open to the outer surface 120s of the housing 120 is formed in the stator 12, and the inspection cover 40 attachable to and detachable from the outer surface 120s of the housing 120 closes the inspection hole 12h to hermetically isolate the accommodation space R from the atmosphere. In this case, the accommodation space R is not limited to being formed in the housing 120, but may also be formed, for example, in the diaphragm 121. This makes it unnecessary to disassemble the compressor 10, for example when checking the condition of the section 21x to be measured in the sacrificial element 20.

[0197] In the second embodiment discussed above, the other surface 211b of the diaphragm plate 211 serves as the portion 21x to be measured, but the disclosure is not limited to this. For example, one surface 211a of the diaphragm plate 211 may serve as the portion 21x to be measured. Accordingly, at least a portion of the diaphragm plate 211 serves as the portion 21x to be measured.

[0198] For example, the compressor systems 1 described in the second and third embodiments do not necessarily include the inspection cover 40.

[0199] The second space R2 described in the second embodiment and the third embodiment is not necessarily open to the atmosphere. For example, the second space R2 may be sealed in an airtight, externally insulated state with a gas maintained at a lower pressure than the first space R1.

[0200] For example, the columnar portion 213 described in the fifth and seventh embodiments may be attached to the impeller 111 in a state where it is slightly inclined with respect to the horizontal plane. The columnar portion 213 described in the sixth embodiment may be attached to the rotor shaft 110 in a state where it is slightly inclined with respect to a virtual plane perpendicular to the axis Ar.

[0201] The recessed portion 213a of the columnar portion 213 described in the fifth embodiment and the seventh embodiment does not need to be arranged in the central portion in the direction in which the columnar portion 213 extends.

[0202] The compressor systems 1 described in the fifth to seventh embodiments may further include, for example, a contact prevention mechanism that prevents a broken piece from coming into contact with the rotor 11 when the columnar portion 213 is broken at a position of the recessed portion 213a that accompanies the rotation of the rotor 11. The contact prevention mechanism is arranged in the accommodation space R, for example, so as not to interfere with the columnar portion 213.

[0203] Furthermore, a plurality of the receiving spaces R described in the first to seventh embodiments may be formed in the stator 12. In this case, each receiving space R can accommodate the sacrificial member 20.

[0204] The portion 21x to be measured described in the first to seventh embodiments is not necessarily made of a metal material having the same composition as the metal material constituting the rotor 11, and the portion 21x to be measured may be made of a metal material different from the metal material of the rotor 11. In this case, examples of the other metal material include a metal material newly applied to the rotor 11 and a metal material of a member other than the rotor 11 (for example, the stator 12).

[0205] Each of the compressors 10 according to the first to seventh embodiments is not limited to a single-shaft multi-stage centrifugal compressor (multi-stage centrifugal compressor), and may be, for example, a single-shaft single-stage centrifugal compressor (single-stage centrifugal compressor).

[0206] Each of the configurations of the compressor systems 1 described in the first to seventh embodiments is not limited to an independent configuration. The compressor system 1 can be configured by appropriately combining the components described in each embodiment. Additional information

[0207] The compressor system described in each embodiment can be understood, for example, as follows.

[0208] (1) A compressor system 1 according to a first aspect includes: a compressor 10 provided with a rotor 11 and a stator 12 that forms a flow path for a fluid (gas G) to be compressed by covering the rotor 11; and a sacrificial member 20 disposed in an accommodation space R and in communication with the flow path, the sacrificial member 20 including a portion to be measured 21x disposed in the accommodation space R and stressed by a pressure of the fluid.

[0209] Thus, for example, by removing the sacrificial member 20 from the receiving space R while the compressor 10 is stopped, the amount of expansion of the section 21x to be measured can be checked. Furthermore, by observing the section 21x to be measured, for example, it is possible to check the degree of wear of the section 21x to be measured caused by the fluid, the presence or absence of a defect, and the like.

[0210] (2) A compressor system 1 according to a second aspect may be the compressor system 1 according to the first embodiment, wherein the portion to be measured 21x may be formed of a metal material having a composition identical to a composition of a metal material constituting the rotor 11.

[0211] (3) A compressor system 1 according to a third aspect may be the compressor system 1 according to the first or second aspect, wherein the fluid may be a hydrogen gas and the accommodation space R may be connected to an outlet flow path.

[0212] (4) A compressor system 1 according to a fourth aspect may be the compressor system 1 according to the third aspect, wherein the outlet flow path P2 in the flow path may be a flow path through which the compressed fluid having the highest pressure flows.

[0213] Thus, the section 21x of the sacrificial member 20 to be measured experiences a higher pressure, for example due to the hydrogen gas, than in a case where hydrogen gas is sucked into the receiving space R before compression or hydrogen gas during compression.

[0214] This means that it is possible to check the condition of the section 21x to be measured, which has deteriorated under more severe embrittlement conditions.

[0215] (5) A compressor system 1 according to a fifth aspect may be the compressor system 1 according to the first or second aspect, wherein the fluid may be a corrosive gas and the receiving space R may be connected to an inlet flow path.

[0216] (6) A compressor system 1 according to a sixth aspect may be the compressor system 1 according to the fifth aspect, wherein the inlet flow path in the flow path may be a flow path through which the fluid having the lowest pressure before compression flows.

[0217] Thus, the section 21x to be measured experiences a greater corrosive effect from the fluid, for example, compared to a case where the section 21x to be measured of the sacrificial member 20 is exposed to the corrosive gas during or after compression. This makes it possible to inspect the condition of the section 21x to be measured that has deteriorated under more severe stress corrosion cracking conditions.

[0218] (7) A compressor system 1 according to a seventh aspect may be the compressor system 1 according to any one of the first to sixth aspects, wherein the accommodation space R may be open at an outwardly facing outer surface 120s of the stator 12, and the compressor system 1 may further include an inspection cover 40 attachable to and detachable from the stator 12 and closing an opening of the accommodation space R.

[0219] Thus, the sacrificial member 20 can be removed from the receiving space R by removing the inspection cover 40. By closing the inspection cover 40, the receiving space R can be hermetically sealed from the outside. Accordingly, it is not necessary to disassemble the compressor 10 when, for example, the sacrificial member 20 is removed from the receiving space R.

[0220] (8) A compressor system 1 according to an eighth aspect may be the compressor system 1 according to any one of the first to seventh aspects, wherein the compressor system 1 may further include a tension detector 30 attached to the portion 21x to be measured and capable of detecting a strain amount of the portion 21x to be measured.

[0221] This allows, for example, a signal indicating the amount of strain detected by the tension tester 30 to be transmitted to the outside of the compressor 10. Therefore, for example, it is possible to monitor a change in the amount of strain of the portion 21x to be measured over time during the operation of the compressor 10 from the outside of the compressor 10.

[0222] (9) A compressor system 1 according to a ninth aspect may be the compressor system 1 according to any one of the first to eighth aspects, wherein the sacrificial member 20 may include a C-ring portion 210 that is convexly curved, arranged in a C-shape, and has a plate shape, and a pressing and holding portion 21 that holds the C-ring portion 210 with both ends (one end 210a and the other end 210b) pressed together to be close to each other; the convex portion of the C-ring portion 210 may be the portion 21x to be measured, and the pressing and holding portion 21 may press the C-ring portion 210 to apply a higher stress to the portion 21x to be measured than a maximum stress acting on the rotor 11 during the rated operation of the compressor 10 with the portion 21x to be measured interposed therebetween.

[0223] This allows the above action to be performed with greater accuracy. Furthermore, it is possible to inspect the condition of the C-ring portion 210, which has deteriorated under conditions more severe than the flow path environment in which the rotor 11 rotates while exposed to fluid. Thus, the degree of wear of the rotor 11 of the compressor 10 can be better assessed.

[0224] (10) A compressor system 1 according to a tenth aspect may be the compressor system 1 according to any one of the first to eighth aspects, wherein the sacrificial member 20 may include a diaphragm plate 211 configured to divide the accommodation space R into a first space R1 in communication with the flow path and a second space R2 open to the atmosphere, and at least a part of the diaphragm plate 211 may be the portion to be measured 21x.

[0225] This allows the above action to be achieved with higher accuracy. Since the measured portion 21x of the diaphragm plate 211 is subjected to, for example, a differential pressure generated between the first space R1 and the second space R2, the amount of stress generated in the diaphragm plate 211 caused by a compressive stress at the time of operation, such as a momentary start-up and stop of the compressor 10, can be detected.

[0226] (11) A compressor system 1 according to an eleventh aspect may be the compressor system 1 according to any one of the first to eighth aspects, wherein the sacrificial member 20 may include a piston ring portion 24 configured to divide the accommodation space R into a first space R1 communicating with the flow path and a second space R2 open to the atmosphere, a fixed plate portion 25 immovably disposed in the first space R1, and a rod portion 212 formed in a columnar shape and connecting the piston ring portion 24 and the fixed plate portion 25, and at least a part of the rod portion 212 may be the portion to be measured 21x.

[0227] This allows the above action to be achieved with greater accuracy. Furthermore, it is possible to verify a change in the amount of strain of the section 21x to be measured in the rod section 212 by applying the same stress mode (tensile stress) as the stress generated in the rotor 11. This allows for a better assessment of the degree of wear of the rotor 11 of the compressor 10.

[0228] (12) A compressor system 1 according to a twelfth aspect may be the compressor system 1 according to the first or second aspect, wherein the accommodation space R in the stator 12 may be formed in an annular shape and surrounds a rotor shaft 110 of the rotor 11, the sacrificial member 20 may include a columnar portion 213 fixed to the rotor 11, and the columnar portion 213 may include, as the portion to be measured 21x, a depressed portion 213a which is depressed while being constricted from an outer surface of the columnar portion 213.

[0229] At this time, the columnar portion 213 disposed in the receiving space R orbits an axis Ar in the receiving space R while being exposed to the fluid accompanying the rotation of the rotor 11. The columnar portion 213 receives the pressure of the fluid while orbiting the axis Ar, thereby engaging the depressed portion 213a as the portion 21x to be measured of the columnar portion 213. Therefore, the columnar portion 213 can more accurately simulate the stress acting on the rotor 11 compared to the configuration described above.

[0230] (13) A compressor system 1 according to a thirteenth aspect may be the compressor system 1 according to the twelfth aspect, wherein the fluid may be a hydrogen gas, the rotor 11 may include a plurality of stages of impellers 111 rotatably mounted on the rotor shaft 110 and configured to compress the fluid in a state of being arranged in a direction in which the rotor shaft 110 extends, and the accommodation space R may be connected to a compression flow path 111p of a rearmost stage impeller (rearmost stage impeller 111e) among the plurality of stages of the impellers 111.

[0231] At this time, for example, the columnar portion 213 receives a higher pressure from the hydrogen gas than in a case where it is connected to the compression flow path 111p of the impeller 111 at a stage before the rearmost stage of the impeller 111. That is, it is possible to check the condition of the columnar portion 213, which has deteriorated under more severe embrittlement conditions.

[0232] (14) A compressor system 1 according to a fourteenth aspect may be the compressor system 1 according to the twelfth aspect, wherein the fluid may be a corrosive gas, the rotor 11 may include a plurality of stages of impellers 111 rotatably mounted on the rotor shaft 110 and configured to compress the fluid in a state of being arranged in a direction in which the rotor shaft 110 extends, and the accommodation space R may be connected to a compression flow path 111p of a front-stage impeller (front-stage impeller 111f) among the plurality of stages of impellers 111.

[0233] For example, the columnar portion 213 experiences a stronger corrosive action from the corrosive gas than in a case where it is connected to the compression flow path 111p of the impeller 111 at one stage after the frontmost stage of the impeller 111. That is, it is possible to check the condition of the columnar portion 213, which has deteriorated under severe stress corrosion cracking conditions.

[0234] (15) A compressor system 1 according to a fifteenth aspect may be the compressor system 1 according to any one of the first to fourteenth aspects, wherein a sight hole 12h is formed in the stator 12, which extends from the accommodation space R to the outer surface 120s of the stator 12 and is open to the outer surface 120s of the stator 12, and the compressor system 1 may further include an inspection cover 40 attachable to and detachable from the outer surface 120s of the stator 12 and closes an opening 12h' of the sight hole 12h.

[0235] By removing the inspection cover 40 from the outer surface 120s of the stator 12 and inserting, for example, an industrial endoscope into the inspection hole 12h, it is possible to check the condition of the section 21x to be measured in the sacrificial member 20. In other words, there is no need to disassemble the compressor 10 when checking the condition of the section 21x to be measured. Industrial applicability

[0236] The present disclosure relates to compressor systems capable of detecting wear, defects, and the like in a wider variety of modes. List of reference symbols 1 compressor system 10 Compressor 11 Rotor 12 Stator 12h viewing hole 12 h' opening 12p connecting flow path 13 storage section 14 Sealing section 14a First sealing section 14b Second sealing section 20 sacrificial link 21 Pressing and holding section 21x Section to be measured 22 Bolt section 23 Nut section 24 Piston ring section 24a First surface 24b Second surface 25 Fixed plate section 25a Main surface 25b Back surface 25h connection hole 30 voltage testers 40 Inspection cover 40h atmosphere opening hole 50 Inspection chamber 60 insertion tube 60a insertion hole 100 intake manifold 110 Rotor shaft 110s exterior surface 111 Wheel 111a disc 111b Blade 111c Cover 111e Rear stage wheel 111f Front stage impeller 111p compression flow path 120 housings 120a Housing inlet flow path 120b Housing outlet flow path 120d deepening 120i interior surface 120s outer surface 121 Diaphragm 121a First flow path 121b Second flow path 121c Intermediate flow path 121d Diffuser flow path 121e Return path 121r Receiving recessed section 121s Opposite surface 122 Inlet nozzle 122a Intake flow path 123 Outlet nozzle 123a Exhaust flow path 130 radial bearings 131 thrust bearings 132 Pressure ring 200 outlet pipe 210 C-Ring section 210a An End 210b The other end 211 Diaphragm plate 211a A surface 211b The other surface 212 rod section 212s side surface 213 Columnar section 213a In-depth section Ar axis B Fastening link Bs industrial endoscope Since axial direction Dal One Page Dar The other side Dc circumferential direction Dr direction of rotation G gap L Flow path length P1 Inlet flow path P2 Outlet flow path R Recording room R1 First Room R2 Second Room QUOTES CONTAINED IN THE DESCRIPTION

[0000] This list of documents submitted by the applicant was generated automatically and is included solely for the convenience of the reader. This list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions. Cited patent literature

[0000] JP 2022

[0001] JP 156117

[0001] JP 2019-82165 A

[0004]

Claims

[1] Compressor system comprising: a compressor provided with a rotor and a stator which form a flow path for a fluid to be compressed by covering the rotor; and a sacrificial member arranged in a receiving space in communication with the flow path, wherein the sacrificial member includes a section to be measured, which is arranged in the receiving space and is subjected to pressure from the fluid. [2] The compressor system according to claim 1, wherein the portion to be measured is formed of a metal material having a composition identical to a composition of a metal material constituting the rotor. [3] A compressor system according to claim 1 or 2, wherein the fluid is a hydrogen gas, and the receiving space is connected to an outlet flow path. [4] The compressor system according to claim 3, wherein the outlet flow path in the flow path is a flow path through which the compressed fluid flows at the highest pressure. [5] A compressor system according to claim 1 or 2, wherein the fluid is a corrosive gas, and the receiving space is connected to an inlet flow path. [6] A compressor system according to claim 5, wherein the inlet flow path in the flow path is a flow path through which the fluid having the lowest pressure before compression flows. [7] Compressor system according to claim 1 or 2, wherein the receiving space is open on an outward-facing outer surface of the stator, and the compressor system further includes an inspection cover attachable to and detachable from the stator and closing an opening of the receiving space. [8] Compressor system according to claim 1 or 2, further comprising: a tension detector attached to the section to be measured and configured to detect a strain amount of the section to be measured. [9] Compressor system 1 according to claim 1 or 2, wherein the sacrificial limb includes a plate-like C-ring section which is convexly curved, arranged in a C-shape and has a plate shape and has a pressing and holding section that holds the C-ring section, whereby both ends of the C-ring section are pressed together so that that they are close to each other, the convex section of the C-ring section is the section to be measured, and the pressing and holding section compresses the C-ring section to apply a higher stress to the section to be measured than a maximum stress acting on the rotor during rated operation of the compressor with the section to be measured being interposed therebetween. [10] Compressor system according to claim 1 or 2, wherein the sacrificial member includes a diaphragm plate configured to divide the receiving space into a first space in communication with the flow path and a second space open to the atmosphere, and at least part of the diaphragm plate is the section to be measured. [11] Compressor system according to claim 1 or 2, wherein the sacrificial limb a piston ring portion configured to divide the receiving space into a first space communicating with the flow path and a second space open to the atmosphere, a fixed plate portion immovably disposed in the first space, and a rod portion which is columnar and connects the piston ring portion and the fixed plate portion, and at least part of the bar section is the section to be measured. [12] Compressor system according to claim 1 or 2, wherein the receiving space in the stator is ring-shaped and surrounds a rotor shaft of the rotor, the sacrificial member includes a columnar portion attached to the rotor, and the columnar portion includes, as the portion to be measured, a depressed portion which is depressed while being constricted by an outer surface of the columnar portion. [13] Compressor system according to claim 12, wherein the fluid is a hydrogen gas, the rotor includes a plurality of stages of impellers rotatably mounted on the rotor shaft and configured to compress the fluid while being arranged in a direction in which the rotor shaft extends, and the receiving space is connected to a compression flow path of an impeller of the rearmost stage among the plurality of stages of impellers. [14] Compressor system according to claim 12, wherein the fluid is a corrosive gas, the rotor includes a plurality of stages of impellers rotatably mounted on the rotor shaft and configured to compress the fluid in a state in which they are arranged in one direction, in which the rotor shaft extends, and the receiving space is connected to a compression flow path of an impeller of the foremost stage among the plurality of impeller stages. [15] Compressor system according to claim 12, wherein a sight hole extending from the receiving space to an outer surface of the stator and open to the outer surface of the stator is formed in the stator, and the compressor system further includes an inspection cover attachable to and removable from the outer surface of the stator and closing an opening of the inspection hole.

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