Compressor system

Abstract

To provide a compressor system that can detect deteriorations and defects in more various modes.SOLUTION: A compressor system comprises: a compressor comprising a rotor, and a stator for forming a flow passage for fluid to be compressed by covering the rotor; and a sacrifice member arranged in a housing space communicating with the flow passage. The sacrifice member comprises a measurement object part arranged in the housing space, and to be distorted by a change in pressure of the fluid.SELECTED DRAWING: Figure 2

Description

Technical Field

[0001] The present disclosure relates to a compressor system.

Background Art

[0002] In the field of turbomachinery such as centrifugal compressors, the materials forming the rotor and stator may deteriorate when exposed to the working fluid. Examples of such deterioration of the material include embrittlement and corrosion caused by the components of the working fluid.

[0003] For example, Patent Document 1 discloses a method of monitoring while measuring the degree of erosion and corrosion of a material by arranging a multi-electrode composite sensor (CMAS) probe capable of detecting an increase in electrical resistance over time inside a compressor so as to be exposed to the working fluid.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] By the way, in the rotor of a high-speed rotating compressor, stress due to centrifugal force acts, and the stress acting is larger than that of the stator. Therefore, deterioration such as embrittlement and corrosion progresses more easily in the rotor than in the stator. Therefore, in the rotor, this stress may combine with corrosion to cause defects such as stress corrosion cracking. Therefore, a technique capable of detecting more diverse modes of deterioration and defects is required.

[0006] The present disclosure has been made to solve the above problems, and an object thereof is to provide a compressor system capable of detecting more diverse modes of deterioration and defects.

Means for Solving the Problems

[0007] To solve the above problems, the compressor system according to this disclosure comprises a compressor having a rotor and a stator that covers the rotor and forms a flow path for the fluid to be compressed, and a sacrificial member arranged in a containment space communicating with the flow path, The stator has a casing that constitutes the outer shell of the compressor, and the casing has a connecting channel formed therein that is connected to an outlet channel through which the fluid, after being compressed in the flow path, flows, and the containment space is formed in the casing, communicates with the connecting channel and is located on the axial end side of the outlet channel, The sacrificial member is placed in the containment space and has a measurement target portion that is deformed by changes in the fluid pressure. Furthermore, the compressor system according to this disclosure comprises a compressor having a rotor and a stator that covers the rotor and forms a flow path for the fluid to be compressed, and a sacrificial member disposed in a housing space communicating with the flow path, wherein the sacrificial member is disposed in the housing space and has a portion to be measured that is deformed by the pressure of the fluid, the housing space is formed in the stator in an annular shape surrounding the rotation axis of the rotor, and the sacrificial member has a columnar portion fixed to the rotor, the columnar portion has a recess that is indented from the outer surface so as to be the portion to be measured. [Effects of the Invention]

[0008] This disclosure provides a compressor system capable of detecting a wider variety of degradation and defects. [Brief explanation of the drawing]

[0009] [Figure 1] This figure shows a schematic configuration of a compressor system according to the first to third embodiments of this disclosure. [Figure 2] This is an enlarged view of the main part of Figure 1, and is a diagram illustrating the configuration of the sacrificial member according to the first embodiment of this disclosure. [Figure 3] This is an enlarged view of the main part of Figure 1, and is a diagram for illustrating the configuration of the sacrificial member according to the second embodiment of this disclosure. [Figure 4] This is an enlarged view of the main part of Figure 1, and is a diagram for illustrating the configuration of the sacrificial member according to the third embodiment of this disclosure. [Figure 5] This figure shows a schematic configuration of a compressor system according to the fourth embodiment of this disclosure. [Figure 6] This figure shows a schematic configuration of a compressor system according to the fifth embodiment of this disclosure. [Figure 7] This is an enlarged view of the main part of Figure 6, and is a diagram illustrating the configuration of the sacrificial member and inspection cover according to the fifth embodiment of this disclosure. [Figure 8] This diagram illustrates the configuration of the sacrificial member and inspection cover according to the sixth embodiment of this disclosure, and corresponds to the portion shown in Figure 7. [Figure 9]This is a diagram for explaining the configuration of a sacrificial member and an inspection lid according to the seventh embodiment of the present disclosure. [Figure 10] This is a diagram showing a schematic configuration of a compressor system according to other embodiments of the present disclosure. [Figure 11] This is a diagram showing a schematic configuration of a compressor system according to other embodiments of the present disclosure.

Embodiments for Carrying Out the Invention

[0010] Hereinafter, embodiments for implementing a compressor system according to the present disclosure will be described with reference to the accompanying drawings.

[0011] <First Embodiment> [Compressor System] The compressor system is a system for detecting deterioration and defects of a compressor operating in a plant. The compressor system in the present embodiment detects deterioration and defects of the rotor of the compressor.

[0012] As shown in FIG. 1, the compressor system 1 includes a compressor 10, a sacrificial member 20, a strain gauge 30, and an inspection lid 40.

[0013] (Compressor) The compressor 10 is disposed, for example, inside a building such as in a chemical plant. The compressor 10 is disposed in the atmospheric environment inside this 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 shown) disposed in the chemical plant.

[0014] The compressor 10 in the present embodiment is a single-shaft multi-stage centrifugal compressor (multi-stage centrifugal compressor) that compresses hydrogen gas (H2) as a process gas. Hereinafter, for convenience of explanation, the process gas to be compressed by the compressor 10 is simply referred to as "gas G".

[0015] The compressor 10 includes a rotor 11, a stator 12, a bearing portion 13, and a seal portion 14.

[0016] (Rotor) The rotor 11 is a part of the compressor 10 that rotates when the compressor 10 is driven. The rotor 11 has a rotating shaft 110 and an impeller 111.

[0017] The rotating shaft 110 is formed in a columnar shape centered on a virtual axis Ar extending in one direction along the horizontal direction. In the present embodiment, for convenience of explanation, the direction in which this axis Ar extends is referred to as the "axial direction Da". Also, of the two sides of the axial direction Da, one side (the left side in FIG. 1) is simply referred to as "one side Dal", and the opposite side (the right side in FIG. 1) is referred to as "the other side Dar".

[0018] Also, the circumferential direction of the rotating shaft 110 extending around the axis Ar is simply referred to as the "circumferential direction Dc". Further, the direction perpendicular to the axis Ar is referred to as the "radial direction". The rotating shaft 110 in the present embodiment is formed of, for example, a metal material.

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

[0020] Hereinafter, for convenience of explanation, the impeller 111 arranged on the most one side Dal among the plurality of impellers 111 is referred to as the "frontmost impeller 111f", and the impeller 111 arranged on the most other side Dar among the plurality of impellers 111 is referred to as the "rearmost impeller 111e". <于 <于

[0021] <于 Each stage of the impeller 111 compresses the gas G flowing into the inside of the impeller 111 from one side Dal and pumps it radially outward by using the centrifugal force generated by rotating around the axis Ar together with the rotating shaft 110. Therefore, each stage of the impeller 111 is exposed to the gas G. <于 <于

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

[0023] When the disk 111a is attached to the rotating shaft 110, it is formed in a cylindrical shape that gradually expands from the axis Ar toward the other side Dar. Therefore, the disk 111a has a side surface (not shown in the figure) that faces toward the other side Dar toward the one side Dar. Furthermore, the disk 111a is integrally fixed to the rotating shaft 110 by the inner circumferential surface (not shown in the figure) of the disk 111a fitting into the outer circumferential surface 110s of the rotating shaft 110.

[0024] The blades 111b are formed integrally with the aforementioned side surface of the disk 111a. Multiple blades 111b are arranged at equal intervals in the circumferential direction Dc. The blades 111b are, for example, widened in a twisting manner in the rotational direction Dr of the rotation axis 110 as they move toward the other side Dar.

[0025] In this embodiment, the rotation direction Dr of the rotating shaft 110 is the direction in which the rotating shaft 110 rotates clockwise when viewed from one side Dal.

[0026] The cover 111c faces the disk 111a from one side Daal, sandwiching the blade 111b in the axial direction Da along with the disk 111a. The cover 111c is formed in a cylindrical shape that gradually widens towards the other side Daal.

[0027] The cover 111c is formed integrally with the blade 111b. Because the cover 111c is formed integrally with the blade 111b, a compression channel 111p is defined between the cover 111c and the disk 111a, through which the gas G is compressed by the blade 111b.

[0028] (Stator) The stator 12 is a part of the compressor 10 that is stationary when the compressor 10 is driven. The stator 12 covers the rotor 11 from the radial outside.

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

[0030] The casing 120 is the outer shell of the compressor 10 and houses various devices that make up the compressor 10. In this embodiment, the casing 120 is formed in a cylindrical shape with both ends closed while extending in the axial direction Da. The outer surface 120s of the casing 120 that faces the outside of the compressor 10 is exposed to the atmosphere. The casing 120 is formed of a metal material, for example.

[0031] The casing 120 has a casing inlet channel 120a for gas G to flow in from the outside to the inside of the casing 120, and a casing outlet channel 120b for gas G to flow out from the inside to the outside of the casing 120.

[0032] These casing inlet channel 120a and casing outlet channel 120b are formed to penetrate the outer wall of the casing 120. Furthermore, the casing inlet channel 120a and casing outlet channel 120b are spaced apart from each other in the axial direction Da. Specifically, the casing inlet channel 120a is located one side Daal of the casing outlet channel 120b.

[0033] The diaphragm 121 is positioned to cover the rotor 11's impeller 111 from the radial outside, and to cover the rotating shaft 110 from the outer circumference, leaving a gap between the rotating shaft 110 and its outer surface 110s. The diaphragm 121 is formed in a cylindrical shape extending around the axis Ar.

[0034] The diaphragm 121 is housed in the casing 120 and is fixed integrally with the casing 120 to the inner surface 120i of the casing 120. The diaphragm 121 is fixed to the inner surface 120i of the casing 120 by fastening members (not shown), such as bolts. The diaphragm 121 is formed of, for example, a metallic material.

[0035] The diaphragm 121 has an inner surface 121s that faces the outer surface 110s of the rotating shaft 110. The diaphragm 121 also has a recess 121r that extends radially outward from this opposing surface 121s and accommodates the impeller 111 inside. The number of recesses 121r is the same as the number of impellers 111 and is arranged in the axial direction Da.

[0036] The diaphragm 121 has multiple passages through which gas G flows. Specifically, the diaphragm 121 has a first passage 121a for introducing (inhaling) gas G into the compression passage 111p of the foremost impeller 111f, a second passage 121b for releasing (discharging) gas G from the compression passage 111p of the last stage impeller 111e, and multiple intermediate passages 121c that connect the compression passages 111p of adjacent impellers 111 between the first passage 121a and the second passage 121b.

[0037] The first channel 121a is the channel located on the furthest side Dal among the multiple channels formed in the diaphragm 121. The first channel 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 inside (radially inside) of the casing 120. The first flow path 121a is also connected to the compression flow path 111p of the foremost impeller 111f from one side Dal.

[0039] The second channel 121b is the channel located furthest to the other side Dar among the multiple channels formed in the diaphragm 121. The second channel 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 last stage impeller 111e from the other side, Dar. The second flow path 121b is also connected to the casing outlet flow path 120b from the inside (radially inside) of the casing 120.

[0041] Multiple intermediate passages 121c are arranged in the axial direction Da with a gap between them between the first passage 121a and the second passage 121b. Each intermediate passage 121c is a passage that guides the gas G compressed in the compression passage 111p of the impeller 111 located on one side Da to the compression passage 111p of the next stage impeller 111 located on the other side Da.

[0042] In this embodiment, the intermediate channel 121c is composed of a diffuser channel 121d and a return channel 121e.

[0043] The diffuser flow path 121d is a flow path that guides the gas G compressed in the compression flow path 111p of the impellers 111, excluding the last stage impeller 111e, to the radially outward direction. One end of the diffuser flow path 121d opens to the inner surface of the housing recess 121r. The opening of one end of the diffuser flow path 121d is positioned so as to radially face the outlet of the compression flow path 111p of the impeller 111.

[0044] The return channel 121e is connected to the opposite end of the diffuser channel 121d, and guides the gas G that has flowed through the diffuser channel 121d radially inward, and also guides this gas G to the compression channel 111p of the next stage impeller 111.

[0045] Therefore, in the gas flow path 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, which consists of the diffuser flow path 121d and the return flow path 121e, alternately repeat. For the sake of explanation, the gas flow path of the impeller 111, which is composed of the compression flow path 111p and the intermediate flow path 121c, will be referred to as the "compression section."

[0046] Furthermore, some of the compressed gas G, which is released as the impeller 111 rotates, flows into the gap between the inner surface of the housing recess 121r and the disk 111a of the impeller 111, and into the gap between the inner surface of the housing recess 121r and the cover 111c of the impeller 111. Therefore, these gaps are in communication with the compression passage 111p of the impeller 111.

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

[0048] An intake passage 122a is formed inside the inlet nozzle 122. For example, gas G that has flowed through the intake piping 100, which is connected to the inlet nozzle 122 and connects the inlet nozzle 122 to a device (not shown) such as a gas supply source outside the compressor 10, flows into this intake passage 122a.

[0049] The intake passage 122a is connected to the casing inlet passage 120a formed in the casing 120 from the outside of the casing 120 (radially outward). Therefore, the gas G flowing through the intake pipe 100 flows into the first passage 121a through the intake passage 122a and the casing inlet passage 120a.

[0050] In this embodiment, the first passage 121a of the diaphragm 121, the casing inlet passage 120a of the casing 120, and the suction passage 122a of the inlet nozzle 122 constitute the inlet passage P1 through which the gas G before compression flows. The inlet passage P1 is the passage through which the gas G with the lowest pressure before being compressed by the compression section flows among the gas G passages in the compressor 10.

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

[0052] A discharge channel 123a is formed inside the outlet nozzle 123. This discharge channel 123a is connected to a casing outlet channel 120b formed in the casing 120 from the outside of the casing 120 (outside in the radial direction). Therefore, compressed gas G flows into the discharge channel 123a through the casing outlet channel 120b, as well as through the second channel 121b formed in the diaphragm 121.

[0053] Furthermore, a discharge pipe 200 is connected to the discharge channel 123a, which connects the outlet nozzle 123 to a device outside the compressor 10. Therefore, the gas G flowing through the discharge channel 123a flows away (is discharged) through this discharge pipe 200 towards the device outside the compressor 10.

[0054] In this 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 outlet nozzle 123 constitute the outlet flow path P2 through which the compressed gas G flows. The outlet flow path P2 is the flow path through which the gas G with the highest pressure, compressed by the compression section, flows among the gas G flow paths in the compressor 10.

[0055] (bearing part) The bearing section 13 is housed in the casing 120. In this embodiment, the bearing section 13 includes a radial bearing 130, a thrust bearing 131, and a thrust collar 132.

[0056] The radial bearings 130 rotatably support the rotating shaft 110 of the rotor 11. The radial bearings 130 are arranged, for example, in pairs spaced apart from each other in the axial direction Da. The pair of radial bearings 130 are arranged so as to sandwich the diaphragm 121 between them in the axial direction Da.

[0057] The thrust bearing 131 suppresses the displacement of the rotor shaft 110 in the axial direction Da due to the compression of gas G by the impeller 111. The thrust bearing 131 suppresses the displacement of the rotor shaft 110 in the axial direction Da by pressing a flange-shaped thrust collar 132, which is integrally attached to the rotor shaft 110, while supporting it in the axial direction Da.

[0058] Specifically, these thrust bearings 131 and thrust collars 132 are arranged, for example, in pairs, spaced apart from each other in the axial direction Da. Furthermore, each pair of thrust bearings 131 and thrust collars is positioned between the diaphragm 121 and the radial bearing 130.

[0059] One of the pair of thrust bearings 131, the thrust bearing 131 located on one side Dal, supports the thrust collar 132 located on one side Dal of the pair of thrust collars 132 by pressing it from one side Dal.

[0060] On the other hand, the thrust bearing 131 located on the other side Dar of the pair of thrust bearings 131 supports the thrust collar 132 located on the other side Dar of the pair of thrust collars 132 by pressing it from the other side Dar.

[0061] (Seal part) The seal portion 14 prevents air from flowing into the compression section through the gap between the rotating shaft 110 of the rotor 11 and the diaphragm 121 of the stator 12. The seal portion 14 is positioned between the rotating shaft 110 and the diaphragm 121. For example, the seal portion 14 is positioned to sandwich a plurality of impellers 111, each pair of which are aligned in the axial direction Da.

[0062] One of the pair of seal portions 14, the seal portion 14 located on one side Dal, prevents air from flowing from the one side Dal into the compression passage 111p of the foremost impeller 111f through the gap between the rotating shaft 110 and the diaphragm 121.

[0063] On the other hand, the seal portion 14 located on the other side Dar of the pair of seal portions 14 prevents air from flowing from the other side Dar into the compression passage 111p of the last stage impeller 111e through the gap between the rotating shaft 110 and the diaphragm 121.

[0064] For the sake of explanation, the seal portion 14 located on one side of the pair of seal portions 14, Dalf, will be referred to as the "first seal portion 14a," and the seal portion 14 located on the other side of the pair of seal portions 14, Dalf, will be referred to as the "second seal portion 14b."

[0065] Although detailed illustrations are omitted, the seal portion 14 (first seal portion 14a and second seal portion 14b) in this embodiment is a labyrinth seal composed of multiple rotor-side fins formed to extend radially outward in a flange shape from the outer peripheral surface 110s of the rotating shaft 110, and multiple stator-side fins formed to extend radially inward in a flange shape from the opposing surface 121s of the diaphragm 121, which are alternately arranged in the axial direction Da. For example, a portion of the compressed gas G flowing through the discharge pipe 200 is supplied to the seal portion 14 as a sealing gas.

[0066] Although detailed illustrations are omitted, a portion of the compressed gas G flowing through the discharge pipe 200 is supplied, for example, from the other side Dar toward the second seal portion 14b.

[0067] As a result, compressed gas G flows through the gap between the outer circumferential surface 110s of the rotating shaft 110 and the opposing surface 121s of the diaphragm 121, on one side Dal of the first seal portion 14a and on the other side Dar of the second seal portion 14b. Therefore, the space in the gap between the diaphragm 121 and the rotating shaft 110 is maintained under high pressure.

[0068] The following describes an example of the flow of gas G compressed by the compressor 10.

[0069] The rotating shaft 110, supported by the bearing section 13, is rotated at a predetermined rotational speed in the rotational direction Dr by a drive source (not shown), such as an electric motor. As the rotating shaft 110 rotates, the impeller 111, which is integrated with the rotating shaft 110, rotates at high speed together with the rotating shaft 110.

[0070] Gas G supplied to the compressor 10 from a gas supply source located outside the compressor 10 via the intake pipe 100 is drawn into the casing 120 through the inlet nozzle 122 as the rotor 11 rotates. The gas G that flows into the first passage 121a of the diaphragm 121 through the intake passage 122a of the inlet nozzle 122 and the casing inlet passage 120a of the casing 120 is compressed by the blades 111b rotating in the compression passage 111p of the subsequent front-stage impeller 111f. In other words, the uncompressed gas G flowing through the intake pipe 100 toward the compressor 10 is guided through the inlet passage P1 of the compressor 10 (intake passage 122a, casing inlet passage 120a, and first passage 121a) to the compression passage 111p of the front-stage impeller 111f.

[0071] The gas G compressed in the compression channel 111p of the foremost impeller 111f is guided through the subsequent diffuser channel 121d and return channel 121e to the compression channel 111p of the next impeller 111, where it is further compressed. The gas G compressed in the compression channel 111p of the impeller 111 flows through the subsequent intermediate channel 121c (diffuser channel 121d and return channel 121e) and is further compressed in the next impeller 111, repeating this step until it reaches the compression channel 111p of the last impeller 111e.

[0072] The gas G compressed in the compression passage 111p of the last stage impeller 111e is discharged into the second passage 121b of the subsequent diaphragm 121, and also flows into the discharge piping 200 through the casing outlet passage 120b of the casing 120 and the discharge passage 123a of the outlet nozzle 123. In other words, the gas G after being compressed through the compression passage 111p of the last stage impeller 111e is guided into the discharge piping 200 through the outlet passage P2 of the compressor 10 (second passage 121b, casing outlet passage 120b, and discharge passage 123a). The gas G that flows into the discharge piping 200 is introduced, for example, into a reaction apparatus (not shown) located outside the compressor 10 and used as a reaction fluid.

[0073] In summary, the uncompressed gas G drawn into the compressor 10 from the intake pipe 100 is guided through the inlet passage P1 (intake passage 122a, casing inlet passage 120a, and first passage 121a) to the compression passage 111p of the foremost impeller 111f in the compression section. The gas G guided into the compression passage 111p of the foremost impeller 111f is compressed in this compression section, which consists of the compression passages 111p of the multiple stages of the impeller 111 and the intermediate passages 121c connecting these compression passages 111p, until it reaches a predetermined high-pressure state over multiple stages. The compressed gas G, compressed by the compression section, is discharged into the discharge piping 200 through the outlet passage P2 (second passage 121b, casing outlet passage 120b, and discharge passage 123a) from the compression passage 111p of the last stage impeller 111e in the compression section.

[0074] (Sacrificial member) The sacrificial member 20 is a component that can simulate the stress acting on the rotor 11 of the driven compressor 10, and the changes and deterioration of the rotor 11 over time due to exposure of the rotor 11 to gas G as the working fluid.

[0075] In this embodiment, the sacrificial member 20 is used, for example, to determine whether the compressor 10 needs inspection and repair, and to determine the timing and frequency of such inspection and repair.

[0076] Here, as shown in Figure 1, the casing 120 of the stator 12 of the compressor 10 described above has a housing space R for housing the sacrificial member 20. In this embodiment, the housing space R is a space defined by the inner surface of a recess 120d formed to recess from the outer surface 120s of the casing 120. That is, the housing space R opens to the outer surface 120s of the casing 120. In this embodiment, the housing space R is located, for example, on the other side Dar of the outlet flow path P2.

[0077] The containment space R is connected to the outlet channel P2 by a connecting channel 12p formed in the casing 120. In other words, the containment space R is connected to (in communication with) the outlet channel P2 through which the gas G with the highest pressure after compression flows, via the connecting channel 12p.

[0078] One end of the connecting channel 12p opens into the containment space R. The other end of the connecting channel 12p opens into the casing outlet channel 120b in the outlet channel P2. Therefore, a portion of the gas G that flows through the outlet channel P2 after being compressed by the compression section is drawn out into the containment space R through this connecting channel 12p.

[0079] The sacrificial member 20 is located in this containment space R. That is, when the compressor 10 is in operation, the sacrificial member 20 is exposed to the gas G after it has been compressed by the compression section. In Figure 1, for illustrative purposes, the sacrificial member 20 is shown as a dotted rectangle. The configuration and shape of the sacrificial member 20 will be explained in detail using Figure 2.

[0080] As shown in Figure 2, the sacrificial member 20 in this embodiment has a C-ring portion 210 and a pressing and holding portion 21.

[0081] (C-ring section) The C-ring portion 210 is made of a metal material having the same composition as the metal material forming the rotor 11 of the compressor 10. In this embodiment, the C-ring portion 210 is made of a metal material having the same composition as the metal material forming the impeller 111 of the rotor 11. In this context, "identical composition" means, for example, that the material is the same as the material used to manufacture rotor 11.

[0082] The C-ring portion 210 has a measurement target area 21x that is deformed by the pressure of the gas G drawn out from the outlet flow path P2.

[0083] The C-ring portion 210 is a plate-shaped member that is curved to form a convex shape and arranged in a C-shape. In this embodiment, the convex portion of the C-ring portion 210 is the measurement target portion 21x. As described above, the C-ring portion 210 is arranged in a C-shape, forming one end 210a and the other end 210b that are close to each other. Hereinafter, the one end 210a and the other end 210b of the C-ring portion 210 may be collectively referred to as "both ends".

[0084] (Pressure-holding part) The pressing and holding portion 21 holds the C-ring portion 210 in a state where both ends (one end 210a and the other end 210b) are pressed together so that they are close to each other. The pressing and holding portion 21 is composed of a bolt portion 22 and a pair of nut portions 23.

[0085] The bolt portion 22 is formed in a columnar shape, and the nut portion 23 can be screwed onto it. The bolt portion 22 passes through both the portion near one end 210a and the portion near the other end 210b of the C-ring portion 210. For the bolt portion 22, for example, a stud bolt, which is a bolt without a head, can be used.

[0086] The pair of nut portions 23 are screwed onto the bolt portion 22, with the C-ring portion 210 sandwiched between them. By screwing the pair of nut portions 23 onto the bolt portion 22, the C-ring portion 210 is held in a state of being pressed against it in a direction that sandwiches the C-ring portion 210 between them.

[0087] Specifically, each of the pair of nut portions 23 is positioned on the outside of the C-ring portion 210 in the direction in which the bolt portion 22 extends, and is screwed onto the bolt portion 22, applying pressure to the C-ring portion 210 such that one end 210a and the other end 210b are brought closer together.

[0088] In this case, the pair of nuts 23 apply a stress to the C-ring portion 210 that is higher than the maximum stress acting on the rotor 11 during the rated operation of the compressor 10, with the C-ring portion 210 sandwiched between them. In this embodiment, the pair of nuts 23 apply a stress to the C-ring portion 210 that is higher than the maximum stress acting on the impeller 111 during the rated operation of the compressor 10. In other words, the tightening torque of the pair of nuts 23 is set so that a stress higher than the maximum stress acting on the impeller 111 of the rotor 11 during the rated operation of the compressor 10 is applied to the measurement target portion 21x of the C-ring portion 210.

[0089] In this context, "maximum stress" refers to the maximum magnitude of the stress acting on the last stage impeller 111e during the rated operation of the compressor 10. Furthermore, the magnitude and direction of the stresses acting on the impeller 111 of the rotor 11, as well as their distribution, are known in advance, for example, through finite element method analysis (FEM analysis).

[0090] The area surrounding the measurement target 21x, including the measurement target 21x, is pulled towards one end 210a and the other end 210b, with the measurement target 21x as the pivot point, due to the pressure applied by the pair of nut portions 23 to the C-ring portion 210. In other words, tensile stress is generated in the measurement target 21x.

[0091] (Strain gauge) The strain gauge 30 is a sensor that detects the amount of strain at the measurement target area 21x. The strain gauge 30 is attached (adhered) to the measurement target area 21x of the C-ring portion 210. The strain gauge 30 is electrically connected to, for example, a monitoring device (not shown) located outside the compressor 10.

[0092] The strain gauge 30 detects the amount of strain at the measurement target area 21x and transmits a signal indicating this amount of strain to the monitoring device. This allows the monitoring device to monitor the amount of strain over time at the measurement target area 21x of the C-ring portion 210, for example.

[0093] (Inspection cover) The inspection cover 40 is a cover member that closes the opening of the recess 120d formed in the casing 120, thereby closing the storage space R. The inspection cover 40 is detachable from the outer surface 120s of the casing 120. Specifically, the inspection cover 40 is detachable from the outer surface 120s of the casing 120 by fastening members B such as bolts.

[0094] In other words, the inspection cover 40 closes the opening of the housing space R by being fixed to the outer surface 120s of the casing 120 by the fastening member B, and opens the housing space R when the fastening member B is loosened and the inspection cover 40 is removed. The inspection cover 40 is made of, for example, a metal material.

[0095] The inspection cover 40 is attached to the outer surface 120s of the casing 120 when the compressor 10 is in operation. By being attached to the outer surface 120s of the casing 120, the inspection cover 40 hermetically isolates the containment space R from the atmosphere. The inspection cover 40 is also removed from the outer surface 120s of the casing 120 when the sacrificial member 20 is removed from the containment space R by the compressor 10 operator or repairer. This allows the compressor 10 operator or repairer to remove and observe the sacrificial member 20 from outside the compressor 10.

[0096] (Effects / Actions) In the above configuration, while the compressor 10 is operating (during rated operation), a portion of the compressed gas G(H2) is drawn out into the containment space R, and the sacrificial member 20, which is placed in the containment space R, is exposed to this drawn-out gas G. As the sacrificial member 20 is exposed to the gas G, the C-ring portion 210 of the sacrificial member 20 is deformed by the pressure of the gas G. This allows, for example, the amount of strain at the measurement target area 21x in the C-ring portion 210 to be checked by removing the sacrificial member 20 from the housing space R when the operation of the compressor 10 is stopped. In other words, the amount of strain, which is an indicator of the degree of deterioration of the C-ring portion 210, can be detected from the measurement target area 21x. The components constituting the compressor 10 are not only subject to deterioration such as corrosion due to the properties of the gas G, but are also greatly affected by deterioration due to the pressure received when they are exposed to high-pressure gas G while rotating, like the rotor 11. In contrast, the sacrificial member 20 is strained by the pressure of the gas G, so the effect of deterioration due to the pressure of the gas G can be detected, as well as the properties of the gas G. Therefore, as pressure from the gas G acts on the C-ring portion 210, it is possible to determine how much stress is acting on the C-ring portion 210. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0097] Furthermore, in the above configuration, the C-ring portion 210 is made of the same metal material as the metal material that forms the impeller 111 of the rotor 11. This allows, for example, when the compressor 10 is stopped, the sacrificial member 20 to be removed from the containment space R, and the surface of the C-ring portion 210 to be observed, thereby confirming the progress of embrittlement (hydrogen embrittlement) that has occurred on the surface of the C-ring portion 210 due to gas G, as well as the presence or absence of defects. In other words, the progress of embrittlement, which is one indicator of the deterioration of the C-ring portion 210, can be detected from the surface of the C-ring portion 210. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0098] In summary, by placing the sacrificial member 20 in the containment space R connected to the fluid flow path compressed by the compressor 10, it becomes possible to detect more potential deterioration and defects in the rotor 11 (impeller 111) of the compressor 10 compared to using a sacrificial member that does not have a measurement target, or a sacrificial member that has a measurement target that is not made of the same metal material as the metal material forming the rotor 11.

[0099] Furthermore, in the above configuration, the containment space R in which the sacrificial member 20 is housed is connected to the outlet passage P2 through which the gas G with the highest pressure after being compressed by the compression section flows. This allows greater pressure to be applied to the C-ring portion 210 from the gas G compared to when the gas G is drawn into the containment space R before or during compression. In other words, it is possible to check the condition of the deteriorated C-ring portion 210 under more severe embrittlement conditions. In particular, when hydrogen gas is used as the process gas, components exposed to the hydrogen gas are strongly affected by hydrogen embrittlement. Hydrogen embrittlement is more likely to occur as the applied pressure increases. Therefore, by placing a sacrificial member 20 in the containment space R connected to the outlet channel P2 through which the gas G with the highest pressure flows, the component in the compressor 10 that is most affected by hydrogen embrittlement can be simulated with high accuracy by the sacrificial member 20. Therefore, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated more accurately.

[0100] Furthermore, in the above configuration, the convex portion of the C-ring portion 210 is designated as the measurement target area 21x, which is deformed by the pressure of the gas G. In addition, the bolt portion 22 penetrates the portion of the C-ring portion 210 near one end 210a and the portion near the other end 210b, and the pair of nuts 23 screwed onto the bolt portion 22 apply a stress to the C-ring portion 210 that is higher than the maximum stress generated in the rotor 11 (impeller 111), in a direction that sandwiches the C-ring portion 210 between them. As a result, during the operation of the compressor 10 (during rated operation), a stress higher than the maximum stress acting on the rotor 11 is constantly acting on the C-ring portion 210. Therefore, it is possible to check the condition of the deteriorated C-ring portion 210 under more severe embrittlement conditions than those in the environment of the compression passage 111p where the rotor 11 rotates while being exposed to gas G. Therefore, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated more accurately.

[0101] Furthermore, in the above configuration, a housing space R in which the sacrificial member 20 is housed is formed in the stator 12 (casing 120) of the compressor 10. This eliminates the need to add components to the compressor 10, such as those used to define the containment space R. Therefore, it is possible to suppress an increase in the number of parts in the compressor 10.

[0102] Furthermore, in the above configuration, a strain gauge 30 is attached to the measurement target area 21x. This makes it possible, for example, to transmit a signal indicating the amount of strain detected by the strain gauge 30 to the outside of the compressor 10, and to monitor the change in the amount of strain at the measurement target part 21x in the C-ring section 210 over time from outside the compressor 10 while the compressor 10 is in operation. Therefore, based on the amount of strain at the measurement target portion 21x of the C-ring portion 210 detected by the strain gauge 30, the rotor 11 of the compressor 10 can be inspected and repaired at the appropriate timing.

[0103] Furthermore, in the above configuration, the opening of the housing space R on the outer surface 120s of the casing 120 is closed by a removable inspection cover 40. This allows the sacrificial member 20 to be removed from the containment space R by removing the inspection cover 40. Furthermore, the containment space R can be airtightly isolated from the atmosphere by closing the inspection cover 40. Therefore, when removing the sacrificial member 20 from the containment space R, it is not necessary to disassemble, for example, the compressor 10. Therefore, the condition of the deteriorated C-ring portion 210 can be easily checked.

[0104] <Second Embodiment> Next, a second embodiment of the sacrificial member according to this disclosure will be described with reference to Figure 3. In the second embodiment described below, components common to the first embodiment described above are denoted by the same reference numerals in the figure, and their descriptions are omitted. In the second embodiment, the configuration of the sacrificial member differs from the configuration of the sacrificial member described in the first embodiment described above.

[0105] In this embodiment, the containment space R is formed as a cylindrical space. That is, the recess 120d is formed to recess in a circular cross-section from the outer surface 120s of the casing 120. In addition, the inspection cover 40 in this embodiment has an atmospheric vent hole 40h that penetrates through to connect the atmosphere outside the compressor 10 with the inside of the containment space R.

[0106] (Sacrificial member) In this embodiment, the sacrificial member 20 has a diaphragm plate 211.

[0107] (Diaphragm plate) The diaphragm plate 211 is formed in a disc shape with a predetermined thickness. The diaphragm plate 211 has one surface 211a and another surface 211b facing the opposite direction from the surface 211a. The diaphragm plate 211 divides the housing space R into two spaces.

[0108] In other words, the diaphragm plate 211 divides the housing space R into two parts: a space located on one side 211a and a space located on the other side 211b. Furthermore, the diaphragm plate 211 is positioned in the housing space R in a state where these two spaces are airtightly isolated from each other.

[0109] Specifically, the diaphragm plate 211 is fixed to the inner surface of the recess 120d. One of the two spaces partitioned by the diaphragm plate 211 (the space located on the side of one surface 211a) is in communication with the outlet channel P2 through the connecting channel 12p. The other of the two spaces partitioned by the diaphragm plate 211 (the space located on the side of the other surface 211b) is open to the atmosphere through the atmospheric vent hole 40h formed in the inspection cover 40.

[0110] For the sake of explanation, the space connected to the outlet channel P2 of the two spaces partitioned by the diaphragm plate 211 will be referred to as the "first space R1". The space open to the atmosphere of the two spaces partitioned by the diaphragm plate 211 will be referred to as the "second space R2".

[0111] In this embodiment, for example, the other surface 211b of the diaphragm plate 211 facing the second space R2 is designated as the measurement target area 21x. The first space R1 becomes high-pressure compared to the second space R2, which is open to the atmosphere, as compressed gas G is drawn into the first space R1 from the outlet channel P2 through the connecting channel 12p. That is, a differential pressure is generated between the first space R1 and the second space R2.

[0112] One surface 211a of the diaphragm plate 211 is strained by this differential pressure so that it becomes convex toward the second space R2 within the first space R1. At the same time, the other surface 211b, which is the measurement target area 21x, is pushed out in the direction that the surface 211a becomes convex (towards the second space R2) due to the differential pressure, and is strained so that it becomes convex toward the second space R2. In other words, compressive stress is generated in the measurement target area 21x of the diaphragm plate 211 when the compressor 10 is in operation.

[0113] (Strain gauge) In this embodiment, the strain gauge 30 is attached (adhered) to the central portion of the other surface 211b of the diaphragm plate 211, which is the measurement target area 21x.

[0114] (Effects / Actions) In the above configuration, while the compressor 10 is operating, a portion of the compressed gas G(H2) is drawn out into the first space R1 of the containment space R, and the diaphragm plate 211 of the sacrificial member 20, which is located in the containment space R, is exposed to this drawn-out gas G. The diaphragm plate 211 is deformed by the pressure of the gas G. This allows, for example, the amount of strain at the measurement target area 21x on the diaphragm plate 211 to be checked by removing the sacrificial member 20 from the housing space R when the compressor 10 is stopped. In other words, the amount of strain, which is an indicator of the degree of deterioration of the diaphragm plate 211, can be detected from the measurement target area 21x. Therefore, as pressure from the gas G acts on the diaphragm plate 211, it is possible to determine how much stress is acting on the diaphragm plate 211. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0115] Furthermore, in the above configuration, the diaphragm plate 211 is made of a metal material having the same composition as the metal material that forms the impeller 111 of the rotor 11. This allows, for example, when the compressor 10 is stopped, the sacrificial member 20 to be removed from the containment space R, and one surface 211a of the diaphragm plate 211 to be observed, thereby confirming the progress of embrittlement (hydrogen embrittlement) that has occurred on one surface 211a of the diaphragm plate 211 due to the gas G, as well as the presence or absence of defects. In other words, the progress of embrittlement, which is an indicator of the degree of deterioration of the diaphragm plate 211, can be detected from one surface 211a of the diaphragm plate 211. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0116] Furthermore, in the above configuration, the diaphragm plate 211 is pushed 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 measurement target area 21x is strained by compressive stress. This allows the strain gauge 30 to detect the amount of strain caused by compressive stress repeatedly generated in the diaphragm plate 211 during operations such as short-period starting and stopping (DSS: Daily Start and Stop) of the compressor 10. Therefore, compared to the configuration of the sacrificial member 20 described in the first embodiment, it is possible not only to confirm the magnitude of strain that is constantly generated in the rotor 11 during the rated operation of the compressor 10, but also to confirm the changes in the amount of strain that repeatedly occurs when the compressor 10 is started and stopped. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated more accurately.

[0117] Furthermore, in the above configuration, the strain gauge 30 is positioned on the other surface 211b facing the second space R2 which is open to the atmosphere. As a result, the strain gauge 30 is not exposed to gas G, and therefore the strain gauge 30 will not fail due to being subjected to the pressure of gas G.

[0118] Furthermore, in the above configuration, the second space R2 is open to the atmosphere through an atmospheric vent hole 40h formed in the inspection cover 40. This prevents, for example, the excessive leakage of gas G from the containment space R to the outside of the compressor 10 at once when the diaphragm plate 211 is damaged and the first space R1 and the second space R2 come into contact. As a result, it is possible to prevent a decrease in the pressure of the gas G flowing through the outlet passage P2.

[0119] <Third Embodiment> Next, a third embodiment of the sacrificial member according to this disclosure will be described with reference to Figure 4. In the third embodiment described below, components common to the first and second embodiments described above are denoted by the same reference numerals in the figure, and their descriptions are omitted. The configuration of the sacrificial member described in the third embodiment differs from the configuration of the sacrificial member described in the first and second embodiments.

[0120] (Sacrificial member) In this embodiment, the sacrificial member 20 has a piston ring portion 24, a fixing plate portion 25, and a rod portion 212.

[0121] (Piston ring section) The piston ring portion 24 is formed in a disc shape having a predetermined thickness. The piston ring portion 24 has a first surface 24a and a second surface 24b facing the opposite direction from the first surface 24a. The piston ring portion 24 divides the housing space R into two spaces.

[0122] In other words, the piston ring portion 24 divides the housing space R into two parts: a space located on the side of the first surface 24a and a space located on the side of the second surface 24b, with the piston ring portion 24 as the boundary. Furthermore, the piston ring portion 24 is positioned in the housing space R in a state where these two spaces are airtightly isolated from each other.

[0123] Specifically, the piston ring portion 24 is positioned to be movable in the direction in which the housing space R extends while sliding in contact with the inner surface of the recess 120d. One of the two spaces partitioned by the piston ring portion 24 (the space located on the side of the first surface 24a) is in communication with the outlet flow path P2 through the connecting flow path 12p. The other of the two spaces partitioned by the piston ring portion 24 (the space located on the side of the second surface 24b) is open to the atmosphere through the atmospheric vent hole 40h formed in the inspection cover 40.

[0124] For the sake of explanation, the space connected to the outlet passage P2 among the two spaces partitioned by the piston ring section 24 will be referred to as the "first space R1". The space open to the atmosphere among the two spaces partitioned by the piston ring section 24 will be referred to as the "second space R2".

[0125] The first space R1 becomes high-pressure compared to the second space R2, which is open to the atmosphere, because gas G is drawn into the first space R1 from the outlet channel P2 through the connecting channel 12p. In other words, a pressure difference is created between the first space R1 and the second space R2.

[0126] (Fixed plate part) The fixing plate portion 25 is formed in the shape of a disc having a predetermined thickness. The fixing plate portion 25 is positioned in the first space R1. The fixing plate portion 25 is fixed to the inner surface of the recess 120d in an immovable manner. The fixing plate portion 25 has a main surface 25a and a back surface 25b that faces the first surface 24a of the piston ring portion 24 in the opposite direction to the main surface 25a.

[0127] The fixed plate portion 25 has a plurality of communication holes 25h that penetrate from the main surface 25a to the back surface 25b. The plurality of communication holes 25h are arranged in a ring shape with equal intervals between them in the direction in which the main surface 25a and the back surface 25b expand.

[0128] In this embodiment, one example is shown where four communication holes 25h are formed in the fixed plate portion 25. The communication holes 25h connect the space on the side of the first surface 24a and the space on the side of the second surface 24b in the first space R1, with the fixed plate portion 25 as the boundary.

[0129] (Rod section) The rod portion 212 is formed in a cylindrical shape. One end of the rod portion 212 is fixed to the central part of the back surface 25b of the fixing plate portion 25. Specifically, one end of the rod portion 212 is fixed to the part of the back surface 25b that is inside each of the multiple communication holes 25h. The other end of the rod portion 212 is fixed to the central part of the first surface 24a of the piston ring portion 24.

[0130] In other words, the rod portion 212 extends between the fixed plate portion 25 and the piston ring portion 24, connecting the fixed plate portion 25 and the piston ring portion 24. In this embodiment, the side surface 212s of the rod portion 212 is designated as the measurement target portion 21x.

[0131] The piston ring portion 24 moves in a manner that reduces the volume of the second space R2 due to the 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, which is the measurement target area 21x, is strained as it is stretched in the direction in which the rod portion 212 extends, as the piston ring portion 24 moves. In other words, tensile stress is generated in the measurement target area 21x when the compressor 10 is in operation.

[0132] (Strain gauge) In this embodiment, the strain gauge 30 is attached (adhered) to the central portion of the side surface 212s, which is the measurement target area 21x of the rod portion 212.

[0133] (Effects / Actions) In the above configuration, while the compressor 10 is in operation, a portion of the compressed gas G(H2) is drawn out into the first space R1 of the containment space R, and the sacrificial member 20, which is placed in the containment space R, is exposed to this drawn-out gas G. As the piston ring portion 24 of the sacrificial member 20 is pushed towards the second space R2 by the gas G, the rod portion 212 of the sacrificial member 20 is strained (stretched) in the direction in which the rod portion 212 extends. This allows, for example, the amount of strain at the measurement target part 21x on the rod portion 212 to be checked by removing the rod portion 212 from the storage space R when the operation of the compressor 10 is stopped. In other words, the amount of strain, which is an indicator of the degree of deterioration of the rod portion 212, can be detected from the measurement target part 21x. Therefore, as pressure from the gas G acts on the rod portion 212, it is possible to determine how much stress is acting on the rod portion 212. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0134] Furthermore, in the above configuration, the rod portion 212 is made of a metal material having the same composition as the metal material that forms the impeller 111 of the rotor 11. This allows, for example, when the compressor 10 is stopped, the rod portion 212 can be removed from the storage space R, and the side surface 212s of the rod portion 212 can be observed to check the progress of embrittlement (hydrogen embrittlement) that has occurred on the side surface 212s of the rod portion 212 due to gas G, as well as the presence or absence of defects. In other words, the progress of embrittlement, which is an indicator of the deterioration of the rod portion 212, can be detected from the side surface 212s of the rod portion 212. As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated.

[0135] Furthermore, in the above configuration, compared to the configuration described in the first embodiment, the measurement target portion 21x of the rod portion 212 is strained by the differential pressure generated between the first space R1 and the second space R2. At that time, the rod portion 212 expands and contracts due to the change in pressure of the gas G flowing into the first space R1. As a result, the measurement target portion 21x is strained by tensile stress. This allows the strain gauge 30 to detect the amount of strain caused by tensile stress repeatedly generated in the rod section 212 during operations such as short-period starting and stopping (DSS: Daily Start and Stop) of the compressor 10.

[0136] In this configuration, tensile stress is generated in the rotor 11 during the operation of the compressor 10 due to the action of centrifugal force. Therefore, with the above configuration, it is possible to observe the change in strain amount due to the same stress mode (tensile stress). As a result, the degree of deterioration of the rotor 11 (impeller 111) of the compressor 10 can be estimated more accurately.

[0137] <Fourth Embodiment> Next, a fourth embodiment of the compressor system 1 according to this disclosure will be described with reference to Figure 5. In the fourth embodiment described below, components common to the first, second, and third embodiments described above are denoted by the same reference numerals in the figure, and their descriptions are omitted.

[0138] In this embodiment, the gas G that the compressor 10 compresses is not hydrogen gas (H2), but a corrosive gas. For example, the gas G that the compressor 10 compresses in this embodiment is hydrogen sulfide gas (H2S).

[0139] In this embodiment, the containment space R is a space defined by the inner surface of a recess 120d formed to recess from the outer surface 120s of the casing 120. That is, the containment space R opens to the outer surface 120s of the casing 120. The containment space R is located, for example, on one side Dal of the inlet flow path P1.

[0140] Furthermore, the containment space R is connected to the inlet channel P1 by a connecting channel 12p formed in the casing 120. In other words, the containment space R is connected to (in communication with) the inlet channel P1 through the connecting channel 12p, through which the gas G before compression flows.

[0141] In this embodiment, one end of the connecting channel 12p opens into the containment space R. The other end of the connecting channel 12p opens into the casing inlet channel 120a in the inlet channel P1. Therefore, a portion of the gas G flowing through the inlet channel P1 before being compressed by the compression section is drawn into the containment space R through this connecting channel 12p.

[0142] The sacrificial member 20 is located in this containment 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. Note that in Figure 5, for space limitations, the sacrificial member 20 is shown as a dotted rectangle.

[0143] In this embodiment, any of the sacrificial members 20 described in the first to third embodiments above may be used as the sacrificial member 20. In this case, the strain gauge 30 is attached (adhered) to the measurement target portion 21x of the sacrificial member 20.

[0144] (Effects / Actions) In the above configuration, while the compressor 10 is operating (during rated operation), a portion of the gas G (H2S) before compression is drawn out into the containment space R, and the sacrificial member 20 placed in the containment space R is exposed to this drawn-out gas G. When the sacrificial member 20 is exposed to the gas G, the measurement target portion 21x of the sacrificial member 20 is strained by the pressure of the gas G. At the same time, since the measurement target portion 21x is made of a metal material with the same composition as the metal material that forms the rotor 11 of the compressor 10, the measurement target portion 21x is subjected to corrosion by the gas G in the same way as the rotor 11 of the compressor 10. In this case, the measurement target portion 21x is exposed to the gas G before compression, which has a higher concentration of corrosive components, compared to, for example, when the measurement target portion 21x is exposed to the gas G during compression or after compression, and therefore receives a greater corrosive effect from the gas G. In other words, it is possible to confirm the state of the measurement target portion 21x that has deteriorated under more severe stress corrosion cracking conditions than 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 deterioration of the rotor 11 of the compressor 10 can be estimated more accurately.

[0145] <Fifth Embodiment> Next, a fifth embodiment of the compressor system 1 according to this disclosure will be described with reference to Figures 6 and 7. In the fifth embodiment described below, components common to the first, second, and third embodiments described above are denoted by the same reference numerals in the figures, and their descriptions are omitted. In the fifth embodiment, the configuration of the sacrificial member differs from the configuration of the sacrificial member described in the first, second, and third embodiments.

[0146] The compressor system 1 in the fifth embodiment does not include strain gauges 30. Furthermore, the gas G that the compressor 10 in this embodiment compresses is hydrogen gas (H2).

[0147] In this embodiment, the accommodation space R is defined by the inner surface of a recess 120d that is formed to recess from the inner surface of the accommodation recess 121r that accommodates the last stage impeller 111e in the diaphragm 121 toward the other side Dar.

[0148] In other words, the accommodation space R opens onto the inner surface of the accommodation recess 121r that accommodates the last stage impeller 111e, and is connected to the compression passage 111p of the last stage impeller 111e. The recess 120d is formed in an annular shape that surrounds the rotation axis 110 of the rotor 11. That is, the accommodation space R is formed as an annular space surrounding the rotation axis 110 of the rotor 11.

[0149] (Sacrificial member) As shown in Figure 7, the sacrificial member 20 in this embodiment has a columnar portion 213.

[0150] (Columnar part) The columnar portion 213 is formed in a columnar shape and is integrally attached to the disk 111a of the last stage impeller 111e in the rotor 11. The columnar portion 213 extends from this disk 111a to the other side Dar. That is, when the compressor 10 is in operation, the columnar portion 213 rotates within the housing space R around the axis Ar as the last stage impeller 111e rotates.

[0151] The columnar portion 213 has a recess 213a that is indented from the outer surface. The recess 213a is located in the central part in the direction in which the columnar portion 213 extends (axial direction Da). In the recess 213a, the cross-sectional area of ​​the columnar portion 213 in the direction perpendicular to the direction in which the columnar portion 213 extends is smaller than that of the parts other than the recess 213a.

[0152] Specifically, in the recess 213a, the cross-sectional area is reduced from the beginning of the outermost side Dal toward the other side Dar, and then reduced from the beginning of the outermost side Dar toward the outer side Dar, before converging.

[0153] Here, the stator 12 has a scope hole 12h that extends from the housing space R to the outer surface 120s of the casing 120 and opens onto the outer surface 120s of the casing 120. Specifically, one end of the scope hole 12h opens onto the inner surface of the recess 120d, and the other end of the scope hole 12h opens onto the outer surface 120s of the casing 120. The scope hole 12h is formed as a single continuous hole spanning the diaphragm 121 and the casing 120.

[0154] (Inspection cover) The inspection cover 40 is a cover member that seals the opening 12h' of the scope hole 12h on the outer surface 120s of the casing 120, thereby airtightly isolating the containment space R from the atmosphere. The inspection cover 40 is detachable from the outer surface 120s of the casing 120.

[0155] Specifically, the inspection cover 40 is detachable from the outer surface 120s of the casing 120 by fastening members B such as bolts. In other words, the inspection cover 40 is fixed to the outer surface 120s of the casing 120 by fastening members B, thereby closing the opening 12h' of the scope hole 12h on the outer surface 120s of the casing 120, and when the fastening members B are loosened, the inspection cover 40 is removed, exposing the opening 12h' of the scope hole 12h.

[0156] The inspection cover 40 is attached to the outer surface 120s of the casing 120 when the compressor 10 is in operation. The inspection cover 40 is also removed from the outer surface 120s of the casing 120 when, for example, the operator or maintenance worker of the compressor 10 checks the condition of the columnar portion 213. When the inspection cover 40 is removed from the outer surface 120s of the casing 120, the operator or maintenance worker of the compressor 10 checks the outer surface of the columnar portion 213 and the condition of the recess 213a using, for example, an industrial endoscope Bs (borescope).

[0157] (Effects / Actions) In the above configuration, while the compressor 10 is operating (during rated operation), a portion of the compressed gas G(H2) is drawn out into the containment space R, and the columnar portion 213 located in the containment space R is exposed to this drawn-out gas G. At the same time, the columnar portion 213 rotates around the axis Ar within the containment space R, which is formed as an annular space surrounding the rotation axis 110, as the last stage impeller 111e of the rotor 11 rotates. As the columnar portion 213 rotates around the axis Ar and receives pressure from the gas G, the recess 213a of the columnar portion 213, which is the measurement target portion 21x, is deformed. Therefore, compared to the configurations described in each of the above embodiments, the columnar portion 213 can simulate the stress acting on the rotor 11 with greater accuracy.

[0158] Furthermore, in the above configuration, a scope hole 12h is formed in the stator 12, which allows access to the columnar portion 213 located in the housing space R from outside the compressor 10 using, for example, an industrial endoscope Bs, and a removable inspection cover 40 closes the opening 12h' of the scope hole 12h on the outer surface 120s of the casing 120. This eliminates the need to disassemble the compressor 10, for example, when checking the condition of the columnar section 213. Therefore, the condition of the deteriorated columnar portion 213 can be easily confirmed.

[0159] <Sixth Embodiment> Next, a sixth embodiment of the compressor system 1 according to this disclosure will be described with reference to Figure 8. In the sixth embodiment described below, components common to the fifth embodiment described above are denoted by the same reference numerals in the figure, and their descriptions are omitted.

[0160] In this embodiment, the accommodation space R is defined by the inner surface of a recess 120d that is formed to recess radially outward from the opposing surface 121s of the diaphragm 121.

[0161] In other words, the accommodation space R opens into the space between the diaphragm 121 and the rotation axis 110 of the rotor 11. The accommodation space R is located on the other side Dar of the second seal portion 14b. The recess 120d is formed in an annular shape that surrounds the rotation axis 110 of the rotor 11. That is, the accommodation space R is formed as an annular space surrounding the rotation axis 110 of the rotor 11.

[0162] (Sacrificial member) In this embodiment, the sacrificial member 20 has a columnar portion 213.

[0163] (Columnar part) The columnar portion 213 is formed in a columnar shape and is integrally attached to the rotating shaft 110 of the rotor 11. The columnar portion 213 extends radially outward from the outer circumferential surface 110s of the rotating shaft 110. That is, when the compressor 10 is in operation, the columnar portion 213 pivots around the axis Ar in accordance with the rotation of the rotating shaft 110.

[0164] The columnar portion 213 has a recess 213a that is indented from the outer surface. The recess 213a is located in the central part of the columnar portion 213 in the direction in which it extends (radial direction). In the recess 213a, the cross-sectional area of ​​the columnar portion 213 in the direction perpendicular to the direction in which it extends is smaller than that of the portion other than the recess 213a.

[0165] Specifically, in the recess 213a, the cross-sectional area is reduced from the innermost radial starting point outward, and from the outermost radial starting point inward, before converging.

[0166] (Effects / Actions) The above configuration can also produce the same effects and benefits as the configuration described in the fifth embodiment.

[0167] Furthermore, in the above configuration, the columnar portion 213 is attached to the rotating shaft 110 with its radial extension. As a result, the direction of the centrifugal force acting on the rotor 11 coincides with the direction of the tensile stress acting on the columnar portion 213. Therefore, compared to the configuration described in the fifth embodiment above, the columnar portion 213 can simulate the stress acting on the rotor 11 with greater accuracy.

[0168] <Seventh Embodiment> Next, a seventh embodiment of the compressor system 1 according to this disclosure will be described with reference to Figure 9. In the seventh embodiment described below, components common to the fifth embodiment described above are denoted by the same reference numerals in the figure, and their descriptions are omitted.

[0169] In this embodiment, the gas G that the compressor 10 compresses is not hydrogen gas (H2), but a corrosive gas. For example, the gas G that the compressor 10 compresses in this embodiment is hydrogen sulfide gas (H2S).

[0170] In this embodiment, the accommodation space R is defined by the inner surface of a recess 120d that is formed to recess toward one side Dal from the inner surface of the accommodation recess 121r that accommodates the foremost impeller 111f in the diaphragm 121.

[0171] In other words, the accommodation space R opens onto the inner surface of the accommodation recess 121r that accommodates the foremost impeller 111f, and is connected to the compression passage 111p of the foremost impeller 111f. The recess 120d is formed in an annular shape that surrounds the rotation axis 110 of the rotor 11. That is, the accommodation space R is formed as an annular space surrounding the rotation axis 110 of the rotor 11.

[0172] (Sacrificial member) In this embodiment, the sacrificial member 20 has a columnar portion 213.

[0173] (Columnar part) The columnar portion 213 is formed in a columnar shape and is integrally attached to the cover 111c of the foremost impeller 111f in the rotor 11. The columnar portion 213 extends from this cover 111c to one side Dal. That is, when the compressor 10 is in operation, the columnar portion 213 rotates within the housing space R around the axis Ar as the foremost impeller 111f rotates.

[0174] The columnar portion 213 has a recess 213a that is indented from the outer surface. The recess 213a is located in the central part in the direction in which the columnar portion 213 extends (axial direction Da). In the recess 213a, the cross-sectional area of ​​the columnar portion 213 in the direction perpendicular to the direction in which the columnar portion 213 extends is smaller than that of the parts other than the recess 213a.

[0175] Specifically, in the recess 213a, the cross-sectional area is reduced from the beginning of the outermost side Dal toward the other side Dar, and then reduced from the beginning of the outermost side Dar toward the outer side Dar, before converging.

[0176] (Effects / Actions) In the above configuration, while the compressor 10 is operating (during rated operation), a portion of the gas G (H2S) compressed by the foremost impeller 111f is drawn out into the containment space R, and the columnar portion 213 located in the containment space R is exposed to this drawn-out gas G. The columnar portion 213 is then subjected to corrosion by the gas G, similar to the rotor 11 of the compressor 10. In this case, since the columnar portion 213 is exposed to the gas G compressed in the compression passage 111p of the foremost impeller 111f, it is subjected to greater corrosion by the gas G compared to, for example, exposure to gas G compressed by an impeller 111 further down the line than the foremost impeller 111f. At the same time, the columnar portion 213 rotates around the axis Ar within the containment space R, which is formed as an annular space surrounding the rotation axis 110, as the foremost impeller 111f in the rotor 11 rotates. As the columnar portion 213 rotates around its axis Ar and receives pressure from the gas G, the recess 213a, which is the measurement target area 21x, is deformed. Therefore, for example, compared to the configuration described in the fourth embodiment above, the conditions for stress corrosion cracking of the rotor 11 can be simulated with greater accuracy.

[0177] (Other embodiments) Although embodiments of this disclosure have been described in detail above with reference to the drawings, the specific configuration is not limited to that of the embodiments, and additions, omissions, substitutions, and other modifications to the configuration are possible without departing from the gist of this disclosure.

[0178] The accommodation space R for accommodating the sacrificial member 20 described in the above embodiment does not necessarily have to be formed in the stator 12. For example, as shown in Figure 10, the compressor system 1 may further include an inspection chamber 50 that defines the accommodation space R on its interior. The inspection chamber 50 is attached, for example, to the outer surface 120s of the casing 120. The inspection chamber 50 is formed, for example, in a cylindrical shape with one end open. The inspection cover 40 described above 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 only needs to be detachable from the inspection chamber 50. In this case, the storage space R inside the inspection chamber 50 should be in communication with the outlet flow path P2 through the connecting flow path 12p formed in the stator 12. The storage space R inside the inspection chamber 50 may also be in communication with the inlet flow path P1 through the connecting flow path 12p. This eliminates the need to form a housing space R in the stator 12. Therefore, it is possible to suppress the reduction in the design flexibility of the stator 12 when arranging the housing space R.

[0179] Furthermore, as shown in Figure 11, for example, the compressor system 1 may further include an introduction pipe 60 that connects the containment space R inside the inspection chamber 50 to the inside of the discharge pipe 200 and guides a portion of the gas G flowing through the discharge pipe 200 into the inspection chamber 50. In this case, the flow path length L between the inlet, which is the connection point between the introduction pipe 60 and the discharge pipe 200, and the connection point between the second flow path 121b and the compression flow path 111p of the final stage impeller 111e (the beginning of the second flow path 121b) is preferably within 10m, for example, in relation to the pressure loss of the gas G. Note that the inlet of the introduction pipe 60 is not limited to being connected to the discharge pipe 200, but may also be connected to the outlet nozzle 123. In other words, the introduction pipe 60 may introduce the compressed gas G flowing through the discharge flow path 123a of the outlet nozzle 123 into the inspection chamber 50.

[0180] Furthermore, each of the pair of nut portions 23 described in the first embodiment above may be positioned inside the C-ring portion 210 in the direction in which the bolt portion 22 extends, screwed onto the bolt portion 22, and pressure may be applied to the C-ring portion 210 such that one end 210a and the other end 210b of the C-ring portion 210 are separated from each other.

[0181] Furthermore, the gas G that the compressor 10 described in the first to third embodiments, fifth embodiment, and sixth embodiment is to compress is not limited to hydrogen gas (H2). Also, the corrosive gas G that the compressor 10 described in the fourth embodiment and seventh embodiment is to compress is not limited to hydrogen sulfide gas (H2S).

[0182] Furthermore, the other end of the connecting passage 12p described in the first to third embodiments is not limited to being connected to the casing outlet passage 120b, but may be connected to, for example, the discharge passage 123a or the second passage 121b. Also, the other end of the connecting passage 12p described in the fourth embodiment is not limited to being connected to the casing inlet passage 120a, but may be connected to, for example, the suction passage 122a or the first passage 121a. Also, the other end of the connecting passage 12p is not limited to being connected to the inlet passage P1 and the outlet passage P2, but may be connected to, for example, the intermediate passage 121c. In this case, the intermediate passage 121c can be used as the outlet passage, and the gas G can be drawn into the containment space R through the connecting passage 12p. Also, for example, if a passage is formed to directly supply gas G to the intermediate passage 121c, this passage can be used as the inlet passage, and the gas G can be drawn into the containment space R through the connecting passage 12p.

[0183] Furthermore, the compressor system 1 described in the first to fourth embodiments above does not necessarily have to be equipped with a strain gauge 30.

[0184] Furthermore, the strain gauges 30 described in the first to fourth embodiments above may be attached in multiples to the measurement target area 21x. This allows the amount of strain at the measurement target area 21x to be measured even if, for example, one strain gauge 30 malfunctions.

[0185] Furthermore, the strain gauge 30 described in the second and third embodiments above does not necessarily have to be attached to the central portion of the measurement target area 21x.

[0186] Furthermore, the accommodation space R described in the second and third embodiments above is not limited to being formed in a cylindrical shape, but may be formed in a rectangular prism shape, for example. In this case, the diaphragm plate 211 described in the second embodiment, and the piston ring portion 24 and fixing plate portion 25 described in the third embodiment, may be formed in a flat plate shape (rectangular plate shape).

[0187] Furthermore, multiple columnar portions 213 described in the first embodiment and the fifth to seventh embodiments may be arranged in the accommodation space R. When multiple sacrificial members 20 described in the fifth to seventh embodiments are arranged in the accommodation space R, for example, they may be attached to the rotor 11 so as to be arranged at equal intervals in the circumferential direction Dc of the rotating shaft 110. This allows, for example, the sacrificial members 20 to be removed one or more at a time after a predetermined period of time, and the condition of the measurement target part 21x can be checked. Therefore, it is possible to understand the changes and deterioration of the measurement target part 21x over time, and consequently the changes and deterioration of the rotor 11 over time, according to the length of the period.

[0188] Furthermore, the containment space described in the first to third embodiments above does not necessarily have to be open to the outer surface 120s of the casing 120. In this case, a scope hole 12h is formed in the stator 12 that extends from the containment space R to the outer surface 120s of the casing 120 and opens to the outer surface 120s of the casing 120, and an inspection cover 40 that is detachably attached to the outer surface 120s of the casing 120 closes this scope hole 12h, thereby hermetically isolating the containment space R from the atmosphere. In this case, the containment space R is not limited to being formed in the casing 120, but may be formed in the diaphragm 121, for example. This eliminates the need to disassemble the compressor 10, for example, when checking the condition of the measurement target part 21x on the sacrificial member 20.

[0189] Furthermore, in the second embodiment described above, the other surface 211b of the diaphragm plate 211 is designated as the measurement target area 21x, but this is not the only limitation. For example, one surface 211a of the diaphragm plate 211 may be designated as the measurement target area 21x. Therefore, it is sufficient that at least a portion of the diaphragm plate 211 is designated as the measurement target area 21x.

[0190] Furthermore, the compressor system 1 described in the second and third embodiments above does not necessarily have to include, for example, an inspection cover 40.

[0191] Furthermore, the second space R2 described in the second and third embodiments above does not necessarily have to be open to the atmosphere. The second space R2 may, for example, be sealed with a gas that is airtightly isolated from the outside and maintained at a lower pressure than the first space R1.

[0192] Furthermore, the columnar portion 213 described in the fifth and seventh embodiments above may be attached to the impeller 111 in a state that is slightly inclined with respect to the horizontal plane, for example. Also, the columnar portion 213 described in the sixth embodiment above may be attached to the rotating shaft 110 in a state that is slightly inclined with respect to a virtual plane perpendicular to the axis Ar.

[0193] Furthermore, the recess 213a of the columnar portion 213 described in the fifth and seventh embodiments above does not necessarily have to be located in the central portion in the direction in which the columnar portion 213 extends.

[0194] Furthermore, the compressor system 1 described in the fifth to seventh embodiments above may further include, for example, a contact prevention mechanism to prevent the broken fragments from coming into contact with the rotor 11 when the columnar portion 213 breaks off from the recess 213a as the rotor 11 rotates. The contact prevention mechanism is, for example, positioned in the housing space R so as not to interfere with the columnar portion 213.

[0195] Furthermore, multiple accommodation spaces R described in the first to seventh embodiments above may be formed in the stator 12. In this case, each accommodation space R may accommodate a sacrificial member 20.

[0196] Furthermore, the measurement target portion 21x described in the first to seventh embodiments above does not necessarily have to be made of a metal material with the same composition as the metal material forming the rotor 11, and the measurement target portion 21x may be made of a different metal material than the rotor 11. In this case, examples of other metal materials include a metal material newly applied to the rotor 11, or a metal material for a component other than the rotor 11 (e.g., the stator 12).

[0197] Furthermore, the compressor 10 in the first to seventh embodiments described above is not limited to a single-shaft multi-stage centrifugal compressor (multi-stage centrifugal compressor), but may also be, for example, a single-shaft single-stage centrifugal compressor (single-stage centrifugal compressor).

[0198] Furthermore, the configurations of the compressor system 1 described in the first to seventh embodiments above are not limited to independent configurations. The components described in each embodiment may be combined as appropriate to form the compressor system 1.

[0199] <Note> The compressor system described in each embodiment can be understood, for example, as follows:

[0200] (1) The compressor system 1 according to the first embodiment comprises a compressor 10 having a rotor 11 and a stator 12 that covers the rotor 11 and forms a flow path for a fluid (gas G) to be compressed, and a sacrificial member 20 arranged in a containment space R that communicates with the flow path, wherein the sacrificial member 20 is arranged in the containment space R and has a measurement target portion 21x that is deformed by the pressure of the fluid.

[0201] This allows, for example, when the compressor 10 is stopped, the amount of strain at the measurement target part 21x to be checked by removing the sacrificial member 20 from the containment space R. Furthermore, by observing the measurement target area 21x, for example, it is possible to check the degree of deterioration of the measurement target area 21x due to the fluid, as well as the presence or absence of defects.

[0202] (2) The compressor system 1 according to the second embodiment is the compressor system 1 of (1), wherein the measurement target portion 21x may be formed of a metal material having the same composition as the metal material forming the rotor 11.

[0203] (3) The compressor system 1 according to the third embodiment is the compressor system 1 of (1) or (2), wherein the fluid is hydrogen gas, and the containment space R may be connected to an outlet flow path.

[0204] (4) The compressor system 1 according to the fourth embodiment is the compressor system 1 of (3), wherein the outlet passage P2 is the passage through which the compressed fluid with the highest pressure among the passages flows.

[0205] As a result, the measurement target portion 21x of the sacrificial member 20 is subjected to greater pressure from the hydrogen gas compared to, for example, the case where hydrogen gas is drawn into the containment space R before or during compression. In other words, it is possible to check the condition of the measured part 21x that has deteriorated under more severe embrittlement conditions.

[0206] (5) The compressor system 1 according to the fifth embodiment is the compressor system 1 of (1) or (2), wherein the fluid is a corrosive gas, and the containment space R may be connected to an inlet passage.

[0207] (6) The compressor system 1 according to the sixth embodiment is the compressor system 1 of (5), which may be the flow path through which the fluid with the lowest pressure before compression flows.

[0208] As a result, for example, the part of the sacrificial member 20 to be measured 21x is subjected to greater corrosive action from the fluid compared to when the part of the sacrificial member 20 to be measured 21x is exposed to corrosive gas during or after compression. In other words, it is possible to check the condition of the measured area 21x that has deteriorated under more severe stress corrosion cracking conditions.

[0209] (7) The compressor system 1 according to the seventh embodiment is any of the compressor systems 1 from (1) to (6), wherein the housing space R is open on the outer surface 120s facing the outside of the stator 12, and may further include an inspection cover 40 that is detachable from the stator 12 and closes the opening of the housing space R.

[0210] This allows the sacrificial member 20 to be removed from the containment space R by removing the inspection cover 40. Furthermore, by closing the inspection cover 40, the containment space R can be airtightly isolated from the outside. Therefore, when removing the sacrificial member 20 from the containment space R, it is not necessary to disassemble the compressor 10, for example.

[0211] (8) The compressor system 1 according to the eighth embodiment is any of the compressor systems 1 from (1) to (7), which may further include a strain gauge 30 attached to the measurement target part 21x and capable of detecting the amount of strain of the measurement target part 21x.

[0212] This makes it possible, for example, to transmit a signal indicating the amount of strain detected by the strain gauge 30 to the outside of the compressor 10. Therefore, for example, the change in the amount of strain at the measurement target part 21x during the operation of the compressor 10 can be monitored over time from outside the compressor 10.

[0213] (9) The compressor system 1 according to the ninth embodiment is any of the compressor systems 1 from (1) to (8), wherein the sacrificial member 20 has a plate-shaped C-ring portion 210 that is curved to be convex and arranged in a C-shape, and a pressing and holding portion 21 that holds both ends of the C-ring portion 210 (one end 210a and the other end 210b) pressed together, wherein the convex portion of the C-ring portion 210 is the measurement target portion 21x, and the pressing and holding portion 21 may press the C-ring portion 210 such that a stress higher than the maximum stress acting on the rotor 11 during rated operation of the compressor 10 is applied to the measurement target portion 21x with the measurement target portion 21x positioned between them.

[0214] This allows the above-mentioned functions to be achieved with greater precision. Furthermore, it is possible to check the condition of the deteriorated C-ring portion 210 under conditions more severe than those in the flow path environment where the rotor 11 rotates while being exposed to fluid. Therefore, the degree of deterioration of the rotor 11 of the compressor 10 can be estimated more accurately.

[0215] (10) The compressor system 1 according to the tenth embodiment is any of the compressor systems 1 from (1) to (8), wherein the sacrificial member 20 has a diaphragm plate 211 that divides the containment space R into a first space R1 that is in communication with the flow path and a second space R2 that is open to the atmosphere, and at least a part of the diaphragm plate 211 may be the measurement target portion 21x.

[0216] This allows the above effects to be achieved with greater precision. Furthermore, since the measurement target portion 21x of the diaphragm plate 211 is strained by the differential pressure generated between the first space R1 and the second space R2, it is possible to detect the amount of strain caused by compressive stress generated in the diaphragm plate 211 during operations such as short-period starting and stopping of the compressor 10.

[0217] (11) The compressor system 1 according to the eleventh embodiment is any of the compressor systems 1 from (1) to (8), wherein the sacrificial member 20 has a piston ring portion 24 that divides the housing space R into a first space R1 that is in communication with the flow path and a second space R2 that is open to the atmosphere, a fixed plate portion 25 that is fixedly positioned in the first space R1 in an immovable state, and a rod portion 212 that is formed in a columnar shape and connects the piston ring portion 24 and the fixed plate portion 25, and at least a part of the rod portion 212 may be the measurement target portion 21x.

[0218] This allows the above effects to be achieved with greater precision. Furthermore, it is possible to confirm the change in the amount of strain at the measurement target part 21x in the rod section 212 due to the same stress mode (tensile stress) as the stress generated in the rotor 11. As a result, the degree of deterioration of the rotor 11 of the compressor 10 can be estimated more accurately.

[0219] (12) The compressor system 1 according to the twelfth embodiment is the compressor system 1 of (1) or (2), wherein the accommodation space R is formed in the stator 12 in an annular shape surrounding the rotation axis 110 of the rotor 11, and the sacrificial member 20 has a columnar portion 213 fixed to the rotor 11, and the columnar portion 213 may have a recess 213a as the measurement target portion 21x that is recessed so as to be constricted from the outer surface.

[0220] As a result, the columnar portion 213, positioned in the containment space R, is exposed to the fluid and rotates around the axis Ar within the containment space R as the rotor 11 rotates. As the columnar portion 213 rotates around the axis Ar and receives fluid pressure, the recess 213a of the columnar portion 213, which is the measurement target portion 21x, is deformed. Therefore, compared to the above configuration, the columnar portion 213 can simulate the stress acting on the rotor 11 with greater accuracy.

[0221] (13) A compressor system 1 according to the 13th embodiment is the compressor system 1 of (12), wherein the fluid is hydrogen gas, the rotor 11 is rotatably mounted on the rotating shaft 110 and has a plurality of impellers 111 that compress the fluid in a manner aligned in the direction extending along the rotating shaft 110, and the containment space R may be connected to the compression passage 111p of the last stage impeller (last stage impeller 111e) of the plurality of impellers 111.

[0222] As a result, the columnar section 213 receives greater pressure from the hydrogen gas compared to, for example, the case where it is connected to the compression passage 111p of the preceding impeller 111 rather than the last stage impeller 111. In other words, it is possible to confirm the condition of the columnar portion 213 that has deteriorated under more severe embrittlement conditions.

[0223] (14) A compressor system 1 according to the 14th embodiment is the compressor system 1 of (12), wherein the fluid is a corrosive gas, the rotor 11 is rotatably mounted on the rotating shaft 110 and has a plurality of impellers 111 that compress the fluid in a manner aligned in the direction extending along the rotating shaft 110, and the containment space R may be connected to the compression passage 111p of the foremost impeller (foremost impeller 111f) among the plurality of impellers 111.

[0224] As a result, the columnar portion 213 is subjected to greater corrosion from corrosive gases compared to, for example, the case where it is connected to the compression passage 111p of the downstream impeller 111 rather than the forward impeller 111. In other words, it is possible to confirm the condition of the columnar portion 213 that has deteriorated under more severe stress corrosion cracking conditions.

[0225] (15) The compressor system 1 according to the 15th embodiment is any of the compressor systems 1 from (1) to (14), wherein the stator 12 has a scope hole 12h that extends from the housing space R to the outer surface 120s of the stator 12 and opens to the outer surface 120s of the stator 12, and may further include an inspection cover 40 that is detachable from the outer surface 120s of the stator 12 and closes the opening 12h' of the scope hole 12h.

[0226] This allows the inspection cover 40 to be removed from the outer surface 120s of the stator 12, and the condition of the measurement target area 21x on the sacrificial member 20 to be checked by inserting, for example, an industrial endoscope into the scope hole 12h. In other words, there is no need to disassemble the compressor 10 to check the condition of the part to be measured 21x. [Explanation of symbols]

[0227] 1…Compressor system 10…Compressor 11…Rotor 12…Stator 12h…Scope hole 12h'…Opening 12p…Connecting passage 13…Bearing section 14…Seal section 14a…First seal section 14b…Second seal section 20…Sacrificial member 21…Pressure holding section 21x…Measurement target area 22…Bolt section 23…Nut section 24…Piston ring section 24a…First surface 24b…Second surface 25…Fixing plate section 25a…Main surface 25b…Back surface 25h…Communication hole 30…Strain gauge 40…Inspection cover 40h…Atmospheric vent hole 50…Inspection chamber 60…Inlet pipe 60a…Inlet hole 100…Suction piping 110…Rotating shaft 110s…Outer surface 111…Impeller 111a…Disc 111b…Blade 111c…Cover 111e…Last stage impeller 111f…Foremost stage impeller 111p…Compression passage 120…Casing 120a…Casing inlet passage 120b…Casing outlet passage 120d…Recess 120i…Inner surface 120s…Outer surface 121…Diaphragm 121a…First passage 121b…Second passage 121c…Intermediate passage 121d…Diffuser passage 121e…Return passage 121r…Retaining recess 121s…Opposite surface 122…Inlet nozzle 122a…Suction passage 123…Outlet nozzle 123a…Discharge passage 130…Radial bearing 131…Thrust bearing 132…Thrust collar 200…Discharge piping 210…C-ring section 210a…One end 210b…Other end 211…Diaphragm plate 211a…One side 211b…Other side 212…Rod section 212s…Side surface 213…Columnar section 213a…Recess Ar…Axis B…Fastening member Bs…Industrial endoscope Da…Axial direction Dal…One side Dar…Other side Dc…Circumferential direction Dr…Rotational direction G…Gas L…Flow path length P1…Inlet flow path P2…Outlet flow path R…Accommodation space R1…First space R2…Second space

Claims

1. A compressor comprising a rotor and a stator that covers the rotor and forms a flow path for the fluid to be compressed, A sacrificial member is arranged in a containment space that communicates with the aforementioned flow path, Equipped with, The stator has a casing that constitutes the outer shell of the compressor, The casing has a connecting channel formed therein, which is connected to an outlet channel through which the fluid, after being compressed in the flow path, flows. The aforementioned containment space is formed in the casing, communicates with the connecting channel, and is located on the axial end side of the outlet channel. The sacrificial member is placed in the containment space and has a measurement target portion that is deformed by the pressure of the fluid. Compressor system.

2. The measurement target area is formed of a metal material having the same composition as the metal material forming the rotor. The compressor system according to claim 1.

3. The fluid is hydrogen gas. The compressor system according to claim 1 or claim 2.

4. The outlet channel is the channel through which the most compressed fluid with the highest pressure flows. The compressor system according to claim 1.

5. The aforementioned housing space is open on the outer surface of the stator that faces the outside, The system further includes an inspection cover that is detachable from the stator and closes the opening of the housing space. The compressor system according to claim 1 or claim 2.

6. The system further comprises a strain gauge attached to the part to be measured, which is capable of detecting the amount of strain in the part to be measured. The compressor system according to claim 1 or claim 2.

7. The aforementioned sacrificial member is A plate-shaped C-ring portion is curved to form a convex shape and arranged in a C-shape, A pressing and holding part that holds the C-ring portion in a state where both ends are pressed together so that they are brought closer to each other, It has, The C-ring portion has a convex portion which is the measurement target area. The pressing and holding portion presses the C-ring portion such that, with the portion to be measured positioned between them, it applies a stress to the portion to be measured that is higher than the maximum stress acting on the rotor during the rated operation of the compressor. The compressor system according to claim 1 or claim 2.

8. The sacrificial member has a diaphragm plate that divides the containment space into a first space that communicates with the flow path and a second space that is open to the atmosphere. At least a portion of the diaphragm plate was designated as the measurement target area. The compressor system according to claim 1 or claim 2.

9. The aforementioned sacrificial member is A piston ring portion divides the housing space into a first space communicating with the aforementioned flow path and a second space open to the atmosphere, A fixed plate portion positioned in the first space in an immovable state, A rod portion formed in a columnar shape, connecting the piston ring portion and the fixing plate portion, It has, At least a portion of the rod portion was designated as the measurement target area. The compressor system according to claim 1 or claim 2.

10. The aforementioned housing space is formed in the stator in an annular shape surrounding the rotation axis of the rotor, The sacrificial member has a columnar portion fixed to the rotor, The columnar portion has a recess that is indented from the outer surface, which serves as the measurement target area. The compressor system according to claim 1 or claim 2.

11. The fluid is hydrogen gas, The rotor is rotatably mounted on the rotating shaft and has multiple impellers arranged in the direction extending along the rotating shaft to compress the fluid. The aforementioned containment space is connected to the compression passage of the last stage impeller among the multiple stages of the impeller. The compressor system according to claim 10.

12. The stator has a scope hole that extends from the housing space to the outer surface of the stator and opens to the outer surface of the stator. The stator further comprises an inspection cover that is detachably attached to the outer surface of the stator and closes the opening of the scope hole. The compressor system according to claim 10.

13. A compressor comprising a rotor and a stator that covers the rotor and forms a flow path for the fluid to be compressed, A sacrificial member is arranged in a containment space that communicates with the aforementioned flow path, Equipped with, The sacrificial member is placed in the containment space and has a measurement target portion that is deformed by the pressure of the fluid, The aforementioned housing space is formed in the stator in an annular shape surrounding the rotation axis of the rotor, The sacrificial member has a columnar portion fixed to the rotor, The columnar portion has a recess that is indented from the outer surface, which serves as the measurement target area. Compressor system.

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