JP2000356344A - Gas turbine combustion equipment and method for controlling its combustion state - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide combustion equipment to sufficiently prevent the generation of combustion vibration even in a case of a wide oscillation frequency without complicating constitution of a combustor and perform stable combustion. SOLUTION: Gas turbine combustion equipment comprises a plurality of fuel nozzles 12 to inject fuel in a combustion chamber; and a fuel feed system 16 to regulate and supply a fuel flow rate, corresponding to a gas turbine load, to the fuel nozzle group. Each fuel nozzle 12 is provided with a plurality of fuel injection means 12A, 12B, 22, and 23, and each fuel injection means is coupled to a fuel supply system through a fuel distributing device 18 to distribute a fuel flow rate.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a gas turbine combustion apparatus and a combustion state control method thereof.

[0002]

2. Description of the Related Art Generally, a gas turbine for driving a generator includes a compressor and a combustor, guides air compressed by the compressor to a combustor, and mixes the air with a predetermined amount of fuel in the combustor for combustion. Like that. The combustion gas generated by the combustion is configured to be injected into a turbine to drive the turbine and generate power by a generator connected to the gas turbine. Most of such combustors are composed of a mixed combustion system of a diffusion combustion system having excellent combustion stability and a premix combustion system effective for reducing NOx (nitrogen oxide). The ratio is increased to reduce NOx.

[0003] This premixed combustion system is effective in reducing NOx, but on the other hand, the flammable range is narrower than that of diffusion combustion, and when the premixed combustion ratio is increased, unstable combustion such as combustion oscillation is likely to occur. Combustion oscillations can cause serious wear, such as wear of the components of the combustor, backflow of the flame inside the premix burner, and damage to the gas turbine blades located downstream of the burnt parts inside the burner. It could lead to an accident.

As a measure for preventing such combustion vibration, for example, as disclosed in Japanese Patent Application Laid-Open No. 8-135970, the position of a fuel injection hole of a fuel nozzle is changed in the flow direction of a premixed gas. In addition, there is a method of dispersing periodic fluctuations of a fuel concentration distribution generated by combustion vibration to prevent an increase in combustion vibration level.

[0005]

As described above, premixed combustion is effective for reducing NOx in a gas turbine combustor, but premixed combustion has a narrower flammable range than diffusion combustion.
Unstable combustion such as combustion oscillation is likely to occur. The combustion vibration of the gas turbine combustor is determined by the natural frequency of the gas column determined by the structure and operating conditions (combustion temperature, premixed gas flow velocity, combustor pressure) of the gas turbine combustor, and the combustion of diffusion burners, premixed burners, etc. It is supposed that the heat energy fluctuates rapidly due to resonance with the fluctuation cycle of the heat energy generated by the instability.

One of the factors of unstable combustion between the diffusion burner and the premixed burner is considered to be flame interference between the diffusion flame and the premixed flame. That is, the diffusion flame formed by the diffusion burner and the premixed flame formed by the premixed burner interfere with each other. When the diffusion flame fluctuates, the premixed flame fluctuates under the influence of the fluctuation and the premixed flame fluctuates. The diffusion flame fluctuates due to the fluctuation of the mixed flame, and this fluctuation is repeated periodically to increase combustion oscillation.

[0007] In this respect, as in the above-mentioned known example, the position of the fuel ejection hole of the fuel nozzle is changed in the flow direction of the premixed gas, and the periodic fluctuation of the fuel concentration distribution accelerated by combustion vibration is dispersed. The method certainly has an effect on suppressing combustion oscillation. However, this method has a great effect on suppressing the combustion vibration of a certain specified frequency, but when the combustion vibration of a different frequency or a plurality of vibration frequencies is generated, a sufficient effect may not be exhibited. .

[0008] There are a large number of natural frequencies of the gas column of the gas turbine combustor, that is, a large number of combustion oscillation frequencies. When these combustion oscillation frequencies coincide with the fluctuation period of the flame accompanying combustion, combustion oscillation is generated. When developing a gas turbine combustor,
A combustion test was conducted to confirm the performance of the combustor, and the frequency and amplitude level of the combustion oscillation were confirmed and adjusted, and the product was usually manufactured. However, the frequency and amplitude level of the combustion vibration generated in the actual power plant often differ from the performance confirmation combustion test due to the boundary condition of the combustor that affects the combustion vibration characteristic and the difference in the amount of heat generated by the fuel. Therefore, there is a need for a technique for adjusting the combustion oscillation characteristics and the like at the time of test operation in an actual power plant. However, in the related art, there are few means for adjusting the combustion vibration and the like, and it has been considered that the structure must be changed by changing the combustor structure.

The present invention has been made in view of the foregoing, and it is an object of the present invention to prevent the generation of combustion vibration even at a wide range of vibration frequency without complicating the structure of the combustor. Another object of the present invention is to provide a gas turbine combustion apparatus of this type capable of performing stable combustion.

[0010]

That is, the present invention relates to a gas turbine combustion apparatus including a fuel nozzle for injecting fuel into a combustion chamber and a fuel supply system for supplying fuel to the fuel nozzle. A plurality of fuel ejection means having different flame patterns are provided, and each of the fuel ejection means is connected to the fuel supply system via a fuel distribution device for distributing a supplied fuel flow rate, thereby achieving an intended purpose. It is something to do.

Further, the present invention provides a gas turbine combustion apparatus having a plurality of fuel nozzles for injecting fuel into a combustion chamber, and a fuel supply system for adjusting a fuel flow rate according to a gas turbine load to the fuel nozzle group. In the above, each of the fuel nozzles is provided with a plurality of fuel ejection means having different fuel ejection states, and each of the fuel ejection means is connected to the fuel supply system via a fuel distribution device for distributing a supplied fuel flow rate. It is intended to be combined.

According to another aspect of the present invention, there is provided a gas turbine combustion apparatus comprising: a plurality of fuel nozzles for injecting fuel into a combustion chamber; and a fuel supply system for adjusting a fuel flow according to a gas turbine load to the fuel nozzle group. A fuel distributing means for distributing fuel from a fuel supply system to the fuel ejecting means between the fuel ejecting means and the fuel supply system; A device is provided, and a combustion state detection device for detecting a combustion state in the combustion chamber is provided in the combustion chamber, and a fuel distribution amount of the fuel distribution device is controlled by a combustion state detection signal from the combustion state detection device. It was done.

In this case, the fuel ejection means is formed so as to have fuel ejection holes having different ejection speeds, ejection flow rates, or ejection directions of the fuel. Further, each of the fuel injection means performs diffusion combustion or premix combustion.

Further, the present invention provides a gas turbine combustion system having a fuel supply system for adjusting and supplying a fuel flow rate according to the load of a gas turbine, and a plurality of fuel nozzles for injecting fuel supplied from the fuel supply system into a combustion chamber. In the combustion state control method of the device, each of the fuel nozzles is provided with a plurality of fuel ejection means having different flame patterns, and the fuel flow supplied to each of the fuel ejection means is distribution-adjusted according to the degree of combustion. The combustion state in the combustion chamber is controlled.

That is, in the gas turbine combustion apparatus formed as described above, the fuel nozzle is provided with a plurality of fuel ejection means having different flame patterns, and each of the fuel ejection means distributes a fuel supply flow rate. Since it is formed so as to be connected to the fuel supply system via an adjustable fuel distribution device, it is possible to control the flame pattern by controlling the ejection method of the fuel ejected from the fuel nozzle. As a result, without complicating the configuration of the combustor, that is, without changing the size and configuration of the combustor, it is possible to sufficiently prevent the occurrence of combustion vibration even at a wide range of vibration frequency, and achieve stable combustion. It is possible to do it.

[0016]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below in detail with reference to the illustrated embodiments. FIG. 1 shows a cross section of a main part of a gas turbine plant provided with the gas turbine combustion device and a fuel nozzle portion. This gas turbine plant mainly includes a gas turbine 1 and this gas turbine 1
And a compressor 2 for obtaining compressed air for combustion, a combustor 3 and the like.

The compressed air discharged from the compressor 2 is guided to the combustor 3 and burns together with the fuel supplied from the nozzles in a combustion chamber 5 formed inside the combustor inner cylinder 4.
The combustion gas generated by the combustion is injected into the gas turbine 1 via the transition piece 6, drives the gas turbine 1, and is configured to generate electric power by the generator 7 connected to the gas turbine.

The main structure of the combustor 3 is composed of a fuel supply system and an air supply system, which are mounted on a pressure vessel 10 hermetically closed by an outer cylinder 8 and an end cover 9. An auxiliary chamber 11 having a smaller diameter than the inner cylinder 4 is provided upstream of the combustor inner cylinder 4 (as viewed from the flow direction of the combustion gas).
A diffusion fuel nozzle 12 is provided at an upstream position of the fuel cell 1.

A premix burner 13 is provided at an outer peripheral position of the sub-chamber 11, and a premix fuel nozzle 14 is disposed upstream of the premix burner 13. Further, on the downstream side of the premix burner 13, a flame stabilizer 15 for stabilizing the premix flame is installed. The diffusion fuel nozzle 12 is provided with a diffusion fuel supply system 16 for controlling the flow rate of the diffusion fuel, and the premix fuel nozzle 14 is provided with a premix fuel supply system 17 for controlling the flow rate of the premix fuel.

In the first embodiment according to the present invention, the diffusion fuel nozzle 12 is provided with a plurality of fuel ejection means having different flame patterns. That is, the diffusion fuel nozzle 12 is
Diffusion fuel nozzles 12A and 12 with different flame patterns
B, and a fuel distribution device 18 that distributes the diffusion fuel to the fuel pipe 19 connected to the diffusion fuel nozzle 12A and the fuel pipe 20 connected to the diffusion fuel nozzle 12B at the downstream position of the diffusion fuel supply system 16. is there.

Generally, the fuel nozzle structure of a gas turbine combustor is determined by the combustion stability in the operating environment of the fuel nozzle, the exhaust gas characteristics, and the like, and its flame pattern (flame shape, flame formation position, etc.) depends on the fuel nozzle. It is determined by the operating environment and fuel flow rate. Therefore,
In the fuel nozzle of the conventional example, when the flow rate of fuel and the flow rate of air supplied to the fuel nozzle are determined, the flame pattern is determined by the operating environment of the fuel nozzle, and it is difficult to change the flame pattern under the same combustion condition.

On the other hand, as described above, one of the causes of the combustion oscillation is the interference between the diffusion flame and the premixed flame. Flame interference is often caused by each other's flame pattern, etc.
That is, it is possible to suppress the occurrence of combustion oscillation.

In this embodiment, the diffusion nozzles 12 are different from the diffusion nozzles 12A and 12B having different flame patterns.
Therefore, while the flow rate of the fuel supplied from the diffusion fuel supply system 16 is kept constant (the flow rate according to the gas turbine load), the distribution of the flow rate of the fuel supplied to the diffusion nozzles 12A and 12B is determined by the fuel distribution device 18. By controlling, it is possible to change the flame pattern,
It is possible to suppress the occurrence of combustion oscillation.

FIG. 2 schematically shows a flame pattern of the diffusion nozzle 12 and the premix burner 13 shown in FIG. Under high load operation conditions, the premixed combustion ratio is determined in consideration of exhaust gas characteristics and reliability, and the diffusion fuel supply system 16
Thus, the flow rate of the fuel supplied to the diffusion nozzle 12 is determined. This figure shows a change in the diffusion flame pattern formed when the fuel distribution device 18 is controlled while the flow rate of the fuel supplied from the diffusion fuel supply system 16 is kept constant.

FIG. 2A shows a case where all the fuel supplied from the diffusion fuel supply system 16 is supplied to the diffusion nozzle 12A. An air swirler 21 is formed in the diffusion nozzle 12 to generate a swirling flow in the air for diffusion combustion. Diffusion nozzle 12A
Is formed so as to follow the swirling air flow, so that the flame of the diffusion nozzle 12A is formed to extend substantially in the radial direction of the combustor as shown in FIG. 2A. .

On the other hand, FIG. 2C shows a flame pattern when all the fuel supplied from the diffusion fuel supply system 16 is supplied to the diffusion nozzle 12B. Diffusion nozzle 12
Since the fuel ejection hole 23 of B is formed so that fuel is ejected in the axial direction of the combustor, the flame of the diffusion nozzle 12B flows in the axial direction of the combustor as shown in FIG. It is formed to extend. FIG. 2B shows the diffusion nozzle 1
It shows a flame pattern when fuel is supplied to 2A and 12B.

FIG. 2 (a) shows an image in which the diffusion flame 24 of the diffusion nozzle 12A and the premixed flame 25 of the flame stabilizer 15 interfere with each other. When the diffusion flame 24 fluctuates, the fluctuation causes the premixed flame 25 to fluctuate. Since the premixed flame 25 has a high combustion rate, fluctuations in the premixed flame 25 cause heat generation fluctuations. When the fluctuation period matches the air column resonance frequency of the combustor, combustion vibrations may increase. In such a case, in the present embodiment, the diffusion flame pattern can be changed from the state shown in FIG. 2A to the state shown in FIG. 2C without changing the diffusion fuel flow rate by controlling the fuel distribution device 18. This makes it possible to suppress the interference between the diffusion flame and the premixed flame and control the combustion oscillation.

As described above, the method of controlling the flame pattern has been described as a method of suppressing the combustion vibration. However, the flame pattern is closely related not only to the combustion vibration but also to the exhaust gas characteristics and the metal temperature characteristics of the components of the combustor. Therefore, by controlling the flame pattern as in the present embodiment, the operation adjustment range of the combustor is expanded, and as a result, the operating margin for stable combustion is increased, and the reliability of the combustor is ensured. It becomes possible.

FIG. 1B and FIGS. 3 to 6 and FIG.
FIG. 1 shows an embodiment and a modified example of a fuel nozzle to which the present invention is applied. FIG. 1B is an enlarged view of the diffusion fuel nozzle 12 described in the first embodiment. The fuel ejection hole 22 is formed substantially in the radial direction of the combustor.
3 is formed in the axial direction of the combustor.

FIG. 3 shows a second embodiment in which ejection holes 26 and 27 having different ejection angles are formed on the same circumference of the diffusion fuel nozzle 28. In the diffusion fuel nozzle 12 described in FIG. 1, when fuel is supplied to the diffusion fuel nozzles 12A and 12B by the fuel distribution device 18, the diffusion flame formed by the diffusion fuel nozzle 12A and the diffusion flame formed by the diffusion fuel nozzle 12B. Although it is conceivable that the flames are formed separately, the diffusion fuel nozzle 28 shown in FIG. 3 has a fuel ejection position on the same circumference, so that the flame is difficult to be dispersed and burns more stably. It can be considered that the same effect as that of the first embodiment can be expected.

The method of changing the ejection direction of the fuel ejection holes for controlling the flame pattern has been described above. As a method of controlling the flame pattern, a method of controlling the ejection speed by changing the diameter of the ejection holes is described. It is also conceivable to change the shape of the nozzle or the outlet, and these methods can be expected to have the same effect as in the first embodiment.

Next, a third embodiment according to the present invention will be described with reference to FIG. FIG. 5 shows the present invention applied to a pilot burner 31 provided with a diffusion fuel nozzle 29 and a premixed fuel nozzle 30. The pilot burner 31 includes a diffusion fuel nozzle 29, a premixed fuel nozzle 30, and a swirl vane 3
2, a pipe 33 is connected to the diffusion fuel nozzle 29, and a pipe 20 is connected to the premixed fuel nozzle 30. The pipes 19 and 20 are connected to the fuel distribution device 18, and the flow rate is controlled by the diffusion fuel supply system 16.
The fuel ejection hole 34 of the diffusion nozzle 29 is located on the downstream side of the swirl vanes 32 and ejects fuel to form a diffusion flame. The premixed fuel nozzle 30 is located upstream of the swirl vanes 32, and the ejected fuel mixes with air to form a premixed flame.

In this embodiment, when the fuel distribution device 18 supplies the entire flow rate to the diffusion fuel nozzle 29, diffusion combustion is performed.
When the entire flow rate is supplied to the premixed fuel nozzle 30, it is possible to perform the entire premixed combustion. Therefore, when the gas turbine is started, diffusion combustion is performed to ensure the stability of the combustor, and during load operation, premixed combustion is performed to control exhaust gas characteristics. Further, the fuel distribution device 1
By controlling the diffusion flame and the premixed flame by the use of No. 8, the combustion oscillation can be suppressed.
The same effect as that of the embodiment can be expected.

Next, a fourth embodiment according to the present invention will be described with reference to FIG. This figure shows that premixed burners 35 are provided with premixed fuel nozzles 36 and 37 having different fuel ejection positions and ejection methods.
The premixed fuel nozzle 36 has a pipe 38
However, a pipe 39 is connected to the premixed fuel nozzle 37. The pipes 38 and 39 are connected to a fuel distribution device 40, and the flow rate is controlled by the premixed fuel supply system 17. The premixed fuel nozzles 36 and 37 are located downstream of the swirl vanes 41 and eject fuel to mix with air to form a mixture. Since the fuel concentration distribution of the premixed burner 35 has a strong influence on the premixed flame pattern, controlling the fuel concentration distribution of the premixed burner 35 can suppress combustion oscillations and improve exhaust gas characteristics. It is.

For example, the premixed fuel nozzle 36 has a structure for ejecting fuel to the outer peripheral side of the premixed burner 35, and the premixed fuel nozzle 37 has a structure for ejecting fuel to the inner peripheral side of the premixed burner 35. . When it is desired to increase the fuel concentration distribution on the inner peripheral side of the premix burner 35 in order to ensure the stability of the flame, the fuel distribution device 40 is adjusted so that the flow rate of fuel injected from the premix fuel nozzle 37 increases. . In general, nitrogen oxides can be reduced by making the fuel concentration distribution uniform. However, in this embodiment, the flow rate of fuel injected from the premixed fuel nozzles 36 and 37 is controlled by the fuel distribution device 4.
By adjusting the value to 0, the fuel concentration distribution can be controlled. As a result, combustion stability is ensured and low NO
x can be achieved, and the same effect as in the first embodiment can be expected.

Next, a fifth embodiment according to the present invention will be described with reference to FIG. FIG. 7 shows a first embodiment in which a combustion vibrometer 42 for measuring the combustion vibration of the combustor is installed, and the combustion vibration level is determined to determine the diffusion fuel supply system 16, the premixed fuel supply system 17, and the fuel distribution device. Arithmetic unit 44 for controlling 18
Is installed.

Since the combustion vibration characteristic of the gas turbine combustor has a property of changing according to the air temperature, the air humidity and the calorific value of the fuel, the fifth embodiment detects the combustion vibration level and increases the combustion vibration level. It is configured to control the fuel distribution device 18 so as not to do so. For example, there is a method in which a plurality of threshold values are provided for the combustion vibration level, and when the combustion vibration level exceeds the threshold value, the fuel flow rate supply system 16 is controlled to set the distribution to a predetermined value. Thus, a stable combustion state can be ensured without an increase in combustion oscillation. Further, in the present embodiment, in addition to the combustion vibration level, a detector 43 for detecting the metal temperature of the combustor, the exhaust gas characteristics, and the like is used in combination, and the flame pattern is controlled in accordance with the detection results to further improve the reliability. Can be improved.

In the above description, the case of providing the fuel nozzles with different flame patterns in the fuel nozzle has been described by taking as an example the case of a nozzle having a concentric double structure. However, the configuration of the fuel nozzle and the configuration of the fuel nozzle are described. The relationship between the fuel injection hole and the fuel injection hole is not limited to the above-described configuration. For example, as shown in FIG.
x, 12y, and 12z, and fuel injection holes 22 and 23 having different injection directions may be provided for each of the fuel injection holes. The fuel injection holes may be formed as shown in FIG. Alternatively, the ejection holes 22a and 22b having different hole diameters D1 and D2 (D1> D2) and ejection directions may be provided in various combinations.

As described above, in the gas turbine combustion apparatus formed as described above, the fuel nozzle is provided with a plurality of fuel injection holes having different flame patterns, and each of the fuel injection holes has Each is formed so as to be connected to the fuel supply system via a fuel distribution device that can adjust the distribution of the fuel supply flow rate, so that the flame pattern is controlled by controlling the ejection state of the fuel ejected from the fuel nozzle. As a result, it becomes possible to suppress combustion oscillation and improve exhaust gas characteristics, and in this case, the physical size of the fuel nozzle is not changed at all.

[0040]

As described above, according to the present invention, the occurrence of combustion oscillation can be sufficiently prevented even at a wide range of oscillation frequency without complicating the structure of the combustor, and stable combustion can be achieved. Can be obtained.

[Brief description of the drawings]

FIG. 1 is a vertical sectional side view showing an embodiment of a gas turbine plant provided with a gas turbine combustion device of the present invention, and a vertical sectional side view of a fuel nozzle used in the combustion device.

FIG. 2 is an explanatory diagram of a flame pattern of a gas turbine combustion device.

FIG. 3 is a sectional view of a main part showing an embodiment of a fuel nozzle used in the gas turbine combustion device of the present invention.

FIG. 4 is a sectional view of a main part showing another embodiment of the fuel nozzle used in the gas turbine combustion device of the present invention.

FIG. 5 is a sectional view of a main part showing another embodiment of the fuel nozzle used in the gas turbine combustion device of the present invention.

FIG. 6 is a sectional view of a main part showing another embodiment of the fuel nozzle used in the gas turbine combustion device of the present invention.

FIG. 7 is a vertical sectional side view showing another embodiment of the gas turbine combustion device of the present invention.

FIG. 8 is a sectional view of a main part showing another embodiment of the fuel nozzle used in the gas turbine combustion device of the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Gas turbine, 2 ... Compressor, 3 ... Combustor, 12 ... Diffusion fuel nozzle, 16 ... Diffusion fuel supply system, 17 ... Premix fuel supply system, 18 ... Fuel distribution device, 30, 36, 37 ... Premix Fuel nozzle, 35: premix burner, 42: combustion vibrometer, 43: detector, 44: arithmetic unit.

 ──────────────────────────────────────────────────続 き Continuing from the front page (72) Inventor Masaya Otsuka 7-2-1, Omika-cho, Hitachi City, Ibaraki Pref. Hitachi, Ltd. Power and Electricity Development Division (72) Inventor Tomoya Murota Omika-cho, Hitachi City, Ibaraki Prefecture 7-2-1, Hitachi, Ltd. Power and Electricity Development Division (72) Inventor Narika Kobayashi 7-2-1, Omika-cho, Hitachi City, Ibaraki Prefecture Hitachi, Ltd. Power and Electricity Development Division (72 Inventor Fumiharu Moriwaki 3-1-1, Komachi, Hitachi-shi, Ibaraki Pref. Hitachi, Ltd.

Claims (7)

[Claims] A fuel nozzle for injecting fuel into a combustion chamber;
A gas turbine combustion device comprising a fuel supply system for supplying fuel to the fuel nozzle, wherein the fuel nozzle is provided with a plurality of fuel ejection means having different flame patterns, and each of the fuel ejection means is provided with a fuel supply. A gas turbine combustion device, wherein the gas turbine combustion device is connected to the fuel supply system via a fuel distribution device that distributes a flow rate. 2. A gas turbine combustion apparatus comprising: a plurality of fuel nozzles for injecting fuel into a combustion chamber; and a fuel supply system for adjusting and supplying a fuel flow according to a gas turbine load to the fuel nozzle group. Each fuel nozzle is provided with a plurality of fuel ejection means having different fuel ejection states, and each of the fuel ejection means is connected to the fuel supply system via a fuel distribution device for distributing a supplied fuel flow rate. A gas turbine combustion device, characterized in that: 3. A gas turbine combustion apparatus comprising: a plurality of fuel nozzles for injecting fuel into a combustion chamber; and a fuel supply system for adjusting and supplying a fuel flow rate to the fuel nozzle group according to a gas turbine load. A plurality of fuel ejection means having different flame patterns are provided for each fuel nozzle, and a fuel distribution device for distributing fuel from a fuel supply system to the fuel ejection means is provided between the fuel ejection means and the fuel supply system. And a combustion state detection device for detecting a combustion state in the combustion chamber is provided in the combustion chamber, and a fuel distribution amount of the fuel distribution device is controlled by a combustion state detection signal from the combustion state detection device. Characteristic gas turbine combustion device. 4. The fuel ejection means according to claim 1, wherein said fuel ejection means has a fuel ejection speed,
The gas turbine combustion device according to any one of claims 1 to 3, further comprising a fuel ejection hole having a different ejection flow rate or ejection direction. 5. The gas turbine combustion device according to claim 1, wherein each of the fuel injection means performs diffusion combustion or premix combustion. 6. Combustion of a gas turbine combustion device having a fuel supply system for adjusting and supplying a fuel flow rate according to a load of a gas turbine and a plurality of fuel nozzles for injecting fuel supplied from the fuel supply system into a combustion chamber. In the state control method, each of the fuel nozzles is provided with a plurality of fuel ejection means having different flame patterns, and the flow rate of fuel supplied to each of the fuel ejection means is adjusted and distributed according to the degree of combustion. A method for controlling a combustion state of a gas turbine combustion device, wherein the combustion state of the gas turbine is controlled. 7. The gas turbine combustion apparatus according to claim 6, wherein the generation of the different flame patterns is performed by changing a fuel injection speed, an injection flow rate, or an injection direction from the fuel nozzle. Combustion state control method.