Control device for gas turbine, gas turbine facility and control method for gas turbine

Abstract

To provide a control device for a gas turbine capable of suppressing damage of a flow divider, a gas turbine facility and a control method for the gas turbine.SOLUTION: A control device for a gas turbine is used for controlling the gas turbine that includes a fuel line, a flow regulating valve provided in the fuel line and a flow divider provided downstream of the flow regulating valve in the fuel line to distribute fuel in the fuel line to a plurality of fuel nozzles. The control device includes: an index acquisition section configured to acquire an index indicating pressure in the fuel line at a position between the flow regulating valve and the flow divider; a threshold value acquisition section configured to acquire a threshold value for comparison with the index; and a signal output section configured to output a signal for protecting the flow divider on the basis of the comparison between the index and the threshold value.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The present disclosure relates to a control device for a gas turbine, a gas turbine installation, and a method for controlling a gas turbine. [Background technology]

[0002] In gas turbine equipment, a flow divider is used to evenly distribute liquid fuel (such as fuel oil) to multiple fuel nozzles.

[0003] Patent Document 1 discloses a control method for a gas turbine equipped with a flow divider that can use both liquid and gas fuels. The control method in Patent Document 1 detects an abnormality in the flow divider based on the differential pressure between the inlet and outlet of the flow divider, and if an abnormality is detected, switches the fuel used from liquid fuel to gas fuel. This prevents misfires and shutdowns of the gas turbine due to a flow divider failure. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Publication No. 59-213929 Summary of the Invention [Problem to be solved by the invention]

[0005] If a flow divider is damaged, inspection and part replacement will require time, which may reduce the availability of the gas turbine equipment. Therefore, it is desirable to prevent damage to the flow divider before it occurs.

[0006] In view of the above circumstances, at least one embodiment of the present invention has an object to provide a gas turbine control device, gas turbine equipment, and a gas turbine control method that can suppress damage to a flow divider. [Means for solving the problem]

[0007] A control device for a gas turbine according to at least one embodiment of the present invention comprises: 1. A control device for controlling a gas turbine including: a fuel line; a flow control valve provided in the fuel line; and a flow divider provided in the fuel line downstream of the flow control valve for distributing fuel in the fuel line to a plurality of fuel nozzles, an index obtaining unit configured to obtain an index indicative of a pressure in the fuel line at a location between the flow rate control valve and the flow divider; a threshold acquisition unit configured to acquire a threshold for comparison with the index; a signal output unit configured to output a signal for protecting the flow divider based on a comparison between the indicator and the threshold; Equipped with.

[0008] Moreover, the gas turbine equipment according to at least one embodiment of the present invention includes: A combustor; a fuel line for supplying fuel to the combustor; a flow control valve provided in the fuel line; a flow divider provided in the fuel line downstream of the flow rate control valve for distributing fuel in the fuel line to a plurality of fuel nozzles; a turbine configured to be driven by combustion gases from the combustor; a gas turbine including: the control device described above for controlling the gas turbine; Equipped with.

[0009] Also, there is provided a control method for controlling a gas turbine including a quantity control valve according to at least one embodiment of the present invention, and a flow divider provided in the fuel line downstream of the flow rate control valve for distributing fuel in the fuel line to a plurality of fuel nozzles, the method comprising: obtaining an indication of pressure in the fuel line at a location between the flow control valve and the flow divider; outputting a signal to protect the flow divider based on a comparison of the indicator with a threshold; Equipped with. [Effects of the Invention]

[0010] According to at least one embodiment of the present invention, a control device for a gas turbine, a gas turbine installation, and a method for controlling a gas turbine are provided that are capable of suppressing damage to a flow divider. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a schematic diagram of a gas turbine according to an embodiment. [Figure 2] 1 is a schematic diagram of a gas turbine installation according to an embodiment; [Figure 3] 1 is a schematic diagram of a gas turbine installation according to an embodiment; [Figure 4] FIG. 2 is a schematic diagram of a control device according to an embodiment. [Figure 5] 4 is a flowchart of a control method for the gas turbine 1 according to one embodiment. [Figure 6] 1 is a graph showing an example of the relationship between a threshold (vertical axis) and a gas turbine output (horizontal axis). [Figure 7] 1 is a graph showing an example of the relationship between a threshold (vertical axis) and a gas turbine output (horizontal axis). DETAILED DESCRIPTION OF THE INVENTION

[0012] 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.

[0013] (Gas turbine equipment configuration) Fig. 1 is a schematic diagram of a gas turbine constituting a gas turbine facility according to an embodiment. Fig. 2 and Fig. 3 are each a schematic diagram of a gas turbine facility according to an embodiment. Fig. 4 is a schematic diagram of a control device according to an embodiment.

[0014] As shown in FIGS. 1 to 3, a gas turbine facility 100 according to one embodiment includes a gas turbine 1 and a control device 60 (not shown in FIG. 1) for controlling the gas turbine 1.

[0015] As shown in FIG. 1, the gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas.

[0016] 1, the compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of moving blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16. Air taken in from an air intake 12 is sent to the compressor 2, and this air is compressed as it passes through the plurality of stator vanes 16 and the plurality of moving blades 18, becoming high-temperature, high-pressure compressed air.

[0017] The combustors 4 are supplied with fuel and compressed air generated by the compressor 2, and the fuel is combusted in the combustors 4 to generate combustion gas, which is a working fluid for the turbine 6. As shown in FIG. 1, the gas turbine 1 has a plurality of combustors 4 arranged in a casing 20 along the circumferential direction around a rotor 8 (rotor axis O).

[0018] Each of the plurality of combustors 4 includes at least one fuel nozzle 30 (see FIGS. 2 and 3) for injecting fuel into a combustion chamber inside the combustor 4. The fuel supplied to the combustor 4 includes at least liquid fuel (fuel oil, etc.), and may be configured to supply both liquid fuel and gas fuel. Furthermore, the gas turbine 1 may be configured so that the fuel supplied to the combustor can be switched between liquid fuel and gas fuel.

[0019] The turbine 6 has a combustion gas passage 28 formed by the turbine casing 22, and includes a plurality of stator vanes 24 and rotor blades 26 provided in the combustion gas passage 28. The stator vanes 24 are fixed to the turbine casing 22 side, and the plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row. The rotor blades 26 are implanted in the rotor 8, and the plurality of rotor blades 26 arranged along the circumferential direction of the rotor 8 constitute a rotor blade row. The stator vane rows and rotor blade rows are arranged alternately in the axial direction of the rotor 8.

[0020] In the turbine 6, the combustion gas from the combustor 4 that flows into the combustion gas passage 28 passes through the plurality of stator vanes 24 and the plurality of rotor blades 26, thereby driving the rotor 8 to rotate about the rotor axis O, which in turn drives the generator connected to the rotor 8 to generate electricity. After driving the turbine 6, the combustion gas is discharged to the outside via an exhaust chamber 29.

[0021] As shown in Figures 2 and 3, the gas turbine equipment 100 includes a fuel line 32 for supplying liquid fuel (oil fuel, etc.) to multiple combustors 4, a flow control valve 40 provided in the fuel line 32, and a flow divider 42.

[0022] 2 and 3, a fuel pump 34 for pumping liquid fuel is provided in the fuel line 32 on the upstream side of the flow rate control valve 40. Also, in the exemplary embodiment shown in Figures 2 and 3, a relief pressure regulation valve 38 for maintaining the pressure in the fuel line 32 upstream of the flow rate control valve 40 at a predetermined pressure is provided in the fuel line 32 on the upstream side of the flow rate control valve 40.

[0023] The opening degree of the flow rate control valve 40 may be adjusted according to the output of the gas turbine, etc. Also, the opening degree of the flow rate control valve 40 may be controlled based on a fuel command value (a command value for the amount of fuel supply determined according to the output, etc.) from a control device.

[0024] The flow divider 42 is provided in the fuel line 32 downstream of the flow control valve 40 and is configured to evenly distribute the fuel in the fuel line 32 to the multiple fuel nozzles. The fuel line 32 branches into multiple branch lines 32a downstream of the flow divider 42, and fuel is supplied to the multiple fuel nozzles 30 via the multiple branch lines 32a, respectively.

[0025] The flow divider 42 may have a plurality of gear pumps provided corresponding to the plurality of branch lines 32a, and may be configured to distribute and supply fuel oil at a uniform flow rate to the plurality of branch lines 32a and the plurality of fuel nozzles 30 by synchronously rotating these gear pumps. The rotating shafts of the plurality of gear pumps may be connected via couplings.

[0026] 2 and 3, a shutoff valve 44 is provided to shut off the supply of fuel to the plurality of fuel nozzles 30 via the plurality of branch lines 32a. The shutoff valve 44 shown in Figures 2 and 3 includes a plurality of valve bodies 46 provided in the plurality of branch lines 32a, respectively. The valve shafts of the plurality of valve bodies 46 are linked to each other so as to open and close simultaneously.

[0027] 2 and 3 , only three of each of the branch lines 32a, combustors 4, fuel nozzles 30, and valve bodies 46 of the shutoff valves 44 are shown, and illustrations of any more than three are omitted. In reality, the number of combustors 4 provided in the gas turbine 1 may be 10 or more or 20 or more, and the number of branch lines 32a and fuel nozzles 30 will correspond to the number of combustors 4.

[0028] 2 and 3 includes a detection unit 50 for detecting an indicator that indicates the pressure P1 of the fuel line 32 at a position between the flow control valve 40 and the flow divider 42. A signal that indicates the detected value of the indicator detected by the detection unit 50 is sent to the control device 60.

[0029] 2, the detection unit 50 includes differential pressure gauges 52 (52A, 52B) configured to detect a differential pressure DP1 across the flow control valve 40 in the fuel line 32 as an indicator of the pressure P1 in the fuel line 32 at a position between the flow control valve 40 and the flow divider 42. As shown in FIGS. 2 and 3, in a gas turbine 1 configured so that the pressure in the fuel line 32 upstream of the flow control valve 40 is kept constant, when the pressure P1 at a position between the flow control valve 40 and the flow divider 42 increases, the differential pressure DP1 across the flow control valve 40 decreases. Therefore, the differential pressure DP1 across the flow control valve 40 can be an indicator of the pressure P1 at a position between the flow control valve 40 and the flow divider 42.

[0030] In the exemplary embodiment shown in FIG. 3, the detection unit includes a pressure gauge 54 (54A, 54B) configured to detect the pressure P1 of the fuel line 32 at a position between the flow control valve 40 and the flow divider 42 as an indicator of the pressure P1 of the fuel line 32 at a position between the flow control valve 40 and the flow divider 42.

[0031] As shown in FIGS. 2 and 3, the detection unit 50 may include a plurality of detectors (differential pressure gauges 52A, 52B or pressure gauges 54A, 54B) configured to independently detect the above-mentioned indicators.

[0032] The control device 60 is configured to control the gas turbine 1 based on the detection value of the above-mentioned indicator (indicator of the pressure P1 in the fuel line 32 at a position between the flow rate control valve 40 and the flow divider 42) detected by the detection unit 50 (such as the differential pressure gauge 52 or the pressure gauge 54). As shown in Fig. 4, the control device 60 includes an indicator acquisition unit 62, a threshold acquisition unit 64, and a signal output unit 66. The control device 60 may also include a threshold setting unit 68.

[0033] The index acquisition unit 62 is configured to acquire an index indicative of the pressure P1 of the fuel line 32 at a position between the flow rate adjustment valve 40 and the flow divider 42.

[0034] The index acquiring unit 62 may acquire the index based on a signal from the detecting unit 50. For example, the index acquiring unit 62 may acquire the differential pressure DP1 before and after the flow rate control valve 40 in the fuel line 32 as the above-mentioned index based on a signal from the differential pressure gauge 52. In the gas turbine 1 configured so that the pressure in the fuel line 32 upstream of the flow rate control valve 40 is kept constant as in the above-mentioned embodiment, when the pressure at a position between the flow rate control valve 40 and the flow divider 42 increases, the pressure difference before and after the flow rate control valve 40 decreases. For this reason, the pressure difference DP1 before and after the flow rate control valve 40 can be an index of the pressure P1 at the position between the flow rate control valve 40 and the flow divider 42.

[0035] Alternatively, the index acquiring unit 62 may acquire the pressure P1 of the fuel line 32 at a position between the flow rate adjustment valve 40 and the flow divider 42 as the index described above based on a signal from the pressure gauge 54.

[0036] The threshold value acquiring unit 64 is configured to acquire a threshold value to be compared with the index (such as the differential pressure DP1 or the pressure P1) acquired by the index acquiring unit 62. The threshold value may be set in advance based on the operating history of the gas turbine 1 or the like. The threshold value set in advance in this manner may be stored in a memory unit (not shown; main memory unit, auxiliary memory unit, etc.) of the control device 60. The threshold value acquiring unit 64 may be configured to acquire the threshold value stored in the memory unit.

[0037] The signal output unit 66 is configured to output a signal for protecting the flow divider 42 based on a comparison between the index acquired by the index acquisition unit 62 and the threshold acquired by the threshold acquisition unit 64. The signal for protecting the flow divider 42 may be a signal for stopping the gas turbine 1, a signal for reducing the load on the gas turbine 1, a signal for switching the type of fuel supplied to the combustor 4, a signal for outputting an alarm, or the like.

[0038] The control device 60 may be configured to control the flow control valve 40 for adjusting the amount of fuel supplied to the combustor 4 or the shutoff valve 44 for cutting off the fuel supply to the combustor 4 based on the signal output from the signal output unit 66.

[0039] The threshold setting unit 68 is configured to set the threshold acquired by the threshold acquiring unit 64. The threshold set by the threshold setting unit 68 may be stored in advance in a memory unit of the control device 60. The threshold setting unit 68 may be configured to determine the threshold based on the above-mentioned index during normal operation and the differential pressure before and after the flow divider 42 when the flow divider 42 reaches its allowable stress. The method of setting the threshold will be described later.

[0040] The control device 60 includes a computer equipped with a processor (e.g., CPU), a main storage device (e.g., memory device; RAM), an auxiliary storage device, an interface, etc. The control device 60 receives signals from the detection unit 50 via the interface. The processor is configured to process the signals received in this manner. The processor is also configured to process a program loaded in the main storage device. This realizes the functions of the above-mentioned functional units (index acquisition unit 62, threshold acquisition unit 64, signal output unit 66, and / or threshold setting unit 68).

[0041] The processing contents of the control device 60 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.

[0042] (Gas turbine control method) 5 is a flowchart of a method for controlling the gas turbine 1 according to one embodiment. Note that, although the following describes a case in which the above-described gas turbine 1 is controlled using the above-described control device 60, in some embodiments, the method for controlling the gas turbine may be executed using another device, or part of the procedure described below may be performed manually.

[0043] In some embodiments, first, the index acquisition unit 62 acquires an index indicating the pressure P1 in the fuel line 32 at a position between the flow rate control valve 40 and the flow divider 42 (S2). In step S2, the index acquired may be a differential pressure DP1 between before and after the flow rate control valve 40 in the fuel line 32. Alternatively, in step S2, the index acquired may be the pressure P1 in the fuel line 32 at a position between the flow rate control valve 40 and the flow divider 42.

[0044] Next, the threshold value acquisition unit 64 acquires a threshold value to be compared with the index acquired in step S2, for example, from a memory unit of the control device 60 (S4). Note that the threshold value differs depending on the index acquired in step S2 (for example, the above-mentioned differential pressure DP1 or the above-mentioned pressure P1).

[0045] Next, the signal output unit 66 compares the index acquired in step S2 with the threshold acquired in step S4 (S6).

[0046] If the indicator acquired in step S2 is the differential pressure DP1 before and after the flow control valve 40 in the fuel line 32, in step S6, if the indicator (differential pressure DP1) is smaller than a threshold value, it is determined that there are signs of damage to the flow divider 42 (Yes in S6), and if the indicator (differential pressure DP1) is equal to or greater than the threshold value, it is determined that no damage has occurred to the flow divider 42 (No in S6).

[0047] If the indicator obtained in step S2 is the pressure P1 of the fuel line 32 at a position between the flow control valve 40 and the flow divider 42, in step S6, if the indicator (pressure P1) is greater than a threshold value, it is determined that there are signs of damage to the flow divider 42 (Yes in S6), and if the indicator (pressure P1) is less than the threshold value, it is determined that no damage has occurred to the flow divider 42 (No in S6).

[0048] As a result of comparing the index with the threshold value in step S6, as long as it is not determined that there is a sign of damage to the flow divider 42 (No in step S6), the process returns to step S2 and continues to acquire the index.

[0049] If it is determined as a result of comparing the indicator with the threshold value in step S6 that there is a sign of damage to the flow divider 42 (Yes in step S6), an operation to protect the flow divider 42 is performed (S8). In step S8, the signal output unit 66 may output a signal for protecting the flow divider 42, thereby performing an operation to protect the flow divider 42. In step S8, an operation to stop the gas turbine 1 may be performed, for example. Note that, in order to stop the gas turbine 1, the opening of the flow control valve 40 may be reduced to reduce the amount of fuel supplied to the combustor 4, or the shutoff valve 44 may be closed to shut off the fuel supply to the combustor 4.

[0050] In some gas turbines (such as the gas turbine 1 described above), the pressure in the fuel line 32 upstream of the flow control valve 40 is kept constant. Therefore, if the flow divider 42 experiences a malfunction and is on the verge of failure, causing the pressure difference across the flow divider 42 to increase, the pressure P1 at the position between the flow control valve 40 and the flow divider 42 will tend to increase accordingly. Here, it is conceivable to determine a fault based on the differential pressure before and after the flow divider 42. However, since the fuel line downstream of the flow divider 42 has branch lines 32a, the number of which corresponds to the number of fuel nozzles 30, it is necessary to measure the differential pressure for each of the branch lines 32a, which would make the device configuration complicated. In the above-described embodiment, an index indicating the pressure P1 in the fuel line 32 at a position between the flow rate control valve 40 and the flow divider 42 is obtained, so that an index related to the state of the flow divider 42 can be obtained with a simple configuration, and a sign of a failure of the flow divider 42 can be appropriately detected based on a comparison between the index and a threshold value. Furthermore, in the above-described embodiment, if a sign of a failure of the flow divider 42 is detected based on a comparison between the index and a threshold value, an operation to protect the flow divider 42 is performed (or a signal to protect the flow divider is output). This controls the operation of the gas turbine, making it easier to prevent a failure of the flow divider 42. Therefore, according to the above-described embodiment, damage to the flow divider 42 can be suppressed with a simple configuration.

[0051] Furthermore, in the above-described embodiment, the pressure difference DP1 before and after the flow control valve or the pressure P1 at a position between the flow control valve 40 and the flow divider 42 is acquired as an index of the pressure at a position between the flow control valve and the flow divider, and therefore, signs of failure of the flow divider 42 can be appropriately detected based on a comparison of the index with a threshold value.

[0052] (About the threshold) In some embodiments, the threshold value acquired in step S4 is a value that changes depending on the output of the gas turbine 1. That is, in step S4, the threshold value may be acquired depending on the output of the gas turbine 1. Alternatively, the threshold value acquiring unit 64 may be configured to acquire the output of the gas turbine 1 from the control device 60 or the like, and acquire the threshold value depending on the acquired output.

[0053] Furthermore, as in the above-described embodiment, by making the threshold value for comparison with the index of the pressure P1 of the fuel line 32 at a position between the flow control valve 40 and the flow divider 42 change according to the output of the gas turbine 1, even if the output of the gas turbine 1 changes, it is possible to appropriately detect signs of failure of the flow divider 42 based on the comparison between the above-described index and the threshold value.

[0054] 6 and 7 are graphs each showing an example of the relationship between the threshold (vertical axis) and the gas turbine output (horizontal axis).

[0055] When the indicator acquired in step S2 is the differential pressure DP1 before and after the flow control valve 40 in the fuel line 32, the threshold value acquired in step S4 may change to become smaller as the output of the gas turbine 1 increases, for example, as shown in the graph of Figure 6.

[0056] When the pressure upstream of the flow control valve 40 is constant, as the output of the gas turbine 1 increases, the opening of the flow control valve 40 increases, and as a result, the pressure difference DP1 before and after the flow control valve 40 tends to decrease. Therefore, by making the threshold value decrease as the output of the gas turbine 1 increases, it is possible to appropriately detect signs of a failure in the flow divider 42 based on a comparison between the above-mentioned index and the threshold value, even if the output of the gas turbine 1 changes.

[0057] If the indicator obtained in step S2 is the pressure P1 of the fuel line 32 at a position between the flow control valve 40 and the flow divider 42, the threshold value obtained in step S4 may change to increase as the output of the gas turbine 1 increases, for example, as shown in the graph of Figure 7.

[0058] When the pressure upstream of the flow control valve 40 is constant, the pressure P1 in the fuel line 32 at a position between the flow control valve 40 and the flow divider 42 tends to increase as the output of the gas turbine 1 increases. Therefore, by setting the threshold value to increase as the output of the gas turbine 1 increases, it is possible to appropriately detect signs of a failure in the flow divider 42 based on a comparison between the above-mentioned index and the threshold value, even if the output of the gas turbine 1 changes.

[0059] In some embodiments, the threshold value obtained in step S4 may be determined based on the above-mentioned indicator (differential pressure DP1 or pressure P1) during normal operation (when the flow divider 42 is normal), and the differential pressure before and after the flow divider 42 when the allowable stress of the flow divider 42 is reached, or a value taking into account a safety factor.

[0060] That is, for example, if the index is a differential pressure DP1, where DP1(1) is the differential pressure of the flow control valve 40 during normal operation, DP2(1) is the differential pressure of the flow divider 42 during normal operation, and DP2(2) is the differential pressure of the flow divider 42 during an abnormality, the differential pressure DP1(2) of the flow control valve during an abnormality of the flow divider 42 can be expressed by the following formula (A). DP1(2)=DP1(1)-(DP2(2)-DP2(1)) …(A) Here, the pressure difference DP2(1) of the flow divider 42 during normal operation is sufficiently small and negligible compared to the pressure difference DP2(2) of the flow divider 42 during abnormal operation, so the pressure difference DP1(2) of the flow control valve during abnormal operation of the flow divider 42 can be expressed by the following equation (B). DP1(2)=DP1(1)-DP2(2) …(B) As shown in equation (B), when the pressure in the fuel line 32 upstream of the flow control valve 40 is constant, it has been found that the difference between the indicator DP1(1) when the flow divider 42 is normal (during normal operation) and the indicator DP1(2) when the flow divider 42 is abnormal (when there are signs of failure) is approximately the same as the differential pressure DP2(2) before and after the flow divider 42 when abnormal. Furthermore, when the differential pressure DP2 across the flow divider 42 reaches a value when the flow divider 42 reaches its allowable stress (for example, when an internal component (such as a coupling) of the flow divider 42 reaches its allowable stress) or a value that takes a safety factor into account, it can be determined that the flow divider 42 is failing or has a sign of failure (i.e., that there is an abnormality). That is, DP2(2) in formulas (A) and (B) can be set to the differential pressure across the flow divider when the flow divider 42 reaches its allowable stress or a value that takes a safety factor into account, and the value can be set in advance based on the product specification information, experimental results, etc. of the flow divider.

[0061] DP1(2) expressed by the above formulas (A) and (B) or a value set based on DP1(2) can be used as a threshold value to be compared with the indicator (pressure difference DP1). That is, the threshold value can be set based on the pressure difference DP1(1), which is an indicator during normal operation, and the pressure difference DP2(2) across the flow divider when the flow divider 42 reaches its allowable stress. Based on the threshold value set in this way, signs of flow divider failure can be appropriately detected.

[0062] The contents described in each of the above embodiments can be understood, for example, as follows.

[0063] [1] At least one embodiment of the present invention provides a control system (60) for a gas turbine, comprising: A control device for controlling a gas turbine (1) including a fuel line (32), a flow control valve (40) provided in the fuel line, and a flow divider (42) provided in the fuel line downstream of the flow control valve for distributing fuel in the fuel line to a plurality of fuel nozzles (30), comprising: an index acquisition unit (62) configured to acquire an index indicative of a pressure (P1) in the fuel line at a position between the flow rate control valve and the flow divider; a threshold acquisition unit (64) configured to acquire a threshold for comparison with the index; a signal output unit (66) configured to output a signal for protecting the flow divider based on a comparison of the indicator and the threshold; Equipped with.

[0064] In some gas turbines, the pressure in the fuel line upstream of the metering valve remains constant, so if the flow divider becomes compromised and is about to fail, the pressure differential across the flow divider will increase, which will tend to increase the pressure between the metering valve and the flow divider. Here, it is possible to determine whether a fault has occurred based on the differential pressure before and after the flow divider. However, because the fuel line downstream of the flow divider has branch lines corresponding to the number of fuel nozzles, it is necessary to measure the differential pressure for each of the branch lines, which makes the device configuration complicated. In the configuration [1] above, an index indicating the pressure in the fuel line at a position between the flow control valve and the flow divider is obtained, making it possible to obtain an index related to the state of the flow divider with a simple configuration, and to appropriately detect signs of flow divider failure based on a comparison between the index and a threshold. Furthermore, in the configuration [1] above, if a sign of flow divider failure is detected based on a comparison between the index and a threshold, a signal for protecting the flow divider is output. By controlling the operation of the gas turbine based on the signal, it becomes easier to prevent flow divider failure. Therefore, the configuration [1] above makes it possible to suppress damage to the flow divider with a simple configuration.

[0065] [2] In some embodiments, in the configuration of [1] above, the index acquisition unit is configured to acquire a differential pressure (DP1) between before and after the flow rate control valve in the fuel line, and to acquire the differential pressure as the index; The signal output unit is configured to output the signal when the index is smaller than the threshold value.

[0066] In gas turbines configured to maintain a constant fuel line pressure upstream of the metering valve, increasing the pressure between the metering valve and the flow divider reduces the pressure differential across the metering valve, which can be an indicator of the pressure between the metering valve and the flow divider. According to the configuration [2] above, since the pressure difference between the upstream and downstream of the flow control valve is acquired as an index of the pressure at a position between the flow control valve and the flow divider, a sign of a flow divider failure can be appropriately detected based on a comparison of the index (pressure difference) with a threshold value. Furthermore, when the index (pressure difference) becomes smaller than the threshold value and a sign of a flow divider failure is detected, a signal to protect the flow divider is output, and by controlling the operation of the gas turbine based on the signal, a flow divider failure can be prevented.

[0067] [3] In some embodiments, in the configuration of [1] above, the index acquisition unit is configured to acquire a pressure (P1) of the fuel line at a position between the flow rate control valve and the flow divider, and to acquire the pressure as the index; The signal output unit is configured to output the signal when the index is greater than the threshold value.

[0068] According to the configuration [3] above, since the pressure at a position between the flow control valve and the flow divider is acquired as an index of the pressure at that position, the index (pressure) can be compared with a threshold value to appropriately detect signs of flow divider failure. Furthermore, when the index (pressure) exceeds the threshold value and a sign of flow divider failure is detected, a signal to protect the flow divider is output, and by controlling the operation of the gas turbine based on the signal, flow divider failure can be prevented.

[0069] [4] In some embodiments, in any of the configurations [1] to [3] above, The signal output unit is configured to output, as the signal, a signal for stopping the gas turbine.

[0070] According to the configuration of [4] above, if a sign of a flow divider failure is detected based on a comparison between the above-mentioned index and a threshold value, a signal for protecting the flow divider is output as an output, and a signal for stopping the gas turbine is also output. Therefore, by controlling the operation of the gas turbine based on this signal, it is possible to more reliably suppress failure of the flow divider.

[0071] [5] In some embodiments, in any of the configurations [1] to [4] above, the threshold value is a value that changes depending on an output of the gas turbine, The threshold value acquisition unit is configured to acquire the threshold value corresponding to an output of the gas turbine.

[0072] While the pressure in the fuel line at a position between the flow control valve and the flow divider changes depending on the output of the gas turbine, the pressure difference between before and after the flow divider hardly changes depending on the output of the gas turbine. In this regard, according to the configuration of [5] above, the threshold value for comparing with the index of the pressure in the fuel line at a position between the flow control valve and the flow divider changes depending on the output of the gas turbine. Therefore, even if the output of the gas turbine changes, it is possible to appropriately detect signs of a flow divider failure based on the comparison between the index and the threshold value.

[0073] [6] In some embodiments, in the configuration of [5] above, the index acquisition unit is configured to acquire a differential pressure between before and after the flow rate control valve in the fuel line, and to acquire the differential pressure as the index, The threshold value decreases as the output of the gas turbine increases.

[0074] The differential pressure across the flow control valve tends to decrease as the output of the gas turbine increases. In this regard, according to the configuration of [6] above, the threshold value for comparison with the differential pressure across the flow control valve as the index decreases as the output of the gas turbine increases, so that even if the output of the gas turbine changes, signs of a flow divider failure can be appropriately detected based on the comparison between the index and the threshold value.

[0075] [7] In some embodiments, in the configuration of [5] above, the index acquisition unit is configured to acquire a pressure in the fuel line at a position between the flow rate adjustment valve and the flow divider, and to acquire the pressure as the index; The threshold value increases as the output of the gas turbine increases.

[0076] The pressure in the fuel line between the flow control valve and the flow divider tends to increase as the output of the gas turbine increases. In this regard, according to the configuration of [7] above, the threshold value for comparison with the pressure in the fuel line between the flow control valve and the flow divider as the index increases as the output of the gas turbine increases. Therefore, even if the output of the gas turbine changes, signs of a flow divider failure can be appropriately detected based on the comparison between the index and the threshold value.

[0077] [8] In some embodiments, in any of the configurations [1] to [7] above, The control device The system further includes a threshold setting unit (68) configured to determine the threshold based on the index during normal operation and a differential pressure across the flow divider when the allowable stress of the flow divider is reached.

[0078] The inventors' research has revealed that, when the pressure in the fuel line upstream of the flow control valve is constant, the difference between the above-mentioned indicator when the flow divider is normal (in normal operation) and the above-mentioned indicator when the flow divider is abnormal is approximately the same as the differential pressure across the flow divider when the flow divider is abnormal. Furthermore, when the differential pressure across the flow divider reaches a value when the flow divider reaches its allowable stress, it can be determined that the flow divider has failed or is showing signs of failure (i.e., is abnormal). Therefore, with the configuration of [8] above, an appropriate threshold can be set that can detect signs of flow divider failure based on the indicator during normal operation and the differential pressure across the flow divider when the flow divider reaches its allowable stress.

[0079] [9] At least one embodiment of the gas turbine installation (100) of the present invention comprises: a combustor (4); a fuel line (32) for supplying fuel to the combustor; a flow control valve (40) provided in the fuel line; a flow divider (42) disposed in the fuel line downstream of the flow control valve for distributing fuel in the fuel line to a plurality of fuel nozzles (30); a turbine (6) configured to be driven by combustion gases from the combustor; a gas turbine (1) including: a control device (60) according to any one of [1] to [8] above for controlling the gas turbine; Equipped with.

[0080] The configuration [9] above acquires an index indicating the pressure in the fuel line at a position between the flow control valve and the flow divider, making it possible to acquire an index related to the state of the flow divider with a simple configuration, and to appropriately detect signs of flow divider failure based on a comparison between the index and a threshold. Furthermore, the configuration [9] above outputs a signal to protect the flow divider when a sign of flow divider failure is detected based on a comparison between the index and a threshold. Controlling the operation of the gas turbine based on the signal makes it easier to prevent flow divider failure. Therefore, the configuration [9] above makes it possible to suppress damage to the flow divider with a simple configuration.

[0081]

[10] In some embodiments, in the configuration of [9] above, The gas turbine facility includes: a detection unit (50) for detecting the indicator; The detection unit includes a plurality of detectors (52A, 52B or 54A, 54B) configured to independently detect the indices.

[0082] According to the configuration of

[10] above, the detection unit for detecting the above-mentioned index is made redundant by including a plurality of detectors, so that the index can be acquired more reliably.

[0083]

[11] At least one embodiment of the present invention relates to a method for controlling a gas turbine, comprising: A control method for controlling a gas turbine (1) including a fuel line (32), a flow control valve (40) provided in the fuel line, and a flow divider (42) provided in the fuel line downstream of the flow control valve for distributing fuel in the fuel line to a plurality of fuel nozzles (30), comprising: obtaining an index indicative of a pressure (P1) in the fuel line at a location between the flow control valve and the flow divider; Steps (S4 to S8) of taking action to protect the flow divider based on a comparison of the indicator with a threshold; Equipped with.

[0084] The method of

[11] above acquires an index indicating the pressure in the fuel line at a position between the flow control valve and the flow divider, making it possible to acquire an index related to the state of the flow divider with a simple configuration, and to appropriately detect signs of flow divider failure based on a comparison between the index and a threshold. Furthermore, the method of

[11] above performs an operation to protect the flow divider when a sign of flow divider failure is detected based on a comparison between the index and a threshold. Controlling the operation of the gas turbine in this manner makes it easier to prevent flow divider failure. Therefore, the method of

[11] above can suppress damage to the flow divider with a simple configuration.

[0085] 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.

[0086] 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]

[0087] 1. Gas turbine 2 Compressor 4 Combustor 6 Turbine 8 rotors 10 Compressor compartment 12 Air intake 16 Stator blade 18 Moving blade 20 Casing 22 Turbine casing 24 Stator blade 26 Moving blade 28 Combustion gas passage 29 Exhaust chamber 30 Fuel Nozzle 32 fuel line 32a Branch Line 34 Fuel pump 38 Relief pressure regulating valve 40 Flow control valve 42 Flow Divider 44 Shut-off valve 46 Valve body 50 Detector 52, 52A, 52B differential pressure gauge 54, 54A, 54B Pressure gauge 60 Control device 62 Index acquisition part 64 Threshold acquisition unit 66 Signal output section 68 Threshold setting unit 100 Gas turbine equipment O Rotor axis

Claims

1. 1. A control device for controlling a gas turbine including: a fuel line; a flow control valve provided in the fuel line; and a flow divider provided in the fuel line downstream of the flow control valve for distributing fuel in the fuel line to a plurality of fuel nozzles, an index obtaining unit configured to obtain an index indicative of a pressure in the fuel line at a location between the flow rate control valve and the flow divider; a threshold acquisition unit configured to acquire a threshold for comparison with the index; a signal output unit configured to output a signal for protecting the flow divider based on a comparison between the indicator and the threshold; A control device for a gas turbine comprising:

2. the index acquisition unit is configured to acquire a differential pressure between before and after the flow rate control valve in the fuel line, and to acquire the differential pressure as the index, The signal output unit is configured to output the signal when the index is smaller than the threshold value. The control device for a gas turbine according to claim 1 .

3. the index acquisition unit is configured to acquire a pressure in the fuel line at a position between the flow rate adjustment valve and the flow divider, and to acquire the pressure as the index; The signal output unit is configured to output the signal when the index is greater than the threshold value. The control device for a gas turbine according to claim 1 .

4. The signal output unit is configured to output, as the signal, a signal for stopping the gas turbine. A control device for a gas turbine according to any one of claims 1 to 3.

5. the threshold value is a value that changes depending on an output of the gas turbine, The threshold value acquisition unit is configured to acquire the threshold value corresponding to an output of the gas turbine. A control device for a gas turbine according to any one of claims 1 to 3.

6. the index acquisition unit is configured to acquire a differential pressure between before and after the flow rate control valve in the fuel line, and to acquire the differential pressure as the index, The threshold value decreases as the output of the gas turbine increases. The control device for a gas turbine according to claim 5.

7. the index acquisition unit is configured to acquire a pressure in the fuel line at a position between the flow rate adjustment valve and the flow divider, and to acquire the pressure as the index; The threshold value increases as the output of the gas turbine increases. The control device for a gas turbine according to claim 5.

8. a threshold setting unit configured to determine the threshold based on the indicator during normal operation and a differential pressure across the flow divider when the allowable stress of the flow divider is reached; A control device for a gas turbine according to any one of claims 1 to 3.

9. A combustor; a fuel line for supplying fuel to the combustor; a flow control valve provided in the fuel line; a flow divider provided in the fuel line downstream of the flow rate control valve for distributing fuel in the fuel line to a plurality of fuel nozzles; a turbine configured to be driven by combustion gases from the combustor; a gas turbine including: A control device according to any one of claims 1 to 3 for controlling the gas turbine; A gas turbine facility comprising:

10. a detection unit for detecting the index, The detection unit includes a plurality of detectors configured to independently detect the indices. The gas turbine installation according to claim 9.

11. 1. A control method for controlling a gas turbine including a fuel line, a flow control valve provided in the fuel line, and a flow divider provided in the fuel line downstream of the flow control valve for distributing fuel in the fuel line to a plurality of fuel nozzles, the method comprising: obtaining an indication of pressure in the fuel line at a location between the flow control valve and the flow divider; taking action to protect the flow divider based on a comparison of the indicator to a threshold; A gas turbine control method comprising:

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