WO2022091899A1 - ガスタービンの燃焼調整方法及び燃焼制御装置 - Google Patents
ガスタービンの燃焼調整方法及び燃焼制御装置 Download PDFInfo
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/263—Control of fuel supply by means of fuel metering valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/32—Control of fuel supply characterised by throttling of fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
- F02C9/54—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by throttling the working fluid, by adjusting vanes
Definitions
- the present disclosure relates to a combustion adjusting method and a combustion control device for a gas turbine.
- This application claims priority based on Japanese Patent Application No. 2020-180324 filed in Japan on October 28, 2020, and this content is incorporated herein by reference.
- Patent Document 1 discloses an example in which after the gas turbine enters normal operation, the occurrence of combustion vibration is predicted and the operating conditions for suppressing the combustion vibration within an allowable level are automatically selected.
- Patent Document 1 is normal due to the difference in the structure of the combustor, the difference in the fuel properties, the difference in the atmospheric conditions, and the like. It may not be possible to shift to the combustion controlled state.
- the permissible range of operating conditions that can suppress combustion vibration within the permissible level is narrow, and it may take time to start up until the rated operation is reached. Therefore, it is important to confirm the allowable range of operating conditions for the fuel-air ratio in advance before starting the test run.
- the present disclosure is a combustion adjustment method and combustion for confirming the combustion margin range with respect to the combustion air ratio of the combustor as a pre-operation at the start of the trial run of the gas turbine or at the restart of the operation after the end of the regular inspection. It is intended to provide a control device.
- a combustion adjustment method used for combustion control of a combustor in order to solve the above problems From the step of selecting the combustion parameter that sets the fuel-air ratio to the load of the gas turbine and the position of the origin, the first increase command process, which is the increase command process for increasing the command value of the combustion parameter, or the command value is decreased.
- the step of executing the first step consisting of the first lowering command process, which is the lowering command process, and the command value reaches the target upper limit value or the target lower limit value without causing combustion vibration in the combustor.
- the second step is terminated and the command value of the second step of the combustion parameter is set to the position of the origin.
- the combustion margin confirmation work is streamlined and the combustion adjustment work is facilitated without depending on the skill of the operator.
- the reliability of the gas turbine is improved.
- FIG. 1 is a diagram schematically showing an apparatus configuration of a gas turbine.
- FIG. 2 is a diagram showing the configuration of the combustion control device.
- FIG. 3 is a diagram showing the configuration of the combustion margin confirmation unit.
- FIG. 4 is a diagram showing a first combustion margin confirmation pattern.
- FIG. 5 is a diagram showing a second combustion margin confirmation pattern.
- FIG. 6 is a diagram showing a third combustion margin confirmation pattern.
- FIG. 7 is a diagram showing a fourth combustion margin confirmation pattern.
- FIG. 8 is a flow chart showing the entire process of the combustion margin adjusting unit.
- FIG. 9 is a flow chart showing a combustion margin confirmation process.
- FIG. 10A is a diagram showing the relationship between the combustion parameter and the combustion load variable of Case 1.
- FIG. 10A is a diagram showing the relationship between the combustion parameter and the combustion load variable of Case 1.
- FIG. 10A is a diagram showing the relationship between the combustion parameter and the combustion load variable of Case 1.
- FIG. 10A is a diagram showing
- FIG. 10B is a diagram showing the relationship between the gas turbine inlet temperature of Case 1 and the combustion load coefficient.
- FIG. 10C is a diagram showing the relationship between the combustion parameters of Case 1 and the gas turbine inlet temperature.
- FIG. 11A is a diagram showing the relationship between the combustion parameter and the combustion load variable of Case 2.
- FIG. 11B is a diagram showing the relationship between the gas turbine inlet temperature and the combustion load coefficient of Case 2.
- FIG. 11C is a diagram showing the relationship between the combustion parameters of Case 2 and the gas turbine inlet temperature.
- FIG. 12 is a flow chart showing a combustion load variable correction process.
- FIG. 13 is a logic diagram of the combustion load variable correction unit.
- FIG. 14 is a schematic diagram showing an example of changing the set value.
- the schematic device configuration of the gas turbine is shown in FIG.
- the gas turbine 1 is provided with an inlet guide blade 11, and takes in atmospheric air from the outside to generate compressed air, and burns the generated compressed air and a separately supplied fuel FL to generate combustion gas FG.
- a turbine 4 that is rotationally driven by the generated combustion gas FG
- a generator 5 that is connected to the turbine 4 and is rotationally driven to generate electric power
- a combustion control device 100 that controls the gas turbine 1.
- the combustor 3 includes a combustion nozzle 30 including a main nozzle 31, a top hat nozzle 32, and a pilot nozzle 33 for each combustor 3.
- the main nozzles 31 are arranged in a ring shape around the pilot nozzle 33.
- the combustor 3 includes a bypass valve 44 and a tail tube 24.
- the combustor 3 further includes a main fuel flow rate control valve 41, a top hat fuel flow rate control valve 42, and a pilot fuel flow rate control valve 43.
- the fuel for the main combustion nozzle is supplied to the main nozzle 31 via the main fuel flow rate control valve 41.
- the top hat fuel is supplied to the top hat nozzle 32 via the top hat fuel flow rate control valve 42, and the pilot fuel is supplied to the pilot nozzle 33 via the pilot fuel flow rate control valve 43.
- the fuel flow rates of the main fuel, the top hat fuel and the pilot fuel are controlled by the flow rate control valves of the main fuel flow rate control valve 41, the top hat fuel flow rate control valve 42 and the pilot fuel flow rate control valve 43.
- the combustion gas FG generated by the combustor 3 is supplied to the turbine 4 via the tail cylinder 24 to rotationally drive the turbine 4.
- FIG. 2 shows a schematic configuration of the combustion control device 100 of the gas turbine 1 in the present embodiment.
- the combustion control device 100 includes a process measurement unit 101, a pressure change measurement unit 102, an acceleration measurement unit 103, a NOx measurement unit 104, a valve operation unit 105, a frequency analysis unit 123, and a control unit 110 installed in the gas turbine 1.
- the process measurement unit 101 is various measuring devices that measure the operating conditions and the process amount indicating the operating state of the gas turbine 1, and the measurement results are transmitted to the control unit 110 of the combustion control device 100 at predetermined time intervals.
- the process amount is, for example, turbine output, atmospheric temperature, humidity, fuel flow rate and fuel pressure of each part, air flow rate and air pressure of each part, combustion gas temperature, combustion gas pressure, rotation speed of compressor 2 and turbine 4, turbine. It means the concentration of waste such as nitrogen oxide (NOx) and carbon monoxide (CO) in the exhaust gas discharged from 4.
- NOx nitrogen oxide
- CO carbon monoxide
- the pressure change measuring unit 102 is a pressure measuring device arranged in each of the plurality of combustors 3, and the pressure change measured value in each combustor 3 is periodically sent to the control unit 110 by a command from the control unit 110. Output.
- the acceleration measuring unit 103 is an acceleration measuring device installed in each combustor 3, and periodically measures the acceleration according to a command from the control unit 110 and outputs the acceleration to the control unit 110.
- the NOx measuring unit 104 is a measuring device for NOx in the exhaust gas of the combustor 3, and the measured value periodically measures NOx according to a command from the control unit 110 and outputs the measured value to the control unit 110.
- the valve operation unit 105 receives a command from the control unit 110 to set the opening degree of each control valve of the main fuel flow rate control valve 41, the top hat fuel flow rate control valve 42, the pilot fuel flow rate control valve 43, and the bypass valve 44, and the compressor 2. It is a mechanism for operating the opening degree of the inlet guide blade 11 and the like.
- the valve operating unit 105 performs main fuel control, top hat fuel control, pilot fuel control, flow rate control of the air flow rate supplied to each combustor 3, flow rate control of atmospheric air supplied to the compressor 2, and the like.
- the frequency analysis unit 123 frequency-analyzes the pressure fluctuation and the acceleration fluctuation detected by the pressure change measurement unit 102 and the acceleration measurement unit 103, and outputs the frequency analysis to the control unit 110.
- the combustion control device 100 includes an automatic combustion adjustment unit 120 and a combustion margin adjustment unit 130 in addition to the various measurement units, measurement units, valve operation units and control units 110 described above.
- the control unit 110 receives output signals from the process measurement unit 101, the pressure change measurement unit 102, the acceleration measurement unit 103, and the frequency analysis unit 123, and transmits them to the automatic combustion adjustment unit 120. Further, the control unit 110 is a signal for operating the valve opening degree of the main fuel flow rate control valve 41, the top hat fuel flow rate control valve 42, the pilot fuel flow rate control valve 43, the bypass valve 44, the inlet guide blade 11 of the compressor 2, and the like. Is output to the valve operating unit 105.
- the automatic combustion adjusting unit 120 shown in FIG. 2 includes an input unit 121, an operating state grasping unit 122, a combustion characteristic grasping unit 124, a correction unit 125, and an output unit 126.
- the automatic combustion adjusting unit 120 controls to select each process amount in the most effective direction for suppressing the combustion vibration when the combustion vibration is generated in the combustor 3.
- the automatic combustion adjustment unit 120 receives the process amount, pressure, acceleration data, etc. of each unit transmitted from the control unit 110 via the input unit 121. Further, from the frequency analysis result in the gas turbine 1 by the frequency analysis unit 123, the operation state grasping unit 122 grasps the operating state of the gas turbine 1, and the combustion characteristic grasping unit 124 grasps the combustion characteristics of each combustor 3. The correction unit 125 determines a control method so as not to generate combustion vibration of the gas turbine 1 based on the data grasped by the operation state grasping unit 122 and the combustion characteristic grasping unit 124.
- the adjustment amount is determined and output to the control unit 110 via the output unit 126.
- the combustion margin adjusting unit 130 grasps the region where combustion vibration does not occur in advance before starting the trial run of the gas turbine having a small amount of data accumulated in the past operating conditions, and transmits the data to the automatic combustion adjusting unit 120. , Accumulate in the database 127 in the automatic combustion adjustment unit 120.
- the combustion margin adjusting unit 130 is rated without generating combustion vibration by using the data of the automatic combustion adjusting unit 120 that reflects the accumulated data at the time of the trial run of the gas turbine 1 or the start-up after the end of the regular inspection. The purpose is to prepare operating conditions that can shift to operation and to realize a state in which the gas turbine can shift to rated operation in a short time.
- the combustion adjustment work such as confirmation of the margin range of the combustion vibration, which has been conventionally performed by the combustion adjuster, is automated by using the combustion margin adjustment unit 130. Therefore, we are trying to optimize the combustion adjustment work.
- the combustion margin adjusting unit 130 includes a combustion margin confirmation unit 132, a combustion load variable correction unit 134, and a set value changing unit 136.
- the combustion load variable correction unit 134 includes a maximum load correction unit 134a and a set value conversion unit 134b.
- each combustion parameter PM is described in the flow of the combustion margin confirmation step S20 (FIGS. 8 and 9) described later.
- the combustion margin is confirmed based on various combustion margin patterns along the line, the combustion margin range of the combustion vibration generated in the combustor 3 is confirmed in advance, acquired as steady data 128, and the operation of the gas turbine 1 is started. We are trying to accumulate various operation data for this purpose.
- the combustion load variable correction unit 134 determines the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM so that the gas turbine 1 outputs the planned maximum output MOP of the gas turbine 1 at the rated value (100%) of the combustion load variable CLP. The purpose is to optimize the relationship between the combustion parameter PM and the combustion load variable CLP while maintaining it. Although the details will be described later, the maximum load correction unit 134a corrects the combustion load variable CLP so that the combustion load variable CLP becomes the rated value (100%) at the planned maximum output MOP.
- the set value conversion unit 134b determines the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP so that the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM is maintained based on the corrected combustion load variable CLP.
- the combustion load variable correction unit 134 By providing the combustion load variable correction unit 134, the generation of combustion vibration of the combustor 3 is suppressed while maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM, and stable operation of the gas turbine 1 becomes possible. ..
- the GT load (GT output) may be simply displayed instead of the gas turbine load (gas turbine output).
- the set value changing unit 136 changes the set value indicating the relationship between the combustion parameter PM and the combustion load variable CLP when combustion vibration occurs and the origin movement (origin shift) described later occurs. Therefore, the purpose is to automatically change the set value of the combustion load variable CLP before the correction to the set value after the correction. By automating the change of set values, the burden on the operation coordinator is reduced and safety is improved.
- the main work of the combustion margin adjusting unit 130 is that the combustion vibration generated in the combustor 3 is suppressed within an allowable level for each combustion parameter PM in the combustion margin adjusting unit 130, and the combustion margin does not generate combustion vibration.
- the point is to check the range.
- the combustion margin range is defined as the origin OP by defining the position or numerical value of the combustion parameter PM with respect to the combustion load variable CLP as a reference operating point. With the origin OP as a reference, the presence or absence of combustion vibration at operating points with different GT loads is confirmed, and a stable operating range in which combustion vibration does not occur is determined.
- the combustion load variable CLP at the planned maximum load MOP or the rated load of the gas turbine 1 is set to the rated value (100%), and the combustion load variable CLP of the output NOP equivalent to no load of the gas turbine is used. Is set to 0 (zero)%. Any gas turbine load is represented by the combustion load variable CLP.
- the combustion parameter PM for any gas turbine load can be displayed as the set value of the corresponding combustion load variable CLP.
- confirmation of the combustion margin range means confirming the range and width in which combustion vibration does not occur in the combustor 3 for each combustion parameter PM. It may be displayed briefly. The fact that the combustion vibration does not occur means a state in which the combustion vibration in the combustor 3 can be suppressed within the permissible level, and the occurrence of the combustion vibration means a state in which the combustion vibration exceeds the permissible level.
- the combustion parameter PMs for which the combustion margin range is confirmed are the pilot ratio PL, the top hat ratio TH, and the bypass valve opening BV.
- the pilot ratio PL is a percentage (%) of the fuel distribution ratio supplied to the pilot nozzle 33 with respect to the total fuel flow rate FL.
- the top hat ratio TH is a percentage (%) of the fuel distribution ratio supplied to the top hat nozzle 32 with respect to the total fuel flow rate FL.
- the bypass valve opening degree BV is a valve opening degree BV expressed as a percentage (%) with respect to the time when the bypass valve 44 is fully opened.
- the presence or absence of combustion vibration in the combustor 3 depends on the set value ST of the pilot ratio PL, the top hat ratio TH, and the bypass valve opening BV with respect to a predetermined GT load.
- As the combustion parameter PM another parameter that affects the combustion state of the combustor 3 may be selected.
- the combustion margin adjusting unit 130 executes the combustion margin confirmation step S20 (FIGS. 8 and 9) for confirming the combustion margin range described later for all the above-mentioned combustion parameter PMs.
- the combustion margin confirmation step S20 As for the priority of the combustion parameter PM, since the confirmation of the combustion margin range is completed in a short time, it is desirable to preferentially execute the combustion margin confirmation step S20 of the combustion parameter PM in which combustion vibration is likely to occur.
- the range in which combustion vibration does not occur means that the level of combustion vibration with respect to the combustion load variable CLP is within the permissible level, and the operating point of the upper limit GT load and the operating point of the lower limit GT load within the permissible level. It means the range of GT load between.
- combustion margin confirmation step S20 For example, as a combustion parameter PM, if combustion vibration occurs during the execution of the combustion margin confirmation step S20 for the pilot ratio PL after the combustion margin confirmation step S20 for the top hat ratio TH is completed, the top hat is again used. For the ratio TH, it is necessary to execute the combustion margin confirmation step S20 again. That is, the repetitive work of the combustion margin confirmation step S20 occurs, and it takes a long time to confirm the combustion margin range of the combustion parameter PM. Therefore, at the time of the trial run of the gas turbine 1 or at the start of the operation after the end of the regular inspection, the selection of the priority of the combustion parameter PM affects the trial run process at the time of starting the gas turbine, so careful selection is required.
- the GT load during the combustion margin confirmation work is selected in the range from 0% to the rated value (100%). ..
- the rated value (100%) of the GT load means the planned maximum load (planned maximum output) or the rated load (rated output) of the gas turbine.
- FIG. 4 shows an example of the combustion margin confirmation pattern.
- the combustion vibration is generated in both the steps of the raising command step STU in the direction of increasing the command value CM indicating the output of the combustion parameter PM and the lowering command step STD in the direction of lowering the command value CM. It is necessary to confirm whether or not it has occurred. After confirming the combustion margin range of both steps, the presence or absence of combustion vibration in a predetermined GT load and the combustion margin range are confirmed.
- the raising command process STU is prioritized or the lower command process STD is prioritized in a predetermined GT load depends on the combustion parameter PM.
- steady-state data 128 in each step is collected.
- the combustion margin confirmation step S20 the two steps of the raising command step STU and the lowering command step STD are completed, and one cycle work of confirming the margin of the target combustion parameter PM is completed.
- the selection of whether to select the raising command process STU in the first step PR1 of the first half and the lowering commanding step STD in the second step of the second half, or vice versa, is the characteristic of the combustor or the combustion state. Is determined by.
- the target margin width TMW to confirm the combustion margin range is set.
- the target margin width TMW is the difference between the target margin upper limit TMUL that defines the upper limit of the command value CM in the raising command process STU and the target wealth lower limit TMLL that defines the lower limit of the command value CM in the lower command process STD. Shown. Basically, it is desirable to select the same width for the target margin upper limit value TMUL and the target margin lower limit value TMLL from the position of the origin OP which is the reference of the output for confirming the combustion margin.
- the command value CM in the raising command process STU and the lowering command process STD, the command value CM may be increased or decreased in one direction at a constant rate, and as shown in FIG. 4, the command value CM may be increased or decreased. May be raised or lowered along the stepped stage S. Which method is selected is selected according to the characteristics of the combustor and the operating condition of the gas turbine. Further, the stage width SW is the same width, and the number of stages S in the raising command process STU or the lowering command process STD from the origin OP to the target wealth upper limit value TMUL or the target wealth lower limit value TMLL is the same, and the combustion margin range. It is desirable to confirm.
- the command value CM is selected by setting the position of the origin OP to zero (%) and increasing the command value CM in the (+) direction from the position of the origin OP.
- the position of the origin OP is set to zero (%), and the command value CM decreases in the ( ⁇ ) direction from the position of the origin OP. It is desirable that the target margin range TMW be variable as long as it does not adversely affect the device.
- FIG. 4 is an example of the first combustion margin confirmation pattern.
- the combustion vibration is suppressed within the permissible level within the range where the command value CM of the combustion parameter PM is within the range of the target margin upper limit value TMUL or the target margin lower limit value TMLL.
- FIG. 5 is an example of the second combustion margin confirmation pattern.
- the second combustion margin confirmation pattern is an example in which the combustion vibration exceeds the permissible level and the combustion vibration occurs before the command value CM of the combustion parameter PM reaches the target margin upper limit value TMUL in the raising command process STU. Is.
- FIG. 4 is an example of the first combustion margin confirmation pattern.
- the combustion vibration is suppressed within the permissible level within the range where the command value CM of the combustion parameter PM is within the range of the target margin upper limit value TMUL or the target margin lower limit value TMLL.
- An example in which the degree confirmation process is completed is shown.
- FIG. 5 is an example of the second combustion margin confirmation pattern.
- the second combustion margin confirmation pattern
- FIG. 6 is an example of the third combustion margin confirmation pattern.
- the third combustion margin confirmation pattern in the processes on both sides of the raising command process STU and the lowering command process STD, before the command value CM of the combustion parameter reaches the target wealth upper limit value TMUL and the target wealth lower limit value TMLL. This is an example in which combustion vibration exceeds the permissible level and combustion vibration occurs.
- FIG. 7 is an example of the fourth combustion margin confirmation pattern.
- the fourth combustion margin confirmation pattern is a modification of the second combustion margin confirmation pattern shown in FIG. 5, and is before the command value CM of the combustion parameter PM reaches the target margin lower limit value TMLL in the lower command process STD. There is an example of combustion vibration occurring in.
- ⁇ 1st combustion margin confirmation pattern >> In the first combustion margin confirmation pattern shown in FIG. 4, it was confirmed that the combustion vibration was suppressed within the permissible level up to the target margin upper limit value TMUL in the raising command process STU of the first step PR1 and no combustion vibration was generated. did it. Further, even in the next lowering command process STD of the second step PR2, it is confirmed that the combustion vibration is suppressed within the permissible level up to the target margin lower limit value TMLL and the combustion vibration does not occur, and the position of the origin OP is reached. An embodiment in which the command value CM is returned and the combustion margin range of one cycle at a predetermined GT load and a predetermined origin OP can be confirmed is shown.
- the fact that the combustion vibration is suppressed within the permissible level means a state in which the combustion vibration is suppressed within the permissible level until a certain holding time elapses at a predetermined set value ST.
- the first combustion margin confirmation pattern will be specifically described with reference to FIG.
- the first combustion margin confirmation pattern shows an example in which the raising command process STU is prioritized as the first step PR1 and the lowering commanding process STD of the second step PR2 is executed after the raising commanding process STU is completed.
- the command value CM is set by adding a predetermined command value input rate BIR starting from the origin OP at the time of initial setting.
- the command value CM reaches a predetermined new command value CM, the predetermined holding time T1 is held and the presence or absence of combustion vibration is confirmed.
- a predetermined command value input rate BIR is added to the command value CM to set a new command value CM of the next stage S.
- the predetermined holding time T1 is held, and the presence or absence of the occurrence of combustion vibration is confirmed. This procedure is repeated with a stage width SW having the same width, and the command value CM reaches the target tolerance upper limit value TMUL, the predetermined holding time T1 is held, and the presence or absence of combustion vibration is confirmed.
- combustion vibration does not occur even after the predetermined holding time T1 has elapsed, it is determined that the combustion margin range with respect to the origin OP at the time of initial setting in the raising command process STU has been confirmed.
- the command value CM reaches the target margin upper limit value TMUL, and the predetermined retention time T2 is maintained from the time when the retention time T1 has elapsed, and the gas turbine 1
- the steady-state data 128 of is collected.
- the command value CM is set by applying a predetermined bias to the current command value CM in which the holding time T1 (first holding time) is maintained without generating combustion vibration.
- the holding time T1 (first holding time) may be selected to be different depending on the characteristics of the combustor and the operating state of the gas turbine.
- a new command value CM is set by subtracting a predetermined command value input rate BIR from the origin OP.
- the predetermined holding time T1 is held and the presence or absence of combustion vibration is confirmed.
- a predetermined command value input rate BIR is subtracted from the command value CM to set a new command value CM of the next stage S.
- the predetermined holding time T1 is held by the new command value CM, and the presence or absence of combustion vibration is confirmed. This procedure is repeated with a stage width SW having the same width, and the command value CM reaches the target tolerance lower limit value TMLL, the predetermined holding time T1 is held, and the presence or absence of combustion vibration is confirmed. If combustion vibration does not occur even after the predetermined holding time T1 has elapsed, it is determined that the combustion margin range with respect to the origin OP at the time of initial setting in the lowering command process STD has been confirmed.
- a predetermined holding time T2 (second holding time) is held from the time when the command value CM reaches the target lower limit value TMLL and the holding time T1 elapses, and steady-state data 128 is collected.
- the command value CM is returned to the position of the original origin OP at the command value release rate BRR at the time of returning to the predetermined origin, and the first combustion margin is obtained.
- the confirmation work of one cycle of the combustion margin range at the predetermined GT load and the predetermined origin OP of the confirmation pattern is completed.
- the collected steady data 128 of the gas turbine 1 is transmitted to the database 127.
- the command value input rate BIR may be a fixed fixed value in a stepped manner, or may be a tilt rate having a constant slope.
- Second combustion margin confirmation pattern is different from the first combustion margin confirmation pattern shown in FIG. Is shown as an example when is not confirmed. That is, in the raising command process STU, the case where the combustion vibration occurs after the command value CM reaches the target tolerance upper limit value TMUL and before the holding time T1 elapses is shown. If combustion vibration occurs without maintaining the holding time T1 in the command value CM that is the target margin upper limit value TMUL, the command value CM of the stage S that is lowered by one stage immediately before the stage S where the combustion vibration occurs is set. , Set as the actual wealth upper limit value AMUL of the raising command process STU.
- the raising command process STU is preferentially executed, and after the raising commanding process STU is completed, the lowering commanding process STD, which is the second step PR2, is executed.
- a new command value CM is set by adding a predetermined set value input rate BIR from the origin OP at the time of initial setting as the starting point, as in the first combustion margin confirmation pattern.
- the command value CM reaches a predetermined new command value CM, the predetermined holding time T1 is held and the presence or absence of combustion vibration is confirmed.
- a predetermined command value input rate BIR is further added to the command value CM, and the presence or absence of combustion vibration in the new command value CM of the next stage S is confirmed.
- the method of repeating this procedure is the same as the first combustion margin confirmation pattern.
- the target combustion margin range that should be originally confirmed is that the command value CM confirms the combustion margin range without causing combustion vibration at the target margin upper limit value TMUL. ..
- the raising command process STU since combustion vibration was generated in the raising command process STU, the raising command process STU was completed in a state where one stage was insufficient. In this case, it is returned to the command value CM which is the stage S immediately before the combustion margin range is confirmed without generating combustion vibration, and this command value CM is set as the actual margin upper limit value AMUL.
- the holding time T2 is maintained from the time point PF when the combustion vibration occurs at this command value CM, and the steady-state data 128 of the gas turbine 1 is collected.
- the collected steady-state data 128 is transmitted to the database 127.
- the number of the original target stages S is one stage short, so in the lowering commanding process STD, the stage of the lowering commanding process STD which is the original target.
- the combustion margin confirmation step S20 is executed with the number of stages one stage larger than the number.
- combustion is further lowered by one stage in the direction of lowering the command value CM from the target lower limit value TMLL at the time of initial setting. Perform a margin check. If the holding time T1 is maintained without the occurrence of combustion vibration in the command value CM that is one step lower than the target margin lower limit value TMLL, it is judged that the combustion margin range in this command value CM has been confirmed, and this The command value CM is set as the actual wealth lower limit value AMLL.
- the specific procedure for confirming the combustion margin range in the second combustion margin confirmation pattern lowering command process STD is the same as the first combustion margin confirmation pattern lowering command process STD, except for the difference in the number of stages.
- the holding time T1 is maintained without the occurrence of combustion vibration at the lower limit of the actual margin value ALL, it is determined that the combustion margin range with this command value CM has been confirmed, and the command value CM is the lower limit value of the actual margin value ALLL.
- the holding time T2 is maintained from the time when the holding time T1 is reached, and the steady data 128 of the gas turbine 1 in the raising command step STU is collected. As a result, it is determined that the second step is completed.
- the second combustion margin confirmation pattern is different from the first combustion margin confirmation pattern in that the number of stages differs between the ascending command process STU and the lowering command process STD. That is, as described above, it is desirable that the number of stages is the same in the raising command process STU and the lowering command process STD centering on the origin OP. Therefore, the position of the origin OP in the second combustion margin confirmation pattern is set to the intermediate position (midpoint position) between the actual wealth upper limit value AMUL of the raising command process STU and the actual wealth lower limit value AMLL of the lowering command process STD. Is desirable.
- the position of the origin OP after confirming the combustion margin range is moved to the position of the command value CM lowered by one stage in the direction of lowering the command value from the position of the origin OP at the time of initial setting, and this position is moved to the position of the new origin.
- NOP the position of the command value CM lowered by one stage in the direction of lowering the command value from the position of the origin OP at the time of initial setting.
- the holding time T1 cannot be maintained and is shorter than the holding time T1.
- combustion vibration is generated at the non-delivery time T0.
- the command value CM is before the target margin upper limit value TMUL, which is the command value CM of the next stage S, is reached from the stage S lowered by one stage immediately before the stage S where the combustion vibration occurs.
- the command value CM in the stage S in which the combustion margin range immediately before the combustion vibration is confirmed is set to the actual margin upper limit value AMUL in the raising command process STU.
- the procedure for confirming the combustion margin range in the lower command step STD of the second step PR2 is the same as the first combustion margin confirmation pattern shown in FIG. 4, and the origin OP at the time of initial setting is a new new one. It is desirable to move to the origin NOP. Further, in the raising command process STU of the first step PR1 shown in FIG. 5, even when the combustion vibration occurs at the command value CM lower than the target margin upper limit value TMUL by two stages or more, the stage S in which the combustion vibration occurs. The command value CM in the stage S in which the immediately preceding combustion margin range is confirmed may be set to the actual margin upper limit value AMUL.
- the lowering command process STD of the second step PR2 it is the difference between the number of stages S of the target margin upper limit value TMUL of the raising command process STU in which combustion vibration is generated and the number of stages of the actual wealth upper limit value AMUL. Then, the number of unachieved stages for which the combustion margin range has not been confirmed is subtracted from the target margin lower limit value TMLL of the lowering command process STD, and a new number of stages is set in the direction of lowering the command value. .. Based on the new number of stages, the number of stages that have not reached the command value CM is lowered from the target lower limit value TMLL by the number of stages, and the combustion margin confirmation of the lower command step STD is executed.
- the command value CM in the final stage S of the lower command process STD is set to the actual margin lower limit value ALL.
- the command value CM which is an intermediate position (midpoint position) between the actual wealth upper limit value AMUL and the actual wealth lower limit value AMLL, is set as the new origin NOP. In this case as well, it is determined that the origin shift has occurred.
- Third combustion margin confirmation pattern As for the third combustion margin confirmation pattern shown in FIG. 6, the raising command process STU is prioritized in the first step PR1 as in the second combustion margin confirmation pattern shown in FIG. However, this is an example different from the second combustion margin confirmation pattern shown in FIG. 5 in that combustion vibration is generated in both steps of the raising command step STU and the lowering command step STD. Further, in the third combustion margin confirmation pattern, the total number of stages between the actual wealth upper limit value AMUL and the actual wealth lower limit value AMLL is the target wealth upper limit value TMUL and the target wealth lower limit value TMLL at the time of initial setting.
- the first combustion margin confirmation pattern and the second combustion margin confirmation pattern are in that the confirmation of the combustion margin range is completed while the total number of stages between the two is not reached and the number of unachieved stages remains. Is a different aspect.
- the command value CM is lowered to the command value CM of the stage S immediately before the combustion vibration occurs, and the command value CM in this stage S is defined as the actual margin upper limit value AMUL.
- the command value CM reaches the actual wealth upper limit value AMUL (PF at the time when the combustion vibration occurs)
- the holding time T2 is maintained and the steady data 128 of the gas turbine 1 is collected, and it is judged that the first step PR1 is completed.
- the command value CM is returned to the position of the origin OP.
- the collected steady-state data 128 is transmitted to the database 127.
- the stage S is one stage more than the original target number of stages. It is desirable to execute the combustion margin confirmation step S20 by the number and maintain the total number of stages between the predetermined target margin upper limit value TMUL and the target margin lower limit value TMLL. Therefore, in the lower command step STD of the second combustion margin confirmation pattern shown in FIG. 5, the combustion margin is confirmed by further lowering the command value CM from the target lower limit value TMLL at the time of initial setting by one step. Running.
- combustion vibration occurs in the stage S before the command value CM reaches the target lower limit value TMLL.
- combustion vibration occurs in the process of lowering the command value CM toward the next stage S after completing the combustion margin confirmation from the position of the origin OP to the three stages S in the lowering direction of the set value ST.
- the command value is further commanded from the position of stage S where the command value CM is the target margin lower limit TMLL.
- combustion vibration occurs in the stage S before the target margin lower limit value TMLL is reached, and the combustion margin cannot be confirmed in the original target range, so that the first step PR1 In the processes on both sides of the raising command process STU and the lowering commanding process STD of the second step PR2, the combustion margin confirmation step S20 was completed while leaving a plurality of unachieved stages S for which the combustion margin range could not be confirmed. It is a pattern.
- the set value ST is returned to the command value CM of the stage S immediately before the combustion vibration is generated, and the command value CM is lowered and set to the actual wealth lower limit value ALL in the command process STD.
- the holding time T2 is maintained from the time when the command value CM which is the lower limit of the actual wealth degree is returned to the command value CM (the time when the combustion vibration occurs), the steady data 128 of the gas turbine 1 is collected, and then the data is transmitted to the database 127. As a result, it is determined that the second step PR2 of this pattern is completed.
- combustion vibration is generated in the raising command process STU, and the combustion margin confirmation step S20 of the raising command process STU is completed while leaving the unachieved stage S, and the target wealth is reached.
- the actual wealth upper limit value AMUL which is an upper limit value lower than the degree upper limit value TMUL, was set.
- Combustion vibration also occurs in the lower command process STD, and the combustion margin confirmation step S20 of the raise command process STU is completed while leaving the unachieved stage S, which is a lower limit lower than the target margin lower limit TMLL.
- the lower limit of actual wealth AMLL was set.
- the range of the confirmed combustion margin (the width between the actual wealth upper limit value AMUL and the actual wealth lower limit value MLL) in this embodiment is the total number of stages of the increase command process STU and the decrease command process STD at the time of initial setting. It means that the combustion margin confirmation step S20 has been completed in a range narrower than the target margin width TMW at the time of initial setting. Further, as a result of checking the combustion margin range in this embodiment, the origin OP at the time of initial setting is changed to an intermediate position (midpoint position) between the actual wealth upper limit value AMUL and the actual wealth lower limit value AMLL. ..
- the command value CM is moved to the position of the new origin NOP at the release rate BRR at the time of returning to the predetermined origin. To. In this case as well, it is determined that the origin shift has occurred.
- the fourth combustion margin confirmation pattern shown in FIG. 7 is a modification in which the first step PR1 and the second step PR2 are exchanged with respect to the second combustion margin confirmation pattern shown in FIG. That is, in the fourth combustion margin confirmation pattern shown in FIG. 7, the second combustion margin confirmation shown in FIG. 5 is executed in the first step PR1 in that the lower command process STD is executed in preference to the raise command process STU. It's a little different from the pattern.
- the lowering command of the first step PR1 is performed, leaving the number of unachieved stages where the combustion vibration is generated in the lowering command process STD and the combustion margin range cannot be confirmed. The process STD has been completed.
- the combustion margin confirmation step S20 is completed.
- the other procedure except for the difference in priority between the raising command process STU and the lowering command process STD is the same as the second combustion margin confirmation pattern shown in FIG.
- the command value CM of the stage S immediately before the stage S where the combustion vibration occurs is set to the actual margin lower limit value ALLL, and the raising command step of the second step PR2 is set.
- the command value CM of the stage S which is the sum of the number of unachieved stages to the target tolerance upper limit value TMUL, is set to the actual wealth upper limit value AMUL.
- the range of the combustion margin confirmed in this pattern (the width between the actual wealth upper limit value AMUL and the actual wealth lower limit value AML) is the same as the target margin width TMW at the time of initial setting.
- the position of the origin OP in the fourth combustion margin confirmation pattern is the actual wealth lower limit value AMLL of the lower command process STD and the actual wealth upper limit of the increase command process STU. It is desirable to use an intermediate position (midpoint position) between the values AMUL. Therefore, the origin OP after confirming the combustion margin range is moved to the position of the command value CM in which the number of unachieved stages is added in the direction of increasing the command value CM from the origin OP at the time of initial setting, and is used as the new origin NOP. There is.
- the command value CM is moved to the position of the new origin NOP at the release rate BRR at the time of returning to the predetermined origin, and the second step PR2 is finished.
- the command value CM which is the stage S immediately before the stage S where the combustion vibration occurs, is the lower limit of the actual margin value, ALL, and the holding time T2 is maintained from the time point PF when the combustion vibration occurs, and the gas is maintained.
- Steering data 128 for turbine 1 is collected and sent to database 127.
- the steady data 128 of the gas turbine 1 whose command value CM is collected in the actual margin upper limit value AMUL is transmitted to the database 127.
- the flow of the entire process shown in FIG. 8 is an example, and is not limited to this flow example.
- the combustion load variable correction step S40 is executed after the combustion margin confirmation step S20, but the combustion load variable correction step S40 may be executed before the combustion margin confirmation step S20. ..
- FIG. 8 shows a combustion margin confirmation step S20 in the direction of increasing the GT load from a small GT load to a rated load (100%) of a large GT load for a plurality of GT loads selected for combustion adjustment. The whole process including is shown.
- the combustion margin adjusting unit 130 shown in FIG. 3 when executing the combustion margin adjustment in the direction of increasing the GT load, as shown in FIG. 8, the combustion adjustment that takes in various operation data, parameters, etc. New when the origin shift occurs in the set value input step S10, the combustion margin confirmation step S20 for operating the gas turbine 1 and confirming the combustion margin range of the combustion parameter PM, and the combustion margin confirmation step S20.
- the setting value change step S30 for changing the set value of the combustion load variable CLP with reference to the origin NOP, and the maximum load for correcting the planned maximum output so that the combustion load variable CLP at the planned maximum output becomes the rated value (100%).
- a combustion load variable correction step S40 comprising a correction step S50, a set value conversion step S70 for modifying the corrected combustion load variable CLP so that the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM is maintained, and a combustion load variable correction step S40. Consists of. If the origin shift does not occur in the combustion margin confirmation step S20, the process may shift to the next combustion load variable correction step S40 without executing the set value changing step S30.
- the target margin width TMW of the combustion parameter PM divides the raising command process STU and the lowering command process STD centering on the origin OP by the same stage width SW, and for each process, The same stage width SW, number of stages SN, and input rate BIR between stages are added as input data.
- the stage width SW of each stage S in the raising command process STU and the stage width SW of each stage S in the lowering commanding process STD may have the same width in the raising commanding process STU and the lowering commanding process STD. , May be different widths.
- FIG. 9 shows the flow of the combustion margin confirmation step S20 of the combustion parameter PM.
- the process of confirming the combustion margin range starts.
- the combustion margin confirmation step S20 first, the priority of the combustion parameter PM for confirming the combustion margin range is set.
- the combustion parameter PM of the first priority is set to PM1, and the second priority is set.
- the combustion parameter PM of priority is assigned as PM2, and the combustion parameter PM of third priority is assigned as PM3 (S21).
- the priority pattern data for the purpose of confirming the combustion margin range stored in the database 127 of the automatic combustion adjustment unit 120 may be called and the priority of the combustion parameter PM may be set.
- the priority pattern data may be, for example, a database capable of automatically selecting the priority of the combustion parameter PM based on the combustion load variable CLP. Further, the priority pattern data may include data that determines the priority of the raising command process STU or the lowering command process STD with respect to the set combustion parameter PM by the combustion load variable CLP.
- the gas turbine load (GT load) for confirming the combustion margin range is set (S22).
- GT load gas turbine load
- a plurality of GT loads are set in the range of the GT load of 0 to 100%.
- the selected GT load is input to the input unit 121.
- the GT load of 100% corresponds to the planned maximum output or the rated output
- the GT load of 0% corresponds to the output at no load.
- the same GT load is used until the confirmation of each combustion margin range of all combustion parameters (pilot ratio PL, top hat ratio TH, bypass valve opening BV) is completed. It is desirable to carry out a check of the combustion margin range.
- the combustion margin confirmation of the first priority first combustion parameter PM1 is executed (S23).
- the specific implementation procedure and contents of confirmation of the combustion margin range of the first combustion parameter PM1 of the first priority are the first combustion margin confirmation pattern or the second combustion margin shown in FIG. 4 or FIG. 5 or FIG. It is executed according to either the confirmation pattern or the fourth combustion margin confirmation pattern (S23).
- the combustion margin confirmation of the first combustion parameter PM1 if combustion vibration does not occur in both processes in the raising command process STU and the lowering command process STD, the combustion margin confirmation of the first combustion parameter PM1 is completed.
- the combustion margin confirmation step S20 is determined to be continued (S23), and the process proceeds to the next step (S25).
- the position of the origin OP1 of the first combustion parameter PM1 is maintained.
- the origin OPs of the first combustion parameter PM1, the second combustion parameter PM2 and the third combustion parameter PM3 are represented by OP1, OP2, OP3, and the new origin NOPs are represented by NOP1, NOP2, NOP3.
- the target margin range TMW is displayed as TMW1, TMW2, and TMW3.
- the origin In the confirmation of the combustion margin range of the first combustion parameter PM1, if combustion vibration occurs in either the raising command process STU or the lowering command process STD, the origin is shifted to a predetermined combustion margin range. It is determined whether or not a certain target margin width TMW1 can be secured (S24). If it is determined that the predetermined combustion margin range of the first combustion parameter PM1 is secured, the combustion margin confirmation of the first combustion parameter PM1 is completed, and it is determined that the combustion margin confirmation step S20 is continued (S24). ), The process proceeds to the next step (S25). In the case of this embodiment, since the origin shift of the first combustion parameter PM1 has occurred, the position of the origin OP1 of the first combustion parameter PM1 moves to the new origin NOP1. The stationary data 128 of the gas turbine 1 and the position data of the new origin NOP1 collected by the first combustion parameter PM1 are transmitted to the database 127 (S24).
- the process proceeds to the confirmation of the combustion margin range of the second combustion parameter PM2.
- the target margin width TMW1 which is a predetermined combustion margin width cannot be secured, but the combustion vibration is narrower than the target margin width TMW1. If it is determined that the range in which the gas turbine 1 does not occur can be maintained, it is determined that the combustion margin range required for stable operation continuation of the gas turbine 1 is secured. In that case, the confirmation of the combustion margin range of the first combustion parameter PM1 is completed, the combustion margin confirmation step S20 is determined to be continued (S24), and the process proceeds to the next step (S25). If it is determined that the combustion margin range required for stable operation of the gas turbine 1 of the first combustion parameter PM1 cannot be secured, it is determined that the combustion margin confirmation step S20 cannot be continued, and the combustion margin confirmation step is performed. S20 ends (S24).
- the combustion margin confirmation of the second combustion parameter PM2 is executed (S25).
- the specific implementation procedure and work contents of the confirmation of the combustion margin range of the second combustion parameter PM2 are the first combustion margin confirmation pattern shown in FIG. 4 or FIG. 5 or FIG. 7, as in the case of the first combustion parameter PM1.
- the combustion margin confirmation pattern or the fourth combustion margin confirmation pattern If combustion vibration does not occur in both the raising command process STU and the lowering command process STD for the second combustion parameter PM2, the combustion margin confirmation of the second combustion parameter PM2 is completed, and the combustion margin confirmation step S20 is continued. (S25), and the process proceeds to the next step (S27). In this case, the position of the origin OP2 of the second combustion parameter PM2 is maintained.
- the origin of the second combustion parameter PM2 is shifted. Then, it is determined whether or not the target margin width TMW2, which is a predetermined combustion margin range, can be secured (S26). If it is determined that the predetermined target margin width TMW2 of the second combustion parameter PM2 is secured, the confirmation of the combustion margin range of the second combustion parameter PM2 is completed, and it is determined that the combustion margin confirmation step S20 is continued. (S26).
- the origin shift of the second combustion parameter PM2 occurs, the position of the origin OP2 of the second combustion parameter PM2 moves to the new origin NOP2, and the first combustion which is the first priority combustion parameter PM is performed. It is returned to the step (S23) of the combustion margin confirmation of the parameter PM1 (S26).
- the reason for returning to the step of confirming the combustion margin of the first combustion parameter PM1 (S23) is that the origin of the second combustion parameter PM2 is shifted in the step of confirming the combustion margin of the second combustion parameter PM2 (S25).
- the target margin width TMW2 which is a predetermined combustion margin width
- the target margin width TMW2 which is a predetermined combustion margin width
- the position of the origin OP2 of the second combustion parameter PM2 moves to the new origin NOP2, and the first priority combustion parameter It is returned to the step (S23) of confirming the combustion margin range of the first combustion parameter PM1 (S26). If it is determined that the predetermined combustion margin range of the second combustion parameter PM2 cannot be secured, it is determined that the combustion margin confirmation step S20 cannot be continued, and the combustion margin confirmation step S20 ends (S26). ..
- the combustion margin confirmation of the third combustion parameter PM3 is executed (S27).
- the specific implementation procedure and work contents of the combustion margin confirmation of the third combustion parameter PM3 are the first combustion margin confirmation pattern, the second combustion margin confirmation pattern, or the fourth combustion shown in FIG. 4 or FIG. 5 or FIG. As shown in one of the margin confirmation patterns.
- the third combustion parameter PM3 if combustion vibration does not occur in both steps in the raising command process STU and the lowering command process STD, the confirmation of the combustion margin range of the third combustion parameter PM3 is completed and the combustion margin is completed.
- the degree confirmation step S20 is determined to be continued (S27), and the process proceeds to the next step (S29).
- the position of the origin OP3 of the third combustion parameter PM3 is maintained, and the stationary data 128 of the gas turbine 1 collected by the third combustion parameter PM3 is transmitted to the database 127.
- the origin is shifted to achieve the target combustion margin within the predetermined combustion margin range. It is determined whether or not the width TMW3 can be secured (S28). If it is determined that the predetermined target margin width TMW3 of the third combustion parameter PM3 is secured, the combustion margin confirmation of the third combustion parameter PM3 is completed, and it is determined that the combustion margin confirmation step S20 is continued. (S28).
- the origin OP3 of the third combustion parameter PM3 has occurred.
- the position of is moved to the new origin NOP3 and returned to the step (S23) of confirming the combustion margin of the first combustion parameter PM1 (S26).
- the reason for returning to the step (S23) for confirming the combustion margin of the first combustion parameter PM1 is the same as the case where the origin shift of the second combustion parameter PM2 occurs.
- the stationary data 128 of the gas turbine 1 collected by the third combustion parameter PM3 is transmitted to the database 127 together with the position data of the new origin NOP3.
- the step (S27) for confirming the combustion margin of the third combustion parameter PM3 is the third combustion margin confirmation pattern shown in FIG. 6, the target margin width TMW3, which is a predetermined combustion margin width, can be secured. However, if it is judged that the range in which combustion vibration does not occur can be maintained even with a margin width narrower than the target margin width TMW3, the combustion margin width necessary for stable operation continuation of the gas turbine 1 is secured. It is determined that the combustion margin confirmation of the third combustion parameter PM3 is completed, and the combustion margin confirmation step S20 is continued (S28).
- the process After completing the combustion margin confirmation (S28) of the third combustion parameter PM3, the process proceeds to the next step (S29), and it is determined whether or not the GT load has reached the maximum load (S29). If the GT load has not reached the maximum load, the process returns to the GT load setting step S22, and the next GT load is set from the GT load at the time of initial setting (S22). Based on the new GT load, the combustion margin confirmation of the combustion parameters is repeated (S23 to S29). When the GT load reaches the maximum load, the combustion margin confirmation step S20 ends (S29), and the process proceeds to the set value changing step S30 shown in FIG.
- combustion margin confirmation step S20 ends (S28). ..
- the flow shown in FIG. 9 is the combustion margin confirmation step S20 in the direction of increasing the GT load, but in the case of the combustion margin confirmation step S20 in the direction of decreasing the GT load, the GT load reaches the minimum load. It is determined whether or not this has been done (S29), the next GT load is set (S22), and the combustion margin confirmation step S20 is executed.
- combustion load variable correction step S40 the combustion parameter PM and the combustion load variable CLP are set so that the gas turbine 1 obtains the planned maximum output MOP at the rated value (100%) of the combustion load variable CLP.
- This is a step of making corrections necessary for optimizing the set value ST indicating the relationship. That is, in the combustion load variable correction step S40, the combustion load variable CLP is the rated value at the planned maximum output MOP of the gas turbine 1 on the precondition that the proper relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM is maintained.
- the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM is maintained. It is composed of a set value conversion step S70 for converting the set value of the combustion load variable CLP.
- the GT load control is executed using the combustion load variable CLP displayed by the following formula instead of the gas turbine inlet temperature GTIT.
- the control of the GT load (GT output) is specifically controlled by the pilot ratio PL, the top hat ratio TH, the bypass valve opening BV, etc., which are the combustion parameter PMs, and each combustion parameter PM is the combustion load variable CLP. Displayed by a function.
- the combustion load variable CLP of the combustion parameter PM can be calculated by the following [Equation 1].
- Combustion load variable CLP (%) [(Turbine output-No-load equivalent output) / (Planned maximum output-No-load equivalent output)] x 100
- the planned maximum output MOP means the turbine output (gas turbine output) at the planned output or the rated output
- the no-load equivalent output NOP means the turbine output at the time of no load.
- the combustion load variable CLP is the rated value (100%)
- the combustion load variable CLP is equivalent to 0 (%). do.
- the result of the combustion margin confirmation step S20 is correctly reflected in the set value indicating the relationship between the combustion parameter PM and the combustion load variable CLP.
- the relationship between the combustion parameter PM and the combustion load variable CLP is the rated value of the combustion load variable CLP while maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM.
- the planned maximum load (planned maximum output) MOP needs to be set to be output. Since the combustion control device 100 is set so that the combustion load variable CLP corresponding to the planned maximum output MOP is the rated value (100%), the set value of the combustion load variable CLP is set lower than the rated value.
- FIGS. 10A to 10C show the concept of the correction means when the gas turbine 1 reaches the planned maximum output MOP at a position where the combustion load variable CLP does not reach the rated value (100%) (Case 1).
- FIG. 10A is a diagram showing the relationship between the combustion parameter PM of Case 1 and the combustion load variable CLP by placing the combustion parameter PM on the vertical axis and the combustion load variable CLP on the horizontal axis.
- FIG. 10B is a diagram showing the relationship between the gas turbine inlet temperature GTIT of Case 1 and the combustion load variable CLP by placing the gas turbine inlet temperature GTIT on the vertical axis and the combustion load variable CLP on the horizontal axis.
- FIG. 10A is a diagram showing the relationship between the combustion parameter PM of Case 1 and the combustion load variable CLP by placing the combustion parameter PM on the vertical axis and the combustion load variable CLP on the horizontal axis.
- FIG. 10B is a diagram showing the relationship between the gas turbine inlet temperature GTIT of Case 1 and the combustion
- FIGS. 10C is a diagram showing the relationship between the gas turbine inlet temperature GTIT of Case 1 and the combustion parameter PM with the combustion parameter PM on the vertical axis and the gas turbine inlet temperature GTIT on the horizontal axis.
- the curve [I-1] and the straight line [I-1] shown by the broken line are the data immediately after being acquired in the combustion margin confirmation step S20.
- the curved line [II-1] and the straight line [II-1] shown by the chain line are the data after being corrected in the maximum load correction step S50.
- the curve [III] and the straight line [III] shown by the solid line are the data after being converted in the set value conversion step S70.
- FIG. 11A to 11C show the concept of the correction means when the gas turbine 1 reaches the planned maximum output MOP at a position where the set value ST of the combustion load variable CLP exceeds the rated value (100%) (Case 2). Shows.
- FIG. 11A is a diagram showing the relationship between the combustion parameter PM of Case 2 and the combustion load variable CLP by placing the combustion parameter PM on the vertical axis and the combustion load variable CLP on the horizontal axis.
- FIG. 11B is a diagram showing the relationship between the gas turbine inlet temperature GTIT of Case 2 and the combustion load variable CLP by placing the gas turbine inlet temperature GTIT on the vertical axis and the combustion load variable CLP on the horizontal axis.
- FIG. 11A is a diagram showing the relationship between the combustion parameter PM of Case 2 and the combustion load variable CLP by placing the combustion parameter PM on the vertical axis and the combustion load variable CLP on the horizontal axis.
- FIG. 11B is a diagram showing the relationship between the gas turbine inlet temperature GTIT
- 11C is a diagram showing the relationship between the gas turbine inlet temperature GTIT of Case 2 and the combustion parameter PM with the combustion parameter PM on the vertical axis and the gas turbine inlet temperature GTIT on the horizontal axis.
- the curve [I-2] and the straight line [I-2] shown by the broken line are the data immediately after being acquired in the combustion margin confirmation step S20.
- the curved line [II-2] and the straight line [II-2] shown by the chain line are the data after being corrected in the maximum load correction step S50.
- the curve [III] and the straight line [III] shown by the solid line are the data after being converted in the set value conversion step S70.
- the curve [I-1] shown in FIG. 10A shows a set value indicating the relationship between the combustion parameter PM acquired in the combustion margin confirmation step S20 and the combustion load variable CLP.
- the curve [I-1] shows an example in which the GT load increases and the combustion parameter PM decreases as the combustion load variable CLP increases.
- the set value shown by the curve [I-1] indicates the set value of the optimum combustion load variable CLP for the gas turbine inlet temperature GTIT of the current device, and is the set value capable of the most appropriate combustion control without generating combustion vibration. be.
- the curve [I-1] shows Y (%) in which the set value of the combustion load variable CLP in the planned maximum output (GT load 100%) MOP is not the rated value (100%) but lower than the rated value (100%). At the position of, the planned maximum output (GT load 100%) MOP has been reached.
- the combustion control device 100 is set so that the combustion load variable CLP becomes the rated value (100%) at the planned maximum output (GT load 100%) MOP.
- the curve [III] shown in FIG. 10A is a set value showing the relationship between the combustion parameter PM incorporated in the combustion control device 100 and the combustion load variable CLP. If the deviation between the rated value (100%) of the combustion load variable CLP shown on the horizontal axis and the coordinate axis of Y (%) is left unattended, the combustion control of the gas turbine 1 is adversely affected. Therefore, the relationship of the curve [I-1] shown in FIG.
- the curve [II-1] shows the relationship between the combustion parameter PM and the combustion load variable CLP before conversion of the set value, which will be described later, and is consistent with the curve [I-1].
- FIG. 10B is a diagram comparing the set values showing the relationship between the combustion parameter PM and the combustion load variable CLP in FIG. 10A by replacing them with the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP.
- the straight line shown in FIG. 10B is obtained by replacing the relationship between the curve [I-1], the curve [II-1] and the curve [III] shown in FIG. 10A with the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP. It corresponds to [I-1], a straight line [II-1] and a straight line [III].
- the relationship between the gas turbine inlet temperature GTIT of the straight line [I-1], the straight line [II-1], and the straight line [III] shown in FIG. 10B and the combustion load variable CLP is proportional to each other.
- FIG. 10C is a diagram comparing the set values showing the relationship between the combustion parameter PM and the combustion load variable CLP shown in FIG. 10A by replacing them with the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT.
- the curve shown in FIG. 10C is obtained by replacing the relationship between the curve [I-1], the curve [II-1], and the curve [III] shown in FIG. 10A with the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP.
- the position of the point P1-1 is corrected in the direction of reducing the difference (deviation) of the combustion load variable CLP from the position of the point P3 corresponding to the rated value (100%) of the CLP, and the straight line [I-1] becomes a straight line [I-1].
- a correction means that matches [III] may be applied. By replacing the data of the straight line [I-1] with the data of the straight line [III] by this correction means, the deviation at the time of initial setting of the combustion load variable CLP is eliminated.
- Equation 2 which will be described later, is a straight line in FIG. 10B in which the straight line [I-1] is moved to the position of the straight line [III] until the position of the point P1-1 at the maximum output temperature TMX coincides with the position of the point P3.
- a correction means for correcting [1-1] to a straight line [III] By executing the correction means according to [Equation 2], the straight line [1-1] becomes a straight line [III] passing through the point P3 indicating the maximum output temperature TMX at the position of the rated value (100%) of the combustion load variable CLP.
- the combustion load variable CLP is in the range of 0 to Y (%).
- the straight line [II-1] is corrected and converted to the straight line [II-1]
- the position of the point P1-1 of the straight line [II-1] is the straight line [II-] where the combustion load variable CLP is Y (%).
- the gas turbine inlet temperature GTIT at the combustion load variable CLP at Y (%) is from the inlet temperature TMX to the inlet temperature TMX1 (the corrected combustion load variable CLP is at Y (%). It drops to the inlet temperature). That is, the curve [I-1] showing the relationship between the combustion parameter PM shown in FIG. 10A and the combustion load variable CLP is replaced with the straight line [II-1] shown in FIG. 10B, and the gas turbine inlet temperature with respect to the combustion load variable CLP is replaced. GTIT decreases.
- the combustion parameter PM and the gas turbine inlet temperature GTIT shown in the curve [I-1] are corrected to the curve [II-1] by correction. That is, the curve [I-1] having the set value that enables proper combustion control after the combustion margin confirmation step S20 is completed has the same relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT as the curve [III]. However, the curve [II-1] corrected by the correction has a relatively lower gas turbine inlet temperature GTIT than the target curve [III].
- the position of the point P11-1 in which the arbitrary combustion load variable CLP on the curve [I-1] shown in FIG. 10A and the straight line [I-1] shown in FIG. 10B corresponds to X1 (%) is corrected as described above.
- the curve [II-1] coincides with the curve [I-1] without being different, so that the position of the point P12-1 also coincides with the point P11-1. ..
- the position of the point P11-1 moves to the point P12-1 on the straight line [II-1] in the same combustion load variable CLP in X1 (%).
- the relationship between the combustion load variable CLP and the combustion parameter PM does not change even if corrected, but the relationship between the combustion load variable CLP and the gas turbine inlet temperature GTIT is corrected and the gas turbine inlet in the same combustion load variable CLP.
- the temperature GTIT decreases.
- the correction means is premised on maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM, and this relationship is not maintained. Therefore, in order to satisfy the condition for maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM, other correction means are required in addition to the above-mentioned correction means.
- the relationship between the combustion parameter PM and the combustion load variable CLP is the combustion load while maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM. It is necessary to set the planned maximum load (planned maximum output) MOP to be output at the rated value (100%) of the variable CLP, and it is desirable to apply a correction means according to the purpose. From this point of view, the curve [II-1] (straight line [II-1] in FIG. 10B) shown in FIG. 10C selected by the correction is a condition for maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM.
- the combustion gas turbine inlet temperature GTIT shown on the horizontal axis is made to match the inlet temperature TMX from the inlet temperature TMX1 while maintaining the combustion parameter PM on the vertical axis of the curve [II-1].
- the set value of the combustion load variable CLP may be converted (only the set value of the combustion load variable CLP is slid in the axial direction of the horizontal axis) (set value conversion step S70).
- set value conversion step S70 By executing the set value conversion step S70, in FIG. 10C, the point P2-1 on the curve [II-1] showing the planned maximum output and the point P3 on the curve [III] showing the planned maximum output without changing the combustion parameter PM.
- the point P12-1 (FIG.
- the maximum load correction step S50 which is a correction means in which the combustion load variable CLP that outputs the planned maximum load MOP becomes the rated value (100%) based on [Equation 2], and the gas turbine inlet temperature GTIT. It is desirable to include a set value conversion step S70, which is a correction means for maintaining the relationship between the combustion parameter PM and the combustion parameter PM.
- the set value of the combustion parameter PM and the combustion load variable CLP is the planned maximum at the rated value (100%) of the combustion load variable CLP while maintaining the relationship between the gas turbine inlet temperature GTIT and the combustion parameter PM.
- the load (planned maximum output) MOP is corrected to be output. That is, it is a combustion load variable CLP that outputs the planned maximum load (planned maximum output) MOP, although the combustion margin range is confirmed in the combustion margin confirmation step S20 and the set value that can be appropriately controlled for combustion is selected.
- the adverse effect on the combustion control due to the deviation from the rated value (100%) of the initial set value is eliminated by the above-mentioned correction means.
- the correction at the time of initial setting enables stable operation for a long period of time even at the stage of steady operation.
- the gas turbine 1 is the planned maximum at the position where the combustion load variable CLP is at the position where the set value of the combustion load variable CLP exceeds the rated value (100%) and is at the position of Z (%). Shows when the output is reached.
- the curve [I-2] shown in FIG. 11A shows the relationship between the set value of the combustion parameter PM and the combustion load variable CLP with respect to the combustion parameter PM acquired in the combustion margin confirmation step S20.
- the curve [I-2] shows the combustion load variable in which the set value of the combustion load variable CLP in the planned maximum output (GT load 100%) MOP exceeds the rated value (100%) instead of the rated value (100%). It differs from Case 1 in that the CLP reaches the planned maximum output (GT load 100%) at the Z (%) position.
- the curve [II-2] shows the relationship between the combustion parameter PM and the combustion load variable CLP after the combustion load variable CLP is corrected by the maximum load correction step S50.
- FIG. 11B is a diagram comparing the relationship between the curve [I-2] and the curve [II-2] and the curve [III] in FIG. 11A by replacing the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP. ..
- the straight line shown in FIG. 11B is obtained by replacing the relationship between the curve [I-2], the curve [II-2] and the curve [III] shown in FIG. 11A with the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP.
- FIG. 11C is a diagram comparing the relationship between the curve [I-2] and the curve [II-2] and the curve [III] in FIG.
- FIG. 11A by replacing the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT. be.
- the curve shown in FIG. 11C is obtained by replacing the relationship between the curve [I-2], the curve [II-2], and the curve [III] shown in FIG. 11A with the relationship between the gas turbine inlet temperature GTIT and the combustion load variable CLP. Corresponds to [I-2], curve [II-2] and curve [III].
- the correction means in the case 2 replaces the curve [I-1] and the curve [II-1] in the above case 1 with the curve [I-2] and the curve [II-2], and the straight line [I-1] and the straight line.
- [II-1] is read as a straight line [I-2] and a straight line [II-2].
- the points P1-1, P2-1, P11-1, and P12-1 can be read as points P1-2, P2-2, P11-2, and P12-2.
- the contents described can be applied to Case 2.
- the gas turbine inlet temperature GTIT of the data acquired in the combustion margin confirmation step S20 is lowered by the correction, and the lowered gas turbine inlet temperature GTIT is maintained at the initial inlet temperature.
- Equation 2 is a combustion load variable corrected by using a combustion load variable correction means in order to correct the deviation between the combustion parameter PM and the initial setting value of the combustion load variable CLP with respect to [Equation 1]. It is a formula for calculating CLP, and is composed of correction means of a combustion load variable correction step S40 (maximum load correction step S50, set value conversion step S70).
- Combustion load variable CLP (%) [(Turbine output (actual output) -No-load equivalent output) / (Planned maximum output x 1st correction coefficient x 2nd correction coefficient-No-load equivalent output)] x 100
- the first correction coefficient 156a and the second correction coefficient 157a are correction coefficients set in the combustion load variable correction step S40 described later.
- the concept of the planned maximum output and the output equivalent to no load is the same as in [Equation 1].
- the first correction coefficient 156a is a correction coefficient for correcting the combustion load variable CLP in order to correct the deviation between the combustion parameter PM and the initial setting value of the combustion load variable CLP.
- the second correction coefficient 157a corrects the combustion load variable CLP in order to correct the deviation between the combustion parameter PM and the set value of the combustion load variable CLP caused by the deterioration of the gas turbine after the gas turbine 1 enters steady operation. It is a correction coefficient.
- the correction means corrects the combustion load variable CLP by multiplying the planned maximum output MOP by the first correction coefficient 156a and the second correction coefficient 157a.
- FIG. 12 is a flow chart showing a work flow of the combustion load variable correction step S40.
- FIG. 13 shows a control logic diagram for calculating the corrected combustion load variable CLP represented by [Equation 2], and shows each configuration of the combustion load variable correction unit 134 constituting the correction means of the combustion load variable correction step S40. Has been done.
- [Equation 2] is an equation for calculating the combustion load variable CLP including the first correction coefficient 156a. If the turbine output matches the planned maximum output MOP or the rated output, the combustion load shown in [Equation 2] is calculated. The variable CLP agrees with [Equation 1]. In this case, the first correction coefficient 156a in [Equation 2] is set to the initial value "1".
- the maximum combustion load variable CLP shown in [Equation 2] is corrected so that the combustion load variable CLP with respect to the planned maximum output MOP becomes the rated value (100%).
- Set value conversion step S70 that converts the set value of the combustion load variable CLP so that the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT is maintained based on the load correction step S50 and the corrected combustion load variable CLP. And, it is composed of.
- the combustion load variable correction step S40 calculates the deviation between the turbine output transmitted from the input unit 121 and the corrected planned maximum output output from the second maximum load multiplier 157 described later. (S51). Next, the calculated deviation is proportionally integrated to calculate the intermediate correction value 151a (S52). A predetermined value ⁇ is added to the calculated intermediate correction value 151a to calculate the second correction value 152a. As the predetermined value ⁇ , 1.0 is usually selected. After starting the execution of the maximum load correction step S50, it is determined whether or not a predetermined time has elapsed (S54).
- the second correction coefficient 157a shown in [Equation 2] is updated to the second correction value 152a (S55).
- the combustion load variable CLP shown in [Equation 2] is calculated based on the updated second correction coefficient 157a (S56), and the set value of the combustion load variable CLP of each combustion parameter PM is transmitted to the control unit 110 (S57). ).
- a control signal is transmitted from the control unit 110 to the gas turbine 1 based on the set value of the corrected combustion load variable CLP.
- the deviation between the turbine output, which is the actual output based on the set value of the corrected combustion load variable CLP, and the planned maximum output is calculated (S51).
- the combustion load variable correction command 161 is transmitted from the correction command unit 160 (S60).
- the switch 154 is switched from the closed (OFF) to the open (ON) state, and the second correction value 152a is input to the switch 154 (S61).
- the switch 154 is switched to the closed (OFF) state in a short time, and the second correction value 152a is replaced with the first correction value 154a (S62).
- the second correction value 152a is reset to the initial value (S62).
- the first correction coefficient 156a shown in [Equation 2] is updated to the first correction value 154a (S63).
- the set value conversion step S70 corrects the gas turbine inlet temperature GTIT using the first correction coefficient 156a so that the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT is maintained based on the corrected combustion load variable CLP. , Converts the set value that determines the relationship between the combustion parameter and the combustion load variable CLP.
- the function generator 141 which is an output calculation means of the planned maximum output, calculates the planned maximum output based on the measured intake air temperature, the intake flow rate, and the IGV opening command value.
- the function generator 142 which is an output calculation means of the no-load equivalent output, calculates the no-load equivalent output based on the measured intake air temperature, the intake flow rate, and the IGV opening command value.
- the divider 147 divides the actually measured intake pressure and the standard atmospheric pressure to calculate the atmospheric pressure ratio.
- the planned maximum output calculated by the function generator 141 is multiplied by the atmospheric pressure ratio calculated by the divider 147 to calculate the planned maximum output in consideration of the atmospheric pressure ratio.
- the multiplier 149 multiplies the no-load equivalent output calculated by the function generator 142 with the atmospheric pressure ratio calculated by the divider 147 to calculate the no-load equivalent output in consideration of the atmospheric pressure ratio.
- the subtractor 145 subtracts from the turbine output transmitted from the input unit 121 and the no-load equivalent output output from the multiplier 149.
- the planned maximum output shown in [Equation 2] is corrected by the first correction coefficient 156a and the second correction coefficient 157a described later.
- the subtractor 143 subtracts from the corrected planned maximum output output from the second maximum load multiplier 157 and the no-load equivalent output output from the multiplier 149 (see [Equation 2]).
- the divider 144 divides based on the calculation result of the subtractor 143 and the calculation result of the subtractor 145 to calculate the corrected combustion load variable CLP shown in [Equation 2].
- the combustion load variable correction unit 134 is composed of a maximum load correction unit 134a and a set value conversion unit 134b.
- the maximum load correction unit 134a is a means for correcting the deviation of the initial setting value of the combustion parameter PM with respect to the combustion load variable CLP, and is shown in the range surrounded by the broken line in FIG.
- the maximum load correction unit 134a corresponds to the maximum load correction step 50
- the set value conversion unit 134b corresponds to the set value conversion step S70.
- the maximum load correction unit 134a includes a subtractor 150 that calculates the deviation between the turbine output and the planned maximum output MOP after correction, a PI calculator 151 that calculates an intermediate correction value 151a, and a predetermined value output from the signal generator 153.
- the adder 152 that calculates the second correction value 152a by adding the value ⁇ to the intermediate correction value 151a and the second correction value 152a output from the adder 152 are accepted and replaced with the existing values of the second correction coefficient 157a.
- the data storage device 155 that stores the second correction value 152a as a new first correction value 154a and the first correction value 154a output from the data storage device 155 are accepted and replaced with the existing values of the first correction coefficient 156a. It is composed of a first maximum load multiplier 156 updated to a first correction value 154a.
- the turbine output input from the control unit 110 via the input unit 121 and the corrected planned maximum output MOP corrected by the second maximum load multiplier 157 are input to the subtractor 150.
- the subtractor 150 calculates the deviation between the turbine output and the corrected maximum output MOP.
- the deviation between the turbine output output from the subtractor 150 and the corrected maximum output MOP is input to the PI calculator 151.
- the deviation between the turbine output and the corrected maximum output MOP is proportionally integrated, and the intermediate correction value 151a is calculated.
- the generated intermediate correction value 151a is added with the predetermined value ⁇ input from the signal generator 153 by the adder 152, and the second correction value 152a is calculated.
- the second correction value 152a output from the adder 152 is input to the second maximum load multiplier 157.
- the second correction coefficient 157a of the second maximum load multiplier 157 shown in [Equation 2] is updated to the second correction value 152a instead of the existing value.
- the corrected planned maximum output is calculated.
- the corrected maximum output is input to the subtractor 143 and subtracted by the no-load equivalent output NOP input from the multiplier 149.
- the corrected combustion load variable CLP shown in [Equation 2] is calculated based on the calculation result from the subtractor 143 and the calculation result from the subtractor 145, and is output to the control unit 110.
- the maximum load correction step S50 when the maximum load correction step S50 is started and a predetermined time elapses, it is determined that the deviation between the turbine output calculated by the subtractor 150 and the corrected planned maximum output MOP is within the allowable value of the output deviation.
- the combustion load variable correction command 161 is transmitted.
- the combustion load variable correction command 161 is input to the PI calculator 151 and the switch 154, the signal of the combustion load variable correction command 161 is temporarily turned on, and the second correction value 152a output from the adder 152 is turned on.
- the signal is input to the data storage device 155 and stored as the first correction value 154a.
- the first correction value 154a is input from the data storage device 155 to the first maximum load multiplier 156.
- the existing value of the first correction coefficient 156a shown in [Equation 2] is updated to the first correction value 154a, and the planned maximum output MOP after correction is based on the updated first correction coefficient 156a. Is calculated. Further, when the combustion load variable correction command 161 is input to the PI calculator 151, the second correction value 152a is reset and updated to the initial setting value. The switch 154 is opened (ON) based on the combustion load variable correction command 161, and the time for updating the first correction coefficient 156a of the first maximum load multiplier 156 to the first correction value 154a ends in a short time. do.
- the switch 154 After the switch 154 is switched to the closed (OFF) state, the circuit in which the signal of the second correction value 152a on the upstream side of the switch 154 enters the switch 154 is cut off. At the same time that the switch 154 is switched to the closed (OFF) state, the second correction value 152a is reset and updated to the initial setting value (usually [1]). The second correction value 152a output from the adder 152 is updated to the initial setting value, but the updated second correction value 152a is not input to the switch 154 and is transmitted to the second maximum load multiplier 157. To.
- the first correction coefficient 156a input to the first maximum load multiplier 156 is the second correction value 152a input when the switch 154 is opened (ON) in response to the combustion load variable correction command 161. Is changed to the first correction value 154a, and is maintained at the first correction value 154a.
- the first correction value 154a input to the data storage device 155 is stored in the data storage device 155.
- the second correction value 152a when the switch 154 is opened (ON) in response to the combustion load variable correction command 161 the deviation between the turbine output and the corrected planned maximum output MOP is within the allowable value. It is a value at the time of entering, and the second correction value 152a is stored in the data storage device 155 as the first correction value 154a.
- the first correction coefficient 156a is corrected for the planned maximum output by using the first correction coefficient 156a and the second correction coefficient 157a, and the rated value (100%) of the combustion load variable CLP is used. Since the purpose is to select a correction coefficient that produces the planned maximum output MOP, the first correction coefficient 156a is updated to the first correction value 154a, and is maintained as it is even after shifting to steady operation.
- the set value conversion unit 134b converts the set value of the corrected combustion load variable CLP calculated by the maximum load correction unit 134a while maintaining the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT. That is, the deviation of the inlet temperature caused by the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT by the correction in the maximum load correction unit 134a is repaired by the conversion of the set value of the combustion load variable CLP in the set value conversion unit 134b.
- the gas turbine inlet temperature GTIT is divided by the first correction coefficient 156a to obtain the corrected new gas turbine inlet temperature GTIT.
- the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT is maintained as the relationship between the combustion parameter PM and the gas turbine inlet temperature GTIT when the combustion margin range is confirmed.
- the combustion load variable CLP is calculated, and the planned maximum output MOP after correction is calculated. It is calculated.
- the second correction coefficient 157a updated to the second correction value 152a is reset to the initial set value (usually [1]) in response to the combustion load variable correction command 161. 2
- the correction coefficient 157a also returns to the initial setting value.
- the combustion load variable before correction is replaced with the combustion load variable CLP after correction based on [Equation 2], and is transmitted to the control unit 110.
- the first correction coefficient 156a of the first maximum load multiplier 156 is updated to the first correction value 154a selected under the condition that the planned maximum output and the turbine output substantially match. 2
- the correction coefficient 157a is transmitted to the control unit 110 with the default setting value.
- the combustion load variable CLP shown in [Equation 2] is replaced with a set value at which the planned maximum output MOP is output at the rated value (100%) of the combustion load variable CLP. Therefore, in the corrected combustion control of the combustor 3, the deviation of the initial setting value of the combustion load variable CLP is eliminated, and appropriate combustion control becomes possible.
- the planned maximum output is calculated by using the first correction coefficient 156a in the maximum load correction step S50 in order to eliminate the deviation of the initial set value.
- a correction means was applied so that the planned maximum output was output at the rated value (100%) of the combustion load variable CLP.
- the gas turbine 1 enters steady operation.
- the deviation between the planned maximum output and the actual output occurs as the gas turbine 1 deteriorates.
- the planned maximum output shown in [Equation 2] is corrected in the same way.
- the correction means for correcting the deviation of the set value ST of the combustion load variable CLP due to the deterioration of the gas turbine 1 is slightly different from the above-mentioned correction means, and among the maximum load correction steps S50 shown in FIG. A learning circuit is applied in which a process of repeating steps S51 to S57 excluding step S54 is executed. By repeating this process, the deviation between the planned maximum output MOP and the set value ST of the combustion load variable CLP is automatically eliminated.
- the first correction coefficient 156a selected by the correction performed at the time of trial run or at the start-up after the end of the regular inspection is maintained as it is, and the set value of the planned maximum output MOP and the combustion load variable CLP is maintained using the second correction coefficient 157a.
- the deviation of ST is corrected.
- the deviation between the turbine output and the planned maximum output is an allowable value.
- the planned maximum output is corrected using the second correction coefficient 157a, the corrected planned maximum output MOP is calculated, and the corrected combustion load variable CLP is calculated.
- the first correction coefficient 156a is fixed at the previously set value.
- the gas turbine 1 enters steady operation.
- the deterioration of the gas turbine 1 causes a deviation between the set value ST of the combustion parameter PM and the combustion load variable CLP, but the first correction coefficient 156a has been updated to the first correction value 154a.
- the second correction coefficient 157a is updated until the deviation between the turbine output and the planned maximum output MOP is within the permissible value. By updating the second correction coefficient 157a, the planned maximum output MOP is corrected and the combustion load variable CLP is automatically corrected.
- the planned maximum output is multiplied by the first correction coefficient 156a and the second correction coefficient 157a as the correction means.
- the reason for applying the two correction coefficients is that the first correction coefficient 156a and the second correction coefficient 157a are updated at the initial setting at the start of the trial run and at the time of restarting the operation after the regular inspection, and the optimum first correction coefficient 156a is applied. This is because the first correction coefficient 156a is fixed and only the second correction coefficient 157a is updated to select the optimum second correction coefficient 157a during steady operation.
- the deviation of the set value is corrected at the initial setting, and the GT is at the steady operation. This is to enable long-term operation of the gas turbine by automatically correcting the deviation of the set value due to deterioration.
- the set value changing step S30 is a step of changing the set values of the combustion parameter PM and the combustion load variable CLP when the origin shift occurs in the combustion margin confirmation step S20.
- the set value changing step S30 is executed before the combustion margin confirmation step S20 is executed and the combustion load variable correction step S40 is executed.
- the set value changing step S30 is a step of changing the set value of the combustion load variable CLP of the combustion parameter PM when the origin shift occurs in the combustion margin confirmation step S20.
- the set value changing step S30 is the result of the combustion margin confirmation step S20 for the combustion parameter PM that determines the set value of the combustion parameter PM (pilot ratio PL, top hat ratio TH, bypass valve opening BV) for the combustion load variable CLP.
- This is a step of automatically correcting the combustion parameter PM when the origin shift occurs. Specifically, for each combustion parameter PM, if the origin shift occurs for each combustion parameter PM before the combustion margin confirmation, the set value of the combustion parameter PM for the predetermined combustion load variable CLP is changed to the set value described later. It means that the position of the origin OP is changed according to the method and the set value ST of the combustion load variable CLP of the combustion parameter PM is corrected.
- the appropriate set value ST of the combustion parameter PM for the combustion load variable CLP is selected, and the generation of combustion vibration is generated. It is possible to set the combustion parameter PM that can be suppressed.
- FIG. 14 is a diagram showing an example of changing the set value ST of the pilot ratio PL in the combustion parameter PM as an example of the set value changing method.
- the horizontal axis shows the combustion load variable CLP, and the vertical axis shows the pilot ratio PL (%).
- the combustion margin confirmation step S20 the combustion load variable CLP corresponding to the predetermined GT load is selected, and the combustion margin range is confirmed.
- the position of the origin OP before executing the combustion margin confirmation step S20 is indicated by a point P1, and as a result of the combustion margin confirmation step S20, the origin shift indicated by the arrow occurs and the origin OP moves.
- the position of the new origin NOP is indicated by the point P2. That is, in FIG. 14, the point P1 indicating the position of the origin OP is indicated by the position where the combustion load variable CLP is X1 (%) and the pilot ratio PL is Y1 (%), and the point P2 which is the new origin NOP is combustion.
- the load variable CLP is shown at the position of X2 (%) and the pilot ratio PL is shown at the position of Y2 (%).
- the points P3 and P4 are adjacent to the points P1 and indicate the points P3 on the side where the combustion load variable CLP increases and the points P4 on the side where the combustion load variable CLP decreases.
- the positions indicated by points P1 to P4 and the like indicate positions corresponding to the GT load selected in the GT load setting step S22 in the combustion margin confirmation step S20 shown in FIG.
- the origin shift did not occur at the positions of the points P3 and P4, and the origin shift occurred in the vicinity of the position of the point P1 sandwiched between the points P3 and P4. This is an example.
- the line segment passing through the points P3 and the points P1 and P4 showing the relationship between the pilot ratio PL immediately before the origin shift occurs at the point P1 and the combustion load variable CLP is shown by a broken line.
- the relationship between the pilot ratio PL and the combustion load variable CLP when the origin OP is changed to the new origin NOP due to the occurrence of origin shift at the point P1 is shown by a solid line passing through the points P3, P2, and P4.
- the position of the point P11 where the line segment P1P4 shown by the broken line intersects the vertical axis passing through X2 of the combustion load variable CLP is such that the initial origin OP is along the line segment P1P4 from the origin OP due to the occurrence of the origin shift.
- the point P1 where the combustion load variable CLP is X1 (%) and the pilot ratio PL is Y1 (%), which is the position of the origin OP before confirming the combustion margin is the origin set value that was the initial target. rice field.
- the position of the point P11 may be considered as an example in which the combustion margin confirmation is executed as the position of the origin during actual operation.
- the combustion margin is confirmed at the position of the point P11 which is the origin during operation, it can be regarded as an example in which the origin position is moved to the position of the point P2 which is the origin movement width WST.
- the setting value change step when the origin shift occurs by setting the point P11 at the position closest to the origin P1, which is the initial origin position, which was the initial target, as the origin during operation and executing the combustion margin confirmation step S20.
- the combustion load variable CLP closest to the initial origin set value is set as the origin during operation, and the combustion margin confirmation step S20 is executed.
- the set value ST of the initial origin OP may be changed to the set value ST of the new origin NOP.
- combustion margin confirmation step S20 when the origin shift occurs at the origin P1 (pilot ratio PL is Y1 (%), combustion load variable CLP is X1 (%)), the position of the new origin NOP after movement is By selecting the position of the combustion load variable CLP “X2” and the origin movement width WST of the pilot ratio PL from the result of the combustion margin confirmation step S20, the position of the point P2 in FIG. 14 can be determined. By this procedure, when the origin shift occurs, it is possible to change the set value to change the position of the point P1 which is the origin OP to the position of the point P2 which is the new origin NOP.
- the combustion adjustment method for a gas turbine according to the first aspect is a combustion adjustment method applied to combustion control of a combustor, and includes a step of selecting a combustion parameter for setting a combustion-air ratio with respect to a load of the gas turbine. From the position of the origin, a first step consisting of a first raising command step, which is a raising command step for raising the command value of the combustion parameter, or a first lowering command step, which is a lowering command step for lowering the command value, is executed.
- a first raising command step which is a raising command step for raising the command value of the combustion parameter
- a first lowering command step which is a lowering command step for lowering the command value
- the first step is terminated and the command value of the combustion parameter is set.
- the step of returning to the position of the origin and the second lowering command process which is the lowering command step of lowering the command value in the direction opposite to the first step from the position of the origin, or the raising command of raising the command value.
- the step of executing the second step consisting of the second raising command step, which is a step, and the command value of the second step without generating combustion vibration are the target wealth lower limit value or the target wealth.
- the combustion margin range of the combustion parameter is confirmed, including the step of ending the second step and returning the command value of the second step of the combustion parameter to the position of the origin. Includes a combustion margin confirmation step.
- the combustion margin range in the direction of increasing and decreasing the command value of the combustion parameter can be confirmed in advance based on the origin position, so that the combustion vibration Stable combustion control of the gas turbine becomes possible without generating the gas turbine, and the reliability of the gas turbine is improved.
- the gas turbine combustion adjusting method according to the second aspect is the gas turbine combustion adjusting method of (1), and is a step of confirming the combustion margin range of the first combustion parameter of the combustion parameter.
- the origin, the command value, the target wealth upper limit value, and the target wealth lower limit value of the first combustion parameter are the first origin, the first command value, the first target wealth upper limit value, and the first target. It is the lower limit of the margin.
- the combustion adjustment method of the gas turbine described in (2) above it is possible to prioritize and confirm the margin range of the combustion vibration of the combustion parameter having a high priority, so that the work of confirming the margin of the combustion vibration is shortened.
- the start-up time of the gas turbine can be shortened.
- the method for adjusting the combustion of the gas turbine according to the third aspect is the method for adjusting the combustion of the gas turbine according to (2), in which the combustion margin confirmation step is the combustion of the second combustion parameter of the combustion parameter. It is a step of confirming the margin range, and the origin, the command value, the target wealth upper limit value, and the target wealth lower limit value of the second combustion parameter are the second origin, the second command value, and the second target. It is the upper limit of the margin and the lower limit of the second target.
- the method for adjusting the combustion of the gas turbine according to the fourth aspect is the method for adjusting the combustion of the gas turbine according to (3), in which the combustion margin confirmation step is the combustion of the third combustion parameter of the combustion parameter. It is a step of confirming the margin range, and the origin, the command value, the target wealth upper limit value, and the target wealth lower limit value of the third combustion parameter are the third origin, the third command value, and the third target. It is the upper limit of the margin and the lower limit of the third target.
- the method for adjusting the combustion of the gas turbine according to the fifth aspect is the method for adjusting the combustion of any one of the gas turbines (1) to (4), and the combustion margin of the acquired combustion parameter.
- the maximum load correction step that corrects the set value so that the combustion load variable with respect to the planned maximum output becomes the rated value for the set value of the combustion load variable whose range has been confirmed, and the combustion parameter and the gas turbine inlet temperature.
- the combustion load variable correction step including the set value conversion step of converting the set value of the combustion load variable calculated in the maximum load correction step while maintaining the relationship is further included.
- the combustion adjustment range of the combustion parameter is confirmed, the set value of the combustion parameter is corrected, and the appropriate relationship between the combustion parameter and the combustion load variable is set. Therefore, proper combustion control of the combustor becomes possible.
- the method for adjusting the combustion of the gas turbine according to the sixth aspect is the method for adjusting the combustion of the gas turbine according to any one of (1) to (5), and the combustion margin confirmation step is the gas turbine. It is executed corresponding to the combustion load variable indicating the load of.
- the method for adjusting the combustion of the gas turbine according to the seventh aspect is the method for adjusting the combustion of the gas turbine according to any one of (1) to (6), and the combustion load variable indicating the load of the gas turbine is used.
- the step of selecting the priority of the combustion parameter and the priority of the change pattern of the command value of the combustion parameter is included.
- the priority of the combustion parameter and the priority of the change pattern of the command value of the combustion parameter can be selected corresponding to the combustion load variable. Since it is possible to preferentially confirm the combustion margin of the combustion parameter in which combustion vibration is likely to occur, the relapse of the combustion margin confirmation is reduced and the combustion margin confirmation work is shortened.
- the gas turbine combustion adjusting method according to the eighth aspect is the combustion adjusting method for any one of the gas turbines (1) to (7), and the first step or the second step is completed. After that, when the command value is returned to the position of the origin, the command value is lowered or raised at the first predetermined rate.
- the gas turbine can be returned to the origin position at the first predetermined rate after the raising command step or the lowering command step of the first step or the second step is completed. , The combustion margin confirmation process is shortened.
- the method for adjusting the combustion of the gas turbine according to the ninth aspect is the method for adjusting the combustion of the gas turbine according to any one of (1) to (8), and is the first step or the second step.
- the step of raising or lowering the command value along the stepped stage from the position of the origin and the stage after the command value is raised or lowered by one stage by the raising command step or the lowering commanding step.
- the generation of combustion vibration is accompanied by a time delay with respect to the command value. Therefore, in each stage, after reaching a predetermined set value, the first holding is performed. By maintaining the time, it is possible to reliably determine the presence or absence of combustion vibration at the corresponding command value, and the command value is raised or lowered while checking the presence or absence of combustion vibration, so the combustion parameters are more reliable. The combustion vibration range of can be confirmed.
- the method for adjusting the combustion of the gas turbine according to the tenth aspect is the method for adjusting the combustion of the gas turbine according to (9), which is the raising command step or the lowering command step of the first step or the second step. However, when the command value is raised or lowered by one stage, the step of raising or lowering the command value at a second predetermined rate is included.
- the gas turbine combustion adjusting method according to the eleventh aspect is the gas turbine combustion adjusting method according to any one of (9) and (10), and the raising of the first step or the second step.
- the command process or the lower command process maintains the command value at the stage where the command value reaches the target tolerance upper limit value or the target wealth lower limit value, and the command value is maintained at the stage without causing combustion vibration.
- the step of maintaining the second holding time from the time when the first holding time has elapsed in the command value and collecting steady data is included.
- the gas turbine combustion adjusting method is the combustion adjusting method for any one of the gas turbines (1) to (10), and the combustion margin confirmation step is the first.
- the step of raising the command if combustion vibration occurs before the command value of the combustion parameter reaches the target tolerance upper limit value, or the command value of the combustion parameter is the target tolerance upper limit value. If combustion vibration occurs after reaching the stage and before reaching the first holding time in the command value, the command value of the stage immediately before the occurrence of combustion vibration is set as the actual wealth upper limit value, and the command value is set. From the position of the origin in the step of returning to the position of the origin and ending the first step and in the lowering command step of the second step in the direction opposite to the raising command step of the first step.
- the difference between the number of stages up to the target tolerance upper limit value in the raising command process in the first step and the number of stages between the position of the origin and the actual wealth upper limit value is calculated, and the difference in the number of stages is calculated.
- the difference of the command value corresponding to the difference of the number of stages of the first step is added in the direction of lowering the command value of the second step with respect to the target tolerance lower limit value of the lowering command step.
- the step of setting the actual wealth lower limit value and the command value of the combustion parameter are lowered from the position of the origin of the lowering command step of the second step to the actual wealth lower limit value without causing combustion vibration.
- the gas turbine combustion adjusting method according to the thirteenth aspect is the combustion adjusting method for any one of the gas turbines (1) to (10), and the combustion margin confirmation step is the first.
- the lowering command step of the step when combustion vibration occurs before the command value of the combustion parameter reaches the target tolerance lower limit value, or the command value of the combustion parameter is the target tolerance lower limit value. If combustion vibration occurs after reaching the stage and before reaching the first holding time in the command value, the command value of the stage immediately before the occurrence of the combustion vibration is set as the lower limit value of the actual wealth, and the command value is set.
- the command value of the combustion parameter is raised from the position of the origin to the actual upper limit of the margin without causing combustion vibration.
- the position of the origin is set to the direction of raising the command value.
- the upper limit of the actual margin which is the upper limit where combustion vibration does not occur in the direction of moving to the position and raising the command value from the position of the new origin
- the lower limit which is the lower limit where the combustion vibration does not occur in the direction of lowering the command value. Since the new origin is set at a position in the middle of the target tolerance without changing the target tolerance between the lower limit and the lower limit, a stable operating range in which combustion vibration does not occur can be secured.
- the method for adjusting the combustion of the gas turbine according to the fourteenth aspect is the method for adjusting the combustion of any one of the gas turbines (9) to (10), and the combustion margin confirmation step is the origin. From the position, the raising command step or the lowering command step of the first step is executed, and combustion vibration occurs before the command value of the stage reaches the target tolerance upper limit value or the target wealth lower limit value. In the case, or when the combustion vibration occurs before the first holding time is reached after the command value of the stage reaches the target tolerance upper limit value or the target tolerance lower limit value, immediately before the combustion vibration occurs.
- the command value of the stage is set to the actual wealth upper limit value or the actual wealth lower limit value
- the actual wealth upper limit value or the actual wealth lower limit value is set to the first set value of the first step
- the lowering commanding step or the raising commanding step of the second step is executed in the direction opposite to the raising commanding step or the lowering commanding step of the first step, and the command value of the stage is set.
- the command value of the stage immediately before the combustion vibration occurs is set to the actual wealth lower limit value or the actual wealth upper limit value of the second step.
- the actual wealth upper limit value or the actual wealth lower limit value of the second step is set as the second set value of the second step, and the position of the midpoint between the first set value and the second set value. Includes a step to set to the new origin.
- the actual wealth upper limit value or the actual wealth lower limit value which is the upper limit or the lower limit in which the combustion vibration of the raising command process or the lowering command process of the first step does not occur.
- the position of the origin is moved to an intermediate position between the lower limit or the upper limit of the actual wealth, which is the lower limit or the upper limit of the combustion vibration in the lower command process or the upper command process of the second step. Since the point is set as the new origin, a stable operating range in which combustion vibration does not occur can be secured even when combustion vibration occurs on both sides of the raising command process and the lowering command process of the first step and the second step.
- the gas turbine combustion adjusting method is the combustion adjusting method for any one of (12) to (14), and the combustion margin confirmation step is the first.
- combustion vibration is generated in the step or the raising command step or the lowering commanding step of the second step, and the position of the origin is moved to select the position of the new origin, the command value at which the combustion vibration is generated is selected. It includes a step of collecting steady data by maintaining a second holding time from the time when combustion vibration occurs at the command value which is lowered by one step or raised by one step.
- the gas turbine combustion adjusting method according to the sixteenth aspect is the combustion adjusting method for any one of (12) to (15), and is the combustion closest to the initial set value of the origin.
- the load variable is set as the origin during operation and the combustion margin confirmation step is executed, the set value of the initial origin is changed, and the new origin is set, the set value of the initial origin is set. Includes a set value changing step of changing to the set value of the new origin.
- the set value of the origin and the set value of the combustion load variable are changed by changing the set value of the origin. Since an appropriate relationship is selected, it is possible to select combustion parameters that can suppress the occurrence of combustion vibration.
- the gas turbine combustion adjusting method is the gas turbine combustion adjusting method of (5), and the maximum load correction step is proportional to the deviation between the turbine output and the planned maximum output.
- Elapsed time after the step of integrating to calculate the intermediate correction value, adding a predetermined value to the intermediate correction value to calculate the second correction value, and the deviation from the start of execution of the combustion load variable correction step.
- a step in which the first correction coefficient is updated to the first correction value based on the combustion load variable correction command.
- the gas turbine combustion adjusting method according to the eighteenth aspect is the gas turbine combustion adjusting method of (17), and in the maximum load correction step, the second correction coefficient is set to the second correction value. Includes additional steps to be updated.
- the combustion adjustment method of the gas turbine described in (18) above in addition to the initial setting at the start of the trial run and after the regular inspection, the deviation of the set value due to the GT deterioration during the steady operation is corrected, and the gas turbine is corrected. Long-term operation is possible.
- the gas turbine combustion adjusting method according to the nineteenth aspect is the gas turbine combustion adjusting method according to any one of (17) and (18), and the set value conversion step is the first correction coefficient.
- the gas turbine inlet temperature is corrected based on the above.
- the gas turbine inlet temperature is corrected based on the first correction coefficient, so that an appropriate relationship between the combustion parameter and the gas turbine inlet temperature is maintained.
- the combustion control device for the gas turbine according to the twentieth aspect includes a control unit that controls the operating state of the gas turbine, an automatic combustion adjustment unit that controls combustion vibration, and combustion that does not generate combustion vibration with respect to the gas turbine load. It includes a combustion margin adjusting unit that determines a combustion margin range of parameters and transmits it to the automatic combustion adjusting unit.
- the combustion margin adjusting unit is capable of selecting the combustion margin range in which combustion vibration does not occur, the combustion adjusting work is automated and the burden on the worker is increased. Is reduced.
- the combustion control device for the gas turbine shown in the 21st aspect is the combustion control device for the gas turbine according to (20), and the combustion margin adjusting unit burns combustion parameters according to the gas turbine load.
- a new origin is set in the combustion margin confirmation unit that confirms the margin range, the combustion load variable correction unit that corrects the combustion load variable for the combustion parameter and sets a new set value, and the combustion margin confirmation unit. If so, it includes a set value changing unit that corrects the relationship between the combustion parameter and the combustion load variable based on the new origin.
- the combustion control device for the gas turbine shown in the 22nd aspect is the combustion control device for the gas turbine according to (21), and in the combustion load variable correction unit, the combustion load variable with respect to the planned maximum output is a rated value.
- the first correction coefficient is provided so as to correct the combustion load variable so that the deviation between the gas turbine output and the planned maximum output is within the permissible value.
- Based on the first correction coefficient so as to maintain the relationship between the combustion parameter and the gas turbine inlet temperature based on the maximum load correction unit that is updated to the value and corrects the combustion load variable and the corrected combustion load variable. Includes a set value converter that corrects the gas turbine inlet temperature.
- the gas turbine combustion control device shown in the 23rd aspect is the gas turbine combustion control device of (22), and the maximum load correction unit determines the deviation between the turbine output and the planned maximum output.
- the correction command unit that detects that the deviation between the turbine output and the planned maximum output is within the allowable value, and issues a combustion load variable correction command, and the correction command unit.
- the switch that is opened based on the transmitted combustion load variable correction command, the second correction value that is output from the adder and is stored as the first correction value via the switch, and the first correction value.
- the first maximum load multiplier having the first correction coefficient that takes in the first correction value output from the data storage and updates the first correction value, and the addition. It includes a second maximum load multiplier having a second correction coefficient that takes in the second correction value from the device and updates it to the second correction value.
- the combustion margin confirmation work is streamlined and the combustion adjustment work is facilitated without depending on the skill of the operator.
- the reliability of the gas turbine is improved.
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Abstract
Description
本願は、2020年10月28日に、日本国に出願された特願2020-180324号に基づき優先権を主張し、この内容をここに援用する。
本開示は、上記課題を解決するため、ガスタービンの試運転開始時または定検終了後の運転再開時の前作業として、燃焼器の燃空比に対する燃焼裕度範囲を確認する燃焼調整方法及び燃焼制御装置を提供することを目的とする。
ガスタービンの負荷に対する燃空比を設定する燃焼パラメータを選定するステップと、原点の位置から、前記燃焼パラメータの指令値を上昇させる上げ指令工程である第1上げ指令工程又は前記指令値を下降させる下げ指令工程である第1下げ指令工程からなる第1工程を実行するステップと、前記燃焼器が燃焼振動を発生することなく前記指令値が目標裕度上限値又は目標裕度下限値に達したら、前記第1工程を終了して、前記燃焼パラメータの前記指令値を前記原点の位置に戻すステップと、前記原点の位置から前記第1工程とは反対方向に前記指令値を下降させる前記下げ指令工程である第2下げ指令工程又は前記指令値を上昇させる前記上げ指令工程である第2上げ指令工程からなる第2工程を実行するステップと、前記燃焼器が燃焼振動を発生することなく前記第2工程の前記指令値が前記目標裕度下限値又は前記目標裕度上限値に達したら、前記第2工程を終了して、前記燃焼パラメータの前記第2工程の前記指令値を前記原点の位置に戻すステップと、を含む、前記燃焼パラメータの燃焼裕度範囲を確認する燃焼裕度確認工程を含む。
ガスタービンの概略装置構成を図1に示す。ガスタービン1は、入口案内翼11を備え、外部から大気空気を取り込み、圧縮空気を生成する圧縮機2と、生成された圧縮空気と別途供給された燃料FLを燃焼させ、燃焼ガスFGを生成する燃焼器3と、生成された燃焼ガスFGにより回転駆動するタービン4と、タービン4に連結して回転駆動され、電力を生成する発電機5と、ガスタービン1を制御する燃焼制御装置100と、を備える。
図2は、本実施形態におけるガスタービン1の燃焼制御装置100の概略構成を示す。燃焼制御装置100は、ガスタービン1に設置されるプロセス計測部101、圧力変化測定部102、加速度測定部103、NOx測定部104、弁操作部105、周波数解析部123及び制御部110を備える。
プロセス計測部101は、ガスタービン1の運転条件や運転状態を示すプロセス量を計測する各種計測機器であり、所定時間毎に、計測結果が燃焼制御装置100の制御部110へ送信される。プロセス量とは、例えば、タービン出力、大気温度、湿度、各部の燃料流量及び燃料圧力、各部の空気流量及び空気圧力、燃焼ガス温度、燃焼ガス圧力、圧縮機2及びタービン4の回転数、タービン4から排出される排ガス中の窒素酸化物(NOx)及び一酸化炭素(CO)等の廃棄物濃度等を意味する。
図2に示す自動燃焼調整部120は、入力部121、運転状態把握部122、燃焼特性把握部124、補正部125及び出力部126を含んで構成されている。自動燃焼調整部120は、燃焼器3で燃焼振動が発生した際に、燃焼振動を抑制する最も効果的な方向で各プロセス量を選定する制御を行なう。
燃焼裕度調整部130は、過去の運転条件のデータ蓄積量が少ないガスタービンの試運転の開始前に、事前に燃焼振動が発生しない領域を把握し、そのデータを自動燃焼調整部120に送信し、自動燃焼調整部120内のデータベース127に蓄積する。燃焼裕度調整部130は、ガスタービン1の試運転又は定検終了後の起動時に、蓄積されたデータを反映させた自動燃焼調整部120のデータを利用して、燃焼振動を発生させることなく定格運転に移行できる運転条件を準備し、ガスタービンが短時間に定格運転に移行できる状態を実現することを目的としている。
次に、各燃焼パラメータPMに共通する燃焼裕度確認方法の考え方及び燃焼裕度パターンについて説明する。なお、以下の説明において、燃焼裕度範囲の確認とは、各燃焼パラメータPMについて、燃焼器3内において、燃焼振動が発生しない範囲及び幅を確認することを意味するが、燃焼裕度確認として簡略表示する場合もある。燃焼振動が発生しないとは、燃焼器3内の燃焼振動が許容レベル以内に抑制できている状態を意味し、燃焼振動が発生するとは、燃焼振動が許容レベルを越えている状態を意味する。
燃焼裕度範囲を確認する対象となる燃焼パラメータPMは、パイロット比PL、トップハット比TH及びバイパス弁開度BVである。パイロット比PLは、全燃料流量FLに対するパイロットノズル33に供給される燃料配分比率をパーセント(%)で表示したものである。トップハット比THは、全燃料流量FLに対するトップハットノズル32に供給される燃料配分比率をパーセント(%)で表示したものである。バイパス弁開度BVは、バイパス弁44の全開時に対する弁開度BVをパーセント(%)で表示したものである。燃焼器3内における燃焼振動の発生の有無は、所定のGT負荷に対するパイロット比PL、トップハット比TH及びバイパス弁開度BVの設定値STに依存する。なお、燃焼パラメータPMとして、燃焼器3の燃焼状態に影響を与える他のパラメータを選択してもよい。
燃焼裕度調整部130では、上述の全ての燃焼パラメータPMについて、後述する燃焼裕度範囲を確認する燃焼裕度確認工程S20(図8、図9)を実行する。燃焼パラメータPMの優先順位は、燃焼裕度範囲の確認を短時間に終了させるため、燃焼振動が発生し易い燃焼パラメータPMの燃焼裕度確認工程S20を優先的に実行することが望ましい。燃焼振動の発生しない範囲とは、燃焼負荷変数CLPに対する燃焼振動のレベルが許容レベル以内にあることを意味し、許容レベル以内の上限のGT負荷の運転点と下限のGT負荷の運転点との間のGT負荷の範囲を意味する。例えば、燃焼パラメータPMとして、トップハット比THについて燃焼裕度確認工程S20が終了後、パイロット比PLについて燃焼裕度確認工程S20を実行している途中で燃焼振動が発生した場合は、改めてトップハット比THについて、再度、燃焼裕度確認工程S20を実行する必要がある。つまり、燃焼裕度確認工程S20の繰り返し作業が発生し、燃焼パラメータPMの燃焼裕度範囲の確認に長時間を要することになる。従って、ガスタービン1の試運転時又は定検終了後の運転開始時において、燃焼パラメータPMの優先順位の選定は、ガスタービン起動時の試運転工程に影響するため、慎重な選定が必要になる。
GT負荷により、燃焼器3内に発生する燃焼振動の周波数帯、発生位置等が異なるため、燃焼裕度確認作業時におけるGT負荷は、0%から定格値(100%)までの範囲で選定する。GT負荷の定格値(100%)とは、ガスタービンの計画最大負荷(計画最大出力)又は定格負荷(定格出力)を意味する。
以下では、燃焼裕度確認工程S20における各燃焼パラメータの燃焼裕度範囲の確認を目的としたいくつかの変更パターン及びその優先度について説明する。
図4に燃焼裕度確認パターンの一例を示す。燃焼裕度確認工程S20では、燃焼パラメータPMの出力を示す指令値CMを上昇させる方向の上げ指令工程STUと、指令値CMを下降させる方向の下げ指令工程STDの両側の工程で、燃焼振動の発生の有無を確認する必要がある。両側の工程の燃焼裕度範囲の確認を終えて、所定のGT負荷における燃焼振動の発生の有無及び燃焼裕度幅が確認される。なお、所定のGT負荷において、上げ指令工程STUを優先させるか又は下げ指令工程STDを優先させるかは、燃焼パラメータPMによって異なっている。上げ指令工程STU及び下げ指令工程STDのそれぞれの工程が終了後、それぞれの工程における定常データ128が採取される。なお、燃焼裕度確認工程S20は、上げ指令工程STU及び下げ指令工程STDの2工程を終えて、対象となる燃焼パラメータPMの裕度確認の1サイクル作業が終了する。前半の第1工程PR1において、上げ指令工程STUを選択し、後半の第2工程において下げ指令工程STDを選択するか、又はその逆の順番にするかの選択は、燃焼器の特性又は燃焼状態により決定される。
図4は、第1燃焼裕度確認パターンの例である。所定のGT負荷における一つの燃焼パラメータPMについて、燃焼パラメータPMの指令値CMが目標裕度上限値TMUL又は目標裕度下限値TMLLの範囲内において、燃焼振動が許容レベル以内に抑えられて燃焼裕度確認工程が終了した例を示している。図5は、第2燃焼裕度確認パターンの例である。同様に、第2燃焼裕度確認パターンは、上げ指令工程STUで、燃焼パラメータPMの指令値CMが目標裕度上限値TMULに達する前に燃焼振動が許容レベルを越え、燃焼振動が発生した例である。図6は、第3燃焼裕度確認パターンの例である。同様に、第3燃焼裕度確認パターンは、上げ指令工程STUと下げ指令工程STDの両側の工程で、燃焼パラメータの指令値CMが目標裕度上限値TMUL及び目標裕度下限値TMLLに達する前に燃焼振動が許容レベルを越え、燃焼振動が発生した例である。図7は、第4燃焼裕度確認パターンの例である。第4燃焼裕度確認パターンは、図5に示す第2燃焼裕度確認パターンの変形例であって、下げ指令工程STDで、燃焼パラメータPMの指令値CMが目標裕度下限値TMLLに達する前に燃焼振動が発生した例ある。
図4に示す第1燃焼裕度確認パターンは、第1工程PR1の上げ指令工程STUで目標裕度上限値TMULまで燃焼振動が許容レベル以内に抑えられ、燃焼振動が発生しなかったことを確認できた。更に、次の第2工程PR2の下げ指令工程STDでも、目標裕度下限値TMLLまで燃焼振動が許容レベル以内に抑えられ、燃焼振動が発生しなかったことを確認して、原点OPの位置まで指令値CMを戻して、所定のGT負荷及び所定の原点OPにおける1サイクルの燃焼裕度範囲が確認できた実施形態を示す。ここで、燃焼振動が許容レベル以内に抑えられたとは、所定の設定値STにおいて、一定の保持時間が経過するまで燃焼振動が許容レベル以内に抑えられた状態を意味する。
図5に示す第2燃焼裕度確認パターンは、図4に示す第1燃焼裕度確認パターンとは異なり、第1工程PR1の上げ指令工程STUにおいて、目標裕度上限値TMULで燃焼裕度範囲が確認出来なかった場合の例を示している。すなわち、上げ指令工程STUにおいて、指令値CMが目標裕度上限値TMULに達した後、保持時間T1が経過する前に燃焼振動が発生した場合を示している。目標裕度上限値TMULである指令値CMにおいて、保持時間T1を維持できずに燃焼振動が発生した場合は、燃焼振動が発生したステージSの直前の1ステージ下げたステージSの指令値CMを、上げ指令工程STUの実裕度上限値AMULとして設定する。
図6に示す第3燃焼裕度確認パターンは、図5に示す第2燃焼裕度確認パターンと同様に、第1工程PR1は、上げ指令工程STUが優先されている。但し、上げ指令工程STUと下げ指令工程STDの両側の工程において、燃焼振動が発生した実施態様である点で、図5に示す第2燃焼裕度確認パターンとは異なる例である。また、第3燃焼裕度確認パターンは、実裕度上限値AMULと実裕度下限値AMLLとの間の合計ステージ数が、初期設定時の目標裕度上限値TMULと目標裕度下限値TMLLの間の合計ステージ数に達せず、未達のステージ数を残したまま燃焼裕度範囲の確認を終了する態様である点で、第1燃焼裕度確認パターン及び第2燃焼裕度確認パターンとは異なる態様である。
図7に示す第4燃焼裕度確認パターンは、図5に示す第2燃焼裕度確認パターンに対して、第1工程PR1と第2工程PR2を入れ替えた変形例である。すなわち、図7に示す第4燃焼裕度確認パターンは、第1工程PR1において、下げ指令工程STDが上げ指令工程STUに優先して実行される点で、図5に示す第2燃焼裕度確認パターンとは若干異なっている。第4燃焼裕度確認パターンを示す本実施態様は、下げ指令工程STDで燃焼振動が発生し、燃焼裕度範囲の確認が出来ない未達のステージ数を残して、第1工程PR1の下げ指令工程STDを終了している。更に、第2工程PR2の上げ指令工程STUにおいて、目標裕度上限値TMULに未達のステージSを加算して燃焼裕度範囲の確認を実行し、燃焼裕度確認工程S20を終了した例である。上げ指令工程STUと下げ指令工程STDの優先順位の違いを除く他の手順は、図5に示す第2燃焼裕度確認パターンと同様である。このパターンでは、第1工程PR1の下げ指令工程STDにおいて、燃焼振動が発生するステージSの直前のステージSの指令値CMを実裕度下限値AMLLに設定し、第2工程PR2の上げ指令工程STUでは、目標裕度上限値TMULに対し未達のステージ数を加算したステージSの指令値CMを実裕度上限値AMULに設定している。このパターンで確認された燃焼裕度の範囲(実裕度上限値AMULと実裕度下限値AMLLの幅)は、初期設定時の目標裕度幅TMWと同じである。
上述のような種々の燃焼裕度確認パターンを前提に、ガスタービンの燃焼調整の全体工程の流れについて、以下に説明する。上述のように、燃焼裕度範囲の確認は、GT負荷が無負荷(0(%))から定格負荷(GT負荷100%)の範囲内で、定格負荷を含めて複数のGT負荷を選定して行う。その際、燃焼裕度範囲の確認は、燃焼振動の発生のし易さ等を考慮して、燃焼裕度範囲の確認の開始時のGT負荷を最小負荷として、GT負荷を上げていくGT負荷上げ方向、又はGT負荷を最大負荷として、GT負荷を下げていくGT負荷下げ方向のいずれかを優先的に選定する。図8は、GT負荷を上げる方向の燃焼調整全体工程を示したフロー図である。但し、図8に示す全体工程のフローは、一例であって、このフローの例に限定されない。例えば、図8の例は、燃焼裕度確認工程S20の後で燃焼負荷変数補正工程S40が実行されるが、燃焼裕度確認工程S20の前に燃焼負荷変数補正工程S40を実行してもよい。
燃焼調整に係る設定値入力工程S10では、GT負荷範囲、燃焼パラメータPMの優先順位、燃焼パラメータPMの燃焼負荷変数CLPの設定値、目標裕度幅TMW、指令値CMの投入レートBIR、各ステージSにおける保持時間T1、定常データ128の採取に必要な保持時間T2、原点復帰時の解除レートBRR、ステージ幅SW、ステージ数SNが、入力部121に入力され、燃焼裕度確認工程S20に送信される。燃焼裕度確認工程S20は、上述のように、燃焼パラメータPMの指令値CMを階段状にステージSに沿って変更させつつ燃焼裕度範囲の確認を行うバイアス投入方式を採用している。図4から図7に示すように、燃焼パラメータPMの目標裕度幅TMWは、原点OPを中心に上げ指令工程STUと下げ指令工程STDを同一のステージ幅SWで区分けし、それぞれの工程について、同一のステージ幅SW及びステージ数SN並びにステージ間の投入レートBIRを入力データとして付与している。なお、上げ指令工程STUにおける各ステージSのステージ幅SWと下げ指令工程STDにおける各ステージSのステージ幅SWは、上げ指令工程STUと下げ指令工程STDとでは、同一の幅であっても良いし、異なる幅であってもよい。
図9は、燃焼パラメータPMの燃焼裕度確認工程S20のフローを示す。図9に示す燃焼裕度確認工程S20に基づき、燃焼裕度範囲の確認の処理が開始する。燃焼裕度確認工程S20では、まず燃焼裕度範囲の確認を行う燃焼パラメータPMの優先順位を設定する。入力部121で入力された燃焼パラメータPMの優先順位に基づき、燃焼裕度範囲の確認を実行する燃焼パラメータPMの優先順位を設定し、第1優先順位の燃焼パラメータPMをPM1とし、第2優先順位の燃焼パラメータPMをPM2とし、第3優先順位の燃焼パラメータPMをPM3として割り当てる(S21)。
この実施態様の場合、第1燃焼パラメータPM1の原点ずらしが発生したため、第1燃焼パラメータPM1の原点OP1の位置は新原点NOP1に移動する。第1燃焼パラメータPM1の採取されたガスタービン1の定常データ128及び新原点NOP1の位置データは、データベース127に送信される(S24)。
図8に示すように、燃焼負荷変数補正工程S40は、ガスタービン1が、燃焼負荷変数CLPの定格値(100%)において計画最大出力MOPが出るように、燃焼パラメータPMと燃焼負荷変数CLPの関係を示す設定値STを適正化するために必要な補正を行う工程である。すなわち、燃焼負荷変数補正工程S40は、ガスタービン入口温度GTITと燃焼パラメータPMとの適正な関係を維持することを前提条件に、ガスタービン1の計画最大出力MOPで燃焼負荷変数CLPが定格値(100%)となるように燃焼負荷変数CLPを補正する最大負荷補正工程S50と、補正後の燃焼負荷変数CLPに基づいて、ガスタービン入口温度GTITと燃焼パラメータPMの関係が維持されるように、燃焼負荷変数CLPの設定値を変換する設定値変換工程S70と、から構成されている。
ここで、計画最大出力MOPとは、計画出力または定格出力時のタービン出力(ガスタービン出力)を言い、無負荷相当出力NOPとは、無負荷時のタービン出力を言う。タービン出力が、計画最大出力MOP又は定格出力の場合は、燃焼負荷変数CLPは定格値(100%)であり、無負荷相当出力NOPの場合は、燃焼負荷変数CLPは、0(%)に相当する。
下記に示す〔式2〕は、〔式1〕に対して、燃焼パラメータPMと燃焼負荷変数CLPの初期設定値のずれを補正するため、燃焼負荷変数補正手段を用いて補正された燃焼負荷変数CLPを算出する式であり、燃焼負荷変数補正工程S40(最大負荷補正工程S50、設定値変換工程S70)の補正手段から構成される。
第1補正係数156a及び第2補正係数157aは、後述する燃焼負荷変数補正工程S40で設定される補正係数である。なお、計画最大出力、無負荷相当出力の考え方は、〔式1〕と同様である。
図8に示すように、設定値変更工程S30は、燃焼裕度確認工程S20において原点ずらしが発生した場合において、燃焼パラメータPMと燃焼負荷変数CLPの設定値の変更を行う工程である。設定値変更工程S30は、燃焼裕度確認工程S20を実行し、燃焼負荷変数補正工程S40を実行する前に実行される。
(1)第1の態様に係るガスタービンの燃焼調整方法は、燃焼器の燃焼制御に適用する燃焼調整方法であって、ガスタービンの負荷に対する燃空比を設定する燃焼パラメータを選定するステップと、原点の位置から、前記燃焼パラメータの指令値を上昇させる上げ指令工程である第1上げ指令工程又は前記指令値を下降させる下げ指令工程である第1下げ指令工程からなる第1工程を実行するステップと、前記燃焼器が燃焼振動を発生することなく前記指令値が目標裕度上限値又は目標裕度下限値に達したら、前記第1工程を終了して、前記燃焼パラメータの前記指令値を前記原点の位置に戻すステップと、前記原点の位置から前記第1工程とは反対方向に前記指令値を下降させる前記下げ指令工程である第2下げ指令工程又は前記指令値を上昇させる前記上げ指令工程である第2上げ指令工程からなる第2工程を実行するステップと、前記燃焼器が燃焼振動を発生することなく前記第2工程の前記指令値が前記目標裕度下限値又は前記目標裕度上限値に達したら、前記第2工程を終了して、前記燃焼パラメータの前記第2工程の前記指令値を前記原点の位置に戻すステップと、を含む、前記燃焼パラメータの燃焼裕度範囲を確認する燃焼裕度確認工程を含む。
2 圧縮機
3 燃焼器
4 タービン
5 発電機
11 入口案内翼
24 尾筒
30 燃焼ノズル
31 メインノズル
32 トップハットノズル
33 パイロットノズル
41 メイン燃料流量制御弁
42 トップハット燃料流量制御弁
43 パイロット燃料流量制御弁
44 バイパス弁
100 燃焼制御装置
101 プロセス計測部
102 圧力変化測定部
103 加速度測定部
104 NOx測定部
110 制御部
121 入力部
122 運転状態把握部
123 周波数解析部
124 燃焼特性把握部
125 補正部
126 出力部
127 データベース
130 燃焼裕度調整部
132 燃焼裕度確認部
134 燃焼負荷変数補正部
134a 最大負荷補正部
134b 設定値変換部
136 設定値変更部
141 関数発生器(計画最大出力)
142 関数発生器(無負荷相当出力)
143、145,150 減算器
144、147 除算器
148、149 乗算器
151 PI演算器
151a 中間補正値
152 加算器
152a 第2補正値
153 信号発生器
154 切替器
154a 第1補正値
155 データ記憶器
156 第1最大負荷乗算器
156a 第1補正係数
157 第2最大負荷乗算器
157a 第2補正係数
160 補正指令部
161 燃焼負荷変数補正指令
PL パイロット比
TH トップハット比
BV バイパス弁開度
CLP 燃焼負荷変数
GTIT ガスタービン入口温度
PM 燃焼パラメータ
PM1 第1燃焼パラメータ
PM2 第2燃焼パラメータ
PM3 第3燃焼パラメータ
S ステージ
SW ステージ幅
CM 指令値
CM1 第1指令値
CM2 第2指令値
CM3 第3指令値
OP 原点
OP1 第1原点
OP2 第2原点
OP3 第3原点
NOP、NOP1、NOP2、NOP3 新原点
WST 原点移動幅
PR1 第1工程
PR2 第2工程
STU 上げ指令工程
STD 下げ指令工程
TMW、TMW1、TMW2、TMW3 目標裕度幅
TMUL 目標裕度上限値
TMLL 目標裕度下限値
AMUL 実裕度上限値
AMLL 実裕度下限値
T1 第1保持時間
T2 第2保持時間
T0 未達時間
BRR 指令値解除レート(第1所定レート)
BIR 指令値投入レート(第2所定レート)
α 所定値
MOP 計画最大負荷(計画最大出力)
NOP 無負荷相当出力
Claims (23)
- 燃焼器の燃焼制御に適用する燃焼調整方法であって、
ガスタービンの負荷に対する燃空比を設定する燃焼パラメータを選定するステップと、
原点の位置から、前記燃焼パラメータの指令値を上昇させる上げ指令工程である第1上げ指令工程又は前記指令値を下降させる下げ指令工程である第1下げ指令工程からなる第1工程を実行するステップと、
前記燃焼器が燃焼振動を発生することなく前記指令値が目標裕度上限値又は目標裕度下限値に達したら、前記第1工程を終了して、前記燃焼パラメータの前記指令値を前記原点の位置に戻すステップと、
前記原点の位置から前記第1工程とは反対方向に前記指令値を下降させる前記下げ指令工程である第2下げ指令工程又は前記指令値を上昇させる前記上げ指令工程である第2上げ指令工程からなる第2工程を実行するステップと、
前記燃焼器が燃焼振動を発生することなく前記第2工程の前記指令値が前記目標裕度下限値又は前記目標裕度上限値に達したら、前記第2工程を終了して、前記燃焼パラメータの前記第2工程の前記指令値を前記原点の位置に戻すステップと、
を含む、
前記燃焼パラメータの燃焼裕度範囲を確認する燃焼裕度確認工程を含む、
ガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記燃焼パラメータの第1燃焼パラメータの前記燃焼裕度範囲を確認する工程であり、
前記第1燃焼パラメータの前記原点及び前記指令値及び前記目標裕度上限値及び前記目標裕度下限値が、第1原点及び第1指令値及び第1目標裕度上限値及び第1目標裕度下限値である、
請求項1に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記燃焼パラメータの第2燃焼パラメータの前記燃焼裕度範囲を確認する工程であり、
前記第2燃焼パラメータの前記原点及び前記指令値及び前記目標裕度上限値及び前記目標裕度下限値が、第2原点及び第2指令値及び第2目標裕度上限値及び第2目標裕度下限値である、
請求項2に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記燃焼パラメータの第3燃焼パラメータの前記燃焼裕度範囲を確認する工程であり、
前記第3燃焼パラメータの前記原点及び前記指令値及び前記目標裕度上限値及び前記目標裕度下限値が、第3原点及び第3指令値及び第3目標裕度上限値及び第3目標裕度下限値である、
請求項3に記載のガスタービンの燃焼調整方法。 - 取得された前記燃焼パラメータの前記燃焼裕度範囲が確認された燃焼負荷変数の設定値に対し、計画最大出力に対する燃焼負荷変数が定格値となるように前記設定値を補正する最大負荷補正工程と、
前記燃焼パラメータとガスタービン入口温度の関係を維持しつつ、前記最大負荷補正工程で演算された前記燃焼負荷変数の前記設定値を変換する設定値変換工程と、
からなる燃焼負荷変数補正工程を更に含む、
請求項1から4のいずれか何れか一項に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、前記ガスタービンの負荷を示す燃焼負荷変数に対応して実行される、
請求項1から5の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記ガスタービンの負荷を示す燃焼負荷変数に対応して、前記燃焼パラメータの優先度及び前記燃焼パラメータの前記指令値の変更パターンの優先度を選定するステップを含む、
請求項1から6の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記第1工程又は前記第2工程が終了した後、前記指令値を前記原点の位置に戻す際、
前記指令値を第1所定レートで下降させ又は上昇させる、
請求項1から7の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記第1工程又は前記第2工程の前記上げ指令工程又は前記下げ指令工程が、
前記原点の位置から階段状のステージに沿って前記指令値を上昇又は下降させるステップと、
前記指令値を1ステージ上昇又は1ステージ下降させた後の前記ステージにおいて、燃焼振動を発生することなく第1保持時間を維持するステップと、
を含む、
請求項1から8の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記第1工程又は前記第2工程の前記上げ指令工程又は前記下げ指令工程が、
前記指令値を1ステージ上昇又は1ステージ下降させる際、第2所定レートで前記指令値を上昇させ又は下降させるステップを含む、
請求項9に記載のガスタービンの燃焼調整方法。 - 前記第1工程又は前記第2工程の前記上げ指令工程又は前記下げ指令工程が、
前記指令値が前記目標裕度上限値又は前記目標裕度下限値に達した前記ステージで前記指令値を維持し、燃焼振動を発生することなく前記ステージで前記第1保持時間に達した場合は、前記指令値において前記第1保持時間を経過した時点から第2保持時間を維持して定常データを採取するステップを含む、
請求項9又は10の何れかに記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記第1工程の前記上げ指令工程において、前記燃焼パラメータの前記指令値が前記目標裕度上限値に達する前に燃焼振動が発生した場合、又は前記燃焼パラメータの前記指令値が前記目標裕度上限値であるステージに達した後、前記指令値において第1保持時間に達する前に燃焼振動が発生した場合、燃焼振動が発生する直前のステージの前記指令値を実裕度上限値に設定し、前記指令値を前記原点の位置に戻して、前記第1工程を終了するステップと、
前記第1工程の前記上げ指令工程とは反対方向の前記第2工程の前記下げ指令工程において、前記原点の位置から前記第1工程の前記上げ指令工程の前記目標裕度上限値までの間のステージ数と前記原点の位置から前記実裕度上限値までの間のステージ数の差分を算出し、前記第2工程の前記下げ指令工程の前記目標裕度下限値に対して前記第2工程の前記指令値を下降させる方向に前記第1工程のステージ数の前記差分に相当する前記指令値の前記差分を加算して実裕度下限値として設定するステップと、
前記第2工程の前記下げ指令工程の前記原点の位置から前記燃焼パラメータの前記指令値を燃焼振動が発生することなく前記実裕度下限値まで前記下げ指令工程を実行するステップと、
前記原点の位置に対して前記第2工程の前記指令値を下降させる方向に前記第1工程のステージ数の前記差分だけ移動させた位置に新原点を設定するステップと、
を含む、
請求項1から10の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記第1工程の前記下げ指令工程において、前記燃焼パラメータの前記指令値が前記目標裕度下限値に達する前に燃焼振動が発生した場合、又は前記燃焼パラメータの前記指令値が前記目標裕度下限値であるステージに達した後、前記指令値において第1保持時間に達する前に燃焼振動が発生した場合、燃焼振動が発生する直前のステージの前記指令値を実裕度下限値に設定し、前記指令値を前記原点の位置に戻し、前記第1工程を終了するステップと、
前記第1工程の前記下げ指令工程とは反対方向の前記第2工程の前記上げ指令工程において、前記原点の位置から前記第1工程の前記下げ指令工程の前記目標裕度下限値までの間のステージ数と前記原点の位置から前記実裕度下限値までの間のステージ数の差分を算出し、前記第2工程の前記上げ指令工程の前記目標裕度上限値に対して前記第2工程の前記指令値を上昇させる方向に前記第1工程のステージ数の前記差分に相当する前記指令値の前記差分を加算して実裕度上限値として設定するステップと、
前記第2工程の前記上げ指令工程において、前記原点の位置から前記燃焼パラメータの前記指令値を燃焼振動が発生することなく前記実裕度上限値まで前記上げ指令工程を実行するステップと、
前記原点の位置に対して前記第2工程の前記指令値を上昇させる方向に前記第1工程のステージ数の前記差分だけ移動させた位置に新原点を設定するステップと、
を含む、
請求項1から10の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記原点の位置から、前記第1工程の前記上げ指令工程又は前記下げ指令工程を実行し、
前記ステージの前記指令値が前記目標裕度上限値又は前記目標裕度下限値に達する前に燃焼振動が発生した場合、又は前記ステージの前記指令値が前記目標裕度上限値又は前記目標裕度下限値に達した後、第1保持時間に達する前に燃焼振動が発生した場合、燃焼振動が発生する直前の前記ステージの前記指令値を実裕度上限値又は実裕度下限値に設定し、前記実裕度上限値又は前記実裕度下限値を前記第1工程の第1設定値に設定し、
前記原点の位置から、前記第1工程の前記上げ指令工程又は前記下げ指令工程とは反対方向に、前記第2工程の前記下げ指令工程又は前記上げ指令工程を実行し、
前記ステージの前記指令値が前記目標裕度下限値又は前記目標裕度上限値に達する前に燃焼振動が発生した場合、又は前記ステージの前記指令値が前記目標裕度下限値又は前記目標裕度上限値に達した後、前記第1保持時間に達する前に燃焼振動が発生した場合、燃焼振動が発生する直前の前記ステージの前記指令値を前記第2工程の実裕度下限値又は実裕度上限値に設定し、前記第2工程の前記実裕度上限値又は前記実裕度下限値を前記第2工程の第2設定値に設定し、
前記第1設定値と前記第2設定値の間の中点の位置を新原点に設定するステップを含む、
請求項9又は10に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
前記第1工程又は前記第2工程の前記上げ指令工程又は前記下げ指令工程において、燃焼振動が発生し、前記原点の位置を移動して前記新原点の位置を選定した場合、燃焼振動が発生した前記指令値より1ステージ下降又は1ステージ上昇した前記指令値において、燃焼振動が発生した時点から第2保持時間を維持して定常データを採取するステップを含む、
請求項12から14の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記燃焼裕度確認工程が、
初期の前記原点の設定値に最も近い燃焼負荷変数を運転時原点に設定して前記燃焼裕度確認工程を実行し、
前記初期の前記原点の前記設定値が変更され、前記新原点を設定した場合、前記初期の前記原点の前記設定値を前記新原点の前記設定値に変更する設定値変更工程を含む、
請求項12から15の何れか一項に記載のガスタービンの燃焼調整方法。 - 前記最大負荷補正工程は、
タービン出力と前記計画最大出力との偏差を比例積分して中間補正値を演算し、前記中間補正値に所定値を加算して第2補正値を演算するステップと、
前記燃焼負荷変数補正工程の実行を開始した後、経過時間が所定時間を経過したら、燃焼負荷変数補正指令を発信するステップと、
前記燃焼負荷変数補正指令に基づき、切替器で前記第2補正値は第1補正値に置き換えられ、前記第2補正値がリセットされるステップと、
前記燃焼負荷変数補正指令に基づき、第1補正係数が前記第1補正値に更新されるステップと、
を含む、
請求項5に記載のガスタービンの燃焼調整方法。 - 前記最大負荷補正工程は、第2補正係数が、前記第2補正値に更新されるステップを更に含む、
請求項17に記載のガスタービンの燃焼調整方法。 - 前記設定値変換工程は、前記第1補正係数に基づき前記ガスタービン入口温度が修正される、
請求項17又は18の何れかに記載のガスタービンの燃焼調整方法。 - ガスタービンの運転状態を制御する制御部と、
燃焼振動を制御する自動燃焼調整部と、
前記ガスタービンの負荷に対する燃焼振動が発生しない燃焼パラメータの燃焼裕度範囲を選定し、前記自動燃焼調整部に送信する燃焼裕度調整部と、
を含む、
ガスタービンの燃焼制御装置。 - 前記燃焼裕度調整部は、
前記ガスタービンの負荷に応じて前記燃焼パラメータの燃焼裕度範囲を確認する燃焼裕度確認部と、
前記燃焼パラメータに対する燃焼負荷変数の設定値を補正して、新設定値を設定する燃焼負荷変数補正部と、
前記燃焼裕度確認部において新原点が設定された場合、前記新原点に基づき、前記燃焼パラメータと前記燃焼負荷変数との関係を補正する設定値変更部と、
を含む、
請求項20に記載のガスタービンの燃焼制御装置。 - 前記燃焼負荷変数補正部は、
計画最大出力に対する燃焼負荷変数が定格値となるように前記燃焼負荷変数を補正する第1補正係数を備え、
前記第1補正係数が、タービン出力と計画最大出力との偏差が出力偏差許容値内に収まるように演算された第1補正値に更新され、前記燃焼負荷変数を補正する最大負荷補正部と、
補正後の前記燃焼負荷変数に基づいて前記燃焼パラメータとガスタービン入口温度の関係を維持するよう前記第1補正係数に基づき前記ガスタービン入口温度を修正する設定値変換部と、
を含む、
請求項21に記載のガスタービンの燃焼制御装置。 - 前記最大負荷補正部は、
前記タービン出力と前記計画最大出力との偏差を演算する減算器と、
前記減算器で演算された前記偏差を比例積分して中間補正値を演算するPI演算器と、
前記PI演算器で演算された前記中間補正値に所定値を加算して第2補正値を演算する加算器と、
前記タービン出力と前記計画最大出力との偏差が許容値内に収まることを検知して燃焼負荷変数補正指令を発する補正指令部と、
前記補正指令部より発信された燃焼負荷変数補正指令に基づき開状態になる切替器と、
前記加算器から出力され、前記切替器を介して前記第2補正値を前記第1補正値として記憶し、前記第1補正値を出力するデータ記憶器と、
前記データ記憶器から出力された前記第1補正値を取り込み、前記第1補正値に更新される第1補正係数を備える第1最大負荷乗算器と、
前記加算器からの前記第2補正値を取り込み、前記第2補正値に更新される第2補正係数を備える第2最大負荷乗算器と、
を含む、
請求項22に記載のガスタービンの燃焼制御装置。
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