A method for controlling a gas turbine system, a control device for executing this control method, and a gas turbine system.

Abstract

The goal is to reduce the restart time of the gas turbine while suppressing surging in the compressor. [Solution] The gas turbine equipment control method includes a fuel control step of controlling the opening degree of a fuel valve that can adjust the flow rate of fuel supplied to the combustor, and an extraction control step of controlling the opening degrees of a high-pressure extraction valve and a low-pressure side extraction valve that can adjust the flow rate of air extracted from the compressor. In the extraction control step, after the fuel valve is closed in the fuel control step, a partial extraction step is performed in which the low-pressure side extraction valve is open and the high-pressure extraction valve is closed.

Description

Technical Field

[0001] The present disclosure relates to a control method for a gas turbine facility, a control device that executes this control method, and a gas turbine facility.

Background Art

[0002] As a gas turbine facility, for example, there is a facility disclosed in Patent Document 1 below. This facility includes a gas turbine, a plurality of extraction lines, and an extraction valve provided for each of the plurality of extraction lines. The gas turbine has a compressor capable of compressing air, a combustor capable of generating combustion gas by burning fuel in the air compressed by the compressor, and a turbine drivable by the combustion gas. The plurality of extraction lines are all connected to the compressor and can extract the air in the compressor to the outside.

[0003] In this gas turbine facility, the extraction valves provided for each of the plurality of extraction lines are controlled for the purpose of suppressing the occurrence of surging in the compressor.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] In recent years, it has been required to shorten the time from when the fuel supply to the combustor of the gas turbine is stopped until the fuel supply to the combustor is resumed again, that is, the restart time of the gas turbine.

[0006] Therefore, an object of the present disclosure is to provide a technology capable of shortening the restart time of the gas turbine while suppressing the occurrence of surging in the compressor.

Means for Solving the Problems

[0007] A control method for gas turbine equipment, as one embodiment for achieving the aforementioned objective, is applicable to the following gas turbine equipment. The gas turbine system comprises a compressor capable of compressing air, a combustor capable of burning fuel in the air compressed by the compressor to produce combustion gas, and a turbine driven by the combustion gas; a fuel valve capable of adjusting the flow rate of fuel supplied to the combustor; a high-pressure bleed line and a low-pressure bleed line capable of bleeding air from inside the compressor to the outside; a high-pressure bleed valve provided in the high-pressure bleed line capable of adjusting the flow rate of air flowing through the high-pressure bleed line; and a low-pressure bleed valve provided in the low-pressure bleed line capable of adjusting the flow rate of air flowing through the low-pressure bleed line. The compressor comprises a compressor rotor rotatable about an axis and a compressor casing covering the compressor rotor. The turbine is positioned downstream of the compressor, between the upstream and downstream sides in the axial direction in which the axis extends. The compressor rotor has a compressor rotor shaft extending in the axial direction with respect to the axis, and a plurality of compressor blade rows mounted on the compressor rotor shaft in the axial direction. Both the high-pressure bleed line and the low-pressure bleed line are connected to the compressor casing. The position where the high-pressure bleed line is connected to the compressor casing is downstream of the axis than the position where the low-pressure bleed line is connected to the compressor casing. This gas turbine equipment control method includes a fuel control step that controls the opening degree of the fuel valve, and an extraction control step that controls the opening degrees of the high-pressure extraction valve and the low-pressure side extraction valve. In the extraction control step, after the fuel valve is closed in the fuel control step, a partial extraction step is performed in which the low-pressure side extraction valve is open and the high-pressure extraction valve is closed.

[0008] A control device for a gas turbine system, as one embodiment for achieving the aforementioned objective, is applicable to the following gas turbine system. The gas turbine system comprises a compressor capable of compressing air, a combustor capable of burning fuel in the air compressed by the compressor to produce combustion gas, and a turbine driven by the combustion gas; a fuel valve capable of adjusting the flow rate of fuel supplied to the combustor; a high-pressure bleed line and a low-pressure bleed line capable of bleeding air from inside the compressor to the outside; a high-pressure bleed valve provided in the high-pressure bleed line capable of adjusting the flow rate of air flowing through the high-pressure bleed line; and a low-pressure bleed valve provided in the low-pressure bleed line capable of adjusting the flow rate of air flowing through the low-pressure bleed line. The compressor comprises a compressor rotor rotatable about an axis and a compressor casing covering the compressor rotor. The turbine is positioned downstream of the compressor, between the upstream and downstream sides in the axial direction in which the axis extends. The compressor rotor has a compressor rotor shaft extending in the axial direction with respect to the axis, and a plurality of compressor blade rows mounted on the compressor rotor shaft in the axial direction. Both the high-pressure bleed line and the low-pressure bleed line are connected to the compressor casing. The position where the high-pressure bleed line is connected to the compressor casing is downstream of the axis than the position where the low-pressure bleed line is connected to the compressor casing. The control device for this gas turbine equipment includes a fuel controller that controls the opening degree of the fuel valve, and an extraction controller that controls the opening degrees of the high-pressure extraction valve and the low-pressure side extraction valve. After the fuel valve is closed by the fuel controller, the extraction controller performs a partial extraction process in which the low-pressure side extraction valve is open and the high-pressure extraction valve is closed.

[0009] A gas turbine equipment apparatus as one embodiment for achieving the above objective is: The system comprises the control device as described above, the gas turbine, the fuel valve, the high-pressure extraction line, the low-pressure extraction line, the high-pressure extraction valve, and the low-pressure extraction valve. [Effects of the Invention]

[0010] In one aspect of this disclosure, the restart time of the gas turbine can be shortened while suppressing the occurrence of surging in the compressor. [Brief explanation of the drawing]

[0011] [Figure 1] This is a schematic diagram of a gas turbine system in one embodiment of the present disclosure. [Figure 2] This is an explanatory diagram illustrating the operation of a gas turbine system in one embodiment of the present disclosure. [Modes for carrying out the invention]

[0012] The embodiments relating to this disclosure will be described below with reference to the drawings.

[0013] "Embodiment of a Gas Turbine System" The gas turbine equipment in this embodiment will be described below with reference to Figures 1 and 2.

[0014] As shown in Figure 1, the gas turbine equipment in this embodiment includes a gas turbine GT, a fuel line 21, a fuel valve 22, a low-pressure side extraction line 41, a high-pressure side extraction line 42, a low-pressure side extraction valve 43, a high-pressure extraction valve 44, and a control device 50.

[0015] The gas turbine GT comprises a compressor 10 capable of compressing air A to produce compressed air Acom, a plurality of combustors 20 that burn fuel F in the compressed air Acom to produce combustion gas G, a turbine 30 driven by the high-temperature, high-pressure combustion gas G, an intake casing 17 capable of guiding air A to the compressor 10, an exhaust casing 37 through which exhaust gas EG, which is the combustion gas G exhausted from the turbine 30, flows, an intermediate casing 27, a front bearing 2f, and a rear bearing 2b.

[0016] The compressor 10 includes a compressor rotor 11 rotatable about axis Ar, a compressor casing 12 covering the compressor rotor 11, a plurality of compressor stator blade rows 13, and an intake volume regulator 14. The turbine 30 includes a turbine rotor 31 rotatable about axis Ar, a turbine casing 32 covering the turbine rotor 31, and a plurality of turbine stator blade rows 33. In the following, the direction in which axis Ar extends will be referred to as the axial direction Da, one side of the axial direction Da will be referred to as the upstream side Dau, and the other side of the axial direction Da will be referred to as the downstream side Da. The circumferential direction around axis Ar will simply be referred to as the circumferential direction Dc. The direction perpendicular to axis Ar will be referred to as the radial direction Dr, the side of the radial direction Dr that approaches axis Ar will be referred to as the radially inward Dri, and the opposite side will be referred to as the radially outward Dro.

[0017] The compressor 10 is positioned axially upstream Dau relative to the turbine 30. In other words, the turbine 30 is positioned axially downstream Dad relative to the compressor 10. The compressor rotor 11 has a compressor rotor shaft 11s extending axially Da with respect to the axis Ar, and a plurality of compressor rotor blade rows 11b attached to this compressor rotor shaft 11s. The plurality of compressor rotor blade rows 11b are aligned axially Da. Each compressor rotor blade row 11b consists of a plurality of rotor blades aligned circumferentially Dc. One of the plurality of compressor stator blade rows 13 is positioned axially downstream Dad of each of the plurality of compressor rotor blade rows 11b. Each compressor stator blade row 13 is mounted inside the compressor casing 12. Each compressor stator blade row 13 consists of a plurality of stator blades aligned circumferentially Dc. The intake volume regulator 14 includes a plurality of inlet guide vanes (IGVs) 14v and a driver 14d that can change the orientation of each inlet guide vane 14v. The plurality of inlet guide vanes 14v are positioned upstream Dau of the axis from the plurality of compressor blade rows 11b. The plurality of inlet guide vanes 14v are arranged in the circumferential direction Dc.

[0018] The annular space between the outer peripheral side of the compressor rotor shaft 11s and the inner peripheral side of the compressor casing 12 forms an air compression flow path 15 through which air A from the intake casing 17 flows and is compressed. The compressor casing 12 has a casing main body 12a and a plurality of stator blade retaining rings 12b. The casing main body 12a is cylindrical so as to cover the outer perimeters of a plurality of compressor rotor blade rows 11b, a plurality of compressor stator blade rows 13, and a plurality of inlet guide vanes 14v. The plurality of stator blade retaining rings 12b are arranged in the axial direction Da on the inner peripheral side of the casing main body 12a and in a portion downstream of the axis Dad in the casing main body 12a. The plurality of stator blade retaining rings 12b are all fixed to the casing main body 12a. The number of the plurality of stator blade retaining rings 12b in the present embodiment is, for example, four. Each of the plurality of stator blade retaining rings 12b holds at least one or more of the plurality of compressor stator blade rows 13. Among the plurality of compressor stator blade rows 13, the compressor stator blade row 13 positioned approximately in the middle in the axial direction Da and all the compressor stator blade rows 13 positioned downstream of the axis Dad from this compressor stator blade row 13 are held by the plurality of stator blade retaining rings 12b. Between the plurality of stator blade retaining rings 12b, an extraction chamber 16 into which air A from the air compression flow path 15 can flow is formed. The plurality of extraction chambers 16 are arranged in the axial direction Da.

[0019] The turbine rotor 31 has a turbine rotor shaft 31s extending in the axial direction Da about an 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 arranged in the axial direction Da. Each turbine rotor blade row 31b is composed of a plurality of rotor blades arranged in the circumferential direction Dc. On the upstream side Dau of each axis of the plurality of turbine rotor blade rows 31b, one of the plurality of turbine stator blade rows 33 is arranged. Each turbine stator blade row 33 is attached inside a turbine casing 32. Each turbine stator blade row 33 is composed of a plurality of stator blades arranged in the circumferential direction Dc.

[0020] The intermediate casing 27 is arranged between the compressor casing 12 and the turbine casing 32 in the axial direction Da. The end of the upstream side Dau of the axis of the intermediate casing 27 is connected to the end of the downstream side Dad of the axis of the compressor casing 12. The end of the downstream side Dad of the axis of the intermediate casing 27 is connected to the end of the upstream side Dau of the axis of the turbine casing 32. The plurality of combustors 20 are attached to the intermediate casing 27 side by side in the circumferential direction Dc.

[0021] The intake casing 17 is connected to the end of the upstream side Dau of the axis of the compressor casing 12. The intake casing 17 has an intake inner casing 17i, an intake outer casing 17o, and a plurality of intake struts 18. The intake inner casing 17i forms a cylindrical shape centered on the axis Ar and covers the portion on the upstream side Dau of the axis from the inlet guide vane 14v in the compressor rotor shaft 11s. This intake inner casing 17i is formed so as to gradually go toward the radially outer side Dro as it goes toward the upstream side Dau of the axis. The intake outer casing 17o forms a cylindrical shape centered on the axis Ar and is arranged at an interval on the radially outer side Dro with respect to the intake inner casing 17i. The end of the downstream side Dad of the axis of the intake outer casing 17o is connected to the end of the upstream side Dau of the axis of the compressor casing 来 自 西 陆 军 事 http: / / www.xilu.com 12. This intake outer casing 17o is also formed so as to gradually go toward the radially outer side Dro as it goes toward the upstream side Dau of the axis. The space between the intake inner casing 17i and the intake outer casing 17o in the radial direction forms an intake passage that guides air into the air compression flow path 15. The space between the end of the upstream side Dau of the axis of the intake inner casing 17i and the end of the upstream side Dau of the axis of the intake outer casing 和 吸 気 外 側 ケーシング17oの軸線上流側Dauの端との間が、吸気口17aiを形成する。この吸気口17aiは、吸気通路内から径方向外側Droに向かって開口している。複数の吸気ストラット18は、吸気内側ケーシング17iと吸気外側ケーシング17oとの間で周方向Dcに並んでいる。吸気ストラット18の径方向内側Driの端は、吸気内側ケーシング17iに接続されている。吸気ストラット18の径方向外側Droの端は、吸気外側ケーシング17oに接続されている。

[0022] It should be noted that there are some garbled or incorrect parts in the original text you provided, such as "来 自 西 陆 军 事 http: / / www.xilu.com" and "和 吸 気 外 側 ケーシング17oの軸線上流側Dauの端との間が、吸気口17aiを形成する。" which may affect the accuracy of the translation. I have tried my best to translate according to the existing content.The exhaust casing 37 is connected to the upstream end Dau of the turbine casing 32. The exhaust casing 37 comprises an inner exhaust casing 37i, an outer exhaust casing 37o, and a plurality of exhaust struts 38. The inner exhaust casing 37i is cylindrical with respect to the axis Ar and covers the portion of the turbine rotor shaft 31s downstream of the plurality of turbine blade rows 31b. The outer exhaust casing 37o is cylindrical with respect to the axis Ar and is positioned radially outward from the inner exhaust casing 37i at a distance of Dro. The upstream end Dau of the outer exhaust casing 37o is connected to the downstream end Dad of the turbine casing 32. The space between the inner exhaust casing 37i and the outer exhaust casing 37o in the radial direction Dr forms an exhaust passage through which the exhaust gas EG, which is the combustion gas G exhausted from the turbine 30, flows. Multiple exhaust struts 38 are arranged circumferentially in the direction Dc between the inner exhaust casing 37i and the outer exhaust casing 37o. The radially inner end Dri of each exhaust strut 38 is connected to the inner exhaust casing 37i. The radially outer end Dro of each exhaust strut 38 is connected to the outer exhaust casing 37o.

[0023] A chimney 39 is connected to the downstream side Da of the exhaust casing 37. Exhaust gas EG from the turbine 30 is discharged through the exhaust casing 37 and out of the chimney 39. In some cases, an exhaust duct is installed between the exhaust casing 37 and the chimney 39. In some cases, a heat recovery boiler that generates steam using the heat of the exhaust gas EG is installed between the exhaust casing 37 and the chimney 39.

[0024] 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. The rotor of the generator GEN is connected to this gas turbine rotor 1. In this embodiment, the generator GEN also functions as a starting motor to rotate the gas turbine rotor 1 when starting the gas turbine GT. The upstream portion of the gas turbine rotor 1 along the axis Dau is supported by the front bearing 2f. The downstream portion of the gas turbine rotor 1 along the axis Da is supported by the rear bearing 2b. The front bearing 2f is located in the axial direction Da where a plurality of intake struts 18 are arranged. This front bearing 2f is supported by a plurality of intake struts 18 via an intake inner casing 17i. The rear bearing 2b is located in the axial direction Da where a plurality of exhaust struts 38 are arranged. This rear bearing 2b is supported by a plurality of exhaust struts 38 via an exhaust inner casing 37i.

[0025] The fuel line 21 is connected to multiple combustors 20 so that fuel can be supplied to multiple combustors 20. A fuel valve 22 is provided in this fuel line 21 and can adjust the flow rate of fuel F flowing through the fuel line 21. In other words, the fuel valve 22 can adjust the flow rate of fuel F supplied to the multiple combustors 20.

[0026] Both the low-pressure side bleed line 41 and the high-pressure bleed line 42 are capable of bleeding air from inside the compressor 10 to the outside. The low-pressure side bleed valve 43 can adjust the flow rate of air flowing through the low-pressure side bleed line 41. The high-pressure bleed valve 44 can adjust the flow rate of air flowing through the high-pressure bleed line 42. The low-pressure side bleed valve 43 can adjust the flow rate of air flowing through the low-pressure side bleed line 41. In this embodiment, the low-pressure side bleed line 41 has a low-pressure bleed line 41a and an intermediate-pressure bleed line 41b. Also, in this embodiment, the low-pressure side bleed valve 43 has a low-pressure bleed valve 43a and an intermediate-pressure bleed valve 43b. The low-pressure bleed valve 43a can adjust the flow rate of air flowing through the low-pressure bleed line 41a. The intermediate-pressure bleed valve 43b can adjust the flow rate of air flowing through the intermediate-pressure bleed line 41b. The low-pressure extraction line 41a is connected to the compressor casing 12 so as to be able to communicate with the extraction chamber 16 located furthest upstream on the axis Dau among the multiple extraction chambers 16. The intermediate-pressure extraction line 41b is connected to the compressor casing 12 so as to be able to communicate with the extraction chamber 16 located at an intermediate position in the axial direction Da among the multiple extraction chambers 16. The high-pressure extraction line 42 is connected to the compressor casing 12 so as to be able to communicate with the extraction chamber 16 located furthest downstream on the axis Da among the multiple extraction chambers 16. Therefore, the position where the high-pressure extraction line 42 is connected to the compressor casing 12 is further downstream on the axis Da than the position where the intermediate-pressure extraction line 41b is connected to the compressor casing 12. Also, the position where the intermediate-pressure extraction line 41b is connected to the compressor casing 12 is further downstream on the axis Da than the position where the low-pressure extraction line 41a is connected to the compressor casing 12.

[0027] The low-pressure extraction line 41a, the medium-pressure extraction line 41b, and the high-pressure extraction line 42 are, for example, all open to the atmosphere or connected to the exhaust casing 37. The low-pressure extraction line 41a, the medium-pressure extraction line 41b, and the high-pressure extraction line 42 may also be connected to the turbine casing 32 to cool the high-temperature components of the turbine 30 with the air flowing through these lines. These high-temperature components of the turbine 30 are the turbine rotor blade row 31b and the turbine stator blade row 33, which are exposed to the combustion gas G.

[0028] The control device 50 includes a fuel controller 51 that controls the opening degree of the fuel valve 22, an IGV controller 52 that controls the operation of the intake volume regulator 14, and an bleed air controller 53 that controls the opening degree of the low-pressure bleed air valve 43a, the opening degree of the medium-pressure bleed air valve, and the opening degree of the high-pressure bleed air valve 44.

[0029] Furthermore, this control device 50 is a computer. The functions of each controller 51, 52, and 53 in this control device 50 are performed when a program stored in the computer's external storage device is loaded into the computer's main memory device, and this program is executed by the computer's CPU (Central Processing Unit).

[0030] Next, the operation of the gas turbine equipment will be explained according to Figure 2.

[0031] The fuel controller 51 performs a fuel control process S10 that controls the opening degree of the fuel valve 22. The extraction controller 53 performs an extraction control process S20 that controls the opening degree of the low-pressure extraction valve 43a, the opening degree of the medium-pressure extraction valve 43b, and the opening degree of the high-pressure extraction valve 44.

[0032] While the gas turbine GT is running and the gas turbine rotor 1 is rotating at its rated speed Nr, the fuel valve 22 is open and fuel is supplied to the multiple combustors 20. During this time, the fuel controller 51 determines the fuel flow rate in response to an external load command. As part of the fuel control process S10, the fuel controller 51 determines the opening degree of the fuel valve 22 according to this fuel flow rate and instructs the fuel valve 22 to set this opening degree. Also during this time, the IGV controller 52 determines the IGV opening degree according to this fuel flow rate and instructs the driver 14d of the intake air volume regulator 14 to set this IGV opening degree. Furthermore, during this time, the extraction controller 53 executes a non-extraction process S21 as part of the extraction control process S20, in which the low-pressure extraction valve 43 is closed and the high-pressure extraction valve 44 is also closed. During this non-extraction process S21, since the low-pressure extraction valve 43a is closed, no air flows into the low-pressure extraction line 41a. Furthermore, since the intermediate pressure extraction valve 43b is closed during the non-extraction process S21, no air flows into the intermediate pressure extraction line 41b. In addition, since the high pressure extraction valve 44 is closed during the non-extraction process S21, no air flows into the high pressure extraction line 42.

[0033] If the control device 50 receives a command from an external source to stop the gas turbine GT while it is running, or if it determines that the gas turbine GT should be stopped based on signals from sensors or other devices that detect various state quantities of the gas turbine GT, the fuel controller 51 instructs the fuel valve 22 to close as part of the fuel control process S10. As a result, the fuel valve 22 closes, fuel is no longer supplied to the multiple combustors 20, and the rotational speed of the gas turbine rotor 1 gradually decreases.

[0034] As the rotational speed of the gas turbine rotor 1 decreases, the likelihood of surging occurring in the compressor 10 increases. Therefore, when the fuel valve 22 closes, the extraction controller 53 executes a full extraction process S22 as part of the extraction control process S20, in which the low-pressure side extraction valve 43 and the high-pressure extraction valve 44 are opened. In this full extraction process S22, a portion of the air flowing through the air compression passage 15 of the compressor 10 flows through the low-pressure extraction line 41a, the medium-pressure extraction line 41b, and the high-pressure extraction line 42. As a result, the mass flow rate of air flowing out from the discharge port of the compressor casing 12 becomes less than the mass flow rate of air flowing into the compressor casing 12, thereby suppressing the occurrence of surging.

[0035] During the entire extraction process S22, when the rotational speed of the gas turbine rotor 1 decreases to a predetermined rotational speed Nhc, the extraction controller 53 keeps the low-pressure extraction valve 43 open while closing the high-pressure extraction valve 44, thereby executing a partial extraction process S23 as part of the extraction control process S20. In this partial extraction process S23, a portion of the air flowing through the air compression passage 15 of the compressor 10 flows through the low-pressure extraction line 41a and the intermediate-pressure extraction line 41b, but does not flow through the high-pressure extraction line 42. In this partial extraction process S23, as in the entire extraction process S22, the mass flow rate of air flowing out from the discharge port of the compressor casing 12 is less than the mass flow rate of air flowing into the compressor casing 12, thereby suppressing the occurrence of surging.

[0036] The predetermined rotational speed Nhc mentioned above is 30% or less of the rated rotational speed Nr, and at least 10% of it. Specifically, in this embodiment, the predetermined rotational speed Nhc is 20% of the rated rotational speed Nr. The extraction controller 53 determines whether the rotational speed of the gas turbine rotor 1 has reached the predetermined rotational speed Nhc based on the rotational speed output from the tachometer that detects the rotational speed of the gas turbine rotor 1, or the time it is assumed that the rotational speed of the gas turbine rotor 1 will reach the predetermined rotational speed Nhc after the fuel valve 22 is closed. The time it takes for the rotational speed of the gas turbine rotor 1 to reach the predetermined rotational speed Nhc after the fuel valve 22 is closed is, for example, 30 minutes.

[0037] When the rotational speed of the gas turbine rotor 1 reaches the turning speed Nt, the turning motor is driven, and the rotational speed of the gas turbine rotor 1 is maintained at the turning speed Nt. The turning speed Nt is a few rpm, less than 10 rpm. The purpose of turning the gas turbine rotor 1 to the turning speed Nt is to suppress the deflection of the gas turbine rotor 1 due to gravity acting on it. Furthermore, this turning is also performed to prevent thermal deformation of the compressor casing 12, intermediate casing 27, and turbine casing 32, which would otherwise occur if the gas turbine rotor 1 were stopped due to the accumulation of high-temperature gas in the upper parts of these casings 12, 27, and 32.

[0038] When a predetermined amount of time has elapsed since the start of the partial extraction process S23 and the possibility of surging has become extremely low, the extraction controller 53 executes a non-extraction process S24 as part of the extraction control process S20, which involves closing the low-pressure extraction valve 43a and the intermediate-pressure extraction valve 43b while keeping the high-pressure extraction valve 44 closed. The time period after the fuel valve 22 is closed in which the possibility of surging becomes extremely low is, for example, 30 minutes.

[0039] The aforementioned turning process ends when the entire compressor 10 and the entire turbine 30 reach near room temperature, and the gas turbine rotor 1 comes to a complete stop.

[0040] When the control device 50 receives an external load command while the gas turbine rotor 1 is completely stopped or turning, the control device 50 starts the generator GEN as a starting motor and gradually increases the rotational speed of the gas turbine rotor 1. When the rotational speed of the gas turbine rotor 1 increases to a predetermined speed, the control device 50 stops the generator GEN as a starting motor. Meanwhile, the fuel controller 51 of the control device 50 instructs the fuel valve 22 to open as part of the fuel control process S10. As a result, fuel F from the fuel line 21 is supplied to multiple combustors 20. The fuel F supplied to the combustors 20 burns within the combustors 20 to produce combustion gas G. This combustion gas G flows into the turbine casing 32 and rotates the turbine rotor 31. Therefore, the rotational speed of the gas turbine rotor 1 increases further to the rated speed Nr.

[0041] As the rotational speed of the gas turbine rotor 1 increases, the likelihood of surging occurring in the compressor 10 also increases. For this reason, the extraction controller 53 opens the low-pressure extraction valve 43a, the medium-pressure extraction valve 43b, and the high-pressure extraction valve 44 during this process as well. As a result, the mass flow rate of air flowing out from the discharge port of the compressor casing 12 becomes less than the mass flow rate of air flowing into the compressor casing 12, thereby suppressing the occurrence of surging.

[0042] Incidentally, while fuel F is supplied to the combustor 20 and the gas turbine GT is running, air flows through the air compression passage 15 of the compressor 10. As this air flows towards the downstream side Da of the axis in the air compression passage 15, it gradually becomes more high in pressure and temperature. Therefore, while the gas turbine GT is running, the compressor casing 12 and compressor rotor 11, which are exposed to the high-temperature air, become very hot. In particular, the temperature at the downstream side Da of the axis in the compressor casing 12 and compressor rotor 11 is several hundred degrees higher than the temperature near the middle of the axial direction Da in the compressor casing 12 and compressor rotor 11.

[0043] As the fuel valve 22 closes and the rotational speed of the gas turbine rotor 1 gradually decreases, the temperatures of the compressor casing 12 and the compressor rotor 11 also gradually decrease. However, because the heat capacity of the compressor casing 12 is smaller than that of the compressor rotor 11, the rate at which the temperature of the compressor casing 12 decreases is faster than the rate at which the temperature of the compressor rotor 11 decreases. Therefore, the rate of contraction of the thermally expanded compressor casing 12 temporarily becomes higher than the rate of contraction of the thermally expanded compressor rotor 11. Consequently, as the fuel valve 22 closes and the rotational speed of the gas turbine rotor 1 gradually decreases, the clearance between the outermost edge of the compressor rotor 11 and the inner circumferential surface of the compressor casing 12 temporarily narrows. The outermost edge of the compressor rotor 11 is the radially outer edge Dro of the compressor blade row 11b of the compressor rotor 11.

[0044] As mentioned above, the temperature at the downstream Da end of the compressor casing 12 and compressor rotor 11 is several hundred degrees higher than the temperature near the middle of the axial direction Da in the compressor casing 12 and compressor rotor 11. Therefore, the ratio of the amount of contraction of the compressor casing 12 at the downstream Da end to the amount of contraction of the compressor rotor 11 at the downstream Da end is higher than the ratio of the amount of contraction of the compressor casing 12 near the middle of the axial direction Da to the amount of contraction of the compressor rotor 11 at the middle of the axial direction Da. Consequently, the clearance between the outermost edge of the compressor rotor 11 and the inner circumferential surface of the compressor casing 12 changes in a direction that makes it narrower at the downstream Da position than at the middle of the axial direction Da. Furthermore, when a portion of the air in the air compression passage 15 flows into the extraction line, the temperature around the location where the extraction line is connected in the compressor casing 12 tends to decrease because the heat around that location is absorbed by the air flowing into the extraction line. Consequently, the aforementioned clearance around the location where the extraction line is connected in the compressor casing 12 becomes narrower than in other areas.

[0045] Here, we assume that after the fuel valve 22 is closed, a full extraction process is performed in which the low-pressure extraction valve 43 and the high-pressure extraction valve 44 are open, and when the possibility of surging has been eliminated, the low-pressure extraction valve 43 and the high-pressure extraction valve 44 are closed to terminate this full extraction process.

[0046] In this case, although surging can be suppressed, the aforementioned clearance becomes narrower in the compressor casing 12 around the location where the high-pressure extraction line 42 is connected, in other words, in the part of the compressor rotor 11 downstream of the axis Dad. Therefore, in this case, there is a risk that the outermost edge of the compressor rotor 11 may come into contact with the inner surface of the compressor casing 12.

[0047] In this embodiment, when the fuel valve 22 is closed, as described above, a partial bleed process S23 is performed in which the low-pressure bleed valve 43 is open and the high-pressure bleed valve 44 is closed. Therefore, thermal contraction around the position where the high-pressure bleed line 42 is connected in the compressor casing 12 is suppressed more than in the previously assumed case. Thus, in this embodiment, the possibility of the outermost edge of the compressor rotor 11 contacting the inner circumferential surface of the compressor casing 12 can be suppressed.

[0048] Therefore, in this embodiment, even during the partial extraction process S23, in which a portion of the air flowing through the air compression passage 15 of the compressor 10 is extracted after the fuel valve 22 has closed, the starting motor is driven to gradually increase the rotational speed of the gas turbine rotor 1, and then fuel F can be supplied to the combustor 20. Accordingly, in this embodiment, the time from when the fuel supply to the combustor 20 is stopped until the fuel supply to the combustor 20 is started again, that is, the restart time of the gas turbine GT can be shortened.

[0049] As described above, in this embodiment, it is possible to suppress the occurrence of surging in the compressor 10 while shortening the restart time of the gas turbine GT.

[0050] "Variations" In the above embodiment, the generator GEN also functions as a starting motor. However, in addition to the generator GEN, a separate starting motor may be connected to the gas turbine rotor 1.

[0051] Furthermore, in the above embodiment, the low-pressure side extraction line 41 has two extraction lines: a low-pressure extraction line 41a and an intermediate-pressure extraction line 41b. However, the low-pressure side extraction line 41 may have only one extraction line, or it may have three or more extraction lines.

[0052] In the above embodiment, while the gas turbine GT is running and the gas turbine rotor 1 is rotating at the rated speed Nr, the low-pressure bleed valve 43a, the intermediate-pressure bleed valve 43b, and the high-pressure bleed valve 44 perform a non-bleeding process S21 in which they are closed. However, as mentioned above, if the low-pressure bleed line 41a, the intermediate-pressure bleed line 41b, and the high-pressure bleed line 42 are connected to the turbine casing 32 in order to cool the high-temperature components of the turbine 30, the low-pressure bleed valve 43a, the intermediate-pressure bleed valve 43b, and the high-pressure bleed valve 44 may be, for example, half-open even while the gas turbine rotor 1 is rotating at the rated speed Nr.

[0053] Furthermore, this disclosure is not limited to the embodiments described above. Various additions, modifications, substitutions, and partial deletions are possible, provided that they do not depart from the conceptual idea and spirit of the present invention derived from the claims and their equivalents.

[0054] "Addendum" The control method for the gas turbine equipment in the above embodiments and modifications can be understood, for example, as follows.

[0055] (1) The control method for gas turbine equipment in the first embodiment is applicable to the following gas turbine equipment. This gas turbine system comprises a gas turbine GT having a compressor 10 capable of compressing air A, a combustor 20 capable of burning fuel F in the air compressed by the compressor 10 to generate combustion gas G, and a turbine 30 driven by the combustion gas G; a fuel valve 22 capable of adjusting the flow rate of fuel F supplied to the combustor 20; a high-pressure bleed line 42 and a low-pressure bleed line 41 capable of bleeding air from inside the compressor 10 to the outside; a high-pressure bleed valve 44 provided in the high-pressure bleed line 42 and capable of adjusting the flow rate of air flowing through the high-pressure bleed line 42; and a low-pressure bleed valve 43 provided in the low-pressure bleed line 41 and capable of adjusting the flow rate of air flowing through the low-pressure bleed line 41. The compressor 10 has a compressor rotor 11 that can rotate about an axis Ar, and a compressor casing 12 that covers the compressor rotor 11. The turbine 30 is positioned on the downstream side Da of the axial direction Da along which the axis Ar extends, relative to the compressor 10, between the upstream side Dau and the downstream side Da. The compressor rotor 11 has a compressor rotor shaft 11s extending in the axial direction Da with the axis Ar as the center, and a plurality of compressor blade rows 11b attached to the compressor rotor shaft 11s in the axial direction Da. Both the high-pressure extraction line 42 and the low-pressure extraction line 41 are connected to the compressor casing 12. The position where the high-pressure extraction line 42 is connected to the compressor casing 12 is downstream Da of the axial direction than the position where the low-pressure extraction line 41 is connected to the compressor casing 12. In the control method for the gas turbine equipment described above, a fuel control step S10 is performed to control the opening degree of the fuel valve 22, and an extraction control step S20 is performed to control the opening degrees of the high-pressure extraction valve 44 and the low-pressure side extraction valve 43. In the extraction control step S20, after the fuel valve 22 is closed in the fuel control step S10, a partial extraction step S23 is performed in which the low-pressure side extraction valve 43 is open and the high-pressure extraction valve 44 is closed.

[0056] As part of the fuel control process S10, when the fuel valve 22 is instructed to close, the fuel valve 22 closes, fuel is no longer supplied to the combustor 20, and the rotational speed of the gas turbine rotor 1 having the compressor rotor 11 gradually decreases.

[0057] As the rotational speed of the gas turbine rotor 1 decreases, the likelihood of surging occurring in the compressor 10 increases. Therefore, when the fuel valve 22 is closed, in this embodiment, a partial extraction process S23 is executed as part of the extraction control process S20, in which the low-pressure side extraction valve 43 is open and the high-pressure side extraction valve 44 is closed. In this partial extraction process S23, a portion of the air flowing through the air compression passage 15 of the compressor 10 flows through the low-pressure side extraction line 41. As a result, the mass flow rate of air flowing out from the discharge port of the compressor casing 12 becomes less than the mass flow rate of air flowing into the compressor casing 12, thereby suppressing the occurrence of surging.

[0058] While fuel is supplied to the combustor 20 and the gas turbine GT is running, air flows through the air compression passage 15 on the inner circumference of the compressor casing 12. As this air flows towards the downstream Da side of the axis in the air compression passage 15, it gradually becomes more high in pressure and temperature. Therefore, while the gas turbine GT is running, the compressor casing 12 and compressor rotor 11, which are exposed to this high-temperature air, become very hot. In particular, the temperature at the downstream Da end of the compressor casing 12 and compressor rotor 11 is several hundred degrees higher than the temperature near the middle of Da in the axial direction of the compressor casing 12 and compressor rotor 11.

[0059] As the fuel valve 22 closes and the rotational speed of the gas turbine rotor 1 gradually decreases, the temperatures of the compressor casing 12 and the compressor rotor 11 also gradually decrease. However, because the heat capacity of the compressor casing 12 is smaller than that of the compressor rotor 11, the rate at which the temperature of the compressor casing 12 decreases is faster than the rate at which the temperature of the compressor rotor 11 decreases. As a result, the contraction rate of the thermally expanded compressor casing 12 temporarily becomes higher than the contraction rate of the thermally expanded compressor rotor 11. Therefore, as the fuel valve 22 closes and the rotational speed of the gas turbine rotor 1 gradually decreases, the clearance between the outermost edge of the compressor rotor 11 and the inner circumferential surface of the compressor casing 12 temporarily narrows.

[0060] As mentioned above, the temperature at the downstream Da end of the compressor casing 12 and compressor rotor 11 is several hundred degrees higher than the temperature near the middle of the axial direction Da in the compressor casing 12 and compressor rotor 11. Therefore, the ratio of the amount of contraction of the compressor casing 12 at the downstream Da end to the amount of contraction of the compressor rotor 11 at the downstream Da end is higher than the ratio of the amount of contraction of the compressor casing 12 near the middle of the axial direction Da to the amount of contraction of the compressor rotor 11 at the middle of the axial direction Da. Consequently, the clearance between the outermost edge of the compressor rotor 11 and the inner circumferential surface of the compressor casing 12 changes in a direction that makes it narrower at the downstream Da position than at the middle of the axial direction Da. Furthermore, when a portion of the air in the air compression passage 15 flows into the extraction line, the heat around the location where the extraction line is connected in the compressor casing 10 is absorbed by the air flowing into the extraction line, causing the temperature around this location to decrease. Consequently, the aforementioned clearance around the location where the extraction line is connected in the compressor casing 12 becomes narrower than in other areas.

[0061] Here, we assume that after the fuel valve 22 is closed, a full extraction process S22 is performed in which the low-pressure extraction valve 43 and the high-pressure extraction valve 44 are open, and when the possibility of surging has been eliminated, the low-pressure extraction valve 43 and the high-pressure extraction valve 44 are closed, thereby ending this full extraction process S22.

[0062] In this case, although surging can be suppressed, the aforementioned clearance becomes narrower in the compressor casing 12 around the location where the high-pressure extraction line 42 is connected, in other words, in the part of the compressor rotor 11 downstream of the axis Dad. Therefore, in this case, there is a risk that the outermost edge of the compressor rotor 11 may come into contact with the inner surface of the compressor casing 12.

[0063] In this embodiment, when the fuel valve 22 is closed, as described above, a partial extraction process S23 is performed in which the low-pressure extraction valve 43 is open and the high-pressure extraction valve 44 is closed. Therefore, thermal contraction around the position where the high-pressure extraction line 42 is connected in the compressor casing 12 is suppressed more than in the previously assumed case. Thus, in this embodiment, the possibility of the outermost edge of the compressor rotor 11 contacting the inner circumferential surface of the compressor casing 12 can be suppressed.

[0064] Therefore, in this embodiment, even during the partial extraction process S23, in which a portion of the air flowing through the air compression passage 15 of the compressor 10 is extracted after the fuel valve 22 has closed, the starting motor is driven to gradually increase the rotational speed of the gas turbine rotor 1, and then fuel F can be supplied to the combustor 20. Accordingly, in this embodiment, the time from when the fuel supply to the combustor 20 is stopped until the fuel supply to the combustor 20 is started again, that is, the restart time of the gas turbine GT can be shortened.

[0065] As described above, in this embodiment, the restart time of the gas turbine GT can be shortened while suppressing the occurrence of surging in the compressor 10.

[0066] (2) The control method for the gas turbine equipment in the second embodiment is: In the control method for the gas turbine equipment according to the first embodiment described above, in the extraction control step S20, after the fuel valve 22 is closed in the fuel control step S10 and before the execution of the partial extraction step S23, a full extraction step S22 is executed in which the low-pressure side extraction valve 43 is open and the high-pressure extraction valve 44 is open.

[0067] In this embodiment, surging in the compressor 10 can be suppressed more effectively than when only the partial extraction process S23 is performed after the fuel valve 22 is closed.

[0068] (3) The control method for the gas turbine equipment in the third embodiment is: In the gas turbine equipment control method according to the second embodiment described above, in the extraction control step S20, after the full extraction step S22, the high-pressure extraction valve 44 is closed while the low-pressure side extraction valve 43 is kept open, and the partial extraction step S23 is executed.

[0069] (4) The control method for the gas turbine equipment in the fourth embodiment is: In the control method for the gas turbine equipment according to the third embodiment described above, in the extraction control step S20, after the fuel valve 22 is closed in the fuel control step S10, the high-pressure extraction valve 44 is closed when the rotational speed of the compressor rotor 11 falls to 30% or less of the rated rotational speed Nr of the compressor rotor 11.

[0070] (5) The control method for the gas turbine equipment in the fifth embodiment is: In the control method for the gas turbine equipment according to the third embodiment, in the extraction control step S20, after the fuel valve 22 is closed in the fuel control step S10, the high-pressure extraction valve 44 is closed when the rotational speed of the compressor rotor 11 falls within a range of 30% or less of the rated rotational speed Nr of the compressor rotor 11 and 10% or more of the rated rotational speed Nr.

[0071] (6) The control method for the gas turbine equipment in the sixth embodiment is: In the gas turbine equipment control method according to any one of the first to fifth embodiments described above, in the extraction control step S20, after the execution of the partial extraction step S23, a non-extraction step S24 is executed in which the low-pressure side extraction valve 43 is closed while the high-pressure extraction valve 44 is kept closed.

[0072] The control devices for the gas turbine equipment in the above embodiments and modifications can be understood, for example, as follows. (7) The control device for the gas turbine equipment in the seventh embodiment is applicable to the following gas turbine equipment. This gas turbine system comprises a gas turbine GT having a compressor 10 capable of compressing air A, a combustor 20 capable of burning fuel F in the air compressed by the compressor 10 to generate combustion gas G, and a turbine 30 driven by the combustion gas G; a fuel valve 22 capable of adjusting the flow rate of fuel F supplied to the combustor 20; a high-pressure bleed line 42 and a low-pressure bleed line 41 capable of bleeding air from inside the compressor 10 to the outside; a high-pressure bleed valve 44 provided in the high-pressure bleed line 42 and capable of adjusting the flow rate of air flowing through the high-pressure bleed line 42; and a low-pressure bleed valve 43 provided in the low-pressure bleed line 41 and capable of adjusting the flow rate of air flowing through the low-pressure bleed line 41. The compressor 10 has a compressor rotor 11 that can rotate about an axis Ar, and a compressor casing 12 that covers the compressor rotor 11. The turbine 30 is positioned on the downstream side Da of the axial direction Da along which the axis Ar extends, relative to the compressor 10, between the upstream side Dau and the downstream side Da. The compressor rotor 11 has a compressor rotor shaft 11s extending in the axial direction Da with the axis Ar as the center, and a plurality of compressor blade rows 11b attached to the compressor rotor shaft 11s in the axial direction Da. Both the high-pressure extraction line 42 and the low-pressure extraction line 41 are connected to the compressor casing 12. The position where the high-pressure extraction line 42 is connected to the compressor casing 12 is downstream Da of the axial direction than the position where the low-pressure extraction line 41 is connected to the compressor casing 12. The control device 50 for the gas turbine equipment described above includes a fuel controller 51 that controls the opening degree of the fuel valve 22, and an extraction controller 53 that controls the opening degrees of the high-pressure extraction valve 44 and the low-pressure side extraction valve 43. After the fuel controller 51 closes the fuel valve 22, the extraction controller 53 executes a partial extraction process S23 in which the low-pressure side extraction valve 43 is open and the high-pressure extraction valve 44 is closed.

[0073] In this embodiment, similar to the control method for the gas turbine equipment in the first embodiment, it is possible to shorten the restart time of the gas turbine GT while suppressing the occurrence of surging in the compressor 10.

[0074] (8) The control device for the gas turbine equipment in the eighth aspect is: In the control device 50 of the seventh embodiment, the extraction controller 53 performs a full extraction process S22 in which the low-pressure side extraction valve 43 is open and the high-pressure side extraction valve 44 is open, after the fuel valve 22 has been closed by the fuel controller 51 and before the partial extraction process S23 is performed.

[0075] In this embodiment, similar to the control method for the gas turbine equipment in the second embodiment, the occurrence of surging in the compressor 10 can be suppressed more effectively than when only the partial extraction process S23 is performed after the fuel valve 22 is closed.

[0076] (9) The control device for the gas turbine equipment in the ninth aspect is: In the control device 50 of the eighth embodiment described above, the extraction controller 53, after the full extraction process S22, closes the high-pressure extraction valve 44 while keeping the low-pressure side extraction valve 43 open, and executes the partial extraction process S23.

[0077] (10) The control device for the gas turbine equipment in the tenth embodiment is: In the control device 50 according to the ninth embodiment described above, the extraction controller 53 closes the high-pressure extraction valve 44 when the rotational speed of the compressor rotor 11 falls to 30% or less of the rated rotational speed Nr of the compressor rotor 11, after the fuel valve 22 has been closed by the fuel controller 51.

[0078] (11) The control device for the gas turbine equipment in the eleventh aspect is: In the control device 50 according to the ninth embodiment described above, the extraction controller 53 closes the high-pressure extraction valve 44 when the rotational speed of the compressor rotor 11 falls within a range of 30% or less of the rated rotational speed Nr of the compressor rotor 11 and 10% or more of the rated rotational speed Nr, after the fuel valve 22 has been closed by the fuel controller 51.

[0079] (12) The control device for the gas turbine equipment in the twelfth aspect is: In the control device 50 in any one of the seventh to eleventh embodiments described above, the extraction controller 53 performs a non-extraction process S24 after the execution of the partial extraction process S23, which involves closing the low-pressure extraction valve 43 while keeping the high-pressure extraction valve 44 closed.

[0080] The gas turbine equipment in the above embodiments and modifications can be understood, for example, as follows. (13) The gas turbine equipment in the thirteenth aspect is: The system comprises a control device 50 according to any one of the seventh to twelfth embodiments, the gas turbine GT, the fuel valve 22, the high-pressure extraction line 42, the low-pressure side extraction line 41, the high-pressure extraction valve 44, and the low-pressure side extraction valve 43. [Explanation of Symbols]

[0081] GT: Gas Turbine 1: Gas turbine rotor 2f: Front bearing 2b: Rear bearing 10: Compressor 11: Compressor rotor 11s: Compressor rotor shaft 11b: Compressor blade row 12: Compressor casing 12a: Casing body 12b: Stator blade retaining ring 13: Compressor stator blade row 14: Intake volume regulator 14v: Entrance guide vane 14d: Driver 15: Air compression channel 16: Extraction chamber 17: Intake casing 17i: Intake inner casing 17o: Intake outer casing 17ai: Air intake 18: Intake strut 20: Combustor 21: Fuel line 22: Fuel valve 27: Intermediate casing 30: Turbine 31: Turbine Rotor 31s: Turbine rotor shaft 31b: Turbine blade row 32: Turbine casing 33: Turbine stator blade row 37: Exhaust casing 37i: Exhaust internal casing 37o: Exhaust outer casing 38: Exhaust strut 39: Chimney 41: Low-pressure side extraction line 41a: Low-pressure extraction line 41b: Medium pressure extraction line 42: High-pressure extraction line 43: Low-pressure side extraction valve 43a: Low-pressure extraction valve 43b: Medium pressure extraction valve 44: High-pressure extraction valve 50: Control device 51: Fuel controller 52: IGV Controller 53: Bleeding controller Ar: Axis line Da: Axial direction Dau: Axis upstream side Dad: Downstream side of the axis Dc: Circumferential direction Dr: Radial direction Dri: Radial inner side Dro: Radial outer side

Claims

1. A gas turbine having a compressor capable of compressing air, a combustor capable of generating combustion gas by burning fuel in the air compressed by the compressor, and a turbine driven by the combustion gas, A fuel valve capable of adjusting the flow rate of fuel supplied to the combustor, A high-pressure extraction line and a low-pressure extraction line that can extract air from inside the compressor to the outside, A high-pressure extraction valve is provided in the high-pressure extraction line and is capable of adjusting the flow rate of air flowing through the high-pressure extraction line, A low-pressure side extraction valve is provided in the low-pressure side extraction line and is capable of adjusting the flow rate of air flowing through the low-pressure side extraction line, Equipped with, The compressor comprises a compressor rotor rotatable about an axis and a compressor casing covering the compressor rotor. The turbine is positioned relative to the compressor on the downstream side of the axis in the axial direction in which the axis extends, rather than on the upstream side and the downstream side of the axis. The compressor rotor comprises a compressor rotor shaft extending in the axial direction with respect to the axis, and a plurality of compressor blade rows mounted on the compressor rotor shaft in the axial direction, Both the high-pressure extraction line and the low-pressure extraction line are connected to the compressor casing. The position where the high-pressure extraction line is connected to the compressor casing is downstream of the axis of connection of the low-pressure extraction line to the compressor casing. In a control method for gas turbine equipment, A fuel control step that controls the opening degree of the fuel valve, A bleed control step that controls the opening degree of the high-pressure bleed valve and the low-pressure bleed valve, Execute, In the extraction control step, after the fuel valve is closed in the fuel control step, a partial extraction step is performed in which the low-pressure side extraction valve is open and the high-pressure side extraction valve is closed. A control method for gas turbine equipment.

2. In the control method for a gas turbine system according to claim 1, In the extraction control step, after the fuel valve is closed in the fuel control step and before the partial extraction step is executed, a full extraction step is performed in which the low-pressure side extraction valve is open and the high-pressure extraction valve is open. A control method for gas turbine equipment.

3. In the control method for a gas turbine system according to claim 2, In the extraction control step, after the entire extraction step, the high-pressure extraction valve is closed while the low-pressure side extraction valve is kept open, and the partial extraction step is performed. A control method for gas turbine equipment.

4. In the control method for a gas turbine system according to claim 3, In the extraction control step, after the fuel valve is closed in the fuel control step, the high-pressure extraction valve is closed when the rotational speed of the compressor rotor falls to 30% or less of the rated rotational speed Nr of the compressor rotor. A control method for gas turbine equipment.

5. In the control method for a gas turbine system according to claim 3, In the extraction control step, after the fuel valve is closed in the fuel control step, when the rotational speed of the compressor rotor falls within the range of 30% or less of the rated rotational speed Nr of the compressor rotor and 10% or more of the rated rotational speed Nr, the high-pressure extraction valve is closed. A control method for gas turbine equipment.

6. A control method for a gas turbine facility according to any one of claims 1 to 5, In the extraction control step, after the execution of the partial extraction step, a non-extraction step is performed in which the low-pressure side extraction valve is closed while the high-pressure extraction valve is kept closed. A control method for gas turbine equipment.

7. A gas turbine having a compressor capable of compressing air, a combustor capable of generating combustion gas by burning fuel in the air compressed by the compressor, and a turbine driven by the combustion gas, A fuel valve capable of adjusting the flow rate of fuel supplied to the combustor, A high-pressure extraction line and a low-pressure extraction line that can extract air from inside the compressor to the outside, A high-pressure extraction valve is provided in the high-pressure extraction line and is capable of adjusting the flow rate of air flowing through the high-pressure extraction line, A low-pressure side extraction valve is provided in the low-pressure side extraction line and is capable of adjusting the flow rate of air flowing through the low-pressure side extraction line, Equipped with, The compressor comprises a compressor rotor rotatable about an axis and a compressor casing covering the compressor rotor. The turbine is positioned relative to the compressor on the downstream side of the axis in the axial direction in which the axis extends, rather than on the upstream side and the downstream side of the axis. The compressor rotor comprises a compressor rotor shaft extending in the axial direction with respect to the axis, and a plurality of compressor blade rows mounted on the compressor rotor shaft in the axial direction, Both the high-pressure extraction line and the low-pressure extraction line are connected to the compressor casing. The position where the high-pressure extraction line is connected to the compressor casing is downstream of the axis of connection of the low-pressure extraction line to the compressor casing. In a control system for a gas turbine, A fuel controller that controls the opening degree of the fuel valve, A bleed control device that controls the opening degree of the high-pressure bleed valve and the low-pressure bleed valve, It has, The extraction controller performs a partial extraction process in which, after the fuel valve is closed by the fuel controller, the low-pressure extraction valve is open and the high-pressure extraction valve is closed. Control device.

8. In the control device according to claim 7, The extraction controller, after the fuel valve is closed by the fuel controller and before the partial extraction process is executed, performs a full extraction process in which the low-pressure extraction valve is open and the high-pressure extraction valve is open. Control device.

9. In the control device according to claim 8, The extraction controller, after the entire extraction process, maintains the low-pressure side extraction valve open while closing the high-pressure extraction valve to execute the partial extraction process. Control device.

10. In the control device according to claim 9, The extraction controller closes the high-pressure extraction valve when the rotational speed of the compressor rotor falls to 30% or less of the rated rotational speed Nr of the compressor rotor, after the fuel valve has been closed by the fuel controller. Control device.

11. In the control device according to claim 9, The extraction controller closes the high-pressure extraction valve when, after the fuel valve is closed by the fuel controller, the rotational speed of the compressor rotor falls within a range of 30% or less of the rated rotational speed Nr of the compressor rotor and 10% or more of the rated rotational speed Nr. Control device.

12. In the control device according to claim 7, The extraction controller, after executing the partial extraction process, performs a non-extraction process in which it closes the low-pressure extraction valve while keeping the high-pressure extraction valve closed. Control device.

13. A control device according to any one of claims 7 to 12, The aforementioned gas turbine, The aforementioned fuel valve, The aforementioned high-pressure extraction line, The low-pressure side extraction line, The aforementioned high-pressure bleed valve, The low-pressure side extraction valve, A gas turbine facility equipped with the following features.

Images