Method for rust prevention of gas turbine and gas turbine plant capable of carrying out method

Abstract

A gas turbine plant is provided with a gas turbine and a dry air system. The dry air system has an air line through which air from an air supply source can flow, and is configured so that the air flowing through the air line can be supplied as dry air into an intake housing of the gas turbine.

Description

Technical Field

[0001] The present invention relates to a rust prevention method for a gas turbine and a gas turbine equipment capable of executing the method.

[0002] This application claims priority based on Japanese Patent Application No. 2022-204295 filed in Japan on December 21, 2022, and the contents are incorporated herein by reference. Background Art

[0003] The gas turbine includes: a compressor that compresses air to generate compressed air; a combustor that burns fuel in the compressed air to generate combustion gas; a turbine that is driven by the combustion gas; an intake casing; and an intermediate casing.

[0004] The compressor includes: a compressor rotor rotatable around an axis line; and a compressor housing covering the compressor rotor. The turbine is arranged on the downstream side of the axis line relative to the compressor. The turbine includes: a turbine rotor connected to the compressor rotor and rotatable around the axis line; and a turbine housing covering the turbine rotor.

[0005] The intake housing is connected to the end of the compressor housing on the upstream side of the axis to guide air into the compressor housing. The intermediate housing is arranged between the compressor housing and the turbine housing in the axial direction. The burner is installed in the intermediate housing so that the compressed air discharged from the compressor into the intermediate housing can flow into it.

[0006] Patent Document 1 below discloses a gas turbine facility including the gas turbine described above, a cooling air system, and a dry air system.

[0007] The cooling air system can supply cooling air to the turbine rotor exposed to the combustion gas when the gas turbine is in operation. The dry air system can supply dry air to the cooling air system when the gas turbine is stopped.

[0008] In the gas turbine equipment described in Patent Document 1, dry air is supplied to the cooling air system during the shutdown of the gas turbine, thereby making it possible to suppress the generation of rust in the air pipe constituting a part of the cooling air system.

[0009] Previous technical literature

[0010] Patent Literature

[0011] Patent Document 1: Japanese Patent Publication No. 2015-140691 Summary of the invention

[0012] Technical issues to be solved by the invention

[0013] If a gas turbine is stopped for a long time, rust may be generated in the gas turbine. Therefore, in the field of gas turbines, it is desired to suppress the generation of rust in the gas turbine.

[0014] Therefore, an object of the present invention is to provide a rust prevention method for a gas turbine capable of suppressing the generation of rust in the gas turbine, and a gas turbine equipment capable of executing the method.

[0015] Means for solving technical problems

[0016] As one mode for achieving the above object, a gas turbine plant includes:

[0017] A gas turbine; and a dry air system capable of supplying dry air into the gas turbine. The gas turbine includes: a compressor capable of compressing air to generate compressed air; a combustor capable of burning fuel in the compressed air to generate combustion gas; a turbine capable of being driven by the combustion gas; an intake casing; and an intermediate casing. The compressor includes: a compressor rotor capable of rotating about an axis; and a compressor casing covering the compressor rotor. The turbine is arranged on the downstream side of the axis of the compressor, one of the upstream side and the downstream side in the axis direction in which the axis extends. The turbine includes: a turbine rotor connected to the compressor rotor and capable of rotating about the axis; and a turbine casing covering the turbine rotor. The intake casing is connected to the upstream end of the compressor casing to guide air into the compressor casing. The intermediate casing is arranged between the compressor casing and the turbine casing in the axis direction, connected to the downstream end of the compressor casing, and connected to the upstream end of the turbine casing to allow the compressed air from the compressor to flow in. The burner is mounted on the intermediate housing so that the compressed air in the intermediate housing can flow in and the combustion gas can be sent into the turbine housing. The dry air system has an air pipe through which air from an air supply source can flow, and is configured to supply the air flowing through the air pipe into the intake housing as the dry air.

[0018] In this method, when the gas turbine is stopped, dry air from the dry air system is supplied to the intake casing. On the exhaust side of the gas turbine, a chimney for discharging exhaust gas from the gas turbine is basically provided. Therefore, due to the draft effect of the chimney, the air in the gas turbine is drawn to the chimney side even when the gas turbine rotor is not rotating. Therefore, the dry air supplied to the intake casing flows into the intermediate casing through the compressor casing. The dry air flowing into the intermediate casing is discharged from the gas turbine through the burner and the turbine casing. In this way, since the dry air flows throughout the substantially entire gas turbine, it is possible to suppress the generation of rust in the gas turbine (especially in the compressor casing).

[0019] A rust prevention method for a gas turbine as one means for achieving the above object is applicable to the following gas turbine.

[0020] The gas turbine includes: a compressor that compresses air to generate compressed air; a combustor that burns fuel in the compressed air to generate combustion gas; a turbine that can be driven by the combustion gas; an intake casing; and an intermediate casing. The compressor includes: a compressor rotor that can rotate around an axis; and a compressor casing that covers the compressor rotor. The turbine is arranged on the downstream side of the axis of the compressor, of the upstream side and the downstream side in the axis direction in which the axis extends. The turbine includes: a turbine rotor that is connected to the compressor rotor and can rotate around the axis; and a turbine casing that covers the turbine rotor. The intake casing is connected to the upstream end of the compressor casing to guide air into the compressor casing. The intermediate casing is arranged between the compressor casing and the turbine casing in the axis direction, connected to the downstream end of the compressor casing, and connected to the upstream end of the turbine casing to allow the compressed air from the compressor to flow in. The combustor is mounted on the intermediate casing to allow the compressed air in the intermediate casing to flow in, and to send the combustion gas into the turbine casing.

[0021] In the gas turbine rust prevention method, a dry air supplying step of supplying dry air into the intake casing is performed while the gas turbine is stopped.

[0022] In this aspect, similarly to the first aspect of the gas turbine equipment, it is possible to suppress the generation of rust in the gas turbine (particularly in the compressor casing).

[0023] Effects of the Invention

[0024] In one aspect of the present invention, it is possible to suppress the generation of rust in the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic configuration diagram of a gas turbine plant in the first embodiment according to the present invention.

[0026] Figure 2 This is a flowchart showing the execution procedure of the rust prevention method for a gas turbine in the first embodiment according to the present invention.

[0027] Figure 3 This is a timing chart of the rust prevention method for a gas turbine in the first embodiment according to the present invention.

[0028] Figure 4 This is a timing chart of a gas turbine rust prevention method in a modified example of the first embodiment according to the present invention.

[0029] Figure 5 It is a schematic configuration diagram of a gas turbine plant in a second embodiment according to the present invention.

[0030] Figure 6 This is a flowchart showing the execution procedure of the rust prevention method for a gas turbine in the second embodiment according to the present invention. DETAILED DESCRIPTION

[0031] Hereinafter, various embodiments of a gas turbine rust prevention method according to the present invention and a gas turbine equipment capable of executing the method will be described with reference to the drawings.

[0032] "First Implementation Method"

[0033] Below, reference Figure 1 to Figure 4 , an embodiment of a rust prevention method for a gas turbine in this embodiment and a gas turbine equipment capable of executing the method will be described.

[0034] The gas turbine equipment in this embodiment is as follows Figure 1 The device shown is equipped with: a gas turbine GT; an air intake duct 18; an exhaust duct 38; a chimney 39; a wash water system 40 that can spray wash water into the gas turbine GT; a dry air system 50 that can supply dry air into the gas turbine GT; and a variety of rust inhibitors 54.

[0035] The gas turbine GT comprises: a compressor 10, which compresses air A to generate compressed air Acom; a plurality of burners 20, which burn fuel F in the compressed air Acom to generate combustion gas G; a turbine 30, which is driven by the high-temperature and high-pressure combustion gas G; an intake casing 15, which can guide the air A from the intake duct 18 to the compressor 10; an exhaust casing 35, through which the combustion gas G, i.e., exhaust gas EG, discharged from the turbine 30 flows; an intermediate casing 25; a front bearing 2f; and a rear bearing 2b.

[0036] The compressor 10 has a compressor rotor 11 that can rotate around the axis Ar, a compressor housing 12 that covers the compressor rotor 11, a plurality of compressor stator blades 13, and an intake air amount regulator 14. The turbine 30 has a turbine rotor 31 that can rotate around the axis Ar, a turbine housing 32 that covers the turbine rotor 31, and a plurality of turbine stator blades 33. In addition, hereinafter, the direction in which the axis Ar extends is set as the axis direction Da, one side in the axis direction Da is set as the axis upstream side Dau, and the other side in the axis direction Da is set as the axis downstream side Dad. In addition, the circumferential direction centered on the axis Ar is simply set as the circumferential direction Dc. In addition, the direction perpendicular to the axis Ar is set as the radial direction Dr, the side close to the axis Ar in the radial direction Dr is set as the radial inner side Dri, and the opposite side is set as the radial outer side Dro.

[0037] The compressor 10 is arranged on the upstream side Dau of the axis relative to the turbine 30. The compressor rotor 11 has a compressor rotor shaft 11s extending along the axis direction Da with the axis Ar as the center and a plurality of compressor moving blades 11b mounted on the compressor rotor shaft 11s. The plurality of compressor moving blades 11b are arranged in the axis direction Da. Each compressor moving blade 11b is composed of a plurality of moving blades arranged in the circumferential direction Dc. Any one of the plurality of compressor stationary blades 13 is arranged on the downstream side Dad of each of the plurality of compressor moving blades 11b. Each compressor stationary blade 13 is mounted on the inner side of the compressor housing 12. Each compressor stationary blade 13 is composed of a plurality of stationary blades arranged in the circumferential direction Dc. The intake air amount regulator 14 has a plurality of inlet guide vanes 14v and a driver 14d capable of changing the direction of each inlet guide vane 14v. The plurality of inlet guide vanes 14v are arranged on the upstream side Dau of the axis than the plurality of compressor moving blades 11b. The plurality of inlet guide vanes 14v are arranged side by side in the circumferential direction Dc.

[0038] The turbine rotor 31 has a turbine rotor shaft 31s extending along the axial direction Da with the axis Ar as the center and a plurality of turbine blade rows 31b mounted on the turbine rotor shaft 31s. A plurality of turbine blade rows 31b are arranged in the axial direction Da. Each turbine blade row 31b is composed of a plurality of blades arranged in the circumferential direction Dc. Any one of a plurality of turbine stator blade rows 33 is arranged on the axial upstream side Dau of each of the plurality of turbine blade rows 31b. Each turbine stator blade row 33 is mounted on the inner side of the turbine casing 32. Each turbine stator blade row 33 is composed of a plurality of stator blades arranged in the circumferential direction Dc.

[0039] The intermediate casing 25 is arranged between the compressor casing 12 and the turbine casing 32 in the axial direction Da. The end of the intermediate casing 25 on the axial upstream side Dau is connected to the end of the compressor casing 12 on the axial downstream side Dad. The end of the intermediate casing 25 on the axial downstream side Dad is connected to the end of the turbine casing 32 on the axial upstream side Dau. A plurality of combustors 20 are arranged in the circumferential direction Dc and mounted on the intermediate casing 25.

[0040] The combustor 20 includes a combustion furnace 21 capable of injecting fuel F and compressed air Acom, and a tail cylinder (or combustion tube) 22 capable of burning the fuel F injected from the combustion furnace 21 in the compressed air Acom. The combustion furnace 21 is connected to a fuel pipeline 24 capable of guiding the fuel F from a fuel supply source to the combustion furnace 21. In the tail cylinder 22, the fuel F burns in the compressed air Acom to generate combustion gas G. The tail cylinder 22 can guide the combustion gas G into the turbine casing 32.

[0041] The intake housing 15 is connected to the end of the axial upstream side Dau of the compressor housing 12. The intake housing 15 has an intake inner housing 15i, an intake outer housing 15o and a plurality of intake struts 16. The intake inner housing 15i is cylindrical with the axis Ar as the center, and covers a portion of the compressor rotor shaft 11s that is closer to the axial upstream side Dau than the inlet guide vane 14v. The intake inner housing 15i is formed so as to gradually move toward the radial outer side Dro as it moves toward the axial upstream side Dau. The intake outer housing 15o is cylindrical with the axis Ar as the center, and is arranged at a distance on the radial outer side Dro relative to the intake inner housing 15i. The end of the axial downstream side Dad of the intake outer housing 15o is connected to the end of the axial upstream side Dau of the compressor housing 12. The intake outer housing 15o is also formed so as to gradually move toward the radial outer side Dro as it moves toward the axial upstream side Dau. In the radial direction Dr, the space between the intake inner housing 15i and the intake outer housing 15o forms an air passage 17 that guides air into the compressor housing 12. An intake port 17i is formed between the end of the intake inner housing 15i on the axial upstream side Dau and the end of the intake outer housing 15o on the axial upstream side Dau. The intake port 17i opens from the inside of the air passage 17 toward the radially outer side Dro. An intake duct 18 is connected to the intake housing 15. Air from the intake duct 18 flows into the air passage 17 of the intake housing 15 through the intake port 17i of the intake housing 15. A plurality of intake struts 16 are arranged in the circumferential direction Dc between the intake inner housing 15i and the intake outer housing 15o. The end of the intake strut 16 on the radially inner side Dri is connected to the intake inner housing 15i. The end of the intake strut 16 on the radially outer side Dro is connected to the intake outer housing 15o.

[0042] The exhaust casing 35 is connected to the end of the axial upstream side Dau of the turbine casing 32. The exhaust casing 35 includes an exhaust inner casing 35i, an exhaust outer casing 35o, and a plurality of exhaust struts 36. The exhaust inner casing 35i is cylindrical with the axis Ar as the center, and covers a portion of the turbine rotor shaft 31s that is closer to the axial downstream side Dad than the plurality of turbine blade rows 31b. The exhaust outer casing 35o is cylindrical with the axis Ar as the center, and is arranged at intervals on the radially outer side Dro relative to the exhaust inner casing 35i. The end of the axial upstream side Dau of the exhaust outer casing 35o is connected to the end of the axial downstream side Dad of the turbine casing 32. In the radial direction Dr, the space between the exhaust inner casing 35i and the exhaust outer casing 35o forms an exhaust passage 37 for the combustion gas G, that is, the exhaust gas EG discharged from the turbine 30 to flow. The plurality of exhaust struts 36 are arranged in the circumferential direction Dc between the exhaust inner casing 35i and the exhaust outer casing 35o. The end portion on the radially inner side Dri of the exhaust strut 36 is connected to the exhaust inner side case 35i. The end portion on the radially outer side Dro of the exhaust strut 36 is connected to the exhaust outer side case 35o.

[0043] An exhaust duct 38 is connected to the end of the exhaust casing 35 on the axial downstream side Dad. A chimney 39 is connected to the end of the exhaust duct 38 on the axial downstream side Dad. The exhaust gas EG from the turbine 30 is discharged from the chimney 39 via the exhaust casing 35 and the exhaust duct 38. In addition, a waste heat recovery boiler that generates steam using the heat of the exhaust gas EG is sometimes provided in the exhaust duct 38.

[0044] The compressor rotor 11 and the turbine rotor 31 are located on the same axis Ar and are connected to each other to form a gas turbine rotor 1. The rotor of the generator GEN is connected to the gas turbine rotor 1. The portion of the gas turbine rotor 1 on the axial upstream side Dau is supported by the front bearing 2f. The portion of the gas turbine rotor 1 on the axial downstream side Dad is supported by the rear bearing 2b. The front bearing 2f is arranged in the axial direction Da at a position where a plurality of intake struts 16 are arranged. The front bearing 2f is supported by the plurality of intake struts 16 via the intake inner housing 15i. The rear bearing 2b is arranged in the axial direction Da at a position where a plurality of exhaust struts 36 are arranged. The rear bearing 2b is supported by the plurality of exhaust struts 36 via the exhaust inner housing 35i.

[0045] The washing water system 40 includes a washing water pipe 41 extending from a water supply source 45 to the inside of the air intake housing 15 and a plurality of nozzles 44 installed at the end of the washing water pipe 41 in the air intake housing 15. The washing water pipe 41 includes a washing water main pipe 41m connected to the water supply source 45, a connecting pipe 41c connected in the middle of the washing water main pipe 41m, a plurality of washing water branch pipes 41b branched from the washing water main pipe 41m at the end of the washing water main pipe 41m, a water stop valve 42, and an air stop valve 43. The ends of the plurality of washing water branch pipes 41b are arranged in the circumferential direction Dc in the air intake housing 15. The ends of the plurality of washing water branch pipes 41b are respectively installed with nozzles 44 capable of spraying water flowing through the washing water pipe 41 to the downstream side Dad of the axis. The water stop valve 42 is provided in the washing water main pipe 41m at a position closer to the water supply source 45 than the position where the connecting pipe 41c is connected. The air shutoff valve 43 is provided at the end of the connecting pipe 41c.

[0046] The dry air system 50 has an air line 51 connected to an air supply source 55, a filter 52 provided in the air line 51, and a dehumidifier 53 provided in the air line 51. The air supply source 55 may be a compressed air tank storing compressed air or a compressor generating compressed air. The compressed air tank is shared in a plant having a gas turbine GT, for example. And, the compressor, for example, sucks in external air and compresses it. The end of the air line 51 is connected to the air shutoff valve 43 of the washing water system 40 before using the dry air system 50. The dehumidifier 53 may be any type of dehumidifier as long as it is a device capable of removing moisture from the air from the air supply source 55. As the type of the dehumidifier 53, for example, there is a type that cools the air and condenses the moisture in the air to remove the moisture, or a type that removes moisture from the air with a dehumidifier or a desiccant, etc.

[0047] A plurality of rust preventives 54 are arranged in the air intake housing 15 before the aforementioned dry air system 50 is used. The rust preventive 54 is a gasifiable solid containing a rust preventive component. The rust preventive 54 is, for example, put into a mesh bag and installed on the air intake outer housing 15o, the air intake strut 16, the nozzle 44 of the cleaning water system 40, etc. As the rust preventive 54, for example, Ferroguard (a registered trademark of USC LIMITED.) can be cited. In addition, the rust preventive 54 can also be a gasifiable liquid. In this case, the liquid rust preventive 54 is infiltrated into cotton, etc., put into a mesh bag, and installed on the aforementioned air intake outer housing 15o, etc.

[0048] Next, a method for preventing rust in the gas turbine GT in the present embodiment will be described.

[0049] The rust prevention method in this embodiment is performed while the gas turbine GT is stopped. Figure 3 As shown in the timing chart of , the fuel supply stop of the gas turbine GT is executed from the stop of the operation of the gas turbine GT to the start of the start of the gas turbine GT. In addition, the stop of the gas turbine GT includes not only the case where the gas turbine rotor 1 does not rotate at all, but also the case where the gas turbine GT rotates. At this time, the air in the compressor housing 12, the intermediate housing 25, and the turbine housing 32 is stirred by the gas turbine rotor 1, so the air density and air humidity in each housing 12, 25, 32 are almost uniform. In addition, the rotation is to rotate the gas turbine rotor 1 at 5 rpm or less in order to suppress the deformation of the gas turbine rotor 1.

[0050] If the gas turbine GT stops, Figure 2 As shown in the flowchart of , the dry air system 50 is set (the step S1 of setting the dry air system 50). In this case, the dry air system 50 prepared in advance is arranged near the air intake housing 15, and the end of the air pipe 51 of the dry air system 50 is connected to the air shutoff valve 43 of the washing water system 40. In addition, a connecting flange may be provided at the end of the air pipe 51 of the dry air system 50, and a connecting flange may also be provided at the end of the connecting pipe 41c of the washing water system 40, and the two flanges may be connected to connect the dry air system 50 and the washing water system 40.

[0051] Next, the rust preventive agent 54 is arranged in the air intake casing 15 (rust preventive agent arrangement step S2). Note that the rust preventive agent arrangement step S2 may be performed after the gas turbine GT is stopped and before the aforementioned installation step S1 of the dry air system 50.

[0052] Next, the water shutoff valve 42 of the washing water system 40 is closed, the air shutoff valve 43 of the washing water system 40 is opened, and compressed air is supplied from the air supply source 55 to the air intake housing 15 via the dry air system 50 (dry air supply process S3). In the dry air supply process S3, dust and the like in the compressed air from the air supply source 55 are removed by the filter 52 of the dry air system 50. In addition, part of the moisture in the compressed air is removed by the dehumidifier 53 (dehumidification process S4). The compressed air from which the moisture is removed, i.e., the dry air, is sprayed into the air intake housing 15 via the air shutoff valve 43 of the washing water system 40, the connecting pipe 41c, a part of the washing water main pipe 41m, the plurality of washing water branch pipes 41b, and the plurality of nozzles 44.

[0053] The air in the gas turbine GT is drawn toward the chimney 39 due to the ventilation effect of the chimney 39 connected to the gas turbine GT even when the gas turbine rotor 1 is not rotating.

[0054] Therefore, the dry air supplied to the air intake casing 15 flows into the intermediate casing 25 through the compressor casing 12. The dry air flowing into the intermediate casing 25 is discharged from the gas turbine GT through the combustor 20, the turbine casing 32, and the exhaust casing 35. In this way, the dry air flows throughout the substantially entire gas turbine GT, so that the generation of rust in the gas turbine GT (particularly, in the compressor casing 12) can be suppressed.

[0055] Then, the rust-proofing components vaporized from the rust-proofing agent 54 disposed in the intake casing 15 flow through the gas turbine GT through the dry air. In this process, the rust-proofing components adhere to the inner peripheral surface of the compressor casing 12, the outer peripheral surface of the compressor rotor shaft 11s, the outer peripheral surface of the moving blades, the outer peripheral surface of the stationary blades, and the outer peripheral surface of the inlet guide vanes 14v, and suppress rusting of these.

[0056] like Figure 3 As shown, the above dry air supply step S3 is continuously executed until the gas turbine GT is restarted.

[0057] The part of the compressor housing 12 on the upstream side Dau of the axis is easy to be attached with dust and the like contained in the air passing through the intake duct 18 and the intake housing 15. Therefore, a cleaning water system 40 is provided to remove dust and the like attached to the part of the compressor housing 12 on the upstream side Dau of the axis. Specifically, dust and the like contained in the air passing through the intake duct 18 and the intake housing 15 are easy to be attached to the compressor moving blade cascade 11b and the compressor stationary blade cascade 13 on the upstream side Dau of the axis. Therefore, the cleaning water system 40 is preferably provided to focus on cleaning the compressor moving blade cascade 11b and the compressor stationary blade cascade 13 on the upstream side Dau of the axis. The part of the compressor housing 12 on the upstream side Dau of the axis is cleaned by water from the cleaning water system 40. In this cleaning, the air shutoff valve 43 of the cleaning water system 40 is closed, the water shutoff valve 42 is opened, and the water from the water supply source 45 is sprayed from the plurality of nozzles 44 toward the downstream side Dad of the axis. This cleaning is preferably performed after the gas turbine GT is stopped and before the rust preventive agent configuration step S2.

[0058] After the dry air supply step S3 is completed and before the gas turbine GT is started, the dry air system 50 disassembly step S5 and the rust preventive agent removal step S6 are performed. In addition, either the dry air system 50 disassembly step S5 or the rust preventive agent removal step S6 may be performed first.

[0059] As described above, in the present embodiment, when the gas turbine GT is stopped, dry air flows through substantially the entire interior of the gas turbine GT, and further, the rust-inhibiting components vaporized from the rust-inhibiting agent 54 flow through the interior of the gas turbine GT and adhere to the interior of the gas turbine GT, thereby suppressing the generation of rust in the gas turbine GT (particularly, in the compressor casing 12).

[0060] In the present embodiment, as described above, dry air from the dry air system 50 is supplied to the air intake housing 15 via a portion of the washing water system 40. That is, in the present embodiment, the portion for spraying fluid in the air intake housing 15 is shared by the washing water system 40 and the dry air system 50. Therefore, in the present embodiment, the equipment cost can be suppressed. In addition, since the nozzle 44 for spraying washing water into the air intake housing 15 also serves as a nozzle for spraying dry air, the number of nozzles 44 arranged in the air intake housing 15 is reduced, and the resistance of the air flowing through the air intake housing 15 can be suppressed.

[0061] In the present embodiment, the rust preventive 54 is disposed in the air intake housing 15, but the rust preventive 54 may be disposed in the air duct 51 of the dry air system 50. In this case, since the dry air system 50 has the rust preventive 54, it is not necessary to perform the rust preventive disposing step S2 and the rust preventive removing step S6 separately.

[0062] Furthermore, in the present embodiment, the dry air supply step S3 is continuously executed during the period from when the gas turbine GT is stopped to when the gas turbine GT is started. Figure 4 As shown, the dry air supplying step S3 may be performed intermittently a plurality of times.

[0063] "Second Implementation Method"

[0064] Hereinafter, regarding the rust prevention method of the gas turbine GT in the present embodiment and the embodiment of the gas turbine equipment capable of executing the method, refer to Figure 5 and Figure 6 Provide explanation.

[0065] like Figure 5 As shown, the gas turbine equipment in this embodiment is provided with a gas turbine GT, an intake duct 18, an exhaust duct 38, a chimney 39, a washing water system 40 capable of spraying washing water into the gas turbine GT, and a plurality of rust preventives 54, similarly to the gas turbine equipment in the first embodiment. Furthermore, the gas turbine equipment is provided with a second dry air system 60 in addition to the first dry air system 50 which is the same as the dry air system 50 in the first embodiment. That is, the gas turbine equipment in this embodiment is a device in which the second dry air system 60 is added to the gas turbine equipment in the first embodiment.

[0066] The second dry air system 60 is a system capable of supplying dry air into the intermediate housing 25. The second dry air system 60 includes an air pipeline 61 connected to an air supply source 65, a filter 62, a dehumidifier 63, a rust inhibitor 64, and an air stop valve 61v. The air pipeline 61 includes a main air pipeline 61m connected to the air supply source 65, a first air pipeline 61a connected to the main air pipeline 61m and connected to the intermediate housing 25, and a second air pipeline 61b connected to the main air pipeline 61m and connected to the combustion furnace 21 of the burner 20. The filter 62, the dehumidifier 63, the rust inhibitor 64, and the air stop valve 61v are all provided in the main air pipeline 61m. The air supply source 65 of the second dry air system 60 may be the same as or different from the air supply source 55 of the first dry air system 50. The intermediate housing 25 is provided with a housing side connection flange 25f for connecting to the first air pipeline 61a, and a first air pipeline side connection flange 61fa that can be connected to the housing side connection flange 25f is provided at the end of the first air pipeline 61a. The first air pipeline 61a is connected to the intermediate housing 25 by connecting the housing side connection flange 25f and the first air pipeline side connection flange 61fa. In addition, the burner 20 is provided with a burner side connection flange 23f for connecting to the combustion furnace 21 and the second air pipeline 61b, and a second air pipeline side connection flange 61fb that can be connected to the burner side connection flange 23f is provided at the end of the second air pipeline 61b. The second air pipeline 61b is connected to the combustion furnace 21 by connecting the housing side connection flange 25f and the second air pipeline side connection flange 61fb.

[0067] Next, regarding the rust prevention method of the gas turbine GT in the present embodiment, Figure 6 The flowchart shown is used for explanation.

[0068] In the rust prevention method of the present embodiment, the same steps as those of the rust prevention method of the first embodiment are also performed. That is, in the present embodiment, the same first dry air system 50 installation step S1 as the dry air system 50 installation step S1 of the first embodiment, the same rust preventive agent configuration step S2 as the rust preventive agent configuration step S2 of the first embodiment, the same first dry air supply step S3 as the dry air supply step S3 of the first embodiment, the same first dry air system 50 disassembly step S5 as the dry air system 50 disassembly step S5 of the first embodiment, and the same rust preventive agent removal step S6 as the rust preventive agent removal step S6 of the first embodiment are performed.

[0069] Furthermore, in the rust prevention method of the present embodiment, the installation step S1 b of the second dry air system 60 , the second dry air supply step S3 b , and the removal step S5 b of the second dry air system 60 are performed.

[0070] The installation step S1b of the second dry air system 60 is performed in parallel with the installation step S1 of the first dry air system 50, or is performed before or after the installation step S1 of the first dry air system 50. In the installation step S1b of the second dry air system 60, the second dry air system 60 prepared in advance is arranged next to the intermediate casing 25, and the first air pipe side connection flange 61fa of the second dry air system 60 is connected to the casing side connection flange 25f of the intermediate casing 25. In addition, the second air pipe side connection flange 61fb of the second dry air system 60 is connected to the burner side connection flange 23f of the burner 20. In addition, in the previous stage of the installation step S1b of the second dry air system 60, blind flanges are connected to the casing side connection flange 25f of the intermediate casing 25 and the burner side connection flange 23f of the burner 20. Therefore, after removing these blind flanges, the first air line side connecting flange 61fa is connected to the casing side connecting flange 25f, and the second air line side connecting flange 61fb is connected to the burner side connecting flange 23f.

[0071] The second dry air supply process S3b is performed in parallel with the first dry air supply process S3. In the second dry air supply process S3b, the air shutoff valve 61v of the second dry air system 60 is opened, and compressed air is supplied from the air supply source 65 to the intermediate housing 25 via the second dry air system 60. Dust and the like in the compressed air from the air supply source 65 are removed by the filter 62 of the second dry air system 60. In addition, a part of the moisture in the compressed air is removed by the dehumidifier 63 (dehumidification process S4b). The compressed air from which the moisture is removed, i.e., the dry air, is mixed with a rust-proof component vaporized from the rust-proof agent 64 provided in the air pipe 61. A part of the dry air mixed with the rust-proof component is injected into the intermediate housing 25 via the first air pipe 61a. In addition, another part of the dry air mixed with the rust-proof component is injected into the combustion furnace 21 via the second air pipe 61b.

[0072] The dry air injected into the center casing 25 from the second dry air system 60 flows into the combustor 20 together with the dry air injected into the first dry air system 50 and flows into the center casing 25 via the compressor casing 12. Furthermore, the dry air injected into the combustion furnace 21 flows into the tail pipe 22 of the combustor 20 together with the dry air flowing into the combustor 20 from the center casing 25. Then, the dry air passes through the turbine casing 32 and the exhaust casing 35 and is discharged from the gas turbine GT.

[0073] The dry air injected from the first dry air system 50 may be moistened by the moisture in the compressor housing 12 during the process of passing through the compressor housing 12. In addition, most of the rust-proof components from the rust-proof agent 54 in the intake housing 15 adhere to the blades and the like in the compressor housing 12. In the present embodiment, as described above, the dry air containing the rust-proof components is injected from the second dry air system 60 into the intermediate housing 25 and the combustion furnace 21 of the combustor 20. Therefore, compared with the first embodiment, the generation of rust in the discharge side portion in the compressor housing 12 or in the intermediate housing 25 (and further in the combustor 20) can be further suppressed.

[0074] The second dry air supply step S3b described above is also continuously performed until the gas turbine GT is restarted, similarly to the first dry air supply step S3. Figure 4 As described above, the first dry air supplying step S3 and the second dry air supplying step S3b may be intermittently performed a plurality of times.

[0075] When the second dry air supplying step S3b is completed, the second dry air system 60 disassembly step S5b is performed in parallel with the first dry air system 50 disassembly step S5, or before or after the first dry air system 50 disassembly step S5. At the end of the second dry air system 60 disassembly step S5b, a blind flange is connected to the housing side connecting flange 25f of the intermediate housing 25.

[0076] "Variation"

[0077] When there is very little dust or the like in the compressed air from the air supply sources 55, 65, that is, when the dust or the like in the air has been removed, the filter 52 of the dry air system 50 in the first embodiment, the filter 52 of the first dry air system 50 in the second embodiment, and the filter 62 of the second dry air system 60 can be omitted.

[0078] When there is very little moisture in the compressed air from the air supply sources 55, 65, that is, when the moisture in the air has been removed, the dehumidifier 53 of the dry air system 50 in the first embodiment, the dehumidifier 53 of the first dry air system 50 in the second embodiment, and the dehumidifier 63 of the second dry air system 60 can be omitted.

[0079] The dry air system 50 in the first embodiment and the first dry air system 50 and the second dry air system 60 in the second embodiment may be permanent.

[0080] The air pipe 61 of the dry air system 50 in the first embodiment and the air pipe 51 of the first dry air system 50 in the second embodiment may be directly connected to the intake housing 15 without passing through the wash water system 40 .

[0081] Furthermore, the present invention is not limited to the above-described embodiments, and various additions, changes, substitutions, partial deletions, etc. may be made without departing from the conceptual idea and gist of the present invention derived from the contents specified in the claims and their equivalents.

[0082] "P.S."

[0083] The gas turbine plant in the above embodiment can be understood, for example, as follows.

[0084] (1) A gas turbine facility according to a first aspect includes: a gas turbine GT; and a dry air system 50 capable of supplying dry air into the gas turbine GT.

[0085] The gas turbine GT includes a compressor 10 that compresses air A to generate compressed air Acom, a combustor 20 that burns fuel F in the compressed air Acom to generate combustion gas G, a turbine 30 that is driven by the combustion gas G, an intake casing 15, and an intermediate casing 25. The compressor 10 includes a compressor rotor 11 that is rotatable around an axis Ar, and a compressor casing 12 that covers the compressor rotor 11. The turbine 30 is disposed on the downstream side Dad of the axis upstream side Dau and the axis downstream side Dad in the axis direction Da in which the axis Ar extends relative to the compressor 10. The turbine 30 includes a turbine rotor 31 that is connected to the compressor rotor 11 and is rotatable around the axis Ar, and a turbine casing 32 that covers the turbine rotor 31. The intake casing 15 is connected to the end of the compressor casing 12 on the upstream side Dau of the axis so as to guide air into the compressor casing 12. The intermediate housing 25 is arranged between the compressor housing 12 and the turbine housing 32 in the axial direction Da, and is connected to the end of the compressor housing 12 on the axial downstream side Dad, and is connected to the end of the turbine housing 32 on the axial upstream side Dau, so that the compressed air Acom from the compressor 10 can flow in. The burner 20 is mounted on the intermediate housing 25 so that the compressed air Acom in the intermediate housing 25 can flow in, and the combustion gas G is sent into the turbine housing 32. The burner 20 has a combustion furnace 21 that can inject fuel F together with the compressed air Acom, and a tail pipe (or combustion tube) 22 in which the fuel F injected from the combustion furnace 21 can be burned in the compressed air Acom. The dry air system 50 has an air pipe 51 through which air from an air supply source 55 can flow, and is configured to supply the air flowing through the air pipe 51 as the dry air into the intake housing 15.

[0086] In this embodiment, when the gas turbine GT is stopped, dry air from the dry air system 50 is supplied to the air intake casing 15. On the exhaust side of the gas turbine GT, a chimney 39 for discharging exhaust gas from the gas turbine GT is basically provided. Therefore, due to the ventilation effect of the chimney 39, the air in the gas turbine GT is drawn to the chimney 39 side even when the gas turbine rotor 1 is not rotating. Therefore, the dry air supplied to the air intake casing 15 flows into the intermediate casing 25 through the compressor casing 12. The dry air flowing into the intermediate casing 25 passes through the combustor 20 and the turbine casing 32 and is discharged from the gas turbine GT. In this way, the dry air flows throughout the substantially entire gas turbine GT, so that the generation of rust in the gas turbine GT (especially in the compressor casing 12) can be suppressed.

[0087] (2) Gas Turbine Equipment According to Second Aspect The gas turbine equipment according to the first aspect is provided with a wash water system 40 that can spray water from the inside of the intake casing 15 into the inside of the compressor casing 12 .

[0088] The cleaning water system 40 includes a cleaning water pipeline 41 extending from a water supply source 45 into the air intake housing 15 and a nozzle 44 installed at the end of the cleaning water pipeline 41 in the air intake housing 15 and capable of spraying water toward the downstream side Dad of the axis. The air pipeline 51 is connected to the cleaning water pipeline 41 .

[0089] In this embodiment, the portion where the fluid is injected into the air intake housing 15 is shared by the wash water system 40 and the dry air system 50. Therefore, in this embodiment, it is possible to suppress an increase in equipment cost. In addition, the number of portions where the fluid is injected into the air intake housing 15 is reduced, and the resistance of the air flowing through the air intake housing 15 can be suppressed.

[0090] (3) Gas Turbine Installation in Third Aspect In the gas turbine installation in the first aspect or the second aspect, the dry air system 50 includes a dehumidifier 53 capable of removing moisture in the air.

[0091] The dehumidifier 53 is disposed on the air pipeline 51 .

[0092] In this embodiment, the moisture in the air supplied into the air intake casing 15 can be reduced.

[0093] (4) A gas turbine equipment in a fourth aspect is the gas turbine equipment in any one of the first to third aspects, further comprising a vaporizable rust inhibitor 54 disposed in the air duct 51 or in the air intake casing 15 .

[0094] In this embodiment, the rust-proofing component vaporized from the rust-proofing agent 54 flows into the compressor housing 12 from the intake housing 15 together with the dry air. Therefore, it is possible to suppress the rust-proofing component from adhering to the components in the intake housing 15 or the compressor housing 12 and causing rust to form on these components.

[0095] (5) Gas Turbine Equipment in Fifth Mode In the gas turbine equipment in any one of the first to fourth modes, in addition to the first dry air system 50 as the dry air system 50 , a second dry air system 60 capable of supplying dry air into the intermediate casing 25 is provided.

[0096] The second dry air system 60 includes an air pipeline 61 connecting the air supply source 65 and the intermediate housing 25 so as to guide the air from the air supply source 65 into the intermediate housing 25 .

[0097] In this embodiment, dry air is injected into the intermediate casing 25 from the second dry air system 60 .

[0098] This dry air passes through the combustor 20 and the turbine casing 32 and is discharged from the gas turbine GT together with the dry air injected from the first dry air system 50 and flows into the intermediate casing 25 via the compressor casing 12 .

[0099] The dry air injected from the first dry air system 50 may be moistened by the moisture in the compressor housing 12 while passing through the compressor housing 12. In this embodiment, as described above, the dry air is injected from the second dry air system 60 into the intermediate housing 25. Therefore, in this embodiment, the generation of rust in the discharge side portion in the compressor housing 12 or in the intermediate housing 25 (and further in the combustor 20) can be suppressed.

[0100] (6) In the gas turbine equipment of the sixth embodiment, in the gas turbine equipment of the fifth embodiment, the air pipeline 61 of the second dry air system 60 includes: a main air pipeline 61m connected to the air supply source 65; a first air pipeline 61a connected to the main air pipeline 61m and connected to the intermediate casing 25; and a second air pipeline 61b connected to the main air pipeline 61m and connected to the combustion furnace 21 of the burner 20.

[0101] In this embodiment, dry air can be injected into the combustion furnace 21 of the burner 20 .

[0102] (7) Gas Turbine Installation in Seventh Aspect In the gas turbine installation in the fifth aspect or the sixth aspect, the second dry air system 60 includes a dehumidifier 63 capable of removing moisture in the air.

[0103] The dehumidifier 63 of the second dry air system 60 is disposed in the air pipeline 61 of the second dry air system 60 .

[0104] In this embodiment, the moisture in the air supplied from the second dry air system 60 into the intermediate casing 25 can be reduced.

[0105] (8) Gas Turbine Equipment in an Eighth Aspect In the gas turbine equipment in any one of the fifth to seventh aspects, the second dry air system 60 includes a vaporizable rust inhibitor 64 disposed in the air pipe 61 of the second dry air system 60 .

[0106] In this embodiment, the rust-proof component vaporized from the rust-proof agent 64 is supplied to the center casing 25 together with the dry air. The rust-proof component flows from the center casing 25 to the combustor 20 and the turbine casing 32 together with the dry air. Therefore, it is possible to suppress the rust-proof component from adhering to the discharge side portion of the compressor casing 12, the inside of the center casing 25, and the components in the combustor 20, thereby preventing rust from being generated on these components.

[0107] The rust prevention method of the gas turbine GT in each of the above embodiments can be understood, for example, as follows.

[0108] (9) The rust prevention method for a gas turbine in the ninth aspect is applicable to the following gas turbine.

[0109] The gas turbine GT includes a compressor 10 that compresses air A to generate compressed air Acom, a combustor 20 that burns fuel F in the compressed air Acom to generate combustion gas G, a turbine 30 that is driven by the combustion gas G, an intake casing 15, and an intermediate casing 25. The compressor 10 includes a compressor rotor 11 that is rotatable around an axis Ar, and a compressor casing 12 that covers the compressor rotor 11. The turbine 30 is disposed on the downstream side Dad of the axis upstream side Dau and the axis downstream side Dad in the axis direction Da in which the axis Ar extends relative to the compressor 10. The turbine 30 includes a turbine rotor 31 that is connected to the compressor rotor 11 and is rotatable around the axis Ar, and a turbine casing 32 that covers the turbine rotor 31. The intake casing 15 is connected to the end of the compressor casing 12 on the upstream side Dau of the axis so as to guide air into the compressor casing 12. The intermediate casing 25 is arranged between the compressor casing 12 and the turbine casing 32 in the axial direction Da, and is connected to the end of the compressor casing 12 on the axial downstream side Dad, and is connected to the end of the turbine casing 32 on the axial upstream side Dau, so that the compressed air Acom from the compressor 10 can flow in. The combustor 20 is mounted on the intermediate casing 25 so that the compressed air Acom in the intermediate casing 25 can flow in, and the combustion gas G is sent into the turbine casing 32. The combustor 20 has a combustion furnace 21 that can inject fuel F together with the compressed air Acom, and a tail pipe (or combustion tube) 22 in which the fuel F injected from the combustion furnace 21 can be burned in the compressed air Acom.

[0110] In the rust prevention method of the gas turbine GT, the dry air supplying step S3 of supplying dry air into the intake casing 15 is performed while the gas turbine GT is stopped.

[0111] In this aspect, similarly to the first aspect of the gas turbine plant, it is possible to suppress the generation of rust in the gas turbine GT (particularly in the compressor casing 12 ).

[0112] (10) Gas Turbine Rust Prevention Method in Tenth Aspect In the gas turbine GT rust prevention method in the ninth aspect, the wash water system 40 for spraying water from the intake casing 15 into the compressor casing 12 is connected to the intake casing 15 .

[0113] The washing water system 40 includes: a washing water pipe 41 extending from a water supply source 45 into the air intake housing 15; and a nozzle 44 installed at the end of the washing water pipe 41 in the air intake housing 15 and capable of spraying water toward the axis downstream side Dad. In the dry air supplying step S3, the dry air is sent into the washing water pipe 41, and the dry air is supplied into the air intake housing 15 via the washing water pipe 41 and the nozzle 44.

[0114] In this embodiment, similarly to the second embodiment of the gas turbine equipment, it is possible to suppress an increase in equipment cost and to suppress the resistance of air flowing through the air intake casing 15 .

[0115] (11) Gas Turbine Rust Prevention Method in the Eleventh Aspect In the gas turbine GT rust prevention method in the ninth aspect or the tenth aspect, the dry air supplying step S3 includes a dehumidification step S4 of removing moisture from the air fed into the air intake casing 15 to generate the dry air.

[0116] In this embodiment, similarly to the third embodiment of the gas turbine equipment, it is possible to reduce the moisture in the air supplied into the air intake casing 15 .

[0117] (12) Gas turbine rust prevention method in the twelfth embodiment In the gas turbine rust prevention method of any one of the ninth to eleventh embodiments, after the gas turbine GT is stopped and before the dry air supply step S3, a rust inhibitor configuration step S2 of configuring a vaporizable rust inhibitor 54 in the intake casing 15 is performed.

[0118] In this embodiment, similarly to the fourth embodiment of the gas turbine equipment, it is possible to suppress the occurrence of rust on the components in the intake casing 15 or the compressor casing 12 due to the adhesion of the rust-proof component to these components.

[0119] (13) The rust prevention method for a gas turbine in the thirteenth embodiment In the rust prevention method for a gas turbine GT in any one of the ninth to twelfth embodiments, in addition to the first dry air supply step S3 as the dry air supply step S3, a second dry air supply step S3b for supplying dry air into the intermediate casing 25 is also performed.

[0120] In this embodiment, similarly to the fifth embodiment of the gas turbine equipment, it is possible to suppress the generation of rust in the discharge side portion in the compressor casing 12 or in the intermediate casing 25 (and further in the combustor 20 ).

[0121] (14) Gas Turbine Rust Prevention Method According to Fourteenth Aspect In the gas turbine GT rust prevention method according to the thirteenth aspect, dry air is supplied to the combustion furnace 21 of the combustor 20 in the second dry air supplying step S3 b .

[0122] (15) Rust prevention method for a gas turbine in a fifteenth aspect In the rust prevention method for a gas turbine GT in the thirteenth aspect or the fourteenth aspect, the second dry air supplying step S3b includes a dehumidification step S4b for removing moisture from the air fed into the intermediate casing 25 to generate the dry air.

[0123] In this embodiment, similarly to the seventh embodiment of the gas turbine plant, it is possible to reduce the moisture in the air supplied from the second dry air system 60 into the intermediate casing 25 .

[0124] Industrial Applicability

[0125] According to one aspect of the present invention, it is possible to suppress the generation of rust in the gas turbine.

[0126] Explanation of symbols

[0127] GT-gas turbine, 1-gas turbine rotor, 2f-front bearing, 2b-rear bearing, 10-compressor, 11-compressor rotor, 11s-compressor rotor shaft, 11b-compressor moving blades, 12-compressor housing, 13-compressor stationary blades, 14-intake air volume regulator, 14v-inlet guide vanes, 14d-driver, 15-intake housing, 15i-intake inner housing, 15o-intake outer housing, 16-intake strut, 17-air channel, 17i-intake port, 18-intake duct, 20-burner, 21-combustion furnace, 22-tail tube (or combustion tube), 23f-burner side connection flange, 24-fuel pipeline, 25-intermediate casing, 25f-casing side connection flange, 30-turbine, 31-turbine rotor, 31s-turbine rotor shaft, 31b-turbine moving blade grid, 32-turbine casing, 33-turbine stationary blade grid, 35-exhaust casing, 35i-exhaust inner casing, 35o-exhaust outer casing, 36-exhaust support, 37-exhaust channel, 38-exhaust pipe, 39-chimney, 40 -cleaning water system, 41-cleaning water pipeline, 41m-cleaning water main pipeline, 41c-connecting pipeline, 41b-cleaning water branch pipeline, 42-water shut-off valve, 43-air shut-off valve, 44-nozzle, 45-water supply source, 50-dry air system or first dry air system, 51-air pipeline, 52-filter, 53-dehumidifier, 54-rust inhibitor, 55-air supply source, 60-second dry air system, 61-air pipeline, 61m-main air pipeline, 61a-first air pipeline, 61 b-second air pipeline, 61fa-first air pipeline side connecting flange, 61fb-second air pipeline side connecting flange, 61v-air shut-off valve, 62-filter, 63-dehumidifier, 64-rust inhibitor, 65-air supply source, A-air, Acom-compressed air, F-fuel, G-combustion gas, EG-exhaust gas, Ar-axis, Da-axis direction, Dau-axis upstream side, Dad-axis downstream side, Dc-circumferential, Dr-radial, Dri-radial inside, Dro-radial outside.

Claims

1. A gas turbine device comprising: gas turbines; and a dry air system capable of supplying dry air to the gas turbine; The gas turbine includes: a compressor that compresses air to generate compressed air; a burner capable of burning fuel in the compressed air to generate combustion gas; a turbine, drivable by the combustion gases; an intake housing; and an intermediate housing, The compressor comprises: a compressor rotor rotatable about an axis line; and a compressor housing covering the compressor rotor. The turbine is arranged on the downstream side of the axis line of the compressor, of the upstream side and the downstream side in the axis line direction in which the axis line extends. The turbine comprises: a turbine rotor connected to the compressor rotor and rotatable about the axis; and a turbine housing covering the turbine rotor. The intake housing is connected to the end portion of the compressor housing on the upstream side of the axis so as to guide air into the compressor housing. The intermediate housing is arranged between the compressor housing and the turbine housing in the axial direction, at the end portion of the compressor housing on the downstream side of the axial direction, and is connected to the end portion of the turbine housing on the upstream side of the axial direction so that the compressed air from the compressor can flow in. The burner is mounted on the intermediate casing so that the compressed air in the intermediate casing can flow in and the combustion gas is sent into the turbine casing. The combustor comprises: a combustion furnace capable of injecting fuel together with the compressed air; and a tail pipe capable of allowing the fuel injected from the combustion furnace to burn in the compressed air. The dry air system includes an air duct through which air from an air supply source can flow, and is configured to supply the air flowing through the air duct into the intake housing as the dry air.

2. The gas turbine equipment according to claim 1, comprising a wash water system capable of spraying water from inside the intake casing into the compressor casing. The cleaning water system comprises: a cleaning water pipeline extending from a water supply source into the air intake housing; and a nozzle installed at the end of the cleaning water pipeline in the air intake housing and capable of spraying water toward the downstream side of the axis. The air pipeline is connected to the cleaning water pipeline.

3. The gas turbine plant according to claim 1 or 2, wherein: The dry air system has a dehumidifier capable of removing moisture from the air. The dehumidifier is arranged on the air pipeline. 4 . The gas turbine equipment according to claim 1 , comprising a vaporizable rust inhibitor disposed in the air duct or in the air intake casing.

5. The gas turbine equipment according to claim 1 or 2, further comprising, in addition to the first dry air system as the dry air system, a second dry air system capable of supplying dry air into the intermediate casing. The second dry air system has an air pipeline connecting the air supply source and the intermediate housing so as to guide the air from the air supply source into the intermediate housing.

6. The gas turbine plant according to claim 5, wherein: The air pipeline of the second dry air system comprises: a main air pipeline connected to the air supply source; a first air pipeline connected to the main air pipeline and connected to the intermediate shell; and a second air pipeline connected to the main air pipeline and connected to the combustion furnace of the burner.

7. The gas turbine plant according to claim 5, wherein: The second dry air system has a dehumidifier capable of removing moisture from the air, The dehumidifier of the second dry air system is arranged in the air pipeline of the second dry air system.

8. The gas turbine plant according to claim 5, wherein: The second dry air system has a vaporizable rust inhibitor disposed in the air line of the second dry air system.

9. A method for preventing rust of a gas turbine, comprising: a compressor that compresses air to generate compressed air; a burner capable of burning fuel in the compressed air to generate combustion gas; a turbine, drivable by the combustion gases; an intake housing; and an intermediate housing, The compressor comprises: a compressor rotor rotatable about an axis line; and a compressor housing covering the compressor rotor. The turbine is arranged on the downstream side of the axis line of the compressor, of the upstream side and the downstream side in the axis line direction in which the axis line extends. The turbine comprises: a turbine rotor connected to the compressor rotor and rotatable about the axis; and a turbine housing covering the turbine rotor. The intake housing is connected to the end portion of the compressor housing on the upstream side of the axis so as to guide air into the compressor housing. The intermediate housing is arranged between the compressor housing and the turbine housing in the axial direction, connected to the end of the compressor housing on the downstream side of the axial line, and connected to the end of the turbine housing on the upstream side of the axial line, so that the compressed air from the compressor can flow in. The burner is mounted on the intermediate casing so that the compressed air in the intermediate casing can flow in and the combustion gas can be sent into the turbine casing. The combustor comprises: a combustion furnace capable of injecting fuel together with the compressed air; and a tail pipe capable of allowing the fuel injected from the combustion furnace to burn in the compressed air. The gas turbine rust prevention method is performed by: The dry air supplying step supplies dry air into the air intake casing while the gas turbine is stopped.

10. The rust prevention method for a gas turbine according to claim 9, wherein: A cleaning water system for spraying water from the air intake housing into the compressor housing is connected to the air intake housing, The cleaning water system comprises: a cleaning water pipeline extending from a water supply source into the air intake housing; and a nozzle installed at an end of the cleaning water pipeline in the air intake housing and capable of spraying water toward the downstream side of the axis. In the dry air supplying step, The dry air is sent into the washing water pipeline, and the dry air is supplied into the air intake housing through the washing water pipeline and the nozzle.

11. The rust prevention method for a gas turbine according to claim 9 or 10, wherein: The dry air supplying step includes a dehumidification step of removing moisture from the air fed into the air intake casing to generate the dry air.

12. The rust prevention method for a gas turbine according to claim 9 or 10, wherein: After the gas turbine is stopped and before the dry air supplying step, a rust preventive placing step of placing a vaporizable rust preventive in the intake casing is performed.

13. The rust prevention method for a gas turbine according to claim 9 or 10, wherein: In addition to the first dry air supplying step as the dry air supplying step, a second dry air supplying step of supplying dry air into the intermediate casing is performed.

14. The rust prevention method for a gas turbine according to claim 13, wherein: In the second dry air supplying step, dry air is supplied to the combustion furnace of the burner.

15. The rust prevention method for a gas turbine according to claim 13, wherein: The second dry air supplying step includes a dehumidification step of removing moisture from the air fed into the intermediate casing to generate the dry air.

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