JP3499026B2 - Gas turbine fuel supply device - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is applied to a power plant or the like, and in a gas turbine equipped with a combustor using a multi-stage combustion method, controls the fuel flow rate to the combustor so as to reduce NOx in exhaust gas. The present invention relates to a gas turbine fuel supply device.

[0002]

2. Description of the Related Art A plurality of gas turbine combustors are incorporated in a gas turbine or a combined cycle power plant, and the combustion gas burned by the gas turbine combustor is guided to the gas turbine to operate the gas turbine. It is designed to drive. In this type of gas turbine plant, it is known that the turbine thermal efficiency is improved by increasing the turbine inlet temperature, and in order to improve the turbine thermal efficiency, the turbine inlet temperature, that is, the outlet temperature of the gas turbine combustor is increased. Has been planned.

The combustion gas temperature is subject to various restrictions due to the heat resistance limits of gas turbine and combustor materials. Further, the combustion gas temperature is also restricted in terms of measures against NOx (nitrogen oxide) in the gas turbine combustor.

The main cause of NOx generation in the gas turbine combustor is local high temperature of the combustion gas in the gas turbine combustor, and the NOx generation amount depends on the combustion gas temperature in the combustion region of the gas turbine combustor. Dependent. A large amount of NOx is generated when the fuel and the air are diffusively mixed and burned inside the gas turbine combustor and burned at a high temperature close to the adiabatic flame temperature in the state where the fuel and the air are close to the equivalence ratio of 1. To do.

As a method for suppressing the generation of NOx in a gas turbine combustor, there is a premixed lean combustion method in which fuel and air are mixed in advance in a lean fuel state and burned.

As a gas turbine combustor adopting the premixed lean burn method, there is one disclosed in Japanese Utility Model Publication No. 4-43726. As shown in FIG. 9, this gas turbine combustor reduces predominantly mixed main fuel and also partially premixed pilot fuel to reduce diffusion combustion with a large amount of NOx generation, thereby significantly reducing NOx. It is intended to be.

The conventional gas turbine combustor shown in FIG.
The inside of the combustor liner 1 is divided into a first stage combustion zone 2 and a second stage combustion zone 3. A pilot fuel nozzle 4 is provided at the head of the combustor liner 1, and the pilot fuel is supplied from the pilot fuel nozzle 4 to the first stage combustion zone 2. The pilot fuel is divided into pilot diffusion fuel and pilot premixed fuel by the pilot fuel nozzle 4. The pilot diffusion fuel is diffused by the swirler 7 and supplied to the first stage combustion zone 2 to be burned, while the pilot premixed fuel is uniformly mixed with air in the air passage portion,
It is adapted to be injected from the swirler 7 into the first-stage combustion zone 2 for combustion.

Around the combustor liner 1, there is provided a premixing duct 6 for premixing the main fuel ejected from the main fuel nozzle 5 with air. The premixing duct 6 premixes the main fuel. The main fuel is injected into the second stage combustion zone 3 and burns.

The fuel distribution of the pilot diffusion fuel and the pilot premixed fuel is uniquely determined by the area of each fuel injection port, but the passage areas of the swirler 7 and the air passage portion are set to the pilot area in order to reduce NOx. The fuel-air ratio of the premixed fuel (fuel weight flow rate / air weight flow rate) is set relatively large so as to be sufficiently low.

FIG. 10 shows a conventional example of a gas turbine fuel supply device in a gas turbine combustor to which such a two-stage combustion system is applied.

In the above fuel supply device, one fuel supply pipe 8 guided from a gas fuel supply source (not shown) is bifurcated, and one of the branched pipes is used as a pilot fuel supply pipe 9 for the pilot system of the combustor. In addition to being connected, the other of the branch pipes is connected as the main fuel supply pipe 10 to the main system of the combustor.

A fuel stop valve 11 and a fuel control valve 12 for controlling the total gas fuel supply amount are provided at a position upstream of the branch point of the fuel supply pipe 8. And
Pilot fuel supply pipe 9 and main fuel supply pipe 10
In addition, a pilot fuel distribution valve 13 and a main fuel distribution valve 14 that set the distribution ratio of the supplied fuel are respectively provided.

The gas turbine control device 15 has a function generator 16 and a calculator 17. The valve position control signal n of the fuel control valve 12 for controlling the speed load of the gas turbine is input to this control device, and the fuel control valve 12 is controlled by this valve position control signal n.

Further, the valve position control signal n is the function generator 1
6 is input. Since the valve position control signal n has a proportional or linear relationship with the load of the gas turbine, the fuel distribution ratio is determined from the valve position control signal n based on the relationship data obtained in advance. Based on this, the function generator 16 outputs a valve position control signal m for the main fuel distribution valve 14 to control the main fuel distribution valve 14. Then, the valve position control signal m is input to the calculator 17, the valve position control signal of the pilot fuel distribution valve 13 is calculated to be (1-m), and the pilot fuel distribution valve 13 is calculated based on the signal. Is controlled.

In the gas turbine combustor shown in FIG. 9, in addition to the main fuel, a part of the pilot fuel is premixed and diluted, so that the proportion of the pilot diffusion fuel can be reduced, resulting in a significant reduction in NOx. Can be achieved. However, since the proportion of this diffusion fuel is uniquely determined by the flow rate of the pilot fuel, it can be narrowed down to only about 20% of the total fuel flow rate, and it is difficult to reduce it further, and low NO
There was a limit to x conversion.

In recent gas turbine plants,
To further improve the thermal efficiency of the gas turbine,
It is being sought to raise the temperature of the combustion gas in the gas turbine combustor, and as the temperature of the combustion gas rises, low NOx
The demand for the realization is increasing. In order to achieve the target value for reducing NOx, diffusion combustion, which generates a large amount of NOx, is suppressed to about several% of the total combustion amount, and the rest is NOx.
There is a demand for the development of a low NOx gas turbine combustor for premixed lean combustion in which almost no generation occurs.

A gas turbine combustor developed in response to these requirements is shown in FIG. This gas turbine combustor uses the first-stage fuel supply means to generate the first fuel in the combustor liner 1.
While the fuel is injected into the stage combustion zone 2, the fuel is injected into the second stage combustion zone 3 in a lean fuel state by the second stage fuel supply means and burned in the combustor liner 1. The first stage fuel is a pilot nozzle 21 including a first diffusion fuel nozzle 18, a second diffusion fuel nozzle 19, and a premix fuel nozzle 20.
Supplied from Among them, the first diffusion fuel nozzle 18 can flow a required flow rate in a low load region where the diffusion combustion ratio is high. Further, the second diffusion fuel nozzle 19 is suitable for flowing about several percent of the diffusion combustion fuel with respect to the total fuel flow rate during the low NOx operation in the high load region of the gas turbine.

Second stage fuel is also supplied from a main fuel nozzle 22 arranged around the combustor liner 1.
The fuel supplied from the main fuel nozzle 22 is premixed with air in the premixing duct 6 and then injected into the second stage combustion zone 3 to perform premixed combustion.

In this combustor, the pilot premixed combustion system is independently provided, so that the proportion of the diffused fuel can be controlled to a necessary and sufficient amount for stable combustion, and the diffused combustion can be controlled to several% of the total combustion amount. Since it can be suppressed, it is possible to significantly reduce NOx.

[0020]

In the above low NOx combustor, the fuel supply system includes a first diffusion system, a second diffusion system of the first stage fuel supply means, a premix system and a pre-mixing system of the second stage fuel supply means. A total of 4 mixed systems are required. However, in the conventional fuel supply device, the first stage fuel supply means is
The system and the second-stage fuel supply means supply fuel to two systems in total, and it is necessary to provide a new fuel supply device for supplying fuel to four systems. At that time, if the control is performed only by the function using the fuel control command as the input signal, NOx
Since the combustion gas temperature that most affects the generation is not in control, low NOx control becomes difficult.

Further, at the time of load shedding and in-house single load operation, there is a risk of misfire due to a sharp decrease in fuel flow rate. In particular, in premixed lean combustion, the risk of misfire when the fuel is reduced is greater than in diffusion combustion. Therefore,
In order to achieve both rapid load reduction and flame holding, it is desirable to reduce premixed lean combustion and maximize the proportion of diffusion combustion. However, in the above-mentioned low NOx combustor, the diffusion combustion is a few% of the total combustion, and therefore, the proportion of the diffusion combustion must be promptly increased at the time of load shedding and at the in-house single load operation. At that time, in the high load region, the first diffusion system is closed, so the supply ratio of the second diffusion fuel system is increased. However, in the second diffusion system that only flows a few percent of the total fuel flow rate during rated operation, it is difficult to secure the minimum fuel flow rate set to about 70% of the fuel flow rate in the no-load rated speed operation state. is there.

The present invention has been made in consideration of the above circumstances, and an object of the present invention is to provide a gas turbine fuel supply device capable of distributing fuel to four systems by simple control.

Another object of the present invention is to provide a low NO during normal operation.
(EN) Provided is a gas turbine fuel supply device capable of easily performing x control.

Still another object of the present invention is to provide a gas turbine fuel supply system capable of achieving both rapid reduction in fuel flow rate and flame holding at the time of load shedding or in-house single operation.

[0025]

In order to achieve the above-mentioned object, the first aspect of the present invention is to provide the fuel required in a low load region.
Gas turbine using a multi-stage combustion method having a pilot fuel nozzle including a diffusion fuel nozzle, a second diffusion fuel nozzle that allows diffusion combustion fuel to flow during low NOx operation in a high load region, and a premix fuel nozzle, and a main fuel nozzle Premix fuel nozzle having a first fuel control valve, a first diffusion fuel supply pipe for supplying fuel to the first diffusion fuel nozzle, and a second fuel control valve, And a fuel supply pipe for supplying fuel to the main fuel nozzle;
A second diffusion fuel supply pipe having a fuel control valve for supplying fuel to the second diffusion fuel nozzle, and a fuel distribution mechanism provided downstream of the fuel supply pipe for the second fuel control valve are provided. It is characterized by

According to a second aspect, a function generator that outputs a distribution function of each fuel control valve, an arithmetic unit that outputs a valve position control signal of each fuel control valve based on each distribution function and a fuel control signal, and a fuel distribution A function generator that outputs a distribution signal to the mechanism,
An arithmetic unit for supplying the arithmetic turbine inlet temperature to the both function generators as an input signal during normal operation, wherein the arithmetic turbine inlet temperature is atmospheric temperature, gas turbine compressor discharge pressure, gas turbine compressor discharge temperature, gas turbine It is characterized in that the calculation is performed based on the exhaust gas temperature and the compressor inlet guide vane angle.

According to a third aspect of the present invention, a function generator which outputs a distribution function of each fuel control valve, an arithmetic unit which outputs a valve position control signal of each fuel control valve based on each distribution function and a fuel control signal, and a fuel distribution A function generator that outputs a distribution signal to the mechanism, both of the function generators are provided with an elapsed time from the start of load shedding as an input signal at the time of load shedding or a single load operation in a station, and a first diffusion fuel It is characterized in that the supply pipe is pre-filled.

[0028]

The fuel is supplied to each diffusion fuel nozzle through a diffusion fuel supply pipe having a fuel control valve, and the premix fuel nozzle and the main fuel nozzle are controlled by the fuel control valve. A large amount of fuel is distributed and supplied by the fuel distribution mechanism. Therefore, with simple control,
It is possible to distribute fuel to four systems.

In the second aspect of the present invention, the operation turbine inlet temperature given to both function generators as an input signal during normal operation is the atmospheric temperature, the gas turbine compressor discharge pressure, the gas turbine compressor discharge temperature, the gas turbine exhaust gas temperature, And the compressor inlet guide vane angle. Therefore, the low NOx control can be easily performed without correcting the fuel control command due to the atmospheric temperature.

According to the third aspect of the present invention, the time elapsed from the start of the load cutoff is given as an input signal to both function generators when the load is cut off or the single load operation is performed in the station. Therefore, it is possible to continue the combustion only by the diffusion combustion having high flame holding property. Further, since the pre-filling operation of the first diffusion fuel supply pipe is performed, it is possible to quickly supply the fuel from the first diffusion fuel supply pipe and to quickly shift to the no-load rated speed operation state after the end of the load cutoff. It will be possible.

[0031]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine fuel supply system according to the present invention will be described below with reference to the accompanying drawings. FIG. 1 is a system diagram showing a first embodiment of a gas turbine fuel supply system according to the present invention. It should be noted that the same or corresponding portions as those of the conventional configuration will be described using the same reference numerals as those in FIG.

In FIG. 1, the fuel supply pipe 8 branches off downstream of the fuel stop valve 11 and is connected to the first fuel control valve 23, the second fuel control valve 24 and the third fuel control valve 25. The downstream side of the second fuel control valve 24 is further branched and connected to the fuel distribution valve 26. A downstream side of the first fuel control valve 23 is connected to a first diffusion fuel supply pipe 27, a downstream side of the fuel distribution valve 26 is connected to a pilot premixed fuel supply pipe 28 and a main fuel supply pipe 29, and a third fuel control valve is connected. The downstream side of 25 is connected to the second diffusion fuel supply pipe 30. Further, the control device 31 controls the first fuel control valve 23, the second fuel control valve 24, and the fuel distribution valve 26 from the fuel control command.

FIG. 2 shows the configuration of elements used for control of the gas turbine control device 31 during normal operation. This configuration
It comprises a calculator 32 for calculating the turbine inlet temperature, a function generator 33 for outputting the distribution ratio of the fuel control valve, a calculator 34 for the valve position control signal of the fuel control valve, and a function generator 35 for the fuel distribution valve position control signal.

FIG. 3 shows the configuration of elements used for the control of the gas turbine control device 31 during the load shedding operation or the in-house single load operation. This configuration is used for each fuel control valve 23, 2
It comprises a function generator 36 for outputting the distribution ratio of 4, 25, a calculator 34 for the valve position control signal of the fuel control valve, and a function generator 37 for the fuel distribution valve position control signal.

Next, the operation of this embodiment will be described.

The gas turbine control unit 31 shown in FIG. 2 has a calculator 32 based on the atmospheric temperature, compressor discharge pressure, compressor discharge temperature, turbine exhaust gas temperature, and compressor inlet guide vane angle.
The calculated turbine inlet temperature T calculated by
The first fuel control valve 23, the second fuel control valve 24, and the third fuel control valve 25 are controlled by the function generator 33 using the input signal as the input signal.
The distribution functions f1, f2, and f3 to the three fuel control valves are output. The distribution ratio of these fuel control valves, the fuel control signal n, and the constant k determined by the size of the fuel control valves.
The valve position control signal of the fuel control valve is output from the arithmetic unit 34 by the product of 1, k2 and k3. Further, the valve position control signal m of the fuel distribution valve 26 is output by the function generator 35 whose input signal is the calculated turbine inlet temperature T.

FIG. 4 shows the change over time in fuel distribution when the load is cut off from the rated operating state in this embodiment. After the start of load shedding, the fuel supplied to the gas turbine decreases as the load suddenly decreases. However, excessive fuel is supplied due to delay of the control system and inflow of fuel remaining in the fuel pipe into the combustor, so that the gas turbine temporarily exceeds the rated speed. At this time, the fuel flow rate is further reduced due to the rotation speed control, and is reduced to the minimum fuel flow rate set to about 70% of the fuel flow rate in the no-load rated speed operation state.

In the present embodiment, in order to simultaneously maintain the diffusion combustion and reduce the fuel flow rate, the second diffusion system is opened to the controllable limit opening, and the pilot premixing system and the main system are closed. In this state, there is no risk of misfire, but the minimum fuel flow rate cannot be supplied, and it is difficult to quickly shift to the no-load rated speed operation state after the end of load shedding. For this reason, it is necessary to open the first diffusion system, but in the high load range, the first diffusion system is closed and air is contained in the fuel pipe. The fuel cannot be supplied from the first diffusion system unless the prefill operation for replacing this with fuel is performed. The opening degree of the first fuel control valve 23 at the time of prefilling is set to an opening degree at which the sum of the flow rate of the second diffusion system and the flow rate of the second diffusion system becomes the minimum fuel flow rate when fuel is flowing in the first diffusion system instead of air. .
Therefore, the total fuel flow rate becomes the minimum fuel flow rate at the end of the prefill. After the completion of the prefill, the operation for switching the first diffusion system and the second diffusion system to the distribution ratio of the normal operation is performed with a margin for safety. After that, when the gas turbine rotation speed falls near the rated rotation speed, the fuel flow rate is increased and the gas turbine rotation speed is controlled to the rated rotation speed for speed control. Through the above operation, the necessary fuel can be supplied only by the diffusion fuel when the load is cut off. In addition, the same operation is performed during the single load operation in the plant.

In order to perform the above operation, in this embodiment,
In the gas turbine control device 31 shown in FIG. 3, the function generator 36 set to cause the fuel control valves 23, 24, 25 to perform the above operation is input with the time t elapsed from the start of load shedding, and The distribution functions f1, f2, f3 to the three fuel control valves of the first fuel control valve 23, the second fuel control valve 24, and the third fuel control valve 25 are calculated. The valve position control signal of the fuel control valve is output from the calculator 34 by the product of the distribution ratio of these fuel control valves and the constants k1, k2, k3 determined by the fuel control signal n and the size of the fuel control valve. It Further, the function generator 37 having the elapsed time t as an input signal
Thus, the valve position control signal m of the fuel distribution valve 26 is output.

Next, the effect of this embodiment will be described.
FIG. 5 shows changes in the fuel distribution rate with respect to the loads of the first diffusion system, the second diffusion system, the pilot premix system, and the main system. From the start-up of the gas turbine to the operating state at the unloaded rated speed, fuel is supplied only from the first and second diffusion systems. Then, as shown in FIG. 5, the premix diffusion system first starts to open, and then the main system starts to open. After that, the first diffusion system is closed and the rated operation state is reached. FIG. 6 shows changes in the valve opening of each valve in such an operation. Figure 6
As shown in (3), the change of the valve opening degree of each valve has good controllability because the control is not performed in the part with poor controllability near the fully closed state.

Further, since the fuel distribution rate is determined only by the calculated turbine inlet temperature T, it is not necessary to correct the fuel control command due to the atmospheric temperature.

Further, even when the load is cut off or the in-house single load operation is performed, by performing control based on the elapsed time t, it is possible to continue combustion only by diffusion combustion having high flame holding property.

FIG. 7 shows a second embodiment of the present invention, in which a splitter valve 38 is used instead of the fuel distribution valve 26 in the first embodiment.

That is, the downstream side of the second fuel control valve 24 is, as shown in FIG. 7, a pilot premixed fuel supply pipe 2
8 and a main fuel supply pipe 29, each fuel supply pipe 28, 29 is provided with a splitter valve 38, and this splitter valve 38 is controlled by a signal from a function generator 35 or 37. It is like this.

In other respects, the structure is the same as that of the first embodiment and the operation is the same.

Therefore, even if the splitter valve 38 is used, the same effect as that of the first embodiment can be obtained.

FIG. 8 shows a third embodiment of the present invention in which a main fuel distribution valve 39 and a pilot premix fuel distribution valve 40 are used instead of the splitter valve 38 in the second embodiment. Is.

That is, as shown in FIG. 8, the main fuel supply pipe 29 and the pilot premixed fuel supply pipe 28, which are branched into two on the downstream side of the second fuel control valve 24, have a main fuel distribution valve 39 and a pilot premixed fuel supply pipe. Mixed fuel distribution valves 40 are provided respectively. And the main fuel distribution valve 3
The opening of 9 is controlled by the signal from the function generator 35 or 37, and the opening of the pilot premixed fuel distribution valve 40 is (41) which calculates (1-m) from this signal.
It is controlled by the signal from.

In other respects, the structure is the same as that of the first embodiment and the operation is the same.

Therefore, according to this embodiment, the same effect as that of the first embodiment can be obtained.

[0051]

As described above, according to the first aspect of the present invention, fuel is supplied to each diffusion fuel nozzle through the diffusion fuel supply pipe having the fuel control valve, and the premix fuel nozzle and the main fuel nozzle are connected. Since the fuel having the flow rate controlled by the fuel control valve is distributed to the fuel nozzle by the fuel distribution mechanism and supplied, the fuel can be distributed to four systems by simple control.

According to the second aspect of the present invention, the calculated turbine inlet temperature given to both function generators as an input signal during the normal operation is represented by atmospheric temperature, gas turbine compressor discharge pressure, gas turbine compressor discharge temperature, gas turbine exhaust gas temperature. , And the compressor inlet guide vane angle, the low NOx control can be easily performed without correcting the fuel control command due to the atmospheric temperature.

According to the third aspect of the present invention, since the elapsed time from the start of load shedding is given as an input signal to both function generators when the load is shed or in the single load operation in the station, diffusion with high flame holding property is provided. It is possible to sustain combustion only by combustion. Further, since the pre-filling operation of the first diffusion fuel supply pipe is performed, the fuel is rapidly and reliably supplied from the first diffusion fuel supply pipe, and the loadless speed operation state is promptly transitioned after the load is cut off. be able to.

[Brief description of drawings]

FIG. 1 is a first gas turbine fuel supply device according to the present invention.
A system diagram showing an example.

FIG. 2 is a schematic diagram of elements used during normal operation of a control device for a gas turbine fuel supply apparatus according to the present invention.

FIG. 3 is a schematic diagram of elements used when the control device of the gas turbine fuel supply apparatus according to the present invention is in a load cut-off state or in a single load operation in a station.

FIG. 4 is a diagram showing a change over time in fuel distribution of the gas turbine combustor during load shedding or in-house single load operation.

FIG. 5 is a diagram showing an example of a fuel distribution ratio with respect to a load of a gas turbine combustor.

FIG. 6 is a diagram showing a change in valve opening with respect to a load of the gas turbine fuel supply system.

FIG. 7 is a second gas turbine fuel supply device according to the present invention.
A system diagram showing an example.

FIG. 8 is a third gas turbine fuel supply device according to the present invention.
A system diagram showing an example.

FIG. 9 is an explanatory diagram showing a structural example of a conventional gas turbine combustor with reduced NOx.

FIG. 10 is a system diagram showing a conventional fuel supply device.

FIG. 11 is an explanatory diagram showing a structural example of a gas turbine combustor having an ultra-low NOx content.

[Explanation of symbols]

1 Combustor liner 2 First stage combustion area 3 Second stage combustion zone 6 premixing duct 8 Fuel supply pipe 11 Fuel stop valve 18 1st diffusion fuel nozzle 19 Second diffusion fuel nozzle 20 Premix fuel nozzle 21 Pilot nozzle 22 Main fuel nozzle 23 First fuel control valve 24 Second fuel control valve 25 Third Fuel Control Valve 26 Fuel distribution valve 27 First diffusion fuel supply pipe 28 Pilot premix fuel supply pipe 29 Main fuel supply pipe 30 Second diffusion fuel supply pipe 31 Control device 32, 34, 41 calculator 33,35,36,37 Function Generator 38 Splitter valve 39 Main fuel distribution valve 40 Pilot premix fuel distribution valve

─────────────────────────────────────────────────── --- Continuation of the front page (56) References JP-A-6-18038 (JP, A) JP-A-7-190370 (JP, A) JP-A-6-137168 (JP, A) JP-A-5- 149149 (JP, A) JP-A-7-166891 (JP, A) (58) Fields investigated (Int.Cl. ⁷ , DB name) F02C ^7/ 22-9/28 F23R 3/28-3/38

Claims (3)

(57) [Claims] 1. A pilot nozzle comprising a first diffusion fuel nozzle for flowing a required fuel in a low load region, a second diffusion fuel nozzle for flowing a fuel for diffusion combustion during low NOx operation in a high load region, and a premixed fuel nozzle. And a main fuel nozzle, a fuel supply device for a gas turbine combustor using a multi-stage combustion method, the first fuel supply valve having a first fuel control valve for supplying fuel to the first diffusion fuel nozzle. A fuel supply pipe having a pipe and a second fuel control valve for supplying fuel to the premix fuel nozzle and the main fuel nozzle; and a third fuel control valve for supplying fuel to the second diffusion fuel nozzle. A gas turbine fuel supply apparatus comprising: a two-diffusion fuel supply pipe; and a fuel distribution mechanism provided on the downstream side of the second fuel control valve of the fuel supply pipe. 2. A function generator that outputs a distribution function of each fuel control valve, an arithmetic unit that outputs a valve position control signal of each fuel control valve based on each distribution function and a fuel control signal, and a distribution to a fuel distribution mechanism. A function generator that outputs a signal, and a calculator that gives a calculation turbine inlet temperature as an input signal to both function generators during normal operation, the calculation turbine inlet temperature is an atmospheric temperature, a gas turbine compressor discharge pressure, The gas turbine fuel supply device according to claim 1, wherein the gas turbine fuel discharge device is operated on the basis of the gas turbine compressor discharge temperature, the gas turbine exhaust gas temperature, and the compressor inlet guide vane angle. 3. A function generator that outputs a distribution function of each fuel control valve, an arithmetic unit that outputs a valve position control signal of each fuel control valve based on each distribution function and a fuel control signal, and a distribution to a fuel distribution mechanism. A function generator that outputs a signal, both of the function generators are provided with an elapsed time from the start of load shedding as an input signal during load shedding or in a single load operation in a station, and the function generator of the first diffusion fuel supply pipe The gas turbine fuel supply apparatus according to claim 1, wherein a prefill operation is performed.