Gas turbine control device, gas turbine facility, gas turbine control method, and gas turbine control program

Abstract

To provide a control device for a gas turbine that can rapidly start the gas turbine while suppressing accidental fire, a gas turbine facility, a control method for the gas turbine, and a control program for the gas turbine.SOLUTION: A control device for a gas turbine that is a control device for controlling an operation of the gas turbine includes: a fuel command value calculation section for calculating a fuel command value to be applied to the gas turbine; and a speed increase rate setting section for setting a speed increase rate set value of a rotor of the gas turbine. The speed increase rate setting section is configured to increase the speed increase rate set value after switching timing at which the fuel command value calculated by the fuel command value calculation section is switched from the constant state to the continuously increasing state during the operation of the gas turbine.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The present disclosure relates to a gas turbine control device, a gas turbine facility, a gas turbine control method, and a gas turbine control program. [Background technology]

[0002] When starting up a gas turbine, after fuel is ignited in the combustor, the rotor speed is increased until the rotor speed reaches a predetermined speed (for example, a rated speed).

[0003] For example, Patent Document 1 describes that when starting a gas turbine, after fuel is ignited, the rotor rotation speed is increased at a predetermined rotation acceleration (acceleration rate) determined based on a safety index that indicates the relationship between damage to gas turbine components and the rotation acceleration of the rotor. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2013-221423 Summary of the Invention [Problem to be solved by the invention]

[0005] In order to shorten the start-up time of a gas turbine, it is conceivable to set the rotor speed increase rate (rotational acceleration) during start-up of the gas turbine to a value greater than conventional. However, if the output of a start-up motor or the like is increased to increase the rotor speed increase rate more than conventionally during the period immediately after ignition of the gas turbine when the fuel supply amount is relatively small, the rotor rotation speed will increase more than conventionally, increasing the amount of air suction in the compressor, which will reduce the fuel-air ratio (F / A ratio) and increase the possibility of misfire in the combustor.

[0006] In view of the above circumstances, at least one embodiment of the present invention aims to provide a gas turbine control device, gas turbine equipment, a gas turbine control method, and a gas turbine control program that are capable of rapidly starting a gas turbine while suppressing misfires. [Means for solving the problem]

[0007] A control device for a gas turbine according to at least one embodiment of the present invention comprises: A control device for controlling operation of a gas turbine, comprising: a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; a speed increase rate setting unit for setting a speed increase rate setting value of a rotor of the gas turbine; Equipped with The speed-up rate setting unit is configured to increase the speed-up rate set value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit switches from a constant value to a continuously increasing value, during startup of the gas turbine.

[0008] Furthermore, a control device for a gas turbine according to at least one embodiment of the present invention includes: A control device for controlling operation of a gas turbine, comprising: a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; a motor output setting unit for setting an output setting value of the startup motor of the gas turbine; Equipped with The motor output setting unit is configured to increase the output set value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit switches from a constant value to a continuously increasing value during startup of the gas turbine.

[0009] Moreover, the gas turbine equipment according to at least one embodiment of the present invention includes: a gas turbine including a compressor for compressing air, a combustor for generating combustion gas by a combustion reaction between the compressed air from the compressor and fuel, and a turbine driven by the combustion gas from the combustor; the controller as described above configured to control operation of the gas turbine; Equipped with.

[0010] Further, a gas turbine control method according to at least one embodiment of the present invention includes: 1. A control method for controlling operation of a gas turbine, comprising: a fuel command value calculation step of calculating a fuel command value to be given to the gas turbine; a speed increase rate setting step of setting a speed increase rate set value of a rotor of the gas turbine; Equipped with In the speed-up rate setting step, during startup of the gas turbine, the speed-up rate set value is increased after a switching timing at which the fuel command value calculated in the fuel command value calculation step switches from a constant value to a continuously increasing value.

[0011] Further, a control program for a gas turbine according to at least one embodiment of the present invention includes: A control program for controlling operation of a gas turbine, comprising: On the computer, a fuel command value calculation step of calculating a fuel command value to be given to the gas turbine; a speed-up rate setting step of setting a speed-up rate set value for a rotor of the gas turbine; configured to cause In the step of setting a speed-up rate, during startup of the gas turbine, the speed-up rate set value is increased after a switching timing at which the fuel command value calculated in the step of calculating a fuel command value switches from a constant value to a continuously increasing value. [Effects of the Invention]

[0012] According to at least one embodiment of the present invention, there are provided a gas turbine control device, gas turbine equipment, a gas turbine control method, and a gas turbine control program that are capable of rapidly starting a gas turbine while suppressing misfires. [Brief explanation of the drawings]

[0013] [Figure 1] 1 is a schematic configuration diagram of a gas turbine facility including a control device according to an embodiment. [Figure 2] FIG. 2 is a schematic configuration diagram of a control device according to an embodiment. [Figure 3] FIG. 2 is a block diagram illustrating the calculation logic of a control device according to an embodiment. [Figure 4] 1 is a graph showing an example of the relationship between the rotor rotation speed and the speed increase rate setting value at the start of the gas turbine. [Figure 5] 1 is a graph showing an example of the relationship between the rotor rotation speed and the output setting value of the startup motor when starting up the gas turbine. [Figure 6] 1 is a graph showing an example of the relationship between the rotor rotation speed and the speed increase rate setting value at the start of the gas turbine. [Figure 7] 1 is a graph showing an example of time-dependent changes in the speed-up rate set value, the startup motor output set value, the rotor rotation speed, the fuel command value, the exhaust gas temperature, and the actual speed-up rate of the rotor when starting up a gas turbine. DETAILED DESCRIPTION OF THE INVENTION

[0014] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present invention.

[0015] (Gas turbine equipment configuration) 1 is a schematic configuration diagram of a gas turbine facility including a control device according to one embodiment. As shown in FIG. 1, the gas turbine facility 100 includes a gas turbine 1 and a control device 40 for controlling the operation of the gas turbine 1.

[0016] The gas turbine 1 includes a compressor 2 for compressing air, a combustor 3 for burning fuel (e.g., natural gas) to generate combustion gas, and a turbine 4 configured to be rotationally driven by the combustion gas. The compressor 2 and turbine 4 are connected via a rotating shaft 5.

[0017] Combustor 3 is supplied with fuel (natural gas, etc.) and compressed air from compressor 2, and the fuel is burned using this compressed air as an oxidizer, generating combustion gas. The flow rate of fuel supplied to combustor 3 can be adjusted by fuel valve 7.

[0018] The combustion gas generated in the combustor 3 is introduced into the turbine 4, and drives the turbine 4 to rotate. After completing its work in the turbine 4, the combustion gas is discharged as exhaust gas from the turbine 4. Note that a generator (not shown) may be connected to the turbine 4 via a rotating shaft 5, and the generator may be driven by the turbine 4 to generate electricity.

[0019] As shown in Fig. 1, the gas turbine 1 may include a startup motor 6. The startup motor 6 is capable of applying rotational power to a rotary shaft 5 of the gas turbine 1 to rotationally drive the rotary shaft 5. The startup motor 6 may be configured to assist in the rotational drive of the gas turbine 1 at the start-up of the gas turbine 1 until the gas turbine 1 can rotate independently using its own combustion energy.

[0020] In some embodiments, the above-mentioned generator connected to the gas turbine 1 via the rotating shaft 5 may receive power supply and function as the start-up motor 6. In this case, to rotate the generator as an electric motor, variable voltage and variable frequency power may be supplied to the generator by a frequency converter such as a static frequency converter (SFC).

[0021] The gas turbine 1 may include a rotation speed measurement unit 8 for measuring the rotation speed of the rotating shaft 5 of the gas turbine 1 (rotor rotation speed of the gas turbine 1). The rotation speed measurement unit 8 may include a rotation speed sensor such as an encoder. A signal indicating the measurement value of the rotor rotation speed measured by the rotation speed measurement unit 8 is sent to the control device 40.

[0022] (Control device configuration) FIG. 2 is a schematic diagram of a control device 40 according to one embodiment. As shown in FIG. 2, the control device 40 includes a fuel command value calculation unit 42 and a speed increase rate setting unit 44. The control device 40 may also include a motor output setting unit 46 and / or a memory unit 48. The control device 40 is configured to receive a signal indicating the measured value (actual rotation speed) of the rotor rotation speed from the rotation speed measurement unit 8 and process the signal. The calculation result by the control device 40 may be sent to the fuel valve 7 or the start-up motor 6, and the fuel valve 7 or the start-up motor 6 may operate based on the calculation result.

[0023] The fuel command value calculation unit 42 is configured to calculate a fuel command value FI to be given to the gas turbine 1. The opening of the fuel valve 7 is adjusted based on this fuel command value FI. The control device 40 may be configured to adjust the opening of the fuel valve 7 so as to match the fuel command value FI.

[0024] The speed-up rate setting unit 44 is configured to set a speed-up rate setting value of the rotor during startup of the gas turbine 1. The speed-up rate setting unit 44 may be configured to set a different speed-up rate setting value depending on the rotation speed (rated rotation speed, etc.) during operation after startup of the gas turbine 1. The speed-up rate setting value may be used by the fuel command value calculation unit 42 to calculate the fuel command value FI.

[0025] The motor output setting unit 46 is configured to set an output set value of the startup motor 6 during startup of the gas turbine 1. The output set value set by the motor output setting unit 46 is sent to the startup motor 6, and the startup motor 6 operates to obtain the set output. Note that when a generator is used as the startup motor 6 together with a frequency conversion device such as an SFC, the motor output setting unit 46 may be configured to set the output set value of the frequency conversion device as the output set value of the startup motor 6.

[0026] The storage unit 48 is configured to store inputs and outputs to the control device 40, calculation results in the control device 40, etc. The acceleration rate setting unit 44 may be configured to read out and set an acceleration rate setting value stored in the storage unit 48. The motor output setting unit 46 may be configured to read out and set an output setting value stored in the storage unit 48. The storage unit 48 may include a main storage device or an auxiliary storage device of a computer constituting the control device 40.

[0027] The control device 40 includes a computer equipped with a processor (e.g., CPU), a main storage device (memory device; e.g., RAM), an auxiliary storage device, an interface, etc. The control device 40 receives signals from the rotation speed measurement unit 8 via the interface. The processor is configured to process the signals received in this manner. The processor is also configured to process programs loaded in the main storage device. This realizes the functions of the above-mentioned functional units (fuel command value calculation unit 42, acceleration rate setting unit 44, and motor output setting unit 46).

[0028] The processing contents of the control device 40 are implemented as programs executed by the processor. The programs may be stored in, for example, an auxiliary storage device. When the programs are executed, they are loaded into the main storage device. The processor reads the programs from the main storage device and executes the instructions contained in the programs.

[0029] 3 is a block diagram showing the calculation logic of the fuel command value calculation unit 42 of the control device 40 according to one embodiment. The fuel command value calculation unit 42 calculates and outputs a fuel command value FI to be given to the gas turbine 1.

[0030] In FIG. 3 , reference numeral 11 denotes a surge prevention control output limiter, 12 denotes a gas turbine rotation speed signal, 14 denotes a subtractor, 16 denotes a function generator, 19 denotes a proportional calculator, 20 denotes a low value selector, 21 denotes a signal generator, 22 denotes an adder, 23 denotes a low value selector, 24 denotes a gas turbine rotation speed control calculation output, 25 denotes a generator output control calculation output, 26 denotes a gas turbine exhaust gas temperature control calculation output, 27 and 28 denote signal generators, 29 denotes a gas turbine fuel ignition command signal, 30 denotes a gas turbine misfire prevention command signal, 31 and 32 denote contacts that close when the respective signals 29 and 30 are on, 33 denotes a high value selector, and 34 denotes a gas turbine control calculation output (fuel command value output).

[0031] In the portions denoted by reference numerals 11 to 22, a fuel flow rate (second command value F2) is calculated and output based on the rotation speed of the rotor of the gas turbine 1, etc., as will be described later. A gas turbine rotation speed control calculation output 24 outputs the fuel flow rate when the gas turbine is at near the rated rotation speed. A generator output control calculation output 25 outputs the fuel flow rate when the generator of the gas turbine 1 is connected to the power grid and transmitting power to it. A gas turbine exhaust gas temperature control calculation output 26 outputs a fuel flow rate that is determined based on the exhaust gas temperature of the gas turbine so that the turbine blades, etc. of the gas turbine do not become abnormally hot. A low value selector 23 selects the lowest value of these outputs and outputs it to a high value selector 33.

[0032] When the gas turbine 1 is started up, the fuel flow rate (second command value F2) from the portion indicated by the reference numerals 11 to 22 among the above-mentioned outputs is the lowest value, and is therefore selected by the low value selector 23 and output to the high value selector 33.

[0033] On the other hand, when the gas turbine 1 is started up, the output of the signal generator 27 when the gas turbine fuel ignition command signal 29 is on or the output of the signal generator 28 when the gas turbine misfire prevention command signal 30 is on is input to the high-value selector 33. The output (first command value F1) of the signal generator 27 or the signal generator 28 is a constant value.

[0034] The maximum value selector 33 selects and outputs the maximum value from among a plurality of inputs. At the start-up of the gas turbine 1, the larger of the output (first command value F1) of the signal generator 27 and the fuel flow rate (second command value F2) from the portion indicated by the reference numerals 11 to 22 is selected and output to the gas turbine control calculation output 34. That is, at the start-up of the gas turbine 1, the larger of the output (first command value F1) of the signal generator 27 and the fuel flow rate (second command value F2) from the portion indicated by the reference numerals 11 to 22 is calculated as the fuel command value FI.

[0035] Here, we will explain the calculations in the parts indicated by the reference numerals 11 to 22. The output of the surge prevention control output limiter 11 is found from the rotation speed (rotor rotation speed) of the gas turbine 1 and the discharge pressure of the compressor. The gas turbine rotation speed signal 12 is a signal received from the rotation speed measurement unit 8 (a signal indicating the actual rotation speed of the rotor of the gas turbine 1), and is input to a subtractor 14 and a function generator 16.

[0036] The function generator 16 receives the actual rotation speed of the rotor from the gas turbine rotation speed signal 12 and also receives a speed-up rate set value from a speed-up rate setting unit 44 (see FIG. 2), and calculates a target rotation speed of the rotor of the gas turbine 1 based on the actual rotation speed of the rotor and the speed-up rate set value. The function generator 16 may calculate the target rotation speed by adding an increase in the rotation speed according to the speed-up rate to the actual rotation speed of the rotor.

[0037] A subtractor 14 subtracts the gas turbine rotation speed signal 12 from the output of a function generator 16, and the result is input to a proportional calculator 19. The proportional calculator 19 multiplies this by an internally set coefficient and outputs the result. A low value selector 20 outputs the lower of the output of the proportional calculator 19 and the output of a signal generator 21. Since the output of the signal generator 21 is normally zero, the output of the low value selector 20 is always a negative value. An adder 22 outputs a value obtained by adding the output of the surge prevention control output limiter 11 and the output of the low value selector 20. In this way, in the parts indicated by reference numerals 11 to 22, an output (second command value) related to the fuel flow rate is calculated based on the rotation speed of the gas turbine 1, etc.

[0038] (Gas turbine control flow) Next, a control method for the gas turbine 1 according to some embodiments will be described. Note that, although the following describes a case where the above-described gas turbine 1 is controlled using the above-described control device 40, in some embodiments, the control method for the gas turbine may be executed using another device, or some or all of the procedures described below may be performed manually.

[0039] Figures 4 and 6 are graphs showing an example of the relationship between the rotor rotation speed and the speed-up rate set value at the start-up of a gas turbine. Figure 5 is a graph showing an example of the relationship between the rotor rotation speed and the output set value of the startup motor at the start-up of a gas turbine. Figure 7 is a graph showing an example of the time changes in the speed-up rate set value, the output set value of the startup motor, the rotor rotation speed (actual rotation speed), the fuel command value, the exhaust gas temperature, and the actual speed-up rate of the rotor at the start-up of a gas turbine for a plurality of cases (cases A to D).

[0040] 4 to 7, R0 is the rotor speed at the time of ignition of the gas turbine 1 (time t0 in FIG. 7), and R_rated is the rotation speed (e.g., rated rotation speed) during operation after startup of the gas turbine 1. The startup of the gas turbine 1 includes the period from when the rotor of the gas turbine 1 starts to rotate until the rotor rotation speed increases to a predetermined rotation speed (e.g., rated rotation speed).

[0041] First, the control flow in case C, which is a typical example of the prior art, will be described with reference to FIG.

[0042] In case C, during the period before time t0, the rotor of the gas turbine 1 is rotationally driven by the startup motor 6. At this time, the output setting value of the startup motor 6 is set to M0.

[0043] At time t0, fuel is ignited in the combustor 3. The rotor rotation speed at this time is R0. At time t0, the speed increase rate setting value and the output setting value of the startup motor 6 are set to predetermined values ​​(for example, values ​​determined in advance according to the rotation speed after startup of the gas turbine 1). In Case C, the speed increase rate setting value is set to A1, and the output setting value of the startup motor 6 is set to M1.

[0044] After time t0, the fuel command value FI calculated by the fuel command value calculation unit 42 is constant. That is, the fuel command value calculation unit 42 calculates the first command value F1, which is the larger of the above-mentioned first command value F1 (constant value) and the second command value F2 calculated from the rotor rotation speed and the like, as the fuel command value FI. Fuel is supplied to the gas turbine 1 based on this fuel command value FI, and the rotor rotation speed increases to a certain extent as shown in the graph.

[0045] At time t6, the fuel command value switches from a constant value to a continuously increasing value. That is, the fuel command value FI calculated by the fuel command value calculation unit 42 switches from the first command value F1, which is a constant value, to a second command value F2, which is calculated based on the rotor speed and the like. The point in time at which the fuel command value switches from a constant value to a continuously increasing value is called the switching timing.

[0046] After time t6, the speed increase rate setting value is maintained at A1, and the output setting value of the startup motor 6 is maintained at M1. After time t6, the rotor rotation speed increases at a substantially constant gradient. This gradient corresponds to the speed increase rate setting value A1. The rotor rotation speed is then increased until it reaches a predetermined rotation speed (for example, the rated rotation speed).

[0047] Next, a control flow of Case A according to one embodiment will be described. The control flow in Case A is the same as that of Case C up to the switching timing (time t6 in Cases A and C) at which the fuel command value switches from a constant value to a continuously increasing value. However, in Case A, after the switching timing, the speed increase rate setting unit 44 increases the speed increase rate setting value from A1 (first speed increase rate) to A2 (second speed increase rate). In the example shown in the graph of FIG. 7, between time t6 (the time of the switching timing) and time t7, the speed increase rate setting value is increased from A1 to A2, and after time t7, the speed increase rate setting value is maintained at A2.

[0048] The speed-up rate setting unit 44 may determine the speed-up rate setting value based on the rotor rotation speed. A1 Set the acceleration rate setting to A1 and the rotor speed to R A1 When this occurs, the acceleration rate setting value may be increased from A1 to A2. A1 is the rotation speed that is equal to or greater than the rotation speed at which the switching timing occurs. In the example shown in Figure 4, when the rotor rotation speed is R A1 From R A2 During this time, the acceleration rate setting value is increased from A1 to A2.

[0049] In the above-described case A, the speed increase rate set value that is set after the switching timing is A2, which is larger than A1 in case C. Therefore, in case A, the gradient of the increase in rotor rotation speed after the switching timing is larger than in case C. As a result, the time required for the rotor rotation speed to increase to a predetermined rotation speed is shortened, and the startup time of the gas turbine 1 is shortened.

[0050] Furthermore, in order to shorten the startup time of the gas turbine 1, it is also possible to set the speed increase rate setting value to a relatively large value (A2) from the time of ignition (time t0), as shown in Case D. However, if the speed increase rate setting value is uniformly set to a large value (A2) as in Case D, the rotor rotation speed increases abruptly, and the fuel-air ratio (F / A ratio) decreases due to an increase in the amount of air suction in the compressor 2, increasing the possibility of misfire in the combustor 3. In the graph of Figure 7, the increase in the exhaust gas temperature in Case D remains low after ignition at time t0, indicating that this is due to the decrease in the fuel-air ratio (F / A ratio) caused by the large increase in the rotation speed.

[0051] In contrast, in the above-described Case A, the acceleration rate setting value is set to a relatively low value (A1) before the switching timing, and the acceleration rate setting value is increased after the switching timing when the fuel command value starts to increase continuously. This makes it possible to suppress a decrease in the fuel-air ratio (F / A ratio) and thereby suppress misfires.

[0052] Therefore, in the above-mentioned Case A, the gas turbine can be started up quickly while suppressing misfires.

[0053] Furthermore, in the compressor 2, if the rotor rotation speed is maintained within a predetermined rotation speed range, a rotating stall may occur, which may damage the blades. In this regard, in the above-described Case A, the speed increase rate set value is set relatively large after the timing at which the fuel command value switches from a constant value to a continuous increase, so that the compressor 2 can quickly pass through the rotation speed range where a rotating stall occurs. Therefore, the gas turbine can be started up quickly while suppressing rotating stall in the compressor.

[0054] In some embodiments, for example, as in the above-described case A, the first speed-up rate A1 is set as the speed-up rate setting value before the switching timing, and the speed-up rate setting value is increased to the second speed-up rate A2 after the switching timing. In some embodiments, the ratio r of the second speed-up rate A2 to the first speed-up rate A (r A =A2 / A1) may be 1.2 or more or 1.5 or more.

[0055] In this way, by increasing the rotor speed increase rate setting value from the value before the switching timing (first speed increase rate A1) to the second speed increase rate A2 after the switching timing, it is possible to start up the gas turbine 1 in a relatively short time while more effectively suppressing misfires due to a decrease in the fuel-air ratio.

[0056] In case A in Fig. 7, after the switching timing, the motor output setting unit 46 increases the output setting value of the startup motor 6 from M1 (first output) to M2 (second output). In the example shown in the graph in Fig. 7, the output setting value is increased from M1 to M2 between time t6 (the time of the switching timing) and time t7, and the output setting value is maintained at M2 after time t7.

[0057] The motor output setting unit 46 may determine the output setting value based on the rotor rotation speed. That is, as shown in FIG. 5, when the rotor rotation speed is R M1 The output setting value is set to M1 and the rotor rotation speed is R M1 When this occurs, the output setting value may be increased from M1 to M2. M1 is the rotation speed that is equal to or greater than the rotation speed at which the switching timing occurs. In the example shown in FIG. 5, when the rotor rotation speed is R M1 From R M2 During this time, the output setting value is increased from M1 to M2.

[0058] In the above-described Case A, during startup of the gas turbine 1, the output set value of the startup motor 6 is increased after the switching timing at which the fuel command value switches from a constant value to a continuously increasing value. In this way, by increasing the startup motor output set value along with the speed increase rate set value after the switching timing, it is possible to increase the rotor speed while suppressing increases in the fuel command value. This makes it possible to suppress increases in the temperature of the combustion gas introduced from the combustor 3 to the turbine 4 (i.e., it also suppresses increases in the exhaust gas temperature shown in FIG. 7). Therefore, it is possible to rapidly start up the gas turbine 1 while suppressing damage to turbine components due to high-temperature combustion gas and preventing misfires.

[0059] In some embodiments, for example, as in the above-described case A, the first output M1 is set as the output setting value of the starter motor 6 before the switching timing, and the output setting value is increased to the second output M2 after the switching timing. In some embodiments, the ratio r of the second output M2 to the first output B (r B =M2 / M1) may be 1.2 or more or 1.5 or more.

[0060] In this way, by increasing the output setting value of the startup motor 6 from the value before the switching timing (first output M1) to the second output M2 after the switching timing, it is possible to effectively suppress a rise in the temperature of the combustion gas introduced from the combustor 3 to the turbine 4. Therefore, it is possible to rapidly start up the gas turbine 1 while effectively suppressing damage to turbine components due to high-temperature combustion gas and suppressing misfires.

[0061] In some embodiments, the ratio r of the second acceleration rate A2 to the first acceleration rate A1 is A and the ratio r of the second output M2 to the first output M1 B Relative to A / r B is between 0.8 and 1.2.

[0062] In the above-described embodiment, the acceleration rate setting value and the startup motor output setting value are increased by the same amount after the timing at which the fuel command value switches from a constant value to a continuous increase during startup of the gas turbine 1. This allows the gas turbine 1 to be started up quickly while effectively suppressing misfires due to a decrease in the fuel-air ratio and damage to turbine components due to an increase in the temperature of the combustion gas.

[0063] In some embodiments, the acceleration rate setting unit 44 and the motor output setting unit 46 are configured to simultaneously increase the acceleration rate setting value and the output setting value after the switching timing. For example, in case A in Fig. 7, the acceleration rate setting value and the output setting value are simultaneously increased between times t6 and t7.

[0064] In the above-described embodiment, the acceleration rate set value and the startup motor output set value are increased simultaneously after the timing at which the fuel command value switches from a constant value to a continuous increase during startup of the gas turbine 1. This allows the gas turbine 1 to be started up quickly while effectively suppressing misfires due to a decrease in the fuel-air ratio and damage to turbine components due to an increase in the temperature of the combustion gas.

[0065] In some embodiments, the speed increase rate setting unit 44 is configured to start increasing the speed increase rate set value from the time of the switching timing until the rotor rotation speed increases by 300 rpm. In case A in Fig. 7, the speed increase rate set value starts increasing simultaneously with the switching timing (time t6).

[0066] In the above-described embodiment, during startup of the gas turbine 1, after the timing at which the fuel command value is switched from a constant value to a continuous increase, the increase in the speed-up rate set value is started within a short period from the switching timing until the rotor rotation speed increases by 300 rpm. This makes it possible to start the gas turbine more quickly while suppressing misfires.

[0067] In some embodiments, the motor output setting unit 46 is configured to start increasing the output setting value of the startup motor 6 from the time of the switching timing until the rotor rotation speed increases by 300 rpm. In case A in Fig. 7, the increase in the output setting value starts simultaneously with the switching timing (at time t6).

[0068] In the above-described embodiment, during startup of the gas turbine 1, after the timing at which the fuel command value switches from a constant value to a continuous increase, the output setting value of the startup motor 6 starts to increase within a short period of time from the timing at which the fuel command value switches from a constant value to a continuous increase until the rotor rotation speed increases by 300 rpm. This makes it possible to start the gas turbine more quickly while suppressing damage to turbine components due to a rise in the temperature of the combustion gas.

[0069] Next, a control flow of Case B according to one embodiment will be described. The control flow in Case B is the same as Case A in that the acceleration rate set value increases from A1 (first acceleration rate) to A2 (second acceleration rate) after the switching timing (time t6 in Case A, time t3 in Case B) when the fuel command value switches from a constant value to a continuously increasing value.

[0070] In Case B, during startup of the gas turbine 1, a first increase rate A1 is set as the increase rate set value prior to the switching timing (time t3), and a third increase rate A3, which is greater than the first increase rate A1, is set as the increase rate set value prior to that. In the example shown in the graph of Fig. 7, after the ignition timing (time t0) of the gas turbine 1, the increase rate set value is maintained at A3 until time t1, and then the increase rate set value is reduced from A3 to A1 between times t1 and t2. Thereafter, the increase rate set value is increased from A1 to A2 between times t4 and t5 after the switching timing (time t3).

[0071] The speed-up rate setting unit 44 may determine the speed-up rate setting value based on the rotor rotation speed. That is, as shown in FIG. 6, when the rotor rotation speed increases from R0 to R A3 Set the acceleration rate setting to A3 and the rotor speed to R A3 When the rotor speed reaches R, the speed increase rate setting value may be decreased from A3 to A1. A3 From R A4 During this time, the speed increase rate setting value is decreased from A3 to A1. A4 Increase from R A1 The set value of the acceleration rate is maintained at A1 until the rotor speed reaches R A1 When the rotor speed reaches R, the speed increase rate setting value may be increased from A1 to A2. A1 From R A2 During this time, the acceleration rate setting value is increased from A1 to A2.

[0072] In Case B, during startup of the gas turbine 1, at a second time point (t0 to t1) prior to a first time point (times t2 to t3) at which a relatively low first increase rate A1 is set as the increase rate set value before the switching timing (time t3), a third increase rate A3 greater than the first increase rate A1 is set as the increase rate set value. Therefore, compared to Case A and the like in which the third increase rate A3 is not set, the second command value F2 based on the deviation between the actual rotor rotation speed and the target rotor rotation speed becomes larger. This makes it possible to advance the switching timing at which the second command value F2 becomes greater than the first command value F1, thereby enabling more rapid startup of the gas turbine.

[0073] The third speed-up rate A3 may be greater than the second speed-up rate A2 set after the switching timing. This increases the second command value F2 based on the deviation between the actual rotor rotation speed and the target rotor rotation speed, and the switching timing at which the second command value F2 becomes greater than the first command value F1 can be further advanced. This enables the gas turbine to be started up even more quickly.

[0074] The contents described in each of the above embodiments can be understood, for example, as follows.

[0075] (1) A control device (40) for a gas turbine according to at least one embodiment of the present invention includes: A control device for controlling operation of a gas turbine (1), a fuel command value calculation unit (42) for calculating a fuel command value to be given to the gas turbine; a speed increase rate setting unit (44) for setting a speed increase rate setting value of a rotor of the gas turbine; Equipped with The speed-up rate setting unit is configured to increase the speed-up rate set value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit switches from a constant value to a continuously increasing value, during startup of the gas turbine.

[0076] According to the configuration (1) above, during startup of the gas turbine, the rotor speed increase rate set value is increased after the switching timing at which the fuel command value switches from a constant value to a continuous increase. In this way, the speed increase rate set value is set to a relatively low value before the switching timing, and is increased after the switching timing at which the fuel command value starts to continuously increase. This makes it possible to start the gas turbine in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfires. In other words, the gas turbine can be started quickly while suppressing misfires.

[0077] (2) In some embodiments, in the configuration of (1), The speed increase rate setting unit is configured to set a first speed increase rate (A1) as the speed increase rate setting value before the switching timing, and to increase the speed increase rate setting value to a second speed increase rate (A2) greater than the first speed increase rate after the switching timing.

[0078] According to the configuration (2) above, after the switching timing, the rotor speed-up rate setting value is increased from the value before the switching timing (first speed-up rate) to the second speed-up rate, so that the gas turbine can be started up in a relatively short time while more effectively suppressing misfires due to a decrease in the fuel-air ratio.

[0079] (3) In some embodiments, in the configuration of (1) or (2), The control device for the gas turbine includes: a motor output setting unit (46) for setting an output setting value of a startup motor for the gas turbine; The motor output setting unit is configured to increase the output setting value after the switching timing.

[0080] According to the configuration (3) above, during startup of the gas turbine, the output set value of the startup motor is increased after the switching timing at which the fuel command value switches from a constant value to a continuously increasing value. In this way, by increasing the output set value of the startup motor together with the speed increase rate setting value after the switching timing, it is possible to increase the rotor speed while suppressing the increase in the fuel command value. This makes it possible to suppress the temperature rise of the combustion gas introduced from the combustor to the turbine. Therefore, it is possible to rapidly start the gas turbine while suppressing damage to turbine components due to high-temperature combustion gas and preventing misfires.

[0081] (4) In some embodiments, in the configuration of (3), The motor output setting unit is configured to set a first output (M1) as the output setting value before the switching timing, and to increase the output setting value to a second output (M2) greater than the first output after the switching timing.

[0082] According to the configuration (4) above, since the output setting value of the startup motor is increased from the value before the switching timing (first output) to the second output after the switching timing, it is possible to effectively suppress the temperature rise of the combustion gas introduced from the combustor to the turbine. Therefore, it is possible to effectively suppress damage to turbine components due to high-temperature combustion gas and to rapidly start the gas turbine while suppressing misfires.

[0083] (5) In some embodiments, in the configuration of (3) or (4), the speed-up rate setting unit is configured to set a first speed-up rate as the speed-up rate setting value before the switching timing, and to increase the speed-up rate setting value to a second speed-up rate greater than the first speed-up rate after the switching timing; the motor output setting unit is configured to set a first output as the output set value before the switching timing, and to increase the output set value to a second output greater than the first output after the switching timing; The ratio r of the second acceleration rate to the first acceleration rate A and the ratio r of the second output to the first output B Relative to A / r B is between 0.8 and 1.2.

[0084] According to the configuration of (5) above, after the timing at which the fuel command value is switched from a constant value to a continuously increasing value during startup of the gas turbine, the acceleration rate set value and the startup motor output set value are increased by the same amount. This makes it possible to rapidly start up the gas turbine while effectively suppressing misfires due to a drop in the fuel-air ratio and damage to turbine components due to an increase in the temperature of the combustion gas.

[0085] (6) In some embodiments, in any of the configurations (3) to (5) above, The speed increase rate setting unit and the motor output setting unit are configured to simultaneously increase the speed increase rate setting value and the output setting value after the switching timing.

[0086] According to the configuration of (6) above, the acceleration rate set value and the output set value of the startup motor are increased simultaneously after the timing at which the fuel command value is switched from a constant value to a continuously increasing value during startup of the gas turbine. This makes it possible to rapidly start up the gas turbine while effectively suppressing misfires due to a decrease in the fuel-air ratio and damage to turbine components due to an increase in the temperature of the combustion gas.

[0087] (7) In some embodiments, in any of the configurations (1) to (6) above, The speed increase rate setting unit is configured to start increasing the speed increase rate set value from the time of the switching timing until the rotation speed of the rotor increases by 300 rpm.

[0088] According to the configuration of (7) above, after the timing at which the fuel command value is switched from a constant value to a continuously increasing value during startup of the gas turbine, the increase in the speed-up rate set value is started within a short period of time from the timing at which the fuel command value is switched from a constant value to a continuously increasing value until the rotational speed of the rotor increases by 300 rpm. This makes it possible to start up the gas turbine more quickly while suppressing misfires.

[0089] (8) In some embodiments, in any of the configurations (1) to (7) above, the fuel command value calculation unit is configured to calculate, during startup of the gas turbine, a larger one of a first command value that is a constant value and a second command value that is calculated based on a deviation between an actual rotation speed of the rotor and a target rotation speed of the rotor, as the fuel command value, The switching timing is a timing at which the fuel command value calculated by the fuel command value calculation unit switches from the first command value to the second command value.

[0090] According to the configuration of (8) above, during startup of the gas turbine, the rotor speed increase rate set value is increased after a switching timing at which the fuel command value switches from the first command value, which is a constant value, to the second command value based on the deviation between the actual rotor rotation speed and the target rotor rotation speed. In this way, the speed increase rate set value is set to a relatively low value before the switching timing, and is increased after the switching timing at which the fuel command value starts to continuously increase. This makes it possible to start the gas turbine in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfires. In other words, the gas turbine can be started up quickly while suppressing misfires.

[0091] (9) In some embodiments, in the configuration of (8), The fuel command value calculation unit is configured to calculate the target rotation speed of the rotor based on the actual rotation speed of the rotor and the speed increase rate set value.

[0092] According to the configuration of (9) above, the target rotation speed of the rotor is calculated based on the actual rotation speed of the rotor and the speed-up rate set value, so the second command value of the fuel command value corresponds to the speed-up rate set value of the rotor. Therefore, the second command value can be appropriately calculated according to the speed-up rate set value.

[0093] (10) In some embodiments, in the configuration of (8) or (9), The speed-up rate setting unit is configured to set a first speed-up rate (A1) as the speed-up rate setting value at a first point in time before the switching timing during startup of the gas turbine, and to set a third speed-up rate (A3) greater than the first speed-up rate as the speed-up rate setting value at a second point in time before the first point in time.

[0094] According to the configuration of (10) above, during startup of the gas turbine, at a second time point prior to the first time point at which the relatively low first speed-up rate is set as the speed-up rate set value before the switching timing, a third speed-up rate greater than the first speed-up rate is set as the speed-up rate set value. This makes it possible to advance the switching timing at which the second command value based on the deviation between the actual rotation speed of the rotor and the target rotation speed becomes greater than the first command value, thereby enabling a more rapid startup of the gas turbine.

[0095] (11) A control device (40) for a gas turbine according to at least one embodiment of the present invention includes: A control device for controlling operation of a gas turbine, comprising: a fuel command value calculation unit (42) for calculating a fuel command value to be given to the gas turbine; a motor output setting unit (46) for setting an output setting value of a startup motor for the gas turbine; Equipped with The motor output setting unit is configured to increase the output set value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit switches from a constant value to a continuously increasing value during startup of the gas turbine.

[0096] According to the configuration of (11) above, during startup of the gas turbine, the output set value of the startup motor is increased after the switching timing at which the fuel command value switches from a constant value to a continuously increasing value. In this way, by increasing the output set value of the startup motor after the switching timing, it is possible to increase the rotor speed while suppressing the increase in the fuel command value. This makes it possible to suppress the temperature rise of the combustion gas introduced from the combustor to the turbine. Therefore, it is possible to suppress damage to turbine components due to high-temperature combustion gas.

[0097] (12) A gas turbine facility (100) according to at least one embodiment of the present invention includes: a gas turbine (1) including a compressor (2) for compressing air, a combustor (3) for generating combustion gas by a combustion reaction between the compressed air from the compressor and fuel, and a turbine (4) driven by the combustion gas from the combustor; a control device (40) according to any one of (1) to (11) above, configured to control operation of the gas turbine; Equipped with.

[0098] According to the configuration of (12) above, during startup of the gas turbine, the rotor speed increase rate set value is increased after the switching timing at which the fuel command value switches from a constant value to a continuous increase. In this way, the speed increase rate set value is set to a relatively low value before the switching timing, and is increased after the switching timing at which the fuel command value starts to continuously increase. This makes it possible to start the gas turbine in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfires. In other words, the gas turbine can be started quickly while suppressing misfires.

[0099] (13) A method for controlling a gas turbine according to at least one embodiment of the present invention includes: 1. A control method for controlling operation of a gas turbine, comprising: a fuel command value calculation step of calculating a fuel command value to be given to the gas turbine; a speed increase rate setting step of setting a speed increase rate set value of a rotor of the gas turbine; Equipped with In the speed-up rate setting step, during startup of the gas turbine, the speed-up rate set value is increased after a switching timing at which the fuel command value calculated in the fuel command value calculation step switches from a constant value to a continuously increasing value.

[0100] According to the method of (13) above, during startup of the gas turbine, the rotor speed increase rate set value is increased after the switching timing at which the fuel command value switches from a constant value to a continuous increase. In this way, the speed increase rate set value is set to a relatively low value before the switching timing, and is increased after the switching timing at which the fuel command value starts to continuously increase. This makes it possible to start the gas turbine in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfires. In other words, the gas turbine can be started quickly while suppressing misfires.

[0101] (14) A control program for a gas turbine according to at least one embodiment of the present invention includes: A control program for controlling operation of a gas turbine, comprising: On the computer, a fuel command value calculation step of calculating a fuel command value to be given to the gas turbine; a speed-up rate setting step of setting a speed-up rate set value for a rotor of the gas turbine; configured to cause In the step of setting a speed-up rate, during startup of the gas turbine, the speed-up rate set value is increased after a switching timing at which the fuel command value calculated in the step of calculating a fuel command value switches from a constant value to a continuously increasing value.

[0102] According to the configuration of (14) above, during startup of the gas turbine, the rotor speed increase rate set value is increased after the switching timing at which the fuel command value switches from a constant value to a continuous increase. In this way, the speed increase rate set value is set to a relatively low value before the switching timing, and is increased after the switching timing at which the fuel command value starts to continuously increase. This makes it possible to start the gas turbine in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfires. In other words, the gas turbine can be started quickly while suppressing misfires.

[0103] The above describes an embodiment of the present invention, but the present invention is not limited to the above-described embodiment, and also includes forms in which the above-described embodiment is modified, or forms in which these forms are appropriately combined.

[0104] In this specification, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement strictly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. Furthermore, in this specification, expressions representing shapes such as a rectangular shape or a cylindrical shape not only represent rectangular shapes or cylindrical shapes in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. Furthermore, in this specification, the expressions "comprise," "include," or "have" a component are not exclusive expressions that exclude the presence of other components. [Explanation of symbols]

[0105] 1. Gas turbine 2 Compressor 3 Combustor 4 Turbines 5 Rotating shaft 6 Starting motor 7 Fuel Valve 8. Rotational speed measurement unit 11 Surge prevention control output limiter 12 Gas turbine speed signal 14 Subtractor 16 Function Generator 19 Proportional calculator 20 Low Value Selector 21 Signal Generator 22 Adder 23 Low Value Selector 24 Gas turbine speed control calculation output 25 Generator output control calculation output 26 Gas turbine exhaust gas temperature control calculation output 27 Signal Generator 28 Signal Generator 29 Gas turbine fuel ignition command signal 30 Gas turbine misfire prevention command signal 33 High Value Selector 34 Gas turbine control calculation output 40 Control device 42 Fuel command value calculation unit 44 Acceleration rate setting section 46 Motor output setting section 48 Memory section 100 Gas turbine equipment

Claims

1. A control device for controlling operation of a gas turbine, comprising: a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; a speed increase rate setting unit for setting a speed increase rate setting value of a rotor of the gas turbine; Equipped with The speed increase rate setting unit is configured to increase the speed increase rate setting value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit switches from a constant value to a continuous increase during startup of the gas turbine. Control devices for gas turbines.

2. The speed-up rate setting unit is configured to set a first speed-up rate as the speed-up rate setting value before the switching timing, and to increase the speed-up rate setting value to a second speed-up rate greater than the first speed-up rate after the switching timing. The control device for a gas turbine according to claim 1 .

3. a motor output setting unit for setting an output setting value of a startup motor of the gas turbine, The motor output setting unit is configured to increase the output setting value after the switching timing. The gas turbine control device according to claim 1 or 2.

4. The motor output setting unit is configured to set a first output as the output set value before the switching timing, and to increase the output set value to a second output greater than the first output after the switching timing. The control device for a gas turbine according to claim 3 .

5. the speed-up rate setting unit is configured to set a first speed-up rate as the speed-up rate setting value before the switching timing, and to increase the speed-up rate setting value to a second speed-up rate greater than the first speed-up rate after the switching timing, the motor output setting unit is configured to set a first output as the output set value before the switching timing, and to increase the output set value to a second output greater than the first output after the switching timing; The ratio r of the second acceleration rate to the first acceleration rate Ａ and the ratio r of the second output to the first output Ｂ Relative to Ａ / r Ｂ is 0.8 or more and 1.2 or less The control device for a gas turbine according to claim 3 .

6. The speed increase rate setting unit and the motor output setting unit are configured to simultaneously increase the speed increase rate setting value and the output setting value after the switching timing. The control device for a gas turbine according to claim 3 .

7. The speed increase rate setting unit is configured to start increasing the speed increase rate setting value from the time of the switching timing until the rotation speed of the rotor increases by 300 rpm. The gas turbine control device according to claim 1 or 2.

8. the fuel command value calculation unit is configured to calculate, during startup of the gas turbine, a larger one of a first command value that is a constant value and a second command value that is calculated based on a deviation between an actual rotation speed of the rotor and a target rotation speed of the rotor, as the fuel command value, The switching timing is a timing at which the fuel command value calculated by the fuel command value calculation unit switches from the first command value to the second command value. The gas turbine control device according to claim 1 or 2.

9. the fuel command value calculation unit is configured to calculate the target rotation speed of the rotor based on the actual rotation speed of the rotor and the speed increase rate set value. The control system for a gas turbine according to claim 8.

10. The speed-up rate setting unit is configured to set a first speed-up rate as the speed-up rate set value at a first time point before the switching timing during startup of the gas turbine, and to set a third speed-up rate greater than the first speed-up rate as the speed-up rate set value at a second time point before the first time point. The control system for a gas turbine according to claim 8.

11. A control device for controlling operation of a gas turbine, comprising: a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; a motor output setting unit for setting an output setting value of the startup motor of the gas turbine; Equipped with The motor output setting unit is configured to increase the output setting value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit switches from a constant value to a continuous increase during startup of the gas turbine. Control devices for gas turbines.

12. a gas turbine including a compressor for compressing air, a combustor for generating combustion gas by a combustion reaction between the compressed air from the compressor and fuel, and a turbine driven by the combustion gas from the combustor; a controller according to claim 1 or 11 configured to control operation of the gas turbine; A gas turbine facility comprising:

13. 1. A control method for controlling operation of a gas turbine, comprising: a fuel command value calculation step of calculating a fuel command value to be given to the gas turbine; a speed increase rate setting step of setting a speed increase rate set value of a rotor of the gas turbine; Equipped with In the speed increase rate setting step, during startup of the gas turbine, the speed increase rate setting value is increased after a switching timing at which the fuel command value calculated in the fuel command value calculation step switches from a constant value to a continuously increasing value. A method for controlling a gas turbine.

14. A control program for controlling operation of a gas turbine, comprising: On the computer, a fuel command value calculation step of calculating a fuel command value to be given to the gas turbine; a speed-up rate setting step of setting a speed-up rate set value for a rotor of the gas turbine; configured to cause In the step of setting the speed-up rate, during startup of the gas turbine, after a switching timing at which the fuel command value calculated in the step of calculating the fuel command value switches from a constant value to a continuously increasing value, the speed-up rate setting value is increased. Gas turbine control program.

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