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

Abstract

A control device for a gas turbine for controlling the operation of the gas turbine, the control device being provided with: a fuel command value calculation unit for calculating a fuel command value to be supplied to the gas turbine; and a rate-of-lift setting unit for setting a rate-of-lift setting value for a rotor of the gas turbine, the rate-of-lift setting unit being configured so as to set a rate-of-lift setting value for the rotor of the gas turbine after a switching timing at which the fuel command value calculated by the fuel command value calculation unit is switched from a constant state to a continuous increase state during the gas turbine start-up. And increasing the speed increasing rate set value.

Description

Technical Field

[0001] The present disclosure relates to a control device for a gas turbine, a gas turbine plant, a control method for a gas turbine, and a control program for a gas turbine.

[0002] This application claims priority based on Japanese Patent Application No. 2022-110230 filed with the Japan Patent Office on July 8, 2022, and the contents of which are incorporated herein by reference. Background Art

[0003] When the gas turbine is started, after the fuel in the combustor is ignited, the rotor speed is increased until the rotor speed reaches a predetermined speed (for example, a rated speed).

[0004] For example, Patent Document 1 describes that when a gas turbine is started, after the fuel is ignited, the rotor rotation speed is increased at a predetermined rotation acceleration (acceleration rate) determined based on a safety index representing the relationship between damage to gas turbine components and the rotation acceleration of the rotor.

[0005] Prior art literature

[0006] Patent Literature

[0007] Patent Document 1: Japanese Patent Application Publication No. 2013-221423 Summary of the invention

[0008] Problems to be solved by the invention

[0009] However, in order to shorten the start-up time of the gas turbine, it is considered to set the rotor acceleration rate (rotational acceleration) during the start-up of the gas turbine to a larger value than before. However, in the period when the fuel supply amount is relatively small immediately after the gas turbine is ignited, if the output of the starting motor and the like is increased in order to increase the rotor acceleration rate, the rotor rotation speed will increase significantly compared with the past, and the air suction amount in the compressor will increase, thereby reducing the fuel-air ratio (F / A ratio), and the possibility of misfire in the combustor will increase.

[0010] In view of the above, an object of at least one embodiment of the present invention is to provide a gas turbine control device, a gas turbine plant, a gas turbine control method, and a gas turbine control program that can quickly start the gas turbine while suppressing misfire.

[0011] Means for solving problems

[0012] A control device for a gas turbine according to at least one embodiment of the present invention is a control device for controlling the operation of a gas turbine, wherein:

[0013] The gas turbine control device comprises:

[0014] a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; and

[0015] a speed-up rate setting unit for setting a speed-up rate setting value of a rotor of the gas turbine,

[0016] The rate of increase setting unit is configured to increase the rate of increase setting value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit is switched from a constant value to a continuous increase during startup of the gas turbine.

[0017] Furthermore, a control device for a gas turbine according to at least one embodiment of the present invention is a control device for controlling the operation of a gas turbine, wherein:

[0018] The gas turbine control device comprises:

[0019] a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; and

[0020] a motor output setting unit for setting an output setting value of a starting motor of the gas turbine,

[0021] 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 is switched from a constant value to a continuous increase during startup of the gas turbine.

[0022] Furthermore, a gas turbine plant according to at least one embodiment of the present invention includes:

[0023] a gas turbine including a compressor for compressing air, a combustor for generating combustion gas by a combustion reaction of compressed air from the compressor and a fuel, and a turbine driven by the combustion gas from the combustor; and

[0024] The above-mentioned control device is configured to control the operation of the gas turbine.

[0025] Furthermore, a gas turbine control method according to at least one embodiment of the present invention is a control method for controlling the operation of a gas turbine, wherein:

[0026] The gas turbine control method comprises:

[0027] a fuel command value calculating step of calculating a fuel command value to be provided to the gas turbine; and

[0028] a step of setting a rate of increase, setting a set value of the rate of increase of the rotor of the gas turbine,

[0029] In the rate of increase setting step, the rate of increase setting value is increased after a switching timing at which the fuel command value calculated in the fuel command value calculation step is switched from a constant value to a continuous increase during the startup of the gas turbine.

[0030] Furthermore, a control program for a gas turbine according to at least one embodiment of the present invention is a control program for controlling the operation of a gas turbine, wherein:

[0031] The gas turbine control program is configured to cause a computer to execute:

[0032] a fuel command value calculation process of calculating a fuel command value to be provided to the gas turbine; and

[0033] The process of setting the rate of increase is to set a set value of the rate of increase of the rotor of the gas turbine.

[0034] In the rate of increase setting process, the rate of increase setting value is increased after a switching timing at which the fuel command value calculated by the fuel command value calculation process is switched from a constant value to a continuous increase during the startup of the gas turbine.

[0035] Effects of the Invention

[0036] According to at least one embodiment of the present invention, there are provided a gas turbine control device, a gas turbine plant, a gas turbine control method, and a gas turbine control program capable of rapidly starting the gas turbine while suppressing misfire. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 This is a schematic configuration diagram of a gas turbine plant including a control device according to an embodiment.

[0038] Figure 2 This is a schematic configuration diagram of a control device according to one embodiment.

[0039] Figure 3 This is a block diagram showing the operation logic of the control device according to one embodiment.

[0040] Figure 4 This is a graph showing an example of the relationship between the rotor rotation speed and the acceleration rate setting value at the time of gas turbine startup.

[0041] Figure 5 This is a graph showing an example of the relationship between the rotor rotation speed and the output setting value of the starting motor when the gas turbine is started.

[0042] Figure 6 This is a graph showing an example of the relationship between the rotor rotation speed and the acceleration rate setting value at the time of gas turbine startup.

[0043] Figure 7This is a graph showing an example of time changes in the acceleration rate setting value, the output setting value of the starting motor, the rotation speed of the rotor, the fuel command value, the exhaust gas temperature, and the actual acceleration rate of the rotor during the startup of the gas turbine. DETAILED DESCRIPTION

[0044] 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 the components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention but are merely illustrative examples.

[0045] (Structure of gas turbine equipment)

[0046] Figure 1 1 is a schematic structural diagram of a gas turbine plant including a control device according to one embodiment. Figure 1 As shown, the gas turbine plant 100 includes a gas turbine 1 and a control device 40 for controlling the operation of the gas turbine 1 .

[0047] The gas turbine 1 includes a compressor 2 for compressing air, a combustor 3 for burning fuel (eg, natural gas) to generate combustion gas, and a turbine 4 configured to be rotated by the combustion gas. The compressor 2 and the turbine 4 are connected via a rotating shaft 5 .

[0048] The combustor 3 is supplied with fuel (natural gas, etc.) and compressed air from the compressor 2 , and the fuel is combusted using the compressed air as an oxidant to generate combustion gas. The flow rate of the fuel supplied to the combustor 3 can be adjusted by a fuel valve 7 .

[0049] The combustion gas generated in the combustor 3 is guided to the turbine 4 to rotate the turbine 4. The combustion gas that has completed the work in the turbine 4 is discharged from the turbine 4 as exhaust gas. It should be noted that a generator (not shown) may be connected to the turbine 4 via a rotating shaft 5, and the turbine 4 may drive the generator to generate electricity.

[0050] like Figure 1 As shown, the gas turbine 1 may also include a starting motor 6. The starting motor 6 can provide rotational power to the rotating shaft 5 of the gas turbine 1 to drive the rotating shaft 5 to rotate. The starting motor 6 may also be configured to assist the rotation drive of the gas turbine 1 until the gas turbine 1 can rotate independently by its own combustion energy when the gas turbine 1 is started.

[0051] In some embodiments, the generator connected to the gas turbine 1 via the rotating shaft 5 may also receive power supply and function as a starter motor 6. In this case, in order to rotate the generator as a motor, variable voltage and variable frequency power may be supplied to the generator through a frequency converter such as a static frequency converter (SFC).

[0052] The gas turbine 1 may include a rotation speed measuring unit 8 for measuring the rotation speed of the rotating shaft 5 of the gas turbine 1 (the rotation speed of the rotor of the gas turbine 1). The rotation speed measuring unit 8 may include a rotation speed sensor such as an encoder. A signal indicating a measured value of the rotation speed of the rotor by the rotation speed measuring unit 8 is sent to the control device 40.

[0053] (Structure of control device)

[0054] Figure 2 FIG. 4 is a schematic diagram of a control device 40 according to an embodiment of the present invention. Figure 2 As shown, the control device 40 includes a fuel command value calculation unit 42 and a rate setting unit 44. The control device 40 may also include a motor output setting unit 46 and / or a storage unit 48. The control device 40 is configured to receive a signal representing a measured value (actual speed) of the rotor speed from the speed measuring unit 8 and process the signal. Alternatively, the calculation result in the control device 40 is sent to the fuel valve 7 or the starting motor 6, and the fuel valve 7 or the starting motor 6 operates based on the calculation result.

[0055] 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 the fuel command value FI. The control device 40 may be configured to adjust the opening of the fuel valve 7 in accordance with the fuel command value FI.

[0056] The acceleration rate setting unit 44 is configured to set an acceleration rate setting value of the rotor during startup of the gas turbine 1. The acceleration rate setting unit 44 may set different acceleration rate setting values ​​according to the rotation speed (rated rotation speed, etc.) during operation after startup of the gas turbine 1. The acceleration rate setting value may also be used in the calculation of the fuel command value FI by the fuel command value calculation unit 42.

[0057] The motor output setting unit 46 is configured to set the output setting value of the starting motor 6 during the starting of the gas turbine 1. The output setting value set by the motor output setting unit 46 is sent to the starting motor 6, and the starting motor 6 operates in a manner to obtain the set output. It should be noted that, when a generator is used together with a frequency conversion device such as an SFC as the starting motor 6, the motor output setting unit 46 may also be configured to set the output setting value of the frequency conversion device as the output setting value of the starting motor 6.

[0058] The storage unit 48 is configured to store input and output to the control device 40, calculation results in the control device 40, etc. The acceleration rate setting unit 44 may also be configured to read and set the acceleration rate setting value stored in the storage unit 48. The motor output setting unit 46 may also be configured to read and set the output setting value stored in the storage unit 48. The storage unit 48 may also include a main storage device or an auxiliary storage device of a computer constituting the control device 40.

[0059] The control device 40 includes a computer having a processor (CPU, etc.), a main storage device (storage device; RAM, etc.), an auxiliary storage device, and an interface. The control device 40 receives a signal from the rotation speed measuring unit 8 via the interface. The processor is configured to process the signal received in this way. In addition, the processor is configured to process the program developed in the main storage device. Thus, 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) are realized.

[0060] The processing contents in the control device 40 are installed as programs executed by the processor. The programs may be stored in, for example, an auxiliary storage device. When the programs are executed, the programs are expanded in the main storage device. The processor reads the programs from the main storage device and executes the commands included in the programs.

[0061] Figure 3 This is a block diagram showing the operation 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.

[0062] exist Figure 3 , reference numeral 11 is a surge prevention control output limiter, 12 is a gas turbine speed signal, 14 is a subtractor, 16 is a function generator, 19 is a proportional operator, 20 is a low value selector, 21 is a signal generator, 22 is an adder, 23 is a low value selector, 24 is a gas turbine speed control operation output, 25 is a generator output control operation output, 26 is a gas turbine exhaust gas temperature control operation output, 27 and 28 are signal generators, 29 is a gas turbine fuel ignition command signal, 30 is a gas turbine misfire prevention command signal, 31 and 32 are contacts that are closed when the signals 29 and 30 are turned on, 33 is a high value selector, and 34 is a gas turbine control operation output (fuel command value output).

[0063] In the parts of the reference numerals 11 to 22, as described later, the 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. The gas turbine rotation speed control calculation output 24 outputs the fuel flow rate in a state where the gas turbine is in the vicinity of the rated rotation speed. The generator output control calculation output 25 outputs the fuel flow rate in a state where the generator of the gas turbine 1 is connected to the power system and transmits power to it. The gas turbine exhaust gas temperature control calculation output 26 outputs the fuel flow rate determined based on the exhaust gas temperature of the gas turbine so that the turbine blades of the gas turbine, etc. do not become abnormally high temperature. The low value selector 23 selects the lowest value among these outputs and outputs it to the high value selector 33.

[0064] When the gas turbine 1 is started, the fuel flow rate from reference numerals 11 to 22 (second command value F2 ) in the above-mentioned output is the lowest value, and is therefore selected by the low value selector 23 and output to the high value selector 33 .

[0065] On the other hand, when the gas turbine 1 is started, the output of the signal generator 27 when the gas turbine fuel ignition command signal 29 is turned on or the output of the signal generator 28 when the gas turbine misfire prevention command signal 30 is turned on is input to the high value selector 33. The output of the signal generator 27 or the signal generator 28 (the first command value F1) is a constant value.

[0066] The high value selector 33 selects the highest value among the plurality of inputs and outputs it. When the gas turbine 1 is started, the larger one of the output of the signal generator 27 (the first command value F1) and the fuel flow rate from the portion of reference numerals 11 to 22 (the second command value F2) is selected and output to the gas turbine control calculation output 34. That is, when the gas turbine 1 is started, the larger one of the output of the signal generator 27 (the first command value F1) and the fuel flow rate from the portion of reference numerals 11 to 22 (the second command value F2) is calculated as the fuel command value FI.

[0067] Here, the calculation of the parts denoted by reference numerals 11 to 22 will be described. The output of the surge prevention control output limiter 11 is obtained based on 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 measuring unit 8 (a signal indicating the actual rotation speed of the rotor of the gas turbine 1), and is input to the subtractor 14 and the function generator 16.

[0068] The function generator 16 receives the actual rotation speed of the rotor from the gas turbine rotation speed signal 12 and receives the actual rotation speed of the rotor from the acceleration rate setting unit 44 (see Figure 2) receives the speed increase rate setting value, and calculates the target speed of the rotor of the gas turbine 1 based on the actual speed of the rotor and the speed increase rate setting value. The function generator 16 may also calculate the value obtained by adding the speed increase amount corresponding to the speed increase rate to the actual speed of the rotor as the target speed.

[0069] The subtractor 14 subtracts the gas turbine speed signal 12 from the output of the function generator 16, and uses the result as the input of the proportional calculator 19. The proportional calculator 19 multiplies the result by a coefficient set internally and outputs the result. The lower value between the output of the proportional calculator 19 and the output of the signal generator 21 is outputted in the low value selector 20. The output of the signal generator 21 is usually zero, so the output of the low value selector 20 is always a negative value. The adder 22 outputs the 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 of the figure numerals 11 to 22, the output (second command value) of the fuel flow rate is calculated based on the speed of the gas turbine 1, etc.

[0070] (Gas turbine control process)

[0071] Next, several embodiments of the control method of the gas turbine 1 will be described. It should be noted that, in the following, the case where the gas turbine 1 is controlled using the control device 40 described above will be described, and in several embodiments, other devices may be used to execute the control method of the gas turbine, or part or all of the steps described below may be performed manually.

[0072] Figure 4 and Figure 6 Each of them is a graph showing an example of the relationship between the rotor rotation speed and the acceleration rate setting value at the time of gas turbine startup. Figure 5 This is a graph showing an example of the relationship between the rotor rotation speed and the output setting value of the starting motor when the gas turbine is started. Figure 7 This is a graph showing an example of time changes in the acceleration rate setting value, the output setting value of the starting motor, the rotor speed (actual speed), the fuel command value, the exhaust gas temperature, and the actual acceleration rate of the rotor during gas turbine startup for multiple cases (cases A to D).

[0073] It should be noted that in Figures 4 to 7 In the figure, R0 is the time when gas turbine 1 is ignited ( Figure 7 R_rated is the rotor speed at the time point t0 in the figure, and R_rated is the speed (e.g., rated speed) of the gas turbine 1 during operation after startup. It should be noted that the startup of the gas turbine 1 includes the period from the start of rotation of the rotor of the gas turbine 1 to the time when the rotor speed increases to a predetermined speed (e.g., rated speed).

[0074] First, refer to Figure 7The control flow in Case C, which is a typical example of the related art, will be described.

[0075] In case C, during the period before time t0, the rotor of the gas turbine 1 is driven to rotate by the starting motor 6. At this time, the output setting value of the starting motor 6 is M0.

[0076] At time t0, the fuel is ignited by the burner 3. The rotor speed at this time is R0. At time t0, the acceleration rate setting value and the output setting value of the starting motor 6 are set to predetermined values ​​(for example, values ​​predetermined according to the speed after the gas turbine 1 is started, etc.). In case C, the acceleration rate setting value is set to A1, and the output setting value of the starting motor 6 is set to M1.

[0077] 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 larger of the first command value F1 (constant value) and the second command value F2 calculated based on the rotation speed of the rotor, etc., that is, the first command value F1 as the fuel command value FI. Fuel is supplied to the gas turbine 1 based on the fuel command value FI, and the rotor rotation speed increases to a certain extent as shown in the graph.

[0078] At time t6, the fuel command value switches from constant to continuous increase. 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 the second command value F2 calculated based on the rotor speed, etc. In this way, the time point when the fuel command value switches from constant to continuous increase is called the switching timing.

[0079] After time t6, the acceleration rate setting value is also maintained at A1, and the output setting value of the starting motor 6 is also maintained at M1. After time t6, the rotor speed increases at a substantially constant slope. This slope corresponds to the acceleration rate setting value A1. Then, the rotor speed is increased until the rotor speed reaches a predetermined speed (e.g., rated speed).

[0080] Next, the control flow of Case A of one embodiment is described. The control flow in Case A is the same as that in Case C until the switching timing (time point t6 in Cases A and C) when the fuel command value switches from a constant value to a continuous increase, but in Case A, after the switching timing, the rate setting unit 44 increases the rate setting value from A1 (first rate) to A2 (second rate). Figure 7 In the example shown in the graph of , the increase rate setting value increases from A1 to A2 during the period from time t6 (the time point of the switching timing) to time t7, and after time t7, the increase rate setting value is maintained at A2.

[0081] It should be noted that the acceleration rate setting unit 44 may also determine the acceleration rate setting value based on the rotor speed. Figure 4 As shown, the rotor speed can also be R A1 Previously, the acceleration rate setting value was set to A1. If the rotor speed becomes R A1 , the rate setting value is increased from A1 to A2. Here, R A1 It is a speed that is higher than the speed at which the switching timing occurs. Figure 4 In the example shown, the rotor speed changes from R A1 becomes R A2 During this period, the rate setting value is increased from A1 to A2.

[0082] In the above-mentioned case A, the speed increase setting value set after the switching timing is A2, which is larger than A1 in the case C. Therefore, in the case A, the slope of the increase in the rotor speed after the switching timing is larger than that in the case C. Therefore, the time required for the rotor speed to increase to the prescribed speed is shortened, and the start-up time of the gas turbine 1 is shortened.

[0083] In order to shorten the start-up time of the gas turbine 1, as shown in Case D, it is also considered to set the acceleration rate setting value to a relatively large value (A2) from the time of ignition (time t0). However, if the acceleration rate setting value is uniformly set to a large value (A2) as in Case D, the rotor speed increases rapidly, and the fuel-air ratio (F / A ratio) decreases due to the increase in the air suction amount in the compressor 2, and the possibility of misfire in the combustor 3 increases. Figure 7 The graph of shows that after the ignition at time t0, the amount of increase in the exhaust gas temperature in Case D decreases while being low. This is because the increase in the rotation speed is large, and therefore the fuel-air ratio (F / A ratio) decreases.

[0084] In contrast, in the above-mentioned 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 continuous increase of the fuel command value starts, thereby suppressing the reduction of the fuel-air ratio (F / A ratio) and suppressing misfire.

[0085] Therefore, in the above-mentioned case A, the gas turbine can be started rapidly while suppressing misfire.

[0086] In addition, in the compressor 2, when the rotor speed is maintained in a predetermined speed range, rotating stall may occur and blade damage may occur. In this regard, in the above-mentioned case A, since the fuel increase rate setting value after the switching timing of switching the fuel command value from constant to continuous increase is relatively large, it is possible to quickly pass through the speed range in which rotating stall occurs in the compressor 2. Therefore, the gas turbine can be started quickly while suppressing the rotating stall in the compressor.

[0087] In some embodiments, for example, as in the above-mentioned example A, at a time point before the switching timing, the first ramp rate A1 is set as the ramp rate setting value, and after the switching timing, the ramp rate setting value increases to the second ramp rate A2. In some embodiments, the ratio of the second ramp rate A2 to the first ramp rate is A (r A =A2 / A1) can be 1.2 or more or 1.5 or more.

[0088] By increasing the rotor acceleration rate setting value from the value before the switching timing (first acceleration rate A1) to the second acceleration rate A2 after the switching timing, the gas turbine 1 can be started in a relatively short time while more effectively suppressing misfire caused by a decrease in the fuel-air ratio.

[0089] exist Figure 7 In case A, after the switching timing, the motor output setting unit 46 increases the output setting value of the starter motor 6 from M1 (first output) to M2 (second output). Figure 7 In the example shown in the graph of , the output setting value increases from M1 to M2 during the period from time t6 (the time point of the switching timing) to time t7 , and the output setting value is maintained at M2 after time t7 .

[0090] It should be noted that the motor output setting unit 46 may also determine the output setting value based on the rotor speed. Figure 5 As shown, the rotor speed can also be R M1 Previously, the output setting value was set to M1. If the rotor speed becomes R M1 , the output setting value increases from M1 to M2. Here, R M1 It is a speed that is higher than the speed at which the switching timing occurs. Figure 5 In the example shown, the rotor speed changes from R M1 Change to R M2 During the period, the output setting value increases from M1 to M2.

[0091] In the above-mentioned case A, during the startup of the gas turbine 1, after the switching timing at which the fuel command value is switched from constant to continuously increasing, the output setting value of the starting motor 6 is increased. In this way, by increasing the output setting value of the starting motor together with the acceleration rate setting value after the switching timing, the rotor speed can be increased while suppressing the increase in the fuel command value. As a result, the temperature rise of the combustion gas introduced from the combustor 3 to the turbine 4 (i.e., Figure 7 (The rise in the exhaust gas temperature shown is also suppressed.) Therefore, damage to the turbine components caused by the high-temperature combustion gas can be suppressed, and the gas turbine 1 can be started quickly while suppressing misfire.

[0092] In some embodiments, for example, as in the above-mentioned example A, the first output M1 is set as the output setting value of the starter motor 6 at a time point 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 of the second output M2 to the first output is B (r B =M2 / M1) can be 1.2 or more or 1.5 or more.

[0093] In this way, by increasing the output setting value of the starting motor 6 from the value before the switching timing (the first output M1) to the second output M2 after the switching timing, it is possible to effectively suppress the temperature rise of the combustion gas introduced from the combustor 3 to the turbine 4. Therefore, it is possible to effectively suppress damage to the turbine components caused by the high-temperature combustion gas, and it is possible to quickly start the gas turbine 1 while suppressing misfires.

[0094] In some embodiments, the ratio of the second rate of increase A2 to the first rate of increase A1 is A The ratio of the second output M2 to the first output M1 B Ratio A / r B It is 0.8 or more and 1.2 or less.

[0095] In the above-described embodiment, during the start-up of the gas turbine 1, the fuel increase rate setting value and the starter motor output setting value are increased by the same amount after the switching timing at which the fuel command value is switched from constant to continuously increasing. Therefore, the gas turbine 1 can be started quickly while effectively suppressing misfires caused by a decrease in the fuel-air ratio and damage to turbine components caused by a temperature increase in the combustion gas.

[0096] In some embodiments, the rate setting unit 44 and the motor output setting unit 46 are configured to increase the rate setting value and the output setting value simultaneously after the switching timing. Figure 7 In case A in FIG. 1 , the rate setting value and the output setting value increase simultaneously between time t6 and time t7.

[0097] In the above-described embodiment, during the start-up of the gas turbine 1, the fuel increase rate setting value and the starter motor output setting value are simultaneously increased after the switching timing at which the fuel command value is switched from constant to continuously increasing. Therefore, the gas turbine 1 can be started rapidly while effectively suppressing misfires caused by a decrease in the fuel-air ratio and damage to turbine components caused by a temperature increase in the combustion gas.

[0098] In some embodiments, the acceleration rate setting unit 44 is configured to start increasing the acceleration rate setting value from the time point of the switching timing to before the rotor speed increases by 300 rpm. Figure 7 In case A, the increase in the rising rate setting value starts at the same time as the switching timing (time point t6).

[0099] In the above-mentioned embodiment, during the start-up of the gas turbine 1, after the switching timing at which the fuel command value is switched from a constant value to a continuously increasing value, the increase in the acceleration rate setting value is started in a short period of time from the time point of the switching timing to the time when the rotor rotation speed increases by 300 rpm, thereby enabling the gas turbine to be started more quickly while suppressing misfire.

[0100] In some embodiments, the motor output setting unit 46 is configured to start increasing the output setting value of the starting motor 6 before the rotor speed increases by 300 rpm from the switching timing. Figure 7 In case A in FIG. 1 , the output setting value starts to increase at the same time as the switching timing (time point t6 ).

[0101] In the above-described embodiment, during the start-up of the gas turbine 1, after the switching timing at which the fuel command value is switched from a constant value to a continuously increasing value, the increase in the output setting value of the starting motor 6 is started in a short period of time from the time point of the switching timing to when the rotation speed of the rotor increases by 300 rpm, thereby enabling the gas turbine to be started more quickly while suppressing damage to the turbine components caused by the increase in the temperature of the combustion gas.

[0102] Next, the control flow of Case B of one embodiment is described. The control flow of Case B is the same as that of Case A in that the fuel increase rate setting value increases from A1 (first fuel increase rate) to A2 (second fuel increase rate) after the switching timing (time point t6 in Case A and time point t3 in Case B) when the fuel command value switches from constant to continuous increase.

[0103] In case B, during the startup of the gas turbine 1, at a time point before the switching timing (time t3), the first rate of increase A1 is set as the rate of increase setting value, and at a time point before that, a third rate of increase A3 greater than the first rate of increase A1 is set as the rate of increase setting value. Figure 7 In the example shown in the graph of , after the ignition time point of the gas turbine 1 (time t0), the speed increase rate setting value is maintained at A3 until time t1, and the speed increase rate setting value is reduced from A3 to A1 between time t1 and t2. Then, between time t4 and t5 after the switching timing (time t3), the speed increase rate setting value is increased from A1 to A2.

[0104] It should be noted that the acceleration rate setting unit 44 may also determine the acceleration rate setting value based on the rotor speed. Figure 6 As shown, the rotor speed can also increase from R0 to R A3 Previously, the acceleration rate setting value was set to A3. If the rotor speed becomes R A3 , then the rate setting value is reduced from A3 to A1. Figure 6 In the example shown, the rotor speed changes from R A3 Change to R A4 During the period of time, the acceleration rate setting value is reduced from A3 to A1. In addition, the rotor speed can also be changed from R A4 Increase to become R A1 Previously, the acceleration rate setting value was maintained at A1. If the rotor speed becomes R A1 , the rate setting value is increased from A1 to A2. Figure 6 In the example shown, the rotor speed changes from R A1 Change to R A2 During this period, the rate setting value is increased from A1 to A2.

[0105] In case B, during the startup of the gas turbine 1, a third acceleration rate A3 greater than the first acceleration rate A1 is set as the acceleration rate setting value at a second time point (t0-t1) before a first time point (time t2-t3) at which the first acceleration rate A1, which is lower, is set as the acceleration rate setting value before the switching timing (time t3). Therefore, the second command value F2 based on the deviation between the actual rotation speed of the rotor and the target rotation speed becomes a larger value than in case A, etc., in which the third acceleration rate A3 is not set. Therefore, the switching timing at which the second command value F2 is greater than the first command value F1 can be advanced, thereby enabling a more rapid startup of the gas turbine.

[0106] It should be noted that the third speed increase rate A3 may be greater than the second speed increase rate A2 set after the switching timing. As a result, the second command value F2 based on the deviation between the actual rotation speed of the rotor and the target rotation speed becomes a larger value, so the switching timing at which the second command value F2 is greater than the first command value F1 can be further advanced. Therefore, the gas turbine can be started more quickly.

[0107] The contents described in each of the above-mentioned embodiments can be understood, for example, as follows.

[0108] (1) A control device (40) for a gas turbine according to at least one embodiment of the present invention is used to control the operation of a gas turbine (1), wherein:

[0109] The control device comprises:

[0110] a fuel command value calculation unit (42) for calculating a fuel command value to be provided to the gas turbine; and

[0111] A speed increase setting unit (44) is used to set a speed increase setting value of a rotor of the gas turbine.

[0112] The rate of increase setting unit is configured to increase the rate of increase setting value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit is switched from a constant value to a continuous increase during startup of the gas turbine.

[0113] According to the configuration of (1) above, during the start-up of the gas turbine, the rotor acceleration rate setting value is increased after the switching timing at which the fuel command value is switched from constant to continuously increasing. In this way, the acceleration rate setting value is set to a relatively low value before the switching timing, and the acceleration rate setting value is increased after the switching timing at which the continuous increase of the fuel command value starts. Therefore, the gas turbine can be started in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfire. That is, the gas turbine can be started quickly while suppressing misfire.

[0114] (2) In some embodiments, based on the structure of (1) above,

[0115] The acceleration rate setting unit is configured to set a first acceleration rate (A1) as the acceleration rate setting value at a time point before the switching timing, and to increase the acceleration rate setting value to a second acceleration rate (A2) greater than the first acceleration rate after the switching timing.

[0116] According to the configuration of (2) above, after the switching timing, the rotor acceleration rate setting value is increased from the value before the switching timing (the first acceleration rate) to the second acceleration rate, so that the gas turbine can be started in a relatively short time while more effectively suppressing misfire caused by a decrease in the fuel-air ratio.

[0117] (3) In some embodiments, based on the structure of (1) or (2) above,

[0118] The control device for the gas turbine includes a motor output setting unit (46) for setting an output setting value of a starting motor of the gas turbine.

[0119] The motor output setting unit is configured to increase the output setting value after the switching timing.

[0120] According to the configuration of (3) above, during the start-up of the gas turbine, after the switching timing at which the fuel command value is switched from constant to continuously increasing, the output setting value of the starting motor is increased. In this way, by increasing the output setting value of the starting motor together with the acceleration rate setting value after the switching timing, the rotor can be accelerated while suppressing the increase in the fuel command value. As a result, the temperature rise of the combustion gas introduced from the combustor to the turbine can be suppressed. Therefore, damage to the turbine components caused by the high-temperature combustion gas can be suppressed, and the gas turbine can be started quickly while suppressing misfires.

[0121] (4) In some embodiments, based on the structure of (3) above,

[0122] The motor output setting unit is configured to set a first output (M1) as the output setting value at a time point before the switching timing, and to increase the output setting value to a second output (M2) larger than the first output after the switching timing.

[0123] According to the configuration of (4) above, after the switching timing, the output setting value of the starting motor is increased from the value before the switching timing (first output) to the second output, so that the temperature rise of the combustion gas introduced from the combustor to the turbine can be effectively suppressed. Therefore, damage to the turbine components caused by the high-temperature combustion gas can be effectively suppressed, and the gas turbine can be started quickly while suppressing misfire.

[0124] (5) In some embodiments, based on the structure of (3) or (4),

[0125] The rate setting unit is configured to set a first rate as the rate setting value at a time point before the switching timing, and to increase the rate setting value to a second rate greater than the first rate after the switching timing.

[0126] The motor output setting unit is configured to set a first output as the output setting value at a time point before the switching timing, and to increase the output setting value to a second output greater than the first output after the switching timing.

[0127] The ratio of the second rate of increase to the first rate of increase is r A The ratio of the second output to the first output B Ratio A / r B It is 0.8 or more and 1.2 or less.

[0128] According to the structure of (5) above, during the start-up of the gas turbine, after the fuel command value is switched from a constant value to a continuously increasing value, the acceleration rate setting value and the output setting value of the starting motor are increased by the same degree, thereby making it possible to quickly start the gas turbine while effectively suppressing misfires caused by a decrease in the fuel-air ratio and damage to turbine components caused by a temperature increase of the combustion gas.

[0129] (6) In some embodiments, based on any one of the structures (3) to (5) above,

[0130] The increase rate setting unit and the motor output setting unit are configured to increase the increase rate setting value and the output setting value simultaneously after the switching timing.

[0131] According to the structure of (6) above, during the start-up of the gas turbine, after the fuel command value is switched from a constant value to a continuously increasing value, the acceleration rate setting value and the output setting value of the starting motor are increased simultaneously, thereby making it possible to start the gas turbine rapidly while effectively suppressing misfires caused by a decrease in the fuel-air ratio and damage to turbine components caused by a temperature increase of the combustion gas.

[0132] (7) In some embodiments, based on any one of the structures (1) to (6) above,

[0133] The speed increase rate setting unit is configured to start increasing the speed increase rate setting value before the rotation speed of the rotor increases by 300 rpm from the time point of the switching timing.

[0134] According to the structure of (7) above, during the start-up of the gas turbine, after the fuel command value is switched from a constant value to a continuously increasing value, the increase in the acceleration rate setting value begins in a short period of time from the time point of the switching timing to the time when the rotor speed increases by 300 rpm, thereby enabling the gas turbine to be started more quickly while suppressing misfire.

[0135] (8) In some embodiments, based on any one of the structures (1) to (7) above,

[0136] The fuel command value calculation unit is configured to calculate, during the 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 as the fuel command value,

[0137] The switching timing is a timing at which the fuel command value calculated by the fuel command value calculation unit is switched from the first command value to the second command value.

[0138] According to the configuration of (8) above, during the start-up of the gas turbine, after the switching timing at which the fuel command value is switched from the first command value, which is a constant value, to the second command value based on the deviation between the actual rotation speed of the rotor and the target rotation speed, the acceleration rate setting value of the rotor is increased. In this way, the acceleration rate setting value is set to a relatively low value before the switching timing, and the acceleration rate setting value is increased after the switching timing at which the continuous increase of the fuel command value starts. Therefore, the gas turbine can be started in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfire. That is, the gas turbine can be started quickly while suppressing misfire.

[0139] (9) In some embodiments, based on the structure of (8),

[0140] The fuel command value calculation unit is configured to calculate the target rotation speed of the rotor based on an actual rotation speed of the rotor and the acceleration rate setting value.

[0141] According to the configuration of (9), the target rotation speed of the rotor is calculated based on the actual rotation speed of the rotor and the acceleration rate setting value, so the second command value of the fuel command value corresponds to the acceleration rate setting value of the rotor. Therefore, the second command value can be appropriately calculated based on the acceleration rate setting value.

[0142] (10) In some embodiments, based on the structure of (8) or (9),

[0143] The acceleration rate setting unit is configured to set a first acceleration rate (A1) as the acceleration rate setting value at a first time point before the switching timing during the startup of the gas turbine, and to set a third acceleration rate (A3) greater than the first acceleration rate as the acceleration rate setting value at a second time point before the first time point.

[0144] According to the configuration of (10), during the startup of the gas turbine, the third acceleration rate greater than the first acceleration rate is set as the acceleration rate setting value at the second time point before the first time point at which the first acceleration rate, which is lower, is set as the acceleration rate setting value before the switching timing. Therefore, 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 can be brought forward, thereby enabling the gas turbine to be started more rapidly.

[0145] (11) A control device (40) for a gas turbine according to at least one embodiment of the present invention is used to control the operation of a gas turbine, wherein:

[0146] The control device comprises:

[0147] a fuel command value calculation unit (42) for calculating a fuel command value to be provided to the gas turbine; and

[0148] a motor output setting unit (46) for setting an output setting value of a starting motor of the gas turbine,

[0149] 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 is switched from a constant value to a continuous increase during startup of the gas turbine.

[0150] According to the configuration of (11) above, during the start-up of the gas turbine, after the switching timing at which the fuel command value is switched from constant to continuously increasing, the output setting value of the starting motor is increased. Thus, by increasing the output setting value of the starting motor after the switching timing, the rotor speed can be increased while suppressing the increase in the fuel command value. Thus, the temperature rise of the combustion gas introduced from the combustor to the turbine can be suppressed. Therefore, damage to the turbine components caused by the high-temperature combustion gas can be suppressed.

[0151] (12) A gas turbine facility (100) according to at least one embodiment of the present invention includes:

[0152] A gas turbine (1) comprising a compressor (2) for compressing air, a burner (3) for generating combustion gas by a combustion reaction of compressed air from the compressor and fuel, and a turbine (4) driven by the combustion gas from the burner; and

[0153] The control device (40) according to any one of (1) to (11) above is configured to control the operation of the gas turbine.

[0154] According to the configuration of (12) above, during the start-up of the gas turbine, the rotor acceleration rate setting value is increased after the switching timing at which the fuel command value is switched from constant to continuously increasing. In this way, the acceleration rate setting value is set to a relatively low value before the switching timing, and the acceleration rate setting value is increased after the switching timing at which the continuous increase of the fuel command value starts. Therefore, the gas turbine can be started in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfire. That is, the gas turbine can be started quickly while suppressing misfire.

[0155] (13) A gas turbine control method according to at least one embodiment of the present invention is a control method for controlling the operation of a gas turbine, wherein:

[0156] The gas turbine control method comprises:

[0157] a fuel command value calculating step of calculating a fuel command value to be provided to the gas turbine; and

[0158] a step of setting a rate of increase, setting a set value of the rate of increase of the rotor of the gas turbine,

[0159] In the rate of increase setting step, the rate of increase setting value is increased after a switching timing at which the fuel command value calculated in the fuel command value calculation step is switched from a constant value to a continuous increase during the startup of the gas turbine.

[0160] According to the method of (13) above, during the start-up of the gas turbine, after the switching timing at which the fuel command value is switched from constant to continuously increasing, the rotor acceleration rate setting value is increased. In this way, the acceleration rate setting value is set to a relatively low value before the switching timing, and the acceleration rate setting value is increased after the switching timing at which the continuous increase of the fuel command value starts. Therefore, the gas turbine can be started in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfire. That is, the gas turbine can be started quickly while suppressing misfire.

[0161] (14) A control program for a gas turbine according to at least one embodiment of the present invention is a control program for controlling the operation of a gas turbine, wherein:

[0162] The gas turbine control program is configured to cause a computer to execute:

[0163] a fuel command value calculation process of calculating a fuel command value to be provided to the gas turbine; and

[0164] The process of setting the rate of increase is to set a set value of the rate of increase of the rotor of the gas turbine.

[0165] In the rate of increase setting process, the rate of increase setting value is increased after a switching timing at which the fuel command value calculated by the fuel command value calculation process is switched from a constant value to a continuous increase during the startup of the gas turbine.

[0166] According to the configuration of (14) above, during the start-up of the gas turbine, the rotor acceleration rate setting value is increased after the switching timing at which the fuel command value is switched from constant to continuously increasing. In this way, the acceleration rate setting value is set to a relatively low value before the switching timing, and the acceleration rate setting value is increased after the switching timing at which the continuous increase of the fuel command value starts. Therefore, the gas turbine can be started in a relatively short time while suppressing a decrease in the fuel-air ratio (F / A ratio) and suppressing misfire. That is, the gas turbine can be started quickly while suppressing misfire.

[0167] As mentioned above, although embodiment of this invention was described, this invention is not limited to the said embodiment, and also includes the form which added deformation|transformation to the said embodiment, and the form which combined these forms suitably.

[0168] In this specification, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" that indicate relative or absolute configurations not only indicate such configurations in a strict sense, but also indicate a state of relative displacement at an angle or distance with a tolerance or a degree that can achieve the same function.

[0169] For example, expressions such as “same”, “equal”, and “homogeneous” indicating a state in which things are equal not only indicate a state of being strictly equal but also indicate a state in which there is a tolerance or a difference to the extent that the same function can be obtained.

[0170] In the present specification, expressions such as a quadrilateral and a cylindrical shape indicate not only shapes such as a quadrilateral and a cylindrical shape in a strict geometric sense, but also shapes including concave-convex portions, chamfered portions, etc. within a range that can obtain the same effect.

[0171] In addition, in this specification, the expression “including”, “comprising” or “having” one component is not an exclusive expression excluding the presence of other components.

[0172] Description of reference numerals:

[0173] 1 Gas turbine

[0174] 2 Compressor

[0175] 3 Burner

[0176] 4 Turbine

[0177] 5 Rotation Axis

[0178] 6 Starting motor

[0179] 7 Fuel valve

[0180] 8. Speed ​​measuring unit

[0181] 11 Surge prevention control output limiter

[0182] 12 Gas turbine speed signal

[0183] 14 Subtractor

[0184] 16 Function Generator

[0185] 19 Proportional operator

[0186] 20 Low value selector

[0187] 21 Signal Generator

[0188] 22 Adder

[0189] 23 Low value selector

[0190] 24 Gas turbine speed control calculation output

[0191] 25 Generator output control calculation output

[0192] 26 Gas turbine exhaust gas temperature control calculation output

[0193] 27 Signal Generator

[0194] 28 Signal Generator

[0195] 29 Gas turbine fuel ignition command signal

[0196] 30 Gas turbine fire prevention command signal

[0197] 33 High value selector

[0198] 34 Gas turbine control calculation output

[0199] 40 Control device

[0200] 42 Fuel command value calculation unit

[0201] 44. Rate setting unit

[0202] 46 Motor output setting unit

[0203] 48 Storage

[0204] 100 Gas turbine equipment.

Claims

1. A control device for a gas turbine, the control device being a control device for controlling the operation of the gas turbine, wherein: The gas turbine control device comprises: a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; and a speed-up rate setting unit for setting a speed-up rate setting value of a rotor of the gas turbine, The rate of increase setting unit is configured to increase the rate of increase setting value after a switching timing at which the fuel command value calculated by the fuel command value calculation unit is switched from a constant value to a continuous increase during startup of the gas turbine.

2. The gas turbine control device according to claim 1, wherein: The rise rate setting unit is configured to set a first rise rate as the rise rate setting value at a time point before the switching timing, and to increase the rise rate setting value to a second rise rate greater than the first rise rate after the switching timing.

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

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

5. The gas turbine control device according to claim 3, wherein: The rate setting unit is configured to set a first rate as the rate setting value at a time point before the switching timing, and to increase the rate setting value to a second rate greater than the first rate after the switching timing. The motor output setting unit is configured to set a first output as the output setting value at a time point before the switching timing, and to increase the output setting value to a second output greater than the first output after the switching timing. The ratio of the second rate of increase to the first rate of increase is r A The ratio of the second output to the first output B Ratio A / r B It is 0.8 or more and 1.2 or less.

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

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

8. The control device for a gas turbine according to claim 1 or 2, wherein: The fuel command value calculation unit is configured to calculate, during the 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 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 is switched from the first command value to the second command value.

9. The gas turbine control device according to claim 8, wherein: The fuel command value calculation unit is configured to calculate the target rotation speed of the rotor based on an actual rotation speed of the rotor and the acceleration rate setting value.

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

11. A control device for a gas turbine, the control device being a control device for controlling the operation of the gas turbine, wherein: The gas turbine control device comprises: a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine; and a motor output setting unit for setting an output setting value of a starting motor of the gas turbine, 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 is switched from a constant value to a continuous increase during startup of the gas turbine.

12. A gas turbine device, wherein: The gas turbine equipment comprises: a gas turbine including a compressor for compressing air, a combustor for generating combustion gases by a combustion reaction of compressed air from said compressor and a fuel, and a turbine driven by said combustion gases from said combustor; as well as The control device according to claim 1 or 11, which is configured to control the operation of the gas turbine.

13. A method for controlling a gas turbine, which is a method for controlling the operation of a gas turbine, wherein: The gas turbine control method comprises: a fuel command value calculating step of calculating a fuel command value to be provided to the gas turbine; and a step of setting a rate of increase, setting a set value of the rate of increase of the rotor of the gas turbine, In the rate of increase setting step, during the startup of the gas turbine, the rate of increase setting value is increased after a switching timing at which the fuel command value calculated in the fuel command value calculation step is switched from a constant value to a continuous increase.

14. A control program for a gas turbine, the control program being for controlling the operation of the gas turbine, wherein: The gas turbine control program is configured to cause a computer to execute: a fuel command value calculation process of calculating a fuel command value to be provided to the gas turbine; and The process of setting the rate of increase is to set a set value of the rate of increase of the rotor of the gas turbine. In the rate of increase setting process, during the startup of the gas turbine, after the switching timing at which the fuel command value calculated by the fuel command value calculation process is switched from a constant value to a continuous increase, the rate of increase setting value is increased.

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