FUEL CONTROL DEVICE, COMBUSTOR, GAS TURBINE, FUEL CONTROL METHOD, AND PROGRAM

Abstract

A fuel control device includes a stem fuel valve opening degree determination unit, a branch line flow rate determination unit, and a correction value determination unit. The stem fuel valve opening degree determination unit is configured to determine an opening degree of a flow rate adjustment valve of a stem fuel supply line. The branch line flow rate determination unit is configured to determine the opening degree of each flow rate adjustment valve of the branch line based on an operation situation of the gas turbine. The correction value determination unit is configured to determine a correction value of the opening degree of each flow rate adjustment valve of the branch line based on a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

Description

TECHNICAL FIELD

The present invention relates to a fuel control device, a combustor, a gas turbine, a fuel control method, and a program.

Priority is claimed on Japanese Patent Application No. 2016-044242, filed Mar. 8, 2016, the content of which is incorporated herein by reference.

BACKGROUND ART

There is a gas turbine including a combustor having a plurality of nozzles. As a related technique, Patent Document 1 discloses a technique that includes a combustor having a plurality of nozzles and which controls a fuel flow rate on the basis of an operation state of a gas turbine.

CITATION LIST

Patent Document

[Patent Document 1] Japanese Unexamined Patent Application, First Publication No. 2007-77866

SUMMARY OF INVENTION

Technical Problem

Incidentally, there may be a problem that when pressure differences between a fuel pressure upstream of each of the nozzles of a combustor and a corrected fuel pressure for the fuel pressure at an outlet varies, the combustion characteristics of the gas turbine vary.

Therefore, an object of the present invention is to provide a fuel control device, a combustor, a gas turbine, a fuel control method, and a program capable of solving the above problem.

Solution to Problem

According to a first aspect of the present invention, a fuel control device includes a stern fuel valve opening degree determination unit configured to determine an opening degree of a flow rate adjustment valve of a stern fuel supply line serving as the basis of a plurality of branch lines on the basis of a fuel control signal command value according to an output of a gas turbine, a branch line flow rate determination unit configured to determine the opening degree of each flow rate adjustment valve of the branch line on the basis of an operation situation of the gas turbine, and a correction value determination unit configured to determine a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

According to a second aspect of the present invention, in the fuel control device of the first aspect, in a case where the pressure difference between the fuel pressure upstream of a second fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is reduced, the correction value determination unit may determine a correction value for increasing a third fuel control signal command value.

According to a third aspect of the present invention, in the fuel control device of the first aspect or the second aspect, in a case where the pressure difference between the fuel pressure upstream of the second fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is in a range of 0.1 megapascals to 1 megapascal, the correction value determination unit may determine the correction value of the opening degree of each flow rate adjustment valve of the branch line.

According to a fourth aspect of the present invention, in the fuel control device of any one of the first to third aspects, in a case where the pressure difference between the fuel pressure upstream of a first fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is reduced, the correction value determination unit may determine the correction value for increasing a first fuel control signal command value.

According to a fifth aspect of the present invention, in the fuel control device of any one of the first to fourth aspects, in a case where the pressure difference between the fuel pressure upstream of the first fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is in a range of 0.01 megapascals to 0.1 megapascals, the correction value determination unit may determine the correction value of the opening degree of each flow rate adjustment valve of the branch line.

According to a sixth aspect of the present invention, a combustor includes a first fuel nozzle of which a flow rate is controlled by a first flow rate adjustment valve included in the fuel control device of any one of the first to fifth aspects, a second fuel nozzle of which a flow rate is controlled by a second flow rate adjustment valve included in the fuel control device, and a third fuel nozzle of which a flow rate is controlled by a third flow rate adjustment valve included in the fuel control device.

According to a seventh aspect of the present invention, a gas turbine includes the fuel control device of any one of the first to fifth aspects, and a combustor including a first fuel nozzle of which a flow rate is controlled by a first flow rate adjustment valve included in the fuel control device, a second fuel nozzle of which a flow rate is controlled by a second flow rate adjustment valve included in the fuel control device, and a third fuel nozzle of which a flow rate is controlled by a third flow rate adjustment valve included in the fuel control device.

According to an eighth aspect of the present invention, a fuel control method includes determining an opening degree of a flow rate adjustment valve of a stem fuel supply line serving as the basis of a plurality of branch lines on the basis of a fuel control signal command value according to an output of a gas turbine, determining the opening degree of each flow rate adjustment valve of the branch line on the basis of an operation situation of the gas turbine, and determining a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

According to a ninth aspect of the present invention, a program causes a computer to execute determining an opening degree of a flow rate adjustment valve of a stem fuel supply line serving as the basis of a plurality of branch lines on the basis of a fuel control signal command value according to an output of a gas turbine, determining the opening degree of each flow rate adjustment valve of the branch line on the basis of an operation situation of the gas turbine, and determining a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

Advantageous Effects of Invention

According to the fuel control device according to the embodiment of the present invention, it is possible to prevent variation in combustion characteristics of a gas turbine occurring in a case where a pressure difference between a fuel pressure upstream of each of the nozzles of a combustor and a corrected fuel pressure for the fuel pressure at an outlet varies.

BRIEF DESCRIPTION OF THE DRAWING

FIG. 1 is a diagram showing a constitution of a gas turbine according to an embodiment of the present invention.

FIG. 2 is a diagram showing a relationship between a fuel control signal command value and a third fuel distribution ratio in an embodiment of the present invention.

FIG. 3 is a diagram showing a relationship between the fuel control signal command value and a Δ third fuel distribution ratio in an embodiment of the present invention.

FIG. 4 is a diagram showing a relationship between a pressure difference of a second fuel nozzle and a correction coefficient according to an embodiment of the present invention.

FIG. 5 is a diagram showing a relationship between the pressure difference of the second fuel nozzle and combustion characteristics of the gas turbine according to an embodiment of the present invention.

FIG. 6 is a diagram showing each of a relationship between a first fuel distribution ratio and a pressure difference of a first fuel nozzle and a relationship between the first fuel distribution ratio and fuel characteristics according to an embodiment of the present invention.

DESCRIPTION OF EMBODIMENTS

Embodiment

Hereinafter, an embodiment will be described in detail with reference to the drawings.

A constitution of a gas turbine 1 according to an embodiment of the present invention will be described.

As shown in FIG. 1, the gas turbine 1 according to an embodiment of the present invention includes a fuel control device 10, a first flow rate adjustment valve 20, a second flow rate adjustment valve 30, a third flow rate adjustment valve 40, a fourth flow rate adjustment valve 50, a combustor 60, and a turbine body 70.

In addition, in FIG. 1, a stem fuel supply line is denoted by a reference sign Ra. In addition, in FIG. 1, a first branch line that is one of a plurality of branch lines branching from the stern fuel supply line Ra is denoted by a reference sign R1. In addition, in FIG. 1, a second branch line branching from the stem fuel supply line Ra is denoted by a reference sign R2, and a third branch line branching from the stem fuel supply line Ra is denoted by a reference sign R3.

The fuel control device 10 includes a stem fuel valve opening degree determination unit 101, a branch line flow rate determination unit 102, and a correction value determination unit 103.

The stein fuel valve opening degree determination unit 101 determines an opening degree of a flow rate adjustment valve (the first flow rate adjustment valve 20) of the stem fuel supply line Ra serving as the basis of a plurality of branch lines (the first branch line R1, the second branch line R2, and the third branch line R3) on the basis of a fuel control signal command value according to an output of the gas turbine 1. For example, the fuel control signal command value according to the output of the gas turbine 1 is defined as a value proportional to an output of an electric generator (not shown) driven by the gas turbine 1 or a value proportional to a gas turbine inlet fuel gas temperature.

The branch line flow rate determination unit 102 determines the opening degrees of each of the flow rate adjustment valves (the second flow rate adjustment valve 30, the third flow rate adjustment valve 40, and the fourth flow rate adjustment valve 50) of the plurality of branch lines branching from the stem fuel supply line Ra on the basis of an operation situation of the gas turbine 1.

The correction value determination unit 103 determines a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference (described as a “pressure difference of nozzle” in the drawing) between a fuel pressure upstream of each of nozzles (a first fuel nozzle 601, a second fuel nozzle 602, and a third fuel nozzle 603 that will be described later) connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

The first flow rate adjustment valve 20 adjusts a flow rate of the stern fuel supply line Ra on the basis of control by the stern fuel valve opening degree determination unit 101.

The second flow rate adjustment valve 30 adjusts a flow rate to the first branch line R1 from the stem fuel supply line Ra on the basis of a control by the branch line flow rate determination unit 102.

The third flow rate adjustment valve 40 adjusts a flow rate to the second branch line R2 from the stem fuel supply line Ra on the basis of control by the branch line flow rate determination unit 102.

The fourth flow rate adjustment valve 50 adjusts a flow rate to the third branch line R3 from the stein fuel supply line Ra on the basis of the control by the branch line flow rate determination unit 102.

The combustor 60 includes the first fuel nozzle 601, the second fuel nozzle 602, and the third fuel nozzle 603.

The first fuel nozzle 601 is connected to the first branch line R1.

The second fuel nozzle 602 is connected to the second branch line R2.

The third fuel nozzle 603 is connected to the third branch line R3.

The combustor 60 combusts a fuel gas supplied from each of the first fuel nozzle 601, the second fuel nozzle 602, and the third fuel nozzle 603 to generate a high temperature combustion gas. The combustor 60 exhausts the generated high temperature combustion gas to the turbine body 70.

The turbine body 70 converts thermal energy obtained by expansion of the high temperature combustion gas acquired and input from the combustor 60 into rotational energy of a rotor (a rotation shaft).

The gas turbine 1 according to an embodiment of the present invention determines the opening degree of the flow rate adjustment valve of the stem fuel supply line Ra on the basis of the fuel control signal command value according to an output of the gas turbine 1 and determines the flow rate of the stern fuel supply line Ra. The gas turbine 1 determines the opening degrees of each of the flow rate adjustment valves of the plurality of branch lines branching from the stem fuel supply line Ra on the basis of the operation situation of the gas turbine 1. A distribution of the flow rates supplied to each of the plurality of branch lines from the stem fuel supply line Ra is determined by the determination of the opening degrees. The gas turbine 1 determines the correction value of the opening degrees of each of the flow rate adjustment valves of the branch line on the basis of the value of the pressure difference between the fuel pressure upstream of each of the nozzles connected to the branch lines respectively and the corrected fuel pressure for the fuel pressure at the outlet, and corrects the distribution of the flow rates supplied to each of the plurality of branch lines from the stem fuel supply line Ra.

Therefore, the gas turbine 1 can prevent variation in combustion characteristics of the gas turbine 1 due to variation of the pressure difference between the fuel pressure upstream of each of the nozzles connected to the branch lines respectively and the corrected fuel pressure for the fuel pressure at the outlet by determining the correction value of the opening degrees of each of the flow rate adjustment valves of the branch line on the basis of the value of the pressure difference between the fuel pressure upstream of each of the nozzles connected to the branch lines respectively and the corrected fuel pressure for the fuel pressure at the outlet and correcting the distribution of the flow rates supplied to each of the plurality of branch lines from the stem fuel supply line Ra.

FIRST EXAMPLE

First, an example in which variation in combustion characteristics of the gas turbine 1 due to variation of a pressure difference between a fuel pressure upstream of the second fuel nozzle 602 that contributes most to combustion in the combustor 60 and the corrected fuel pressure for the fuel pressure at an outlet is prevented will be described.

The pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet is able to be obtained by the following formula (1).

[Math. 1]

The pressure difference of the second nozzle 602=a manifold pressure−a pressure of the combustor 60   (1)

Note that the manifold pressure of the second fuel nozzle 602 is determined using a pressure gauge.

A casing pressure is detected using the pressure gauge, and the pressure of the combustor 60 (a pressure in an upstream of the turbine body 70) is able to be obtained by calculating (cabin pressure)×α.

A relationship between the fuel control signal command value and a Δ third fuel distribution ratio according to the output of the gas turbine 1 shown in FIG. 3 is able to be obtained by converting the third fuel distribution ratio in a relationship between the fuel control signal command value and a third fuel distribution ratio according to the output of the gas turbine 1 shown in FIG. 2 from 0 to 1.

In an example of a relationship between the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet and a correction coefficient shown in FIG. 4, the correction coefficient is 0 in a case where the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet is greater than Pr1 [MPa] (megapascal). In addition, in an example of the relationship between the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet and the correction coefficient shown in FIG. 4, the correction efficient decreases when the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet decreases from Pr1 [MPa].

The relationship between the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet and the correction coefficient may be determined as follows. That is, a relationship between the second fuel nozzle 602 in the gas turbine 1 and the combustion characteristics of the gas turbine 1 as shown in FIG. 5 is obtained, and in a case where the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet is for example, equal to or less than Pr1 [MPa], the gas turbine 1 determines a correction for reducing the third fuel distribution ratio and performs the correction. The pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet increases and it is possible to prevent variation in the combustion characteristics of the gas turbine 1 by performing the correction to reduce the third fuel distribution ratio in a case where the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet is equal to or less than Pr1 [MPa].

Note that the relationship between the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet and the correction coefficient may be determined by performing an experiment on the actual gas turbine 1 and on the basis of experiment results thereof.

In addition, with respect to the example of the relationship between the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet and the combustion characteristics of the gas turbine 1 shown in FIG. 5, it is determined to perform the correction reducing the third fuel distribution ratio in a case where the pressure difference is equal to or less than Pr1 [MPa], but the present invention is not limited thereto. A range of the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet when performing correction for reducing the third fuel distribution ratio is determined is about 0.1 [MPa] to 1 [MPa].

The correction value of the third fuel distribution ratio is able to be obtained by multiplying the third fuel distribution ratio shown in FIG. 3 by the correction coefficient shown in FIG. 4.

That is, a third fuel distribution ratio FTH after the correction is able to be calculated by the following formula (2), using a third fuel distribution ratio FX1 before the correction shown in FIG. 2, the third fuel distribution ratio shown in FIG. 3, and the correction coefficient shown in FIG. 4.

[Math. 2]

FTH=FX1+FX2×FX3   (2)

The stem fuel valve opening degree determination unit 101 determines the opening degree of the flow rate adjustment valve (the first flow rate adjustment valve 20) of the stem fuel supply line Ra on the basis of the fuel control signal command value according to the output of the gas turbine 1. The branch line flow rate determination unit 102 determines the opening degrees of each of the flow rate adjustment valves (the second flow rate adjustment valve 30, the third flow rate adjustment valve 40, and the fourth flow rate adjustment valve 50) of the plurality of branch lines (the first branch line R1, the second branch line R2, and the third branch line R3) branching from the stem fuel supply line Ra on the basis of the operation situation of the gas turbine 1. In a case where the variation in the combustion characteristics of the gas turbine 1 due to reduction of the pressure difference between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet is prevented, the correction value determination unit 103 increases the ratio of the third fuel control signal command value and increases the second fuel control signal command value on the basis of the pressure difference value between the fuel pressure upstream of the second fuel nozzle 602 and the corrected fuel pressure for the fuel pressure at the outlet.

SECOND EXAMPLE

Next, an example in which variation in combustion characteristics of the gas turbine 1 due to variation of a pressure difference between a fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at an outlet is prevented in the combustor 60 will be described.

Incidentally, in a case where the variation in the combustion characteristics of the gas turbine 1 due to the variation of the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 of the combustor 60 and the corrected fuel pressure for the fuel pressure at the outlet is prevented, a first fuel control signal command value is controlled on the basis of the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet.

For example, when a relationship between the first fuel distribution ratio and the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet or a relationship between the first fuel distribution ratio and fuel characteristics shown in FIG. 6 is established, in a case where the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet is equal to or less than Pr2 [MPa] from the relationship between the first fuel distribution ratio and the fuel characteristics, it is determined to perform correction increasing the first fuel distribution ratio. The pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet increases and it is possible to prevent the variation in the combustion characteristics of the gas turbine 1 by performing the correction increasing the first fuel distribution ratio in a case where the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet is equal to or less than Pr2 [MPa].

Note that the relationship between the first fuel distribution ratio and the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet may be determined by performing an experiment on the actual gas turbine 1 and on the basis of an experiment result thereof.

In addition, with respect to the example of the relationship between the first fuel distribution ratio and the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet shown in FIG. 6, it is determined to perform the correction increasing the first fuel distribution ratio in a case where the pressure difference is equal to or less than Pr2 [MPa], but the present invention is not limited thereto. The range of the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet determined to perform the correction increasing the first fuel distribution ratio is about 0.01 [MPa] to 0.1 [MPa].

The stem fuel valve opening degree determination unit 101 determines the opening degree of the flow rate adjustment valve (the first flow rate adjustment valve 20) of the stem fuel supply line Ra on the basis of the fuel control signal command value according to the output of the gas turbine 1. The branch line flow rate determination unit 102 determines the opening degrees of each of the flow rate adjustment valves (the second flow rate adjustment valve 30, the third flow rate adjustment valve 40, and the fourth flow rate adjustment valve 50) of the plurality of the branch branching from the stem fuel supply lines (the first branch line R1, the second branch line R2, and the third branch line R3) on the basis of the operation situation of the gas turbine 1. In a case where the variation in the combustion characteristics of the gas turbine 1 due to the reduction of the pressure difference between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet is prevented, the correction value determination unit 103 increases the ratio of the first fuel control signal command value on the basis of the pressure difference value between the fuel pressure upstream of the first fuel nozzle 601 and the corrected fuel pressure for the fuel pressure at the outlet.

The gas turbine 1 according to an embodiment of the present invention has been described above. In the gas turbine 1, the fuel control device 10 includes the stem fuel valve opening degree determination unit 101, the branch line flow rate determination unit 102, and the correction value determination unit 103. The stern fuel valve opening degree determination unit 101 determines the opening degree of the flow rate adjustment valve (the first flow rate adjustment valve 20) of the stem fuel supply line Ra on the basis of the fuel control signal command value according to the output of the gas turbine 1. The branch line flow rate determination unit 102 determines the opening degrees of each of the flow rate adjustment valves (the second flow rate adjustment valve 30, the third flow rate adjustment valve 40, and the fourth flow rate adjustment valve 50) of the plurality of branch lines (the first branching line R1, the second branching line R2, and the third branching line R3) branching from the stem fuel supply line Ra on the basis of the operation situation of the gas turbine 1. The correction value determination unit 103 determines the correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of the value of a pressure difference between the fuel pressure upstream of each of nozzles (the first fuel nozzle 601, the second fuel nozzle 602, and the third fuel nozzle 603) connected to the branch lines respectively and the corrected fuel pressure for the fuel pressure at the outlet.

Therefore, the fuel control device 10 can prevent the variation in the combustion characteristics of the gas turbine 1 occurred in a case where the pressure difference between the fuel pressure upstream of each of the nozzles of the combustor 60 and the corrected fuel pressure for the fuel pressure at the outlet varies.

Although the embodiment of the present invention has been described, the fuel control device 10 described above may have a computer system therein. In addition, procedures for processes described above are stored in a computer-readable recording medium in the form of a program and the processes described above are performed by the computer reading and executing the program. Here, as the computer-readable recording medium, there are a magnetic disk, a magneto-optical disc, a CD-ROM, a DVD-ROM, a semiconductor memory, and the like. In addition, the computer program may be distributed to the computer through a communication line and the computer receiving the distribution may execute the program.

In addition, the program described above may realize a part of the functions described above. In addition, the program described above may be a file that is able to realize the functions described above by a combination with a program recorded in the computer system in advance, so called a difference file (a difference program).

Although several embodiments of the present invention have been described, these embodiments are examples and do not limit the scope of the invention. Various additions, omissions, substitutions, and changes may be made to these embodiments without departing from the gist of the invention.

INDUSTRIAL APPLICABILITY

According to the fuel control device according to the embodiment of the present invention, it is possible to prevent variation in combustion characteristics of a gas turbine occurred in a case where a pressure difference between a fuel pressure upstream of each of the nozzles of a combustor and a corrected fuel pressure for the fuel pressure at an outlet varies.

Reference Signs List

1 Gas turbine

10 Fuel control device

20 First flow rate adjustment valve

30 Second flow rate adjustment valve

40 Third flow rate adjustment valve

50 Fourth flow rate adjustment valve

60 Combustor

70 Turbine body

101 Stem fuel valve opening degree determination unit

102 Branch line flow rate determination unit

103 Correction value determination unit

601 First fuel nozzle

602 Second fuel nozzle

603 Third fuel nozzle

Claims

1. A fuel control device comprising: a stem fuel valve opening degree determination unit configured to determine an opening degree of a flow rate adjustment valve of a stem fuel supply line serving as the basis of a plurality of branch lines on the basis of a fuel control signal command value according to an output of a gas turbine;a branch line flow rate determination unit configured to determine the opening degree of each flow rate adjustment valve of the branch line on the basis of an operation situation of the gas turbine; anda correction value determination unit configured to determine a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

2. The fuel control device of claim 1, wherein, in a case where the pressure difference between the fuel pressure upstream of a second fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is reduced, the correction value determination unit determines the correction value for increasing a third fuel control signal command value.

3. The fuel control device of claim 1, wherein, in a case where the pressure difference between the fuel pressure upstream of the second fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is in a range of from 0.1 megapascals to 1 megapascal, the correction value determination unit determines the correction value of the opening degree of each flow rate adjustment valve of the branch line.

4. The fuel control device of claim 1, wherein, in a case where the pressure difference between the fuel pressure upstream of a first fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is reduced, the correction value determination unit determines the correction value for increasing a first fuel control signal command value.

5. The fuel control device of claim 1, wherein, in a case where the pressure difference between the fuel pressure upstream of the first fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is in a range of from 0.01 megapascals to 0.1 megapascals, the correction value determination unit determines the correction value of the opening degree of each flow rate adjustment valve of the branch line.

6. A combustor comprising: a first fuel nozzle of which a flow rate is controlled by a first flow rate adjustment valve included in the fuel control device of claim 1;a second fuel nozzle of which a flow rate is controlled by a second flow rate adjustment valve included in the fuel control device; anda third fuel nozzle of which a flow rate is controlled by a third flow rate adjustment valve included in the fuel control device.

7. A gas turbine comprising: the fuel control device of claim 1; anda combustor including a first fuel nozzle of which a flow rate is controlled by a first flow rate adjustment valve included in the fuel control device, a second fuel nozzle of which a flow rate is controlled by a second flow rate adjustment valve included in the fuel control device, and a third fuel nozzle of which a flow rate is controlled by a third flow rate adjustment valve included in the fuel control device.

8. A fuel control method comprising: determining an opening degree of a flow rate adjustment valve of a stem fuel supply line serving as the basis of a plurality of branch lines on the basis of a fuel control signal command value according to an output of a gas turbine;determining the opening degree of each flow rate adjustment valve of the branch line on the basis of an operation situation of the gas turbine; anddetermining a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

9. A non-transitory computer-readable computer medium storing a program that causes a computer to execute: determining an opening degree of a flow rate adjustment valve of a stem fuel supply line serving as the basis of a plurality of branch lines on the basis of a fuel control signal command value according to an output of a gas turbine;determining the opening degree of each flow rate adjustment valve of the branch line on the basis of an operation situation of the gas turbine; anddetermining a correction value of the opening degree of each flow rate adjustment valve of the branch line on the basis of a value of a pressure difference between a fuel pressure upstream of each of nozzles connected to the branch lines respectively and a corrected fuel pressure for the fuel pressure at an outlet.

10. The fuel control device of claim 2, wherein, in a case where the pressure difference between the fuel pressure upstream of the second fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is in a range of from 0.1 megapascals to 1 megapascal, the correction value determination unit determines the correction value of the opening degree of each flow rate adjustment valve of the branch line.

11. The fuel control device claim 2, wherein, in a case where the pressure difference between the fuel pressure upstream of a first fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is reduced, the correction value determination unit determines the correction value for increasing a first fuel control signal command value.

12. The fuel control device of claim 2, wherein, in a case where the pressure difference between the fuel pressure upstream of the first fuel nozzle connected to the branch line and the corrected fuel pressure for the fuel pressure at the outlet is in a range of from 0.01 megapascals to 0.1 megapascals, the correction value determination unit determines the correction value of the opening degree of each flow rate adjustment valve of the branch line.

13. A combustor comprising: a first fuel nozzle of which a flow rate is controlled by a first flow rate adjustment valve included in the fuel control device of claim 2;a second fuel nozzle of which a flow rate is controlled by a second flow rate adjustment valve included in the fuel control device; anda third fuel nozzle of which a flow rate is controlled by a third flow rate adjustment valve included in the fuel control device.

14. A gas turbine comprising: the fuel control device of claim 4; anda combustor including a first fuel nozzle of which a flow rate is controlled by a first flow rate adjustment valve included in the fuel control device, a second fuel nozzle of which a flow rate is controlled by a second flow rate adjustment valve included in the fuel control device, and a third fuel nozzle of which a flow rate is controlled by a third flow rate adjustment valve included in the fuel control device.