Rust prevention method for gas turbine and gas turbine equipment capable of implementing this method

Abstract

Gas turbine equipment according to the present invention comprises a gas turbine and a drying air system. The drying air system has an air line down which air from an air supply source can flow. The drying air system is configured such that air that has flowed down the air line can be supplied into an intake casing of the gas turbine as drying air.

Description

[Technical Field]

[0001] The present disclosure relates to a method for preventing corrosion in a gas turbine and a gas turbine installation capable of carrying out this method. This application claims priority based on Japanese Patent Application No. 2022-204295, filed on December 21, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] A gas turbine has 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.

[0003] The compressor has a compressor rotor rotatable about an axis and a compressor casing that covers the compressor rotor. The turbine is disposed axially downstream from the compressor. The turbine has a turbine rotor connected to the compressor rotor and rotatable about an axis and a turbine casing that covers the turbine rotor.

[0004] The intake casing is connected to the axially upstream end of the compressor casing so as to introduce air into the compressor casing. The intermediate casing is disposed between the compressor casing and the turbine casing in the axial direction. The combustor is attached to the intermediate casing so that compressed air discharged from the compressor into the intermediate casing can flow into the combustor.

[0005] Patent Document 1 below discloses a gas turbine facility including the gas turbine described above, a cooling air system, and a drying air system.

[0006] The cooling air system may provide cooling air to a turbine rotor exposed to combustion gases during operation of the gas turbine, and the dry air system may provide dry air to the cooling air system during shutdown of the gas turbine.

[0007] In the gas turbine equipment described in Patent Document 1, by supplying dry air to the cooling air system while the gas turbine is not in operation, it is possible to suppress the occurrence of rust in the air piping that constitutes part of the cooling air system. [Prior art documents] [Patent documents]

[0008] [Patent Document 1] Japanese Patent Application Laid-Open No. 2015-140691 Summary of the Invention [Problem to be solved by the invention]

[0009] When a gas turbine is left out of operation for an extended period of time, rust may form inside the gas turbine. For this reason, there is a demand in the field of gas turbines for suppressing rust formation inside the gas turbine.

[0010] Therefore, an object of the present disclosure is to provide a rust prevention method for a gas turbine that can suppress the occurrence of rust inside the gas turbine, and gas turbine equipment on which this method can be implemented. [Means for solving the problem]

[0011] One aspect of a gas turbine facility for achieving the above object is to A gas turbine, During the shutdown of the gas turbine a dry air system capable of supplying dry air into the gas turbine; A volatile rust inhibitor,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 rotatable about an axis, and a compressor casing that covers the compressor rotor. The turbine is disposed on the downstream side of the compressor between an upstream side and a downstream side in the axial direction in which the axis extends. The turbine includes a turbine rotor connected to the compressor rotor and rotatable about the axis, and a turbine casing that covers the turbine rotor. The intake casing is connected to the upstream end of the compressor casing so as to introduce air into the compressor casing. The intermediate casing is disposed between the compressor casing and the turbine casing in the axial direction, and is connected to an end of the compressor casing on the downstream side in the axial direction so that the compressed air from the compressor can flow therein, and is connected to an end of the turbine casing on the upstream side in the axial direction. The combustor is attached to the intermediate casing so that the compressed air in the intermediate casing can flow therein and the combustion gas can be sent into the turbine casing. The drying air system has an air line through which air from an air supply source can flow, and is configured to supply the air flowing through the air line into the intake casing as the dried air. The rust inhibitor is disposed inside the intake casing, downstream of the axis from a position where the dry air is supplied into the intake casing.

[0012] In this aspect, dry air from the dry air system is supplied into the intake casing while the gas turbine is stopped. A chimney is generally provided on the exhaust side of the gas turbine to discharge exhaust gas from the gas turbine. Therefore, the air inside the gas turbine is drawn toward the chimney due to the draft effect of the chimney, even when the gas turbine rotor is not rotating. The dry air supplied into the intake casing then flows into the intermediate casing via the compressor casing. The dry air that has flowed into the intermediate casing then flows through the combustor and turbine casing before being exhausted from the gas turbine. Because the dry air flows throughout almost the entire gas turbine, rusting inside the gas turbine, particularly inside the compressor casing, can be suppressed.

[0013] The corrosion prevention method for a gas turbine, which is one aspect for achieving the above object, is applied to the following gas turbine. This 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 rotatable about an axis and a compressor casing covering the compressor rotor. The turbine is disposed on the downstream side of the compressor between an upstream side and a downstream side in the axial direction in which the axis extends. The turbine includes a turbine rotor connected to the compressor rotor and rotatable about the axis, and a turbine casing covering the turbine rotor. The intake casing is connected to the upstream end of the compressor casing so as to introduce air into the compressor casing. The intermediate casing is disposed between the compressor casing and the turbine casing in the axial direction, and is connected to an end of the compressor casing on the downstream side in the axial direction so that the compressed air from the compressor can flow in, and is connected to an end of the turbine casing on the upstream side in the axial direction. The combustor is attached to 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. In this gas turbine rust prevention method, a dry air supply step is performed to supply dry air into the intake casing while the gas turbine is stopped. At the same time, a rust inhibitor disposing step is performed in which a volatile rust inhibitor is disposed in the intake casing after the gas turbine is stopped and before the dry air supply step. In the rust inhibitor disposing step, the rust inhibitor is disposed in the intake casing downstream of the axis from a position where the dry air is supplied into the intake casing. .

[0014] In this aspect, similarly to the first aspect of the gas turbine facility, it is possible to suppress the occurrence of rust inside the gas turbine, particularly inside the compressor casing. [Effects of the Invention]

[0015] According to one aspect of the present disclosure, rust formation within a gas turbine can be suppressed. [Brief explanation of the drawings]

[0016] [Figure 1] 1 is a schematic configuration diagram of a gas turbine facility according to a first embodiment of the present disclosure. FIG. [Figure 2] 3 is a flowchart showing the procedure for executing a corrosion prevention method for a gas turbine in the first embodiment according to the present disclosure. [Figure 3] 3 is a time chart of a corrosion prevention method for a gas turbine in the first embodiment according to the present disclosure. [Figure 4] 6 is a time chart of a corrosion prevention method for a gas turbine in a modified example of the first embodiment according to the present disclosure. [Figure 5] FIG. 4 is a schematic configuration diagram of a gas turbine facility according to a second embodiment of the present disclosure. [Figure 6] 10 is a flowchart showing the procedure for executing a corrosion prevention method for a gas turbine according to a second embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0017] Hereinafter, various embodiments of a gas turbine rust prevention method and a gas turbine facility on which this method can be implemented according to the present disclosure will be described with reference to the drawings.

[0018] "First embodiment" Hereinafter, an embodiment of a method for preventing rust in a gas turbine and a gas turbine facility on which this method can be implemented will be described with reference to FIGS.

[0019] As shown in FIG. 1 , the gas turbine facility in this embodiment includes a gas turbine GT, an intake duct 18, an exhaust duct 38, a chimney 39, a wash water system 40 capable of injecting wash water into the gas turbine GT, a dry air system 50 capable of supplying dry air into the gas turbine GT, and a plurality of rust inhibitors 54.

[0020] The gas turbine GT includes a compressor 10 capable of compressing air A to generate compressed air Acom, a plurality of combustors 20 that burn fuel F in the compressed air Acom to generate combustion gas G, a turbine 30 that is driven by the high-temperature, high-pressure combustion gas G, an intake casing 15 that can guide the air A from the intake duct 18 to the compressor 10, an exhaust casing 35 through which exhaust gas EG, which is the combustion gas G exhausted from the turbine 30, flows, an intermediate casing 25, a front bearing 2f, and a rear bearing 2b.

[0021] The compressor 10 includes a compressor rotor 11 rotatable about an axis Ar, a compressor casing 12 that covers the compressor rotor 11, multiple compressor stator vane rows 13, and an intake air flow rate regulator 14. The turbine 30 includes a turbine rotor 31 rotatable about the axis Ar, a turbine casing 32 that covers the turbine rotor 31, and multiple turbine stator vane rows 33. In the following description, the direction in which the axis Ar extends is referred to as the axial direction Da, one side of the axial direction Da is referred to as the axial upstream side Dau, and the other side of the axial direction Da is referred to as the axial downstream side Dad. The circumferential direction centered on the axis Ar is simply referred to as the circumferential direction Dc. The direction perpendicular to the axis Ar is referred to as the radial direction Dr, and the side of the radial direction Dr that approaches the axis Ar is referred to as the radially inner side Dri, and the opposite side is referred to as the radially outer side Dro.

[0022] The compressor 10 is disposed on the axial upstream side Dau with respect to the turbine 30. The compressor rotor 11 has a compressor rotor shaft 11s that extends in the axial direction Da about the axis Ar, and a plurality of compressor rotor blade rows 11b attached to the compressor rotor shaft 11s. The plurality of compressor rotor blade rows 11b are aligned in the axial direction Da. Each compressor rotor blade row 11b is composed of a plurality of rotor blades aligned in the circumferential direction Dc. One of a plurality of compressor stator vane rows 13 is disposed on the axial downstream side Dad of each of the plurality of compressor rotor blade rows 11b. Each compressor stator vane row 13 is attached inside the compressor casing 12. Each compressor stator vane row 13 is composed of a plurality of stator vanes aligned in the circumferential direction Dc. The intake air amount regulator 14 has a plurality of inlet guide vanes 14v and a driver 14d that can change the orientation of each inlet guide vane 14v. The plurality of inlet guide vanes 14v are arranged on the axially upstream side Dau of the plurality of compressor rotor blade rows 11b. The plurality of inlet guide vanes 14v are arranged side by side in the circumferential direction.

[0023] The turbine rotor 31 has a turbine rotor shaft 31s that extends in the axial direction Da around the axis Ar, and a plurality of turbine rotor blade rows 31b attached to the turbine rotor shaft 31s. The plurality of turbine rotor blade rows 31b are aligned in the axial direction Da. Each turbine rotor blade row 31b is made up of a plurality of rotor blades aligned in the circumferential direction Dc. One of the plurality of turbine stator blade rows 33 is arranged on the axial upstream side Dau of each of the plurality of turbine rotor blade rows 31b. Each turbine stator blade row 33 is attached inside the turbine casing 32. Each turbine stator blade row 33 is made up of a plurality of stator blades aligned in the circumferential direction Dc.

[0024] The intermediate casing 25 is disposed between the compressor casing 12 and the turbine casing 32 in the axial direction Da. An end of the intermediate casing 25 on the axial upstream side Dau is connected to an end of the compressor casing 12 on the axial downstream side Dad. An end of the intermediate casing 25 on the axial downstream side Dad is connected to an end of the turbine casing 32 on the axial upstream side Dau. The multiple combustors 20 are attached to the intermediate casing 25 and lined up in the circumferential direction Dc.

[0025] The combustor 20 has a burner 21 capable of injecting fuel F and compressed air Acom, and a transition piece (or combustion piece) 22 in which the fuel injected from the burner 21 can be combusted in the compressed air Acom. A fuel line 24 capable of guiding fuel F from a fuel supply source to the burner 21 is connected to the burner 21. In the transition piece 22, the fuel is combusted in the compressed air Acom, and combustion gas G is generated. The transition piece 22 can guide this combustion gas G into the turbine casing 32.

[0026] The intake casing 15 is connected to the axially upstream end Dau of the compressor casing 12. The intake casing 15 has an intake inner casing 15i, an intake outer casing 15o, and a plurality of intake struts 16. The intake inner casing 15i is cylindrical and centered on the axis Ar, and covers the portion of the compressor rotor shaft 11s that is axially upstream of the inlet guide vane 14v. The intake inner casing 15i is formed so as to gradually extend radially outward Dro as it approaches the axially upstream end Dau. The intake outer casing 15o is cylindrical and centered on the axis Ar, and is disposed radially outward Dro and spaced apart from the intake inner casing 15i. The axially downstream end Dad of the intake outer casing 15o is connected to the axially upstream end Dau of the compressor casing 12. The intake outer casing 15o is also formed so as to gradually increase in diameter toward the radially outer side Dro as it increases toward the axial upstream side Dau. The space between the intake inner casing 15i and the intake outer casing 15o in the radial direction forms an air passage 17 that guides air into the compressor casing 12. An intake port 17i is formed between the axially upstream end Dau of the intake inner casing 15i and the axially upstream end Dau of the intake outer casing 15o. This intake port 17i opens from the air passage 17 toward the radially outer side Dro. An intake duct 18 is connected to the intake casing 15. Air from the intake duct 18 flows into the air passage 17 of the intake casing 15 through the intake port 17i of the intake casing 15. A plurality of intake struts 16 are aligned in the circumferential direction Dc between the intake inner casing 15i and the intake outer casing 15o. The radially inner end Dri of the intake strut 16 is connected to the intake inner casing 15i, and the radially outer end Dro of the intake strut 16 is connected to the intake outer casing 15o.

[0027] The exhaust casing 35 is connected to the axially upstream end Dau of the turbine casing 32. The exhaust casing 35 has an exhaust inner casing 35i, an exhaust outer casing 35o, and multiple exhaust struts 36. The exhaust inner casing 35i is cylindrical and centered on the axis Ar, and covers a portion of the turbine rotor shaft 31s that is axially downstream Dad of the multiple turbine blade rows 31b. The exhaust outer casing 35o is cylindrical and centered on the axis Ar, and is disposed radially outwardly Dro with a gap therebetween from the exhaust inner casing 35i. The axially upstream end Dau of the exhaust outer casing 35o is connected to the axially downstream end Dad of the turbine casing 32. The space between the exhaust inner casing 35i and the exhaust outer casing 35o in the radial direction Dr forms an exhaust passage 37 through which exhaust gas EG, which is combustion gas G exhausted from the turbine 30, flows. The multiple exhaust struts 36 are arranged in the circumferential direction Dc between the inner exhaust casing 35i and the outer exhaust casing 35o. The radially inner ends Dri of the exhaust struts 36 are connected to the inner exhaust casing 35i. The radially outer ends Dro of the exhaust struts 36 are connected to the outer exhaust casing 35o.

[0028] An exhaust duct 38 is connected to the axial downstream end Dad of the exhaust casing 35. A chimney 39 is connected to the axial downstream end Dad of this exhaust duct 38. Exhaust gas EG from the turbine 30 is exhausted from the chimney 39 via the exhaust casing 35 and exhaust duct 38. Note that a heat recovery boiler that uses the heat of the exhaust gas EG to generate steam may be installed in the exhaust duct 38.

[0029] The compressor rotor 11 and the turbine rotor 31 are located on the same axis Ar and are connected to each other to form the gas turbine rotor 1. A rotor of a generator GEN is connected to this gas turbine rotor 1. An axially upstream portion Dau of the gas turbine rotor 1 is supported by a front bearing 2f. An axially downstream portion Dad of the gas turbine rotor 1 is supported by a rear bearing 2b. The front bearing 2f is disposed at a position in the axial direction Da where multiple intake struts 16 are disposed. This front bearing 2f is supported by multiple intake struts 16 via an intake inner casing 15i. The rear bearing 2b is disposed at a position in the axial direction Da where multiple exhaust struts 36 are disposed. This rear bearing 2b is supported by multiple exhaust struts 36 via an exhaust inner casing 35i.

[0030] The flush water system 40 includes a flush water line 41 extending from a water supply source 45 into the intake casing 15 and multiple nozzles 44 attached to the end of the flush water line 41 inside the intake casing 15. The flush water line 41 includes a main flush water line 41m connected to the water supply source 45, a connection line 41c connected midway along the main flush water line 41m, multiple branch flush water lines 41b branching off from the main flush water line 41m at its end, a water stop valve 42, and an air stop valve 43. The ends of the multiple branch flush water lines 41b are aligned in the circumferential direction Dc inside the intake casing 15. A nozzle 44 is attached to each end of the multiple branch flush water lines 41b, capable of spraying water flowing through the flush water line 41 toward the axial downstream side Dad. The water stop valve 42 is located in the main flush water line 41m, closer to the water supply source 45 than the connection line 41c. An air stop valve 43 is provided at the end of the connecting line 41c.

[0031] The dry air system 50 includes 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 that stores compressed air, or a compressor that generates compressed air. The compressed air tank may be shared, for example, within a plant that includes a gas turbine GT. The compressor may, for example, draw in outside air and compress it. The end of the air line 51 is connected to the air stop valve 43 of the cleaning water system 40 before use in the dry air system 50. The dehumidifier 53 may be any type of dehumidifier that can remove moisture from the air supplied from the air supply source 55. The dehumidifier 53 may be, for example, a type that cools the air to condense the moisture in the air and remove the moisture, or a type that uses a desiccant or desiccant to remove moisture from the air.

[0032] A plurality of rust inhibitors 54 are placed inside the intake casing 15 before the dry air system 50 is used. The rust inhibitors 54 are volatile solids containing rust-preventing components. The rust inhibitors 54 are placed in, for example, a mesh bag and attached to the intake outer casing 15o, the intake strut 16, the nozzle 44 of the cleaning water system 40, or the like. An example of the rust inhibitor 54 is Ferroguard (a registered trademark of USC Corporation). The rust inhibitor 54 may also be a volatile liquid. In this case, the liquid rust inhibitor 54 is impregnated into cotton or the like, placed in a mesh bag, and attached to the intake outer casing 15o or the like.

[0033] Next, a rust prevention method for a gas turbine GT according to this embodiment will be described.

[0034] The rust prevention method in this embodiment is performed while the gas turbine GT is stopped. Specifically, as shown in the time chart of FIG. 3 , the method is performed from when the fuel supply to the gas turbine GT is stopped and the operation of the gas turbine GT is stopped until the gas turbine GT starts to start up. Note that stopping the gas turbine GT includes not only a case where the gas turbine rotor 1 is not rotating at all, but also a case where the gas turbine GT is turning. In this case, the air in the compressor casing 12, the intermediate casing 25, and the turbine casing 32 is agitated by the gas turbine rotor 1, so that the air density, air humidity, and the like are approximately uniform within each of the casings 12, 25, and 32. Note that turning means rotating the gas turbine rotor 1 at 5 rpm or less to suppress deformation of the gas turbine rotor 1.

[0035] When the gas turbine GT is shut down, the dry air system 50 is installed (installation step S1 of the dry air system 50) as shown in the flowchart of Fig. 2. In this case, the dry air system 50 that has been prepared in advance is placed near the intake casing 15, and the end of the air line 51 of this dry air system 50 is connected to the air stop valve 43 of the cleaning water system 40. It is also possible to provide a connection flange at the end of the air line 51 of the dry air system 50, and also provide a connection flange at the end of the connection line 41c of the cleaning water system 40, and connect both flanges to connect the dry air system 50 and the cleaning water system 40.

[0036] Next, the rust inhibitor 54 is placed inside the intake casing 15 (rust inhibitor placing step S2). Note that this rust inhibitor placing step S2 may be performed after the gas turbine GT is stopped and before the above-described dry air system 50 installation step S1.

[0037] Next, the water stop valve 42 of the cleaning water system 40 is closed, and the air stop valve 43 of the cleaning water system 40 is opened, and compressed air is supplied from the air supply source 55 into the intake casing 15 via the dry air system 50 (dry air supply step S3). In this dry air supply step S3, dust and the like in the compressed air from the air supply source 55 is removed by the filter 52 of the dry air system 50. Also, some of the moisture in this compressed air is removed by the dehumidifier 53 (dehumidification step S4). The dry air, which is the compressed air from which the moisture has been removed, is sprayed into the intake casing 15 via the air stop valve 43 of the cleaning water system 40, the connection line 41c, part of the cleaning water main line 41m, the plurality of cleaning water branch lines 41b, and the plurality of nozzles 44.

[0038] The air inside the gas turbine GT is drawn toward the chimney 39 due to the draft effect of the chimney 39 connected to the gas turbine GT even when the gas turbine rotor 1 is not rotating. Therefore, the dry air supplied into the intake casing 15 passes through the compressor casing 12 and then flows into the intermediate casing 25. The dry air that has flowed into the intermediate casing 25 passes through the combustor 20, the turbine casing 32, and the exhaust casing 35, and is then exhausted from the gas turbine GT. In this way, the dry air flows throughout almost the entire interior of the gas turbine GT, and therefore, it is possible to suppress the occurrence of rust inside the gas turbine GT, and in particular inside the compressor casing 12.

[0039] Furthermore, the rust-preventive components vaporized from the rust-preventive agent 54 disposed inside the intake casing 15 flow through the gas turbine GT with the dry air. During this process, the rust-preventive components adhere to the inner circumferential surface of the compressor casing 12, the outer circumferential surface of the compressor rotor shaft 11s, the outer circumferential surfaces of the rotor blades, the outer circumferential surfaces of the stator vanes, and the outer circumferential surfaces of the inlet guide vanes 14v, thereby suppressing the formation of rust thereon.

[0040] The above-described dry air supply step S3 is continuously executed until immediately before the gas turbine GT is restarted, as shown in FIG.

[0041] Dust and the like contained in the air that has passed through the intake duct 18 and the intake casing 15 easily adheres to the axially upstream portion Dau of the compressor casing 12. For this reason, a washing water system 40 is provided to remove dust and the like that has adhered to the axially upstream portion Dau of the compressor casing 12. Specifically, dust and the like contained in the air that has passed through the intake duct 18 and the intake casing 15 easily adheres to the compressor rotor blade row 11b and the compressor stator blade row 13 on the axially upstream side Dau. For this reason, it is desirable to provide the washing water system 40 so that it can intensively wash the compressor rotor blade row 11b and the compressor stator blade row 13 on the axially upstream side Dau. The axially upstream portion Dau of the compressor casing 12 is washed with water from this washing water system 40. In this cleaning, the air stop valve 43 of the cleaning water system 40 is closed, the water stop valve 42 is opened, and water from a water supply source 45 is sprayed from a plurality of nozzles 44 toward the axial downstream side Dad. This cleaning is preferably performed after the gas turbine GT is stopped and before the rust inhibitor application step S2.

[0042] After the dry air supply step S3 is completed and before the start of the gas turbine GT, a removal step S5 of the dry air system 50 and a rust inhibitor removal step S6 are executed. Either of the removal step S5 of the dry air system 50 or the rust inhibitor removal step S6 may be executed first.

[0043] As described above, in this embodiment, while the gas turbine GT is stopped, dry air flows throughout almost the entire interior of the gas turbine GT, and the rust-preventive components vaporized from the rust inhibitor 54 flow through the gas turbine GT and adhere to the interior of the gas turbine GT, making it possible to suppress the occurrence of rust inside the gas turbine GT, and in particular inside the compressor casing 12.

[0044] In this embodiment, as described above, dry air from the dry air system 50 is supplied into the intake casing 15 via a part of the cleansing water system 40. That is, in this embodiment, the part that injects fluid into the intake casing 15 is shared by the cleansing water system 40 and the dry air system 50. Therefore, in this embodiment, equipment costs can be reduced. Furthermore, since the nozzles 44 that inject cleansing water into the intake casing 15 also serve as nozzles that inject dry air, the number of nozzles 44 arranged inside the intake casing 15 can be reduced, and resistance to the air flowing inside the intake casing 15 can be reduced.

[0045] In this embodiment, the rust inhibitor 54 is placed inside the intake casing 15, but the rust inhibitor 54 may be placed in the air line 51 of the dry air system 50. In this case, the dry air system 50 will have the rust inhibitor 54, so there is no need to separately perform the rust inhibitor placement step S2 and the rust inhibitor removal step S6.

[0046] Furthermore, in this embodiment, the dry air supply step S3 is executed continuously from the time the gas turbine GT is stopped until the start of startup of the gas turbine GT. However, the dry air supply step S3 may be executed intermittently multiple times from the time the gas turbine GT is stopped until the start of startup of the gas turbine GT, as shown in FIG.

[0047] Second Embodiment Hereinafter, an embodiment of a rust prevention method for a gas turbine GT and a gas turbine facility capable of implementing this method will be described with reference to FIGS. 5 and 6. FIG.

[0048] 5, the gas turbine facility of this embodiment, like the gas turbine facility of the first embodiment, includes a gas turbine GT, an intake duct 18, an exhaust duct 38, a chimney 39, a wash water system 40 capable of injecting wash water into the gas turbine GT, and a plurality of rust inhibitors 54. Furthermore, this gas turbine facility includes a first dry air system 50 that is the same as the dry air system 50 of the first embodiment, as well as a second dry air system 60. That is, the gas turbine facility of this embodiment is a facility in which the second dry air system 60 is added to the gas turbine facility of the first embodiment.

[0049] The second dry air system 60 is a system capable of supplying dry air into the intermediate casing 25. The second dry air system 60 includes an air line 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 line 61 includes a main air line 61m connected to the air supply source 65, a first air line 61a connected to the main air line 61m and also connected to the intermediate casing 25, and a second air line 61b connected to the main air line 61m and also connected to the burner 21 of the combustor 20. The filter 62, the dehumidifier 63, the rust inhibitor 64, and the air stop valve 61v are all provided in the main air line 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 casing 25 is provided with a casing-side connection flange 25f for connection to the first air line 61a, and a first air-line-side connection flange 61fa connectable to the casing-side connection flange 25f is provided at the end of the first air line 61a. The first air line 61a is connected to the intermediate casing 25 by connecting the casing-side connection flange 25f to the first air-line-side connection flange 61fa. The combustor 20 is also provided with a combustor-side connection flange 23f for connecting the burner 21 to the second air line 61b, and a second air-line-side connection flange 61fb connectable to the combustor-side connection flange 23f is provided at the end of the second air line 61b. The second air line 61b is connected to the burner 21 by connecting the casing-side connection flange 25f to the second air-line-side connection flange 61fb.

[0050] Next, a rust prevention method for a gas turbine GT according to this embodiment will be described with reference to the flowchart shown in FIG.

[0051] The rust prevention method of this embodiment also performs the same steps as the rust prevention method of the first embodiment. That is, this embodiment performs the installation step S1 of the first dry air system 50, which is the same as the installation step S1 of the dry air system 50 of the first embodiment, the rust inhibitor arrangement step S2, which is the same as the rust inhibitor arrangement step S2 of the first embodiment, the first dry air supply step S3, which is the same as the dry air supply step S3 of the first embodiment, the removal step S5 of the first dry air system 50, which is the same as the removal step S5 of the dry air system 50 of the first embodiment, and the rust inhibitor removal step S6, which is the same as the rust inhibitor removal step S6 of the first embodiment.

[0052] Furthermore, in the rust prevention method of this embodiment, an installation step S1b of the second dry air system 60, a second dry air supply step S3b, and a removal step S5b of the second dry air system 60 are performed.

[0053] 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 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, which has been prepared in advance, is disposed next to the intermediate casing 25, and the first air line 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. Furthermore, the second air line side connection flange 61fb of the second dry air system 60 is connected to the combustor side connection flange 23f of the combustor 20. Note that, prior to 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 combustor side connection flange 23f of the combustor 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 combustor side connecting flange 23f.

[0054] The second dry air supply step S3b is performed in parallel with the first dry air supply step S3. In this second dry air supply step S3b, the air stop valve 61v of the second dry air system 60 is opened, and compressed air is supplied from the air supply source 65 into the intermediate casing 25 via the second dry air system 60. Dust and other contaminants in the compressed air from the air supply source 65 are removed by the filter 62 of the second dry air system 60. A portion of the moisture in the compressed air is removed by the dehumidifier 63 (dehumidification step S4b). The dry air, which is the compressed air from which moisture has been removed, is mixed with a rust-preventive component vaporized from the rust inhibitor 64 provided in the air line 61. A portion of the dry air mixed with the rust-preventive component is injected into the intermediate casing 25 via the first air line 61a. Another portion of the dry air mixed with the rust-preventive component is injected into the burner 21 via the second air line 61b.

[0055] The dry air injected from the second dry air system 60 into the intermediate casing 25 flows into the combustor 20 together with the dry air injected from the first dry air system 50 and flowing into the intermediate casing 25 via the compressor casing 12. Furthermore, the dry air injected into the burner 21 flows into the transition piece 22 of the combustor 20 together with the dry air that has flowed into the combustor 20 from the intermediate casing 25. Then, this dry air passes through the turbine casing 32 and the exhaust casing 35 and is exhausted from the gas turbine GT.

[0056] The dry air injected from the first dry air system 50 may become wet with moisture inside the compressor casing 12 as it passes through the compressor casing 12. Furthermore, most of the rust-preventive components from the rust inhibitor 54 inside the intake casing 15 adhere to the blades and the like inside the compressor casing 12. In this embodiment, as described above, dry air containing the rust-preventive components is injected from the second dry air system 60 into the intermediate casing 25 and the burner 21 of the combustor 20. Therefore, the occurrence of rust in the discharge side portion of the compressor casing 12, inside the intermediate casing 25, and further inside the combustor 20 can be suppressed more effectively than in the first embodiment.

[0057] Similar to the first dry air supplying step S3, the second dry air supplying step S3b is also continuously executed until immediately before the gas turbine GT is restarted. Note that, as described with reference to Fig. 4, the first dry air supplying step S3 and the second dry air supplying step S3b may be executed intermittently multiple times.

[0058] When the second dry air supply step S3b is completed, a removal step S5b of the second dry air system 60 is carried out in parallel with the removal step S5 of the first dry air system 50, or before or after the removal step S5 of the first dry air system 50. At the end of the removal step S5b of the second dry air system 60, a blind flange is connected to the casing-side connecting flange 25f of the intermediate casing 25.

[0059] "Variations" If there is very little dust or the like in the compressed air from the air supply sources 55, 65, i.e., if the dust or the like in the air has already been removed, the filter 52 of the dry air system 50 in the first embodiment, and the filter 52 of the first dry air system 50 and the filter 62 of the second dry air system 60 in the second embodiment may be omitted.

[0060] If the moisture content in the compressed air from the air supply sources 55, 65 is extremely low, i.e., if the moisture in the air has already been removed, the dehumidifier 53 of the dry air system 50 in the first embodiment, and the dehumidifier 53 of the first dry air system 50 and the dehumidifier 63 of the second dry air system 60 in the second embodiment may be omitted.

[0061] 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 permanently installed.

[0062] The air line 61 of the dry air system 50 in the first embodiment and the air line 51 of the first dry air system 50 in the second embodiment may be connected directly to the intake casing 15 without passing through the cleaning water system 40 .

[0063] Furthermore, the present disclosure is not limited to the embodiments described above, and various additions, modifications, substitutions, partial deletions, etc. are possible within the scope of the conceptual idea and spirit of the present invention as derived from the content defined in the claims and their equivalents.

[0064] "Addendum" The gas turbine facilities in the above embodiments can be understood, for example, as follows.

[0065] (1) A gas turbine facility according to a first aspect includes: The gas turbine GT includes a gas turbine GT and a dry air system 50 capable of supplying dry air into the gas turbine GT. The gas turbine GT includes a compressor 10 capable of compressing air A to generate compressed air Acom, a combustor 20 capable of burning fuel F in the compressed air Acom to generate combustion gas G, a turbine 30 capable of being driven by the combustion gas G, an intake casing 15, and an intermediate casing 25. The compressor 10 includes a compressor rotor 11 rotatable about an axis Ar and a compressor casing 12 covering the compressor rotor 11. The turbine 30 is disposed on the downstream side Dad of the axial direction Da in which the axis Ar extends, out of an upstream side Dau and a downstream side Dad, relative to the compressor 10. The turbine 30 includes a turbine rotor 31 connected to the compressor rotor 11 and rotatable about the axis Ar, and a turbine casing 32 covering the turbine rotor 31. The intake casing 15 is connected to the axially upstream end Dau of the compressor casing 12 so as to guide air into the compressor casing 12. The intermediate casing 25 is disposed between the compressor casing 12 and the turbine casing 32 in the axial direction Da, and is connected to the axially downstream end Dad of the compressor casing 12 so as to allow the compressed air Acom from the compressor 10 to flow therein, and is also connected to the axially upstream end Dau of the turbine casing 32. The combustor 20 is attached to the intermediate casing 25 so as to allow the compressed air Acom in the intermediate casing 25 to flow therein and to send the combustion gas G into the turbine casing 32. The combustor 20 includes a burner 21 that can inject fuel F together with the compressed air Acom, and a transition piece (or combustion piece) 22 that can combust the fuel F injected from the burner 21 in the compressed air Acom. The dry air system 50 has an air line 51 through which air from an air supply source 55 can flow, and is configured so that the air flowing through the air line 51 can be supplied into the intake casing 15 as the dry air.

[0066] In this embodiment, dry air from the dry air system 50 is supplied into the intake casing 15 while the gas turbine GT is stopped. A chimney 39 that discharges exhaust gas from the gas turbine GT is basically provided on the exhaust side of the gas turbine GT. For this reason, the air inside the gas turbine GT is drawn toward the chimney 39 due to the draft effect of the chimney 39, even when the gas turbine rotor 1 is not rotating. Therefore, the dry air supplied into the intake casing 15 passes through the compressor casing 12 and flows into the intermediate casing 25. The dry air that has flowed into the intermediate casing 25 passes through the combustor 20 and the turbine casing 32 and is then exhausted from the gas turbine GT. In this way, the dry air flows throughout almost the entire inside of the gas turbine GT, thereby suppressing the occurrence of rust inside the gas turbine GT, particularly inside the compressor casing 12.

[0067] (2) The gas turbine facility according to the second aspect includes: The gas turbine equipment according to the first aspect includes a wash water system 40 capable of injecting water from inside the intake casing 15 into the compressor casing 12. The wash water system 40 includes a wash water line 41 extending from a water supply source 45 into the intake casing 15, and a nozzle 44 attached to an end of the wash water line 41 inside the intake casing 15 and capable of injecting water toward the axial downstream side Dad. The air line 51 is connected to the wash water line 41.

[0068] In this embodiment, the parts that inject fluid inside the intake casing 15 are shared by the cleaning water system 40 and the dry air system 50. Therefore, in this embodiment, it is possible to suppress an increase in equipment costs. Also, the number of parts that inject fluid inside the intake casing 15 is reduced, and resistance to the air flowing inside the intake casing 15 can be suppressed.

[0069] (3) The gas turbine facility according to the third aspect includes: In the gas turbine facility according to the first or second aspect, the dry air system 50 includes a dehumidifier 53 capable of removing moisture from the air. The dehumidifier 53 is provided in the air line 51.

[0070] In this embodiment, the moisture content in the air supplied into the intake casing 15 can be reduced.

[0071] (4) A gas turbine facility according to a fourth aspect includes: The gas turbine facility according to any one of the first to third aspects includes a vaporizable corrosion inhibitor 54 disposed in the air line 51 or in the intake casing 15.

[0072] In this embodiment, the rust-preventing components vaporized from the rust-preventing agent 54 flow together with dry air from the intake casing 15 into the compressor casing 12. This prevents the rust-preventing components from adhering to components inside the intake casing 15 and the compressor casing 12, thereby preventing rust from forming on these components.

[0073] (5) A gas turbine facility according to a fifth aspect includes: In the gas turbine facility according to any one of the first to fourth aspects, 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. The second dry air system 60 has an air line 61 connecting the air supply source 65 and the intermediate casing 25 so as to introduce air from the air supply source 65 into the intermediate casing 25.

[0074] In this embodiment, dry air is injected into the intermediate casing 25 from the second dry air system 60 . This dry air, together with the dry air injected from the first dry air system 50 and flowing into the intermediate casing 25 via the compressor casing 12, passes through the combustor 20 and the turbine casing 32 and is exhausted from the gas turbine GT.

[0075] The dry air injected from the first dry air system 50 may become wet with moisture inside the compressor casing 12 while passing through the compressor casing 12. In this embodiment, as described above, the dry air is injected from the second dry air system 60 into the intermediate casing 25. Therefore, in this embodiment, it is possible to suppress the occurrence of rust in the discharge side portion of the compressor casing 12, inside the intermediate casing 25, and further inside the combustor 20.

[0076] (6) A gas turbine facility according to a sixth aspect includes: In the gas turbine equipment of the fifth aspect, the air line 61 of the second drying air system 60 has a main air line 61m connected to the air supply source 65, a first air line 61a connected to the main air line 61m and also connected to the intermediate casing 25, and a second air line 61b connected to the main air line 61m and also connected to the burner 21 of the combustor 20.

[0077] In this embodiment, dry air can be injected into the burner 21 of the combustor 20 .

[0078] (7) A gas turbine facility according to a seventh aspect includes: In the gas turbine facility according to the fifth or sixth aspect, the second dry air system 60 includes a dehumidifier 63 capable of removing moisture from the air. The dehumidifier 63 of the second dry air system 60 is provided in the air line 61 of the second dry air system 60.

[0079] In this embodiment, the moisture content of the air supplied from the second dry air system 60 into the intermediate casing 25 can be reduced.

[0080] (8) In an eighth aspect, the gas turbine facility comprises: In a gas turbine equipment according to any one of the fifth to seventh embodiments, the second dry air system 60 has a volatile corrosion inhibitor 64 arranged in the air line 61 of the second dry air system 60.

[0081] In this embodiment, the rust-preventing component vaporized from the rust inhibitor 64 is supplied together with dry air into the intermediate casing 25. This rust-preventing component flows together with the dry air from the intermediate casing 25 to the combustor 20 and the turbine casing 32. As a result, the rust-preventing component adheres to the components on the discharge side of the compressor casing 12, inside the intermediate casing 25, and inside the combustor 20, thereby preventing rust from forming on these components.

[0082] The rust prevention method for the gas turbine GT in each of the above embodiments can be understood, for example, as follows.

[0083] (9) The corrosion prevention method for a gas turbine according to the ninth aspect is applied to the following gas turbines. The gas turbine GT includes a compressor 10 capable of compressing air A to generate compressed air Acom, a combustor 20 capable of burning fuel F in the compressed air Acom to generate combustion gas G, a turbine 30 capable of being driven by the combustion gas G, an intake casing 15, and an intermediate casing 25. The compressor 10 includes a compressor rotor 11 rotatable about an axis Ar and a compressor casing 12 that covers the compressor rotor 11. The turbine 30 is disposed on the axial downstream side Dad of the axial upstream side Dau and the axial downstream side Dad in the axial direction Da in which the axis Ar extends with respect to the compressor 10. The turbine 30 includes a turbine rotor 31 connected to the compressor rotor 11 and rotatable about the axis Ar, and a turbine casing 32 that covers the turbine rotor 31. The intake casing 15 is connected to the axially upstream end Dau of the compressor casing 12 so as to guide air into the compressor casing 12. The intermediate casing 25 is disposed between the compressor casing 12 and the turbine casing 32 in the axial direction Da, and is connected to the axially downstream end Dad of the compressor casing 12 so as to allow the compressed air Acom from the compressor 10 to flow therein, and is also connected to the axially upstream end Dau of the turbine casing 32. The combustor 20 is attached to the intermediate casing 25 so as to allow the compressed air Acom in the intermediate casing 25 to flow therein and to send the combustion gas G into the turbine casing 32. The combustor 20 includes a burner 21 that can inject fuel F together with the compressed air Acom, and a transition piece (or combustion piece) 22 that can combust the fuel F injected from the burner 21 in the compressed air Acom. In this rust prevention method for a gas turbine GT, a dry air supply step S3 is executed in which dry air is supplied into the intake casing 15 while the gas turbine GT is stopped.

[0084] In this embodiment, similarly to the first embodiment of the gas turbine facility, the occurrence of rust inside the gas turbine GT, particularly inside the compressor casing 12, can be suppressed.

[0085] (10) A method for preventing rust of a gas turbine according to a tenth aspect includes the steps of: In the rust prevention method for a gas turbine GT according to the ninth aspect, a wash water system 40 that injects water from inside the intake casing 15 into the compressor casing 12 is connected to the intake casing 15. The wash water system 40 has a wash water line 41 that extends from a water supply source 45 to the inside of the intake casing 15, and a nozzle 44 that is attached to an end of the wash water line 41 inside the intake casing 15 and is capable of injecting water toward the axial downstream side Dad. In the dry air supply step S3, the dry air is sent into the wash water line 41, and the dry air is supplied into the intake casing 15 via the wash water line 41 and the nozzle 44.

[0086] In this embodiment, similarly to the second embodiment of the gas turbine facility, it is possible to suppress an increase in facility costs and also to suppress resistance to air flowing inside the intake casing 15.

[0087] (11) A corrosion prevention method for a gas turbine according to an eleventh aspect includes the steps of: In the rust prevention method for a gas turbine GT according to the ninth or tenth aspect, the dry air supply process S3 includes a dehumidification process S4 of removing moisture from the air sent into the intake casing 15 to generate the dry air.

[0088] In this embodiment, similarly to the third embodiment of the gas turbine facility, the moisture content in the air supplied into the intake casing 15 can be reduced.

[0089] (12) A method for preventing corrosion of a gas turbine according to a twelfth aspect includes the steps of: In the rust prevention method for a gas turbine GT according to any one of the ninth to eleventh embodiments, a rust prevention agent arrangement step S2 is executed after the gas turbine GT is stopped and before the dry air supply step S3, in which a volatile rust prevention agent 54 is arranged in the intake casing 15.

[0090] In this embodiment, similarly to the fourth embodiment of the gas turbine facility, the rust-preventive component adheres to the members inside the intake casing 15 and the compressor casing 12, thereby preventing rust from occurring on these members.

[0091] (13) A method for preventing corrosion of a gas turbine according to a thirteenth aspect includes the steps of: 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 is executed to supply dry air into the intermediate casing 25.

[0092] In this embodiment, similarly to the fifth embodiment of the gas turbine equipment, rust can be suppressed in the discharge side portion of the compressor casing 12, in the intermediate casing 25, and further in the combustor 20.

[0093] (14) A method for preventing corrosion of a gas turbine according to a fourteenth aspect includes the steps of: In the rust prevention method for a gas turbine GT according to the thirteenth aspect, dry air is supplied to the burner 21 of the combustor 20 in the second dry air supplying step.

[0094] (15) A method for preventing corrosion of a gas turbine according to a fifteenth aspect includes the steps of: In the rust prevention method for a gas turbine GT according to the thirteenth or fourteenth aspect, the second dry air supply step S3b includes a dehumidification step S4b of removing moisture from the air to be sent into the intermediate casing 25 to generate the dry air.

[0095] In this embodiment, similarly to the seventh embodiment of the gas turbine facility, the moisture content in the air supplied from the second dry air system 60 into the intermediate casing 25 can be reduced. [Industrial Applicability]

[0096] According to one aspect of the present disclosure, rust occurrence within a gas turbine can be suppressed. [Explanation of symbols]

[0097] GT: Gas turbine 1: Gas turbine rotor 2f: Front bearing 2b: rear bearing 10: Compressor 11: Compressor rotor 11s: Compressor rotor shaft 11b: Compressor rotor blade row 12: Compressor casing 13: Compressor stator blade row 14: Intake volume regulator 14v: Inlet guide vane 14d: Driver 15: Intake casing 15i: Intake inner casing 15o: Intake outer casing 16: Intake strut 17: Air passage 17i: Air intake 18: Intake duct 20: Combustor 21: Burner 22: Transition tube (or combustion tube) 23f: Combustor side connection flange 24: Fuel line 25: Intermediate casing 25f: Casing side connection flange 30: Turbine 31: Turbine rotor 31s: Turbine rotor shaft 31b: Turbine blade row 32: Turbine casing 33: Turbine stator blade row 35: Exhaust casing 35i: Exhaust inner casing 35o: Exhaust outer casing 36: Exhaust strut 37: Exhaust passage 38: Exhaust duct 39: Chimney 40: Cleaning water system 41: Cleaning water line 41m: Main washing water line 41c: Connection line 41b: Cleaning water branch line 42: Water stop valve 43: Air stop valve 44: Nozzle 45: Water supply source 50: Dry air system or first dry air system 51: Air line 52: Filter 53:Dehumidifier 54: Rust inhibitor 55:Air supply source 60: Second dry air system 61: Air line 61m: Main air line 61a: First air line 61b: Second air line 61fa: First air line side connection flange 61fb: Second air line side connection flange 61v:Air stop 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 line Da: Axial direction Dau: Axis upstream side Dad: Downstream of the axis Dc: Circumferential direction Dr: Radial direction Dri: Radial inner direction Dro: Radial outer side

Claims

1. A gas turbine, a dry air system capable of supplying dry air into the gas turbine while the gas turbine is stopped; A volatile rust inhibitor, Equipped with 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 rotatable about an axis and a compressor casing that covers the compressor rotor, the turbine is disposed on the axial downstream side of the compressor in an axial direction in which the axis extends, and the turbine includes a turbine rotor connected to the compressor rotor and rotatable about the axis, and a turbine casing covering the turbine rotor, the intake casing is connected to an end of the compressor casing on the upstream side in the axial direction so as to introduce air into the compressor casing; the intermediate casing is disposed between the compressor casing and the turbine casing in the axial direction, and is connected to an end of the compressor casing on a downstream side in the axial direction so that the compressed air from the compressor can flow in, and is connected to an end of the turbine casing on an upstream side in the axial direction; the combustor is attached to 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 includes a burner capable of injecting fuel together with the compressed air, and a transition piece in which the fuel injected from the burner can be combusted in the compressed air, 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 into the intake casing as the dry air, the rust inhibitor is disposed inside the intake casing, downstream of a position where the dry air is supplied into the intake casing along the axis. Gas turbine equipment.

2. The gas turbine equipment according to claim 1, a cleaning water system capable of injecting water from inside the intake casing into the compressor casing while the gas turbine is stopped; the wash water system includes a wash water line extending from a water supply source into the intake casing, and a nozzle attached to an end of the wash water line inside the intake casing and capable of spraying water toward the axial downstream side, The air line is connected to the flush water line. Gas turbine equipment.

3. The gas turbine facility according to claim 1 or 2, the dry air system has a dehumidifier capable of removing moisture from the air; The dehumidifier is provided in the air line. Gas turbine equipment.

4. The gas turbine facility according to claim 1 or 2, 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 is provided, The second drying air system has an air line connecting the air supply source and the intermediate casing so as to introduce air from the air supply source into the intermediate casing. Gas turbine equipment.

5. In the gas turbine equipment according to claim 4, the air lines of the second drying air system include a main air line connected to the air supply source, a first air line connected to the main air line and also connected to the intermediate casing, and a second air line connected to the main air line and also connected to the burner of the combustor. Gas turbine equipment.

6. In the gas turbine facility according to claim 4, the second dry air system has a dehumidifier capable of removing moisture from the air; the dehumidifier of the second dry air system is provided in the air line of the second dry air system. Gas turbine equipment.

7. In the gas turbine facility according to claim 4, the second dry air system has a volatile rust inhibitor disposed in the air line of the second dry air system. Gas turbine equipment.

8. The 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 rotatable about an axis and a compressor casing that covers the compressor rotor, the turbine is disposed on the axial downstream side of the compressor in an axial direction in which the axis extends, and the turbine includes a turbine rotor connected to the compressor rotor and rotatable about the axis, and a turbine casing covering the turbine rotor, the intake casing is connected to an end of the compressor casing on the upstream side in the axial direction so as to introduce air into the compressor casing; the intermediate casing is disposed between the compressor casing and the turbine casing in the axial direction, and is connected to an end of the compressor casing on a downstream side in the axial direction so that the compressed air from the compressor can flow in, and is connected to an end of the turbine casing on an upstream side in the axial direction; the combustor is attached to 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 includes a burner capable of injecting fuel together with the compressed air, and a transition piece in which the fuel injected from the burner can be combusted in the compressed air. A corrosion prevention method for a gas turbine, comprising: performing a dry air supplying step of supplying dry air into the intake casing while the gas turbine is stopped; performing a rust inhibitor disposing step of disposing a vaporizable rust inhibitor in the intake casing after the gas turbine is stopped and before the dry air supply step; In the rust inhibitor disposing step, the rust inhibitor is disposed in the intake casing, downstream of a position where the dry air is supplied into the intake casing along the axis. A method for preventing corrosion in gas turbines.

9. The rust prevention method for a gas turbine according to claim 8, a cleaning water system that injects water from inside the intake casing into the compressor casing while the gas turbine is stopped is connected to the intake casing; the wash water system includes a wash water line extending from a water supply source into the intake casing, and a nozzle attached to an end of the wash water line inside the intake casing and capable of spraying water toward the axial downstream side, In the dry air supplying step, the dry air is sent into the wash water line, and the dry air is supplied into the intake casing through the wash water line and the nozzle. A method for preventing corrosion in gas turbines.

10. The method for preventing rust of a gas turbine according to claim 8 or 9, The dry air supplying step includes a dehumidifying step of removing moisture from the air to be sent into the intake casing to generate the dry air. A method for preventing corrosion in gas turbines.

11. The method for preventing rust of a gas turbine according to claim 8 or 9, In addition to the first dry air supplying step as the dry air supplying step, a second dry air supplying step is carried out to supply dry air into the intermediate casing. A method for preventing corrosion in gas turbines.

12. The method for preventing rust of a gas turbine according to claim 11, In the second dry air supplying step, the dry air is supplied to the burner of the combustor. A method for preventing corrosion in gas turbines.

13. The method for preventing rust of a gas turbine according to claim 11, The second dry air supplying step includes a dehumidifying step of removing moisture from air to be sent into the intermediate casing to generate the dry air. A method for preventing corrosion in gas turbines.

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