JP4929029B2 - Gas turbine control method and gas turbine power generator - Google Patents

Description

  The present invention relates to a gas turbine control method and a gas turbine power generator.

The combustor of the gas turbine has a pilot nozzle and a plurality of main nozzles. The main nozzle is divided into a nozzle group A and a nozzle group B as shown in FIG. The number of nozzles constituting the nozzle group A is smaller than the number of nozzles constituting the nozzle group B.
In such a combustor, the nozzle group used for fuel supply is switched according to the load of the gas turbine. For example, Patent Document 1 discloses that the nozzle group is smoothly switched by controlling the amount of fuel supplied to each nozzle group during the nozzle switching period. Specifically, as shown in FIG. 24, when switching from the nozzle group A to the nozzle group B, the fuel supply amount to the nozzle group B is increased, while the nozzle group A is only supplied to the increase amount. Control to reduce the amount of fuel supply. That is, during the nozzle switching period, the fuel supply amount to each nozzle group is adjusted so that the sum of the fuel supply amount to the nozzle group A and the fuel supply amount to the nozzle group B is constant.
JP-A-8-312377

  However, the invention disclosed in Patent Document 1 does not take into account fluctuations in combustion efficiency. Therefore, as shown in FIG. 25, there is a problem that the gas turbine output fluctuates during the nozzle switching period.

  The present invention has been made to solve the above problem, and an object of the present invention is to provide a gas turbine control method and a gas turbine power generation device capable of reducing the output fluctuation of the gas turbine during the nozzle switching period.

In order to solve the above problems, the present invention employs the following means.
The present invention provides a gas turbine having a combustor and a plurality of nozzles different from each other, and a plurality of nozzle groups for supplying fuel gas to the combustor, wherein the nozzle is used for fuel supply according to an operating state. A gas turbine control method for switching a group , wherein a fuel supply amount is gradually increased in the first nozzle group during a nozzle switching period in which the first nozzle group used so far is switched to a second nozzle group to be used. A first fuel supply sharing ratio to be decreased is set in advance, and a second fuel supply sharing ratio for gradually increasing the fuel supply amount is set in advance in the second nozzle group, and in the nozzle switching period, The first fuel supply share ratio and the second fuel supply share ratio are set so that the fuel supply amount supplied to the combustor is larger than the fuel supply amount command value. At least one of them is corrected, and the increase in the fuel supply amount is a deviation between the primary delay of the second fuel supply share ratio and the second fuel supply share ratio or the primary delay of the first fuel supply share ratio. And a control method of the gas turbine determined based on a deviation between the first fuel supply share ratio and the first fuel supply share ratio .

According to such a control method, since the fuel supply amount to the combustor is increased from the fuel supply amount command value in the nozzle switching period, it is possible to suppress a decrease in combustion efficiency in the combustor. As a result, fluctuations in gas turbine output can be reduced.
Further, the increase in the fuel supply amount is determined based on the deviation between the fuel supply sharing ratio of the second nozzle group and its primary delay or the deviation between the fuel supply sharing ratio of the first nozzle group and its primary delay. The fuel supply amount can be increased gradually.

In the gas turbine control method, the first fuel supply share ratio and the second fuel supply share ratio so that an increase in the fuel supply amount is distributed to the first nozzle group and the second nozzle group. May be corrected .
In the gas turbine control method, the increase in the fuel supply amount may be distributed more to the nozzle group having the larger fuel supply share ratio.
In the gas turbine control method, the increase in the fuel supply amount is largely distributed to the first nozzle group in the first half of the nozzle switching period, and the second nozzle group in the second half of the nozzle switching period. It is good also as being distributed to many.

  In the gas turbine control method, the increase in the fuel supply amount may be adjusted according to the operating state of the power plant.

  Thereby, it becomes possible to adjust the fuel increase amount according to the operation state of the gas turbine.

  In the gas turbine control method, the increase in the fuel supply amount may be assigned to the first nozzle group and the second nozzle group at a rate in consideration of combustion efficiency.

  In this way, the fuel increase is shared between the first nozzle group and the second nozzle group, and the ratio of each share is determined in consideration of the combustion efficiency, so that the operating efficiency of the gas turbine is further improved. Is possible.

  In the gas turbine control method, the increase in the fuel supply amount may be determined according to combustion efficiency in the combustor.

  As a result, it is possible to perform fuel supply that compensates for deterioration in combustion efficiency.

  In the gas turbine control method, the combustion efficiency is calculated based on, for example, an air flow rate and a fuel flow rate supplied to the combustor.

  Thus, by obtaining the combustion efficiency by calculation, a sensor or the like for detecting the combustion efficiency can be made unnecessary.

  In the gas turbine control method, the increase in the fuel supply amount may be determined based on a deviation between the output command value of the gas turbine and the output of the gas turbine.

  Thereby, the controllability regarding the gas turbine output can be improved. In addition, since the output of the gas turbine is fed back and used, robust control can be performed with respect to combustion efficiency, plant individual differences, and other variations. Furthermore, it becomes possible to cope with different load change rates and switching load bands.

The present invention includes a combustor and a plurality of nozzle groups each having a different number of main nozzles and supplying fuel gas to the combustor, and the nozzle group used for fuel supply is switched according to the operating state. 1st fuel supply share ratio which is a gas turbine electric power generating apparatus, and is used in the nozzle switching period which switches the 1st nozzle group used until now to the 2nd nozzle group to be used from now on gradually reduces the fuel supply amount And a second supply share ratio for gradually increasing the fuel supply amount, and the fuel supply amount supplied to the combustor during the nozzle switching period is larger than the fuel supply amount command value. A correction unit that corrects at least one of the first fuel supply share ratio and the second fuel supply share ratio, and the correction unit sets the first fuel supply share ratio to When corrected, the corrected first fuel supply share ratio is used, and when the first fuel supply share ratio is not corrected by the correction unit, the stored first fuel supply share ratio is used. A first control unit for setting the fuel supply amount of the first nozzle group, and when the second fuel supply share ratio is corrected by the correction unit, the corrected second fuel supply share ratio is used. A second control unit that sets the fuel supply amount of the second nozzle group using the stored second fuel supply sharing ratio when the second fuel supply sharing ratio is not corrected by the correction unit. The increase in the fuel supply amount is a deviation between the first-order lag of the second fuel supply share ratio and the second fuel supply share ratio or the first-order lag of the first fuel supply share ratio and the first fuel. Based on deviation from supply sharing ratio To provide a gas turbine power generation system to be determined.

  According to the present invention, it is possible to reduce the output fluctuation of the gas turbine during the nozzle switching period.

  Hereinafter, an embodiment of a gas turbine control method and a gas turbine power generator according to the present invention will be described with reference to the drawings.

[First Embodiment]
FIG. 1 is a block diagram showing a schematic configuration of a gas turbine power generator according to a first embodiment of the present invention.
As shown in FIG. 1, the gas turbine power generation device 1 compresses a combustor 2 that combusts gasified fuel, a gas turbine 3 that rotates by expanding the combustion gas supplied from the combustor 2, and air. A compressor 4 and a generator (not shown) connected to the gas turbine 3 are provided as main components.

  As shown in FIG. 23, the combustor 2 is provided with a pilot nozzle 51 and a plurality of main nozzles 52 arranged at intervals on the outer periphery of the pilot nozzle 51. The main nozzle 52 is divided into a nozzle group A and a nozzle group B. The number of main nozzles 52 constituting the nozzle group A is smaller than the number of main nozzles 52 constituting the nozzle group B. In the present embodiment, the nozzle group A has three main nozzles 52, and the nozzle group B has five main nozzles 52.

  The combustor 2 is connected to a first fuel flow path 5 that supplies fuel gas to the nozzle group A and a second fuel flow path 6 that supplies fuel gas to the nozzle group B. The first fuel flow path 5 and the second fuel flow path 6 are respectively provided with a first flow rate adjustment valve 7 and a second flow rate adjustment valve 8 for adjusting the flow rate of the fuel gas. The opening degree of the first flow rate control valve 7 and the second flow rate control valve 8 is controlled by the gas turbine control device 10. Of course, a fuel flow path for supplying fuel gas to the pilot nozzle 51 is also provided, but is omitted here.

  The gas turbine control device 10 controls the opening degree of the first flow rate control valve 7 and the second flow rate control valve 8 described above, and also uses a nozzle group for supplying fuel to the combustor 2 in accordance with the output of the gas turbine. Control to switch between A and B is performed. Details of the control by the gas turbine control device 10 will be described later.

  In such a gas turbine power generation device 1, air compressed from the compressor 4 is supplied to the combustor 2 and fuel gas is supplied from the nozzle groups A and B and the like. The combustor 2 mixes and supplies the supplied compressed air and fuel gas to burn, and supplies a high-temperature and high-pressure combustion gas to the gas turbine 3. Thereby, the gas turbine 3 is rotated by the energy when the combustion gas expands, and the power is transmitted to a generator (not shown) to generate electric power.

Next, fuel flow control in the nozzle switching period in the control by the gas turbine control device 10 will be described with reference to FIG.
FIG. 2 is a diagram illustrating an example of a control block included in the gas turbine control device 10.
As shown in FIG. 2, the gas turbine control device 10 includes a first control unit 11 that sets a first fuel supply command value MACSO, which is a fuel command for the nozzle group A, and a second fuel command for the nozzle group B. The second control unit 12 sets the fuel supply command value MBCSO, and the correction unit 13 corrects the second fuel supply command value MBCSO set by the second control unit 12 in the direction in which the fuel supply amount increases. .

  Here, the gas turbine control device 10 has a fuel supply sharing ratio (hereinafter referred to as “sharing ratio”) used in the nozzle switching period. This sharing ratio is provided for each of the nozzle groups that have been used so far (hereinafter referred to as “first nozzle group”) and the nozzle group that will be used in the future (hereinafter referred to as “second nozzle group”). . Here, a sharing ratio corresponding to the first nozzle group is a first sharing ratio MAR, and a sharing ratio corresponding to the second nozzle group is a second sharing ratio MBR.

  For example, in the gas turbine power generation device 1 shown in FIG. 1, when the nozzle group is switched from the nozzle group A to the nozzle group B, the first sharing ratio MAR described above is used for the fuel flow control of the nozzle group A, For the fuel flow control of the nozzle group B, the above-described second sharing ratio MBR is used. Conversely, when the nozzles are switched from the nozzle group B to the nozzle group A, the first sharing ratio MAR is used for the nozzle group B, and the second sharing ratio MBR is used for the nozzle group A.

  FIG. 3 shows an example of the first sharing ratio MAR, and FIG. 4 shows an example of the second sharing ratio MBR. As shown in FIG. 3, for example, the first sharing ratio MAR is set to decrease at a constant rate from 100% to 0% in the nozzle switching period. Further, the second sharing ratio MBR is set to increase at a constant rate from 0% to 100% during the nozzle switching period. In the present embodiment, the first sharing ratio MAR and the second sharing ratio MBR are set so that the total of the sharing ratio at each time is constant at 100%.

Hereinafter, fuel flow control when the nozzles are switched from the nozzle group A to the nozzle group B will be described with reference to FIG.
First, in the nozzle switching period, the first control unit 11 acquires the first sharing ratio MAR (see FIG. 3), and multiplies the fuel supply command value CSO by the first sharing ratio MAR, so that the nozzle group A First fuel supply command value MACSO is set. By adjusting the first flow control valve 7 (see FIG. 1) according to the first fuel supply command value MACSO, the amount of fuel supplied to the combustor 2 by the nozzle group A decreases at a substantially constant rate. It will be.

  On the other hand, the second control unit 12 acquires the second sharing ratio MBR (see FIG. 4) during the nozzle switching period, and gives the second sharing ratio MBR to the correction unit 13. The correction unit 13 sets a correction amount based on the second sharing ratio MBR.

  Specifically, the correction unit 13 calculates the deviation between the second sharing ratio MBR and its first-order lag, and the second function that processes the output C1 from the incomplete differentiation unit 21 based on the function FX2. 22, the third function unit 23 that processes the second sharing ratio MBR based on the function FX 3, the first multiplier 24 that multiplies the output of the second function unit 22 and the output of the third function unit 23, and the gas turbine A correction amount C3 is generated by multiplying the output of the first function unit 25 by the output of the first function unit 25 and the output C2 of the first multiplier 24, and processing the parameter relating to the operation control based on the function FX1. The second multiplier 26 is provided.

The function FX2 provided in the second function unit 22 and the function FX3 provided in the third function unit 23 both finely adjust the correction amount that cannot be formed by the incomplete differentiation unit 21.
Further, as shown in FIG. 5, the function FX1 included in the first function unit 25 is set to a high adjustment amount when the output of the gas turbine is low, and outputs a low adjustment amount when the output of the gas turbine is high. Is set to That is, it is set so that a larger adjustment amount is output as the output of the gas turbine is lower.

FIG. 6 shows an example of the output C1 of the incomplete differentiation unit 21, the output C2 of the first multiplier 24, and the output C3 of the second multiplier 26 described above.
The correction amount obtained by the correction unit 13 in this way is output to the adder 27 provided in the second control unit 12. The adder 27 of the second control unit 12 obtains a corrected second sharing ratio MBR ′ by adding the correction amount to the second sharing ratio MBR. Then, the second control unit 12 sets the second fuel supply command value MBCSO of the nozzle group B by multiplying the fuel supply command value CSO by the corrected second sharing ratio MBR ′.

  The amount of fuel supplied to the combustor 2 by the nozzle group B is simply determined by adjusting the opening of the second flow rate control valve 8 (see FIG. 1) in accordance with the second fuel supply command value MBCSO. The fuel flow rate is greater than the fuel supply command value CSO multiplied by the second sharing ratio MBR. As a result, more fuel than the fuel supply command value CSO is supplied to the combustor 2, and a reduction in combustion efficiency in the combustor 2 can be suppressed.

As described above, according to the gas turbine control method and the gas turbine power generator 1 according to the present embodiment, the fuel supply amount to the combustor 2 is determined from the fuel supply amount command value CSO during the nozzle switching period. Therefore, a decrease in combustion efficiency in the combustor 2 can be suppressed, and as a result, fluctuations in gas turbine output can be reduced.
Further, the increase in the fuel supply amount is determined based on the deviation between the second share ratio MBR of the second nozzle group (nozzle group B in the above embodiment) to be used for fuel supply and the first order lag. Therefore, the fuel supply amount of the second nozzle group (nozzle group B) can be gradually increased.
Furthermore, by adjusting the correction amount C2 determined in this manner according to the output of the gas turbine and the like, it becomes possible to adjust the fuel increase amount according to the output status of the gas turbine. In addition to the output of the gas turbine, for example, as the above-described function FX1, a function expression or map using parameters related to the operating state of the gas turbine such as the required output command of the gas turbine, the fuel supply command CSO, the turbine inlet temperature T1T, etc. May be prepared in advance, and the adjustment amount may be obtained using these function equations and maps. By doing in this way, it becomes possible to adjust the amount of fuel increase according to the operating condition of a gas turbine.

7 to 9 are diagrams showing the effects of the gas turbine power generator according to the above embodiment.
FIG. 7 is a diagram illustrating an example of a corrected second sharing ratio MBR ′ obtained by adding a correction amount to the second sharing ratio MBR in the gas turbine control device 10 according to the present embodiment, and FIG. 8 is a correction illustrated in FIG. 7. FIG. 9 shows the output of the gas turbine when the fuel to the combustor 2 is increased by adopting the second sharing ratio MBR ′, and FIG. 9 shows the first sharing ratio MAR and the correction number shown in FIG. FIG. 4 is a diagram showing the fuel supply amount of the nozzle group A, the fuel supply amount of the nozzle group B, and the total fuel supply amount supplied to the combustor 2 when controlled by the 2-sharing ratio MBR ′.

  FIG. 10 is a diagram showing the first sharing ratio MAR and the second sharing ratio MBR, and FIG. 11 is a gas turbine when the first sharing ratio MAR and the second sharing ratio MBR shown in FIG. 10 are adopted. FIG. 12 shows the output of the nozzle group A, the fuel supply amount of the nozzle group B, and the fuel supply amount of the nozzle group B when controlled by the first sharing ratio MAR and the second sharing ratio MBR shown in FIG. FIG. 3 is a diagram showing the total amount of fuel supplied to the combustor 2.

  As shown in these drawings, particularly FIGS. 8 and 11, it is understood that the output fluctuation of the gas turbine is suppressed by increasing the fuel supply amount to the combustor 2 in the nozzle switching period.

  In the above-described embodiment, the parameter Pr related to the operating state of the gas turbine is processed by the function FX1 included in the first function unit 25, and this output is used as the adjustment amount. As shown in FIG. 13, a subtractor 31 that calculates the deviation between the gas turbine output and the required output command of the gas turbine and a PID controller 32 that performs PID control on the output of the subtractor 31 may be employed. By setting it as such a structure, it becomes possible to improve the controllability regarding a gas turbine output.

In the above embodiment, the correction amount is determined using the second sharing ratio MBR, but instead, the correction amount is determined using the first sharing ratio MAR as shown in FIG. It is good as well.
For example, when switching from the nozzle group A to the nozzle group B, as shown in FIG. 15, in the region where the sharing ratio of the nozzle group A is reduced, the fuel-air ratio of the nozzle group A in the combustor 2 is reduced. As shown, the combustion efficiency is reduced. For this reason, there exists a possibility that the output of a gas turbine may fall.

In this case, increasing the flow rate of the nozzle group A having a relatively low flow rate is less effective, and the effect can be expected by correcting the flow rate of the nozzle group B having a relatively high flow rate. Therefore, by determining the correction amount of the nozzle group B using the first sharing ratio MAR of the nozzle group A, it is possible to realize a more efficient operation of the gas turbine.
The fuel-air ratio is expressed as the reciprocal of the air-fuel ratio, and can be obtained by dividing the fuel flow rate by the air flow rate as shown below, for example.
Fuel-air ratio = fuel flow rate / air flow rate

[Second Embodiment]
Next, a gas turbine control method and a gas turbine power generator according to a second embodiment of the present invention will be described.
In the first embodiment described above, the correction amount is determined using the first sharing ratio MAR or the second sharing ratio MBR. However, in this embodiment, as shown in FIG. Based on this, the correction amount is determined. Specifically, the combustion efficiency is processed by the function FX4 provided in the fourth function unit 35, and this output is used as the correction amount. Here, as shown in FIG. 18, the function FX4 is set to output a high correction amount when the combustion efficiency is low and a low correction amount when the combustion efficiency is high. This makes it possible to set the second fuel supply command value MBCSO that compensates for the deterioration in combustion efficiency. In the function FX4, the maximum correction amount α is set to a value of 1 or less.

  Here, the combustion efficiency may be obtained based on the measured value of the exhaust gas from the gas turbine 3, or may be obtained by calculation as shown in FIG. For example, the fuel / air ratio is obtained based on the air flow rate command signal for adjusting the amount of air supplied to the compressor 4 and the second fuel supply command value MBCSO of the nozzle group B, and the combustion corresponding to this fuel / air ratio. It is good also as acquiring combustion efficiency by acquiring efficiency from a map.

  FIG. 20 is a diagram showing an example of a map for obtaining combustion efficiency. As shown in FIG. 20, the combustion efficiency takes a higher value as the fuel / air ratio increases, and becomes constant when a certain fuel / air ratio is exceeded. And the combustion efficiency calculated | required by calculation in this way is input into the 4th function unit 35 mentioned above. Thus, by obtaining the combustion efficiency by calculation, a sensor or the like for detecting the combustion efficiency can be made unnecessary.

[Third Embodiment]
Next, a gas turbine control method and a gas turbine power generator according to a third embodiment of the present invention will be described.
In the first embodiment described above, the correction amount is determined using the first sharing ratio MAR and the second sharing ratio MBR. However, in the present embodiment, as shown in FIG. A correction amount is determined based on the deviation between the output and the required output command of the gas turbine.
Specifically, as shown in FIG. 21, the deviation between the output of the gas turbine and the required output command of the gas turbine is processed by a function FX7 included in the seventh function unit 37, and this output is used as a correction amount. Here, as shown in FIG. 22, the function FX7 is set so that a larger correction amount is output as the deviation increases.

Thus, controllability can be improved by obtaining the correction amount by feeding back the output of the gas turbine. In addition, since the feedback value is used, it is possible to perform robust control with respect to combustion efficiency, plant individual differences, and other variations. Furthermore, it becomes possible to cope with different load change rates and switching load bands.
In the present embodiment, a PID controller 32 as shown in FIG. 13 may be used instead of the seventh function unit 37 described above.

[Fourth Embodiment]
Next, a gas turbine control method and a gas turbine power generation apparatus according to a fourth embodiment of the present invention will be described.
In the first embodiment described above, by correcting the second sharing ratio MBR of the nozzle group B, the fuel supply command MBCSO of the nozzle group B is increased, and the amount of fuel supplied to the combustor 2 is increased. However, instead of this, the fuel supply amount to the combustor 2 may be increased by correcting the first sharing ratio MAR of the nozzle group A and the second sharing ratio MBR of the nozzle group B.
As described above, by sharing the fuel increase by the nozzle group A and the nozzle group B, it is possible to further improve the operation efficiency of the gas turbine.

  Further, as described above, when the fuel-air ratio is lowered, the combustion efficiency is lowered and the output of the gas turbine is lowered. In consideration of such characteristics of combustion efficiency, for example, during the period when the fuel supply amount of the nozzle group A is larger than the fuel supply amount of the nozzle group B, for example, in the first half of the nozzle switching period, the correction amount of the nozzle group A is set. The correction amount of the nozzle group B is set to be larger than the correction amount of the nozzle group B, and during the period when the fuel supply amount of the nozzle group B is larger than the fuel supply amount of the nozzle group A, for example, in the latter half of the nozzle switching period. By setting the amount to be larger than the correction amount of the nozzle group A, it is possible to increase the amount of fuel by using a nozzle group with good combustion efficiency. Thereby, combustion efficiency can be improved and the output fall of the gas turbine at the time of nozzle switching can be further suppressed.

  As mentioned above, although embodiment of this invention was explained in full detail with reference to drawings, the specific structure is not restricted to this embodiment, The design change etc. of the range which does not deviate from the summary of this invention are included.

For example, in each of the above-described embodiments, the nozzle group A and the nozzle group B have two nozzle groups, and switching between them has been described. However, two or more nozzle groups may be provided. Also in this case, since the nozzle groups are sequentially switched, the previously used nozzle group is defined as the first nozzle group, and the nozzle group to be used in the future is defined as the second nozzle group. The second sharing ratio may be used.
Further, the first sharing ratio MAR and the second sharing ratio MBR are examples, and may be drawn with different characteristics.

1 is a block diagram showing a schematic configuration of a gas turbine power generator according to a first embodiment of the present invention. It is the figure which showed an example of the control block which a gas turbine control apparatus has. It is a figure which shows an example of a 1st sharing ratio. It is a figure which shows an example of 2nd sharing ratio MBR. It is the figure which showed an example of the function FX1 with which a 1st function device is provided. It is the figure which showed an example of the output of an incomplete differentiation part, the output of a 1st multiplier, and the output of a 2nd multiplier. In the gas turbine control device according to the first embodiment of the present invention, it is a diagram showing an example of a corrected second sharing ratio in which a correction amount is added to the second sharing ratio. It is the figure which showed the output of the gas turbine when the fuel to a combustor increased by employ | adopting the correction | amendment 2nd sharing ratio shown by FIG. The fuel supply amount of the nozzle group A, the fuel supply amount of the nozzle group B, and the total fuel supply amount supplied to the combustor when controlled by the first sharing ratio and the corrected second sharing ratio shown in FIG. FIG. It is the figure which showed the 1st sharing ratio and the 2nd sharing ratio. It is the figure which showed the output of the gas turbine at the time of employ | adopting the 1st sharing ratio and the 2nd sharing ratio which are shown by FIG. FIG. 10 shows the fuel supply amount of the nozzle group A, the fuel supply amount of the nozzle group B, and the total fuel supply amount supplied to the combustor when controlled by the first sharing ratio and the second sharing ratio shown in FIG. It is a figure. It is the figure which showed the other structural example of the correction | amendment part with which the gas turbine control apparatus which concerns on the 1st Embodiment of this invention is provided. In the correction part with which the gas turbine control device concerning a 1st embodiment of the present invention is provided, it is a figure showing the example of composition which decided to determine the amount of correction using the 1st share ratio. It is a figure for demonstrating when the sharing ratio of the nozzle group A falls. It is the figure which showed the relationship between fuel-air ratio and fuel efficiency. It is the figure which showed an example of the control block which the gas turbine control apparatus which concerns on the 2nd Embodiment of this invention has. It is the figure which showed an example of the function FX4 with which a 4th function device is provided. FIG. 18 is a diagram showing another configuration example of the control block shown in FIG. 17. It is the figure which showed an example of the map which calculates | requires combustion efficiency. It is the figure which showed an example of the control block which the gas turbine control apparatus which concerns on the 3rd Embodiment of this invention has. It is the figure which showed an example of the function FX7 with which a 7th function device is provided. It is a figure for demonstrating a pilot nozzle and several main nozzles. It is a figure for demonstrating the conventional fuel flow control in a nozzle switching period. It is the figure which showed typically the output fluctuation of the gas turbine at the time of performing the conventional fuel flow control.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Gas turbine power generator 2 Combustor 3 Gas turbine 4 Compressor 5 1st fuel flow path 6 2nd fuel flow path 7 1st flow control valve 8 2nd flow control valve 10 Gas turbine control apparatus 11 1st control part 12 1st 2 Control unit 13 Correction unit

Claims (10)

In a gas turbine having a combustor and a plurality of nozzles each having a different number of main nozzles and supplying fuel gas to the combustor, a gas for switching the nozzle group used for fuel supply according to an operating state A turbine control method comprising:
For the nozzle switching period in which the first nozzle group that has been used so far is switched to the second nozzle group that will be used from now on, a first fuel supply sharing ratio that gradually decreases the fuel supply amount is preset in the first nozzle group. A second fuel supply sharing ratio for gradually increasing the fuel supply amount is set in advance in the second nozzle group,
In the nozzle switching period, at least one of the first fuel supply share ratio and the second fuel supply share ratio is set so that the fuel supply amount supplied to the combustor is larger than the fuel supply amount command value. Correct,
The increase in the fuel supply amount is a deviation between the first-order lag of the second fuel supply share ratio and the second fuel supply share ratio, or the first-order lag of the first fuel supply share ratio and the first fuel supply share ratio. The control method of the gas turbine determined based on the deviation . The first fuel supply share ratio and the second fuel supply share ratio are corrected so that an increase in the fuel supply amount is distributed to the first nozzle group and the second nozzle group. The gas turbine control method described.   2. The gas turbine control method according to claim 1, wherein an increase in the fuel supply amount is distributed more to a nozzle group having a larger fuel supply share ratio.   The increase in the fuel supply amount is largely distributed to the first nozzle group in the first half of the nozzle switching period, and is largely distributed to the second nozzle group in the second half of the nozzle switching period. Gas turbine control method. The gas turbine control method according to any one of claims 1 to 4, wherein an increase in the fuel supply amount is adjusted according to an operating state of a power plant. The increase in fuel supply amount, relative to the first nozzle group and said second nozzle group, of a gas turbine according to any one of claims 1 to 5 which are assigned in a ratio in consideration of its combustion efficiency Control method.   The gas turbine control method according to any one of claims 1 to 6, wherein an increase in the fuel supply amount is determined according to combustion efficiency in the combustor.   The gas turbine control method according to claim 7, wherein the combustion efficiency is calculated based on an air flow rate and a fuel flow rate supplied to the combustor.   The gas turbine control method according to any one of claims 1 to 8, wherein the increase in the fuel supply amount is determined based on a deviation between an output command value of the gas turbine and an output of the gas turbine. A gas turbine power generator having a combustor and a plurality of nozzle groups each having a different number of main nozzles and supplying a fuel gas to the combustor, wherein the nozzle group used for fuel supply is switched according to an operating state Because
Gradually increase the first fuel supply sharing ratio and the fuel supply amount that are used during the nozzle switching period to switch the first nozzle group that has been used up to now to the second nozzle group to be used. Means for storing a second supply share ratio to be made;
In the nozzle switching period, at least one of the first fuel supply share ratio and the second fuel supply share ratio is set so that the fuel supply amount supplied to the combustor is larger than the fuel supply amount command value. A correction unit to correct,
When the correction unit corrects the first fuel supply share ratio, the corrected first fuel supply share ratio is used, and when the correction unit does not correct the first fuel supply share ratio. A first control unit configured to set a fuel supply amount of the first nozzle group using the stored first fuel supply share ratio;
When the second fuel supply share ratio is corrected by the correction unit, the corrected second fuel supply share ratio is used, and when the second fuel supply share ratio is not corrected by the correction unit. A second control unit configured to set a fuel supply amount of the second nozzle group using the stored second fuel supply share ratio;
With
The increase in the fuel supply amount is a deviation between the first-order lag of the second fuel supply share ratio and the second fuel supply share ratio, or the first-order lag of the first fuel supply share ratio and the first fuel supply share ratio. A gas turbine power generator determined based on the deviation .

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