JPH0933010A - Gas turbine combustor and premixed fuel control method thereof - Google Patents

Abstract

(57) [Summary] [Object] To provide a gas turbine combustor that has a simple structure, is excellent in responsiveness and reliability, and can reduce combustion oscillation. A gas turbine combustor disposed upstream of a combustion chamber and provided with a premixed combustion burner for burning the gas mixed by the premixer 8, wherein a fuel injection port portion in the premixer 8 is provided. , A fuel branching means 16 for branching the injected fuel into the inside of the premixer and the outside of the premixer, and between the fuel branching means and the combustion chamber 3, a pressure guiding pipe 18 connecting the two is provided. At the same time, the fuel branch means side opening of the pressure guiding tube is formed so that the fuel injected into the fuel branch means is branched and supplied to the inside of the premixer as the gas pressure in the combustion chamber becomes higher.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION The present invention relates to improvements in gas turbine combustors and their methods of operation, in particular with a premixer,
The present invention relates to a gas turbine combustor configured to perform premixed combustion.

[0002]

2. Description of the Related Art In a gas turbine combustor of this type that has been generally adopted conventionally, a premixed combustion system is adopted as a measure for reducing NOx. This premixed combustion system generates a lean air-fuel mixture in advance and holds the air-fuel mixture with a flame stabilizer installed upstream of the combustion chamber to form a low-temperature premixed flame. , NO in exhaust gas
The x concentration is reduced.

The premixed combustion method is an effective combustion method for reducing the NOx concentration of exhaust gas as described above, but on the other hand, the premixed combustion method causes a decrease in flame stability with a decrease in flame temperature. Therefore, there is a possibility that combustion vibration may be induced by the flapping of this unstable flame. As a current countermeasure for reducing the combustion vibration, a method of improving the flame holding performance of the flame stabilizer to suppress flapping of the flame or dispersing the flame cycle by dividing the flame is adopted.

Further, since the oscillation condition of the combustion vibration is determined by the phase difference between the fluctuation of the heat value of the flame and the fluctuation of the pressure,
As a conventional combustor, there is known a combustor in which the fuel flow rate is changed according to the combustion vibration and the fluctuation of the heat generation amount is controlled to reduce the combustion vibration.

[0005] Incidentally, examples of those related to this type of gas turbine combustor are, for example, JP-A-4-98014, JP-A-61-115829, and JP-A-6-115829.
No. 1-132729 is cited.

[0006]

Even in the combustor in which various measures are taken against the NOx reduction and the combustion oscillation as described above, when the flame holding performance of the flame holder is further improved, the premixer is used. Pressure loss on the downstream side may increase, combustion efficiency may deteriorate, and even slight fluctuations in the flame cause fluctuations in the amount of heat generation and pressure. May occur.

Further, when combustion fluctuations occur, when the fuel flow rate is changed according to the pressure fluctuations to control the fluctuations in the amount of heat generation, if there is a mechanically moving part like a conventional combustor, the response will occur. There is a risk that it may cause a failure due to heat generated by combustion and the like. When an active control device that converts a signal of pressure fluctuation into an electric signal and amplifies it and changes the fuel flow rate using the electric signal is provided,
There is also a dislike that the control method becomes complicated and the cost increases.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a gas turbine combustor of this type which has a simple structure, is excellent in responsiveness and reliability, and is capable of reducing combustion vibration, and a pre-combustor. A mixed fuel control method is provided.

[0009]

That is, the present invention provides a gas turbine combustor provided upstream of a combustion chamber and provided with a premixed combustion burner for burning gas mixed by the premixer. A fuel branching means for branching the injected fuel into the inside of the premixer and the outside of the premixer is provided at the fuel jetting section in the mixer, and both are provided between the fuel branching section and the combustion chamber. With a pressure guiding tube connecting
The fuel branch means side opening of the pressure guiding tube is formed so that the fuel injected into the fuel branch means is branched and supplied to the inside of the premixer as the gas pressure in the combustion chamber becomes higher. Is achieved.

Further, a premix combustion burner which is arranged upstream of the combustion chamber and burns the gas mixed by the premixer is provided, and the amount of fuel supplied to the premixer depends on the turbine load. In a premixed fuel control method for a gas turbine combustor controlled accordingly, a fuel branch in which the injected fuel is branched into a premixer inside and a premixer outside at a fuel injection port in the premixer. A means is provided, and the fuel is branched at this branch portion by the gas pressure in the combustion chamber, and the flow rate of the fuel flowing into the premixer is controlled to control the degree of mixture of the air-fuel mixture. .

[0011]

It is known that the condition for producing combustion oscillation is Rayleigh oscillation condition when the phase difference between the variation of the heat generation amount and the variation of the pressure is smaller than π / 2. The following loop exists as a combustion vibration transmission system. First, fluctuations in the amount of heat generated in the combustion chamber create pressure fluctuations as thermodynamic work. Due to the pressure loss due to this pressure fluctuation, the premixed gas flow rate and the air flow rate are changed, and the degree of mixing of fuel and air is changed. This change in the degree of mixing changes the combustion state again, leading to a change in the calorific value. Through such a feedback mechanism, the combustion oscillation oscillates and is amplified in a self-excited manner. Further, when an acoustic air resonance phenomenon that depends on the shape and temperature of the combustion chamber is added to this, combustion oscillation further increases.

Therefore, in order to reduce combustion oscillation,
A means having a negative feedback mechanism for reducing the vibration may be added to each variation amount of the loop. For example, when the pressure increases due to the fluctuation of the calorific value, the pressure loss increases and the air flow rate flowing into the premixer decreases, so that the fuel concentration of the premixed gas increases. here,
If a control means is provided to reduce the flow rate of the fuel flowing into the premixed air when the pressure increases, a negative feedback mechanism is added to the combustion vibration transmission system in the direction of suppressing the vibration.

According to the present invention, when the pressure fluctuation or the fluctuation of the air flow rate or the fluctuation of the premixed gas flow rate occurs, the fluctuation quantity is directly applied to the fuel flow to passively control the fuel flow rate flowing into the premixer. In addition, it can be controlled by a method having no mechanical moving parts.

As a method of controlling the fuel flow using the pressure fluctuation, the Coanda effect can be used. When the fuel nozzle is provided as in the present invention and the fuel is discharged into the fluid in a certain region from the fuel nozzle in a torus state, a pressure drop such as that of the surrounding fluid is generated around the fuel discharge port. Occurs in. The Coanda effect is a phenomenon in which the discharge direction of the fuel flow changes due to the uneven pressure drop. By transmitting the pressure fluctuation generated in the combustor to a certain pressure drop region around the fuel discharge port through the pressure guiding pipe, it becomes possible to control the fuel discharge direction according to the pressure fluctuation.

Further, when a certain amount of fuel is discharged at an angle with respect to the flow direction of the air or the premixed gas as in the present invention, the flow line of the fuel flows according to the flow velocity of the air or the premixed gas. The orbit changes. In this way, it becomes possible to control the fuel discharge direction according to the flow rate variation of air or premixed air.

Further, by distributing the above-mentioned fuel discharge direction into the premixer and the air flow for diffusion in accordance with pressure fluctuations or fluctuations in the flow rate of air or premixed gas, the air and fuel in the premixer are separated. The degree of mixing can be controlled. Similarly, the fuel-air ratio of the premixed gas can be controlled by distributing the fuel discharge direction to the upstream side and the downstream side of the air or the premixed gas.

[0017]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below in detail with reference to the illustrated embodiments. FIG. 1 shows the gas turbine combustor in cross section. The combustor is surrounded by an outer cylinder wall 1, a combustion chamber 3 surrounded by an inner cylinder wall 2, a diffusion swirl burner 4 for diffusive combustion,
It comprises a premixer 8 for mixing fuel and air, and a fuel and air supply device.

The diffusion swirl burner 4 installed on the central axis of the combustor swirls the diffusion combustion air 12c by the swirl vanes 5, and further mixes the fuel discharged from the fuel discharge port 6 with the combustion chamber 3 to diffuse it. Form a flame 7. The premixer 8 installed around the diffusion swirl burner 4 premixes the fuel discharged from the premixing fuel nozzle 9 with the premixing air 12b to generate a premixed gas, and the combustion downstream of this premixed gas is performed. The flame stabilizer 10 provided at the inlet of the chamber 3 forms the premixed flame 11 to hold the flame.

The fuel is diffusion fuel 21a and premixed fuel 21.
b and the control fuel 21c for vibration suppression are respectively supplied to the diffusion swirl burner 4, the premixer 8 and the plurality of fuel branching devices 16. The fuel branching device 16 is the fuel supply pipe 1
7, a pressure conduit 18 that guides pressure fluctuations near the premixed flame 11 at the premixed gas outlet, and a premixing branch pipe 19 that supplies fuel to the premixer 8 and a diffusion pipe that supplies fuel to the diffusion air 12c. A branch pipe 20 is installed.

The pressure conduit 18 is installed near the premixed flame 11 in which the amplitude of pressure fluctuation due to combustion vibration is large. The fuel branching device 16 includes the fuel supply pipe 1
7, the flow direction of the fuel 21c supplied from
The pre-mixing branch pipe 19 or the diffusion branch pipe 20 can be selected according to the amplitude of the pressure fluctuation detected at 8.

The main air 12a discharged from the compressor 14 is
It is supplied to the diffusion swirl burner 4 and each premixer 8 through an air passage surrounded by the outer cylinder wall 1 and the inner cylinder wall 2. Further, the high-temperature and high-pressure combustion gas 13 generated in the combustion chamber is sent to the turbine 15 to generate electricity.

As an example of the method of operating this combustor, first, the diffusion swirl burner 4 is ignited to form a diffusion flame 7. In this state, the partial load operation of the gas turbine can be performed by adjusting the flow rate of the fuel 21a supplied to the diffusion swirl burner 4. Next, the fuel 21b is supplied to the premixer 8 and ignited by the diffusion flame 7, and the flameholder 10 installed upstream of the premixer 8 forms the premixed flame 11. After this N
In order to reduce Ox, the flow rate of the fuel 21a of the diffusion swirl burner 4 is narrowed down, and when the premixed flame 11 can hold flame only with the flame stabilizer 10, the supply of the diffusion fuel 21a is stopped, Extinguish diffusion flame 7. Further, the fuel concentration of the premixture and the air flow rate are increased until the rated load operation of the gas turbine.

Combustion vibration is caused when the amount of heat generated in the combustion chamber and the pressure increase, and the energy applied to the vibration increases.
It grows gradually. That is, the combustion vibration becomes remarkable at or near the rated load of the gas turbine combustor. When vibration occurs in the combustion state at or near the rated load, the vibration suppressing fuel 21c is supplied to the fuel branching device 16 through the fuel supply pipe 17.

The flow rate of the control fuel 21c to be supplied is the premixed fuel 21b discharged from the fuel nozzle 9 of the premixer 8.
The flow rate of the premixed fuel 21b is reduced to about several percent of the flow rate of the control fuel 21c.

An example of the structure of the fuel branching device 16 used in this embodiment is shown in FIGS. 2 and 3. 2 shows the case where the control fuel 21c is discharged to the premixer 8 side, and FIG. 3 shows the case where the control fuel 21c is discharged to the diffusion side.

In the fuel branching device 16, a fuel supply pipe 17, a pressure conduit 18, a premixing branch pipe 19 and a diffusion branch pipe 20 are connected as shown in the figure. The control fuel 21c that has passed through the fuel supply pipe 17 is discharged as a torrent in an enlarged portion provided downstream of the control fuel 21c. The pressure conduit 18 introduces a pressure fluctuation near the premixing flame 11 to the premixing pipe 19 side installed near the fuel nozzle 9, and the discharge direction of the fuel flow is premixed due to the amplitude of this pressure fluctuation. It will be determined whether it will be the branch pipe 19 for diffusion or the branch pipe 18 for diffusion.

Next, the operating principle of the fuel branching device 16 will be described. In the enlarged portion provided at the outlet of the fuel supply pipe 17, the fluid around the fuel mound is entrained in the mound to reduce the pressure and form a low-pressure vortex region 22 around the mound. Here, when the flow path is bent in the upstream part of the mound, the entrainment in the bent direction becomes active, so that the low-pressure vortex region 22
The decompression of the torus becomes remarkable, and the trajectory of the tomb is bent in the same direction.

If the pressure introduced by the pressure conduit 18 increases in the state of FIG. 2, the premixing pipe side 1
The pressure in the low-pressure vortex region 22 formed in 9 also increases, and the torrent trajectory is attracted to the low-pressure vortex region 22 formed in the diffusion branch pipe 20. The torch trajectory is a branch pipe for diffusion 2
When it is bent to the 0 side, the decompression of the low pressure vortex region 22 on the diffusion side becomes remarkable, and as a result, as shown in FIG.
The c is discharged into the diffusion branch pipe 20. When the pressure introduced by the pressure conduit 18 decreases in this state, the control fuel 21c is again discharged to the premixing branch pipe 19 side by the effect opposite to the above phenomenon.

In accordance with the above principle, the fuel branching device 1
6 discharges the control fuel 21c into the premixer 8 when the pressure in the vicinity of the premixed flame 11 is small, and into the diffusion air 12c when the pressure is large.

The conditions for operating the fuel branching device 16 mainly depend on the device shape, the velocity of the fuel jet and the pressure fluctuation range. There is a velocity gradient between the jet of fuel and the surrounding fluid. If the fuel injection velocity is sufficiently high, the surrounding fluid is entrained by a large velocity gradient, and the low pressure vortex region 2
2 can be formed. If the pressure difference between the pressure in the low-pressure vortex region 22 and the ambient pressure is the same or larger than the amplitude of the pressure fluctuation due to combustion oscillation, or larger than the amplitude width, the trajectory of the fuel torso can be changed by the pressure fluctuation. It will be possible. Further, in order to improve the responsiveness of the fuel branch, it is necessary to reduce the opening area of the fuel supply pipe 17 and form a thin fuel flow.

When the inclination angles of the premixing branch pipe 19 and the diffusion branch pipe 20 with respect to the axial direction of the fuel supply pipe 17 are small, the bent fuel tracks reattach to the side walls of the respective pipes. And the flow becomes stable. Therefore, in order to activate the fuel branching device 16 only when combustion oscillation occurs, the inclination angle of the premixing branch pipe 19 is made smaller than the inclination angle of the diffusion branch pipe 20, and the pressure in the pressure conduit 18 fluctuates. When there is no fuel, the fuel is allowed to flow in the premixer 8. Further, in addition to the inclination angles of the premixing branch pipe 19 and the diffusion branch pipe 20, the distance from the fuel discharge port to the branch wall 23 and the shape of the branch wall 23 are different from the pressure fluctuation width introduced by the pressure conduit 18. The conditions for the fuel to diverge.

As a condition for reducing the combustion oscillation, the fluctuation of the fuel discharged from the fuel branching device 16 to the premixer 8 may act so as to cancel the fluctuation of the fuel-air ratio of the premixed gas. To this end, it is necessary to set the lengths of the pressure conduit 18 and the premixing branch pipe 19 in consideration of the time difference from the pressure fluctuation to the fuel-air ratio fluctuation. The time τp required for the pressure fluctuation to be transmitted into the fuel branching device 16 is expressed as follows: sonic velocity is a and pressure conduit length is Lp.

[0033]

## EQU1 ## τp = Lp / a (1)

Further, the time τf for discharging the control fuel 21c into the premixed gas is as follows: the fuel discharge speed is υf and the length of the premixing branch pipe 19 is Lf.

[0035]

(2) τf = Lf / υf (2)

Further, by combining the time τs required for fuel branching, the time τt required for the pressure fluctuation to act on the fuel-air ratio of the premixed gas is:

[0037]

## EQU3 ## τt = τp + τs + τf (3)

If the total time of this action time τt and the time during which the pressure fluctuation has an effect on the fuel-air ratio fluctuation in the mechanism in which combustion vibration actually occurs is a multiple of the vibration cycle, Ratio fluctuations can be suppressed.

FIG. 4 shows an example of changes over time in pressure fluctuation and fuel-air ratio fluctuation which are reduced by the present invention. The vertical axis represents each variation amount, and the horizontal axis represents time.
At points a to c in the figure, the amplitude of the pressure fluctuation is large, and the fuel branching device 16 operates according to the fluctuation range shown by the shaded area in the figure,
The control fuel 21c flowing into the premixer 8 decreases from point a'to point c'in the figure.

The flow rate of the control fuel 21c flowing into the premixer 8 is τt from the point a by the operation of the fuel branching device 16.
It starts to change with the passage of time, and further changes in the opposite phase to the change in the fuel-air ratio of the premixed gas. Therefore, this control fuel 2
The flow rate fluctuation of 1c reduces the fluctuation range of the fuel-air ratio and the pressure, and consequently reduces the combustion oscillation.

As a second embodiment according to the present invention, FIG. 5 shows a half of the central longitudinal section of the combustor from the central axis. The fuel branching device 16 is installed at the inlet of the premixer 8 and controls the flow rate of the control fuel 21c flowing into the premixer 8 by the flow rate of the premixing air 12c. A resistor 25 is provided at the inlet of the premixer 8 and the inlet of the diffusion air 12c so that the premixing air 12c can sufficiently flow into the air supply pipe 24 of the fuel branching device 16.

Fuel branching device 16 used in this combustor
6 and 7 are schematic structural diagrams of the above. 6 shows a case where a large amount of fuel is discharged to the premixer 8 side, and FIG. 7 shows a case where a large amount of fuel is discharged to the diffusion side. In the fuel branching device 16, a fuel supply pipe 17, an air supply pipe 24, a premixing branch pipe 19, and a diffusion branch pipe 20 are connected as shown in the figure. The fuel 21c that has passed through the fuel supply pipe 17 is discharged into the air flow 12b for premixing that has flowed in from the air supply pipe 23 at an angle with respect to the air outflow direction. The discharged fuel 21c is bent by the flow velocity of the airflow 12b.

When the velocity of the air flow 12b is high, the trajectory of the fuel jet is largely bent, and a large amount of fuel 21c flows into the premixing pipe 19 side. On the contrary, when the air velocity is low, the trajectory of the fuel jet is not bent so much, and a large amount of fuel flows into the diffusion pipe side 18. Therefore, in the combustor in which the fuel branching device 16 is installed, it is possible to reduce the fluctuation of the fuel-air ratio of the premixed gas caused by the fluctuation of the flow rate of the premixing air 12b, or to change it by shifting the phase.

Further, unlike the fuel branching device 16 by pressure control of the first embodiment, the flow rate of the control fuel 21c flowing into the premixer 8 can be continuously changed even with a slight change in the air flow rate. .

The conditions for reducing the combustion oscillation are the same as those described above, so that the control fuel 21c cancels the fluctuation of the fuel-air ratio of the premixed gas that occurs with the fluctuation of the air flow rate flowing into the premixer 8. It should work. However, since the fluctuation of the air flow rate directly leads to the change of the flow rate of the control fuel 21c discharged to the premixer 8, it is necessary to consider the time from the pressure fluctuation to the control of the fuel-air ratio as in the first embodiment. It is possible to control the fuel-air ratio with good response.

Even if the fuel-air ratio does not fluctuate, and the calorific value of combustion changes due to fluctuations in the flow rate of the premixed gas and induces combustion oscillation, the fluctuation of the calorific value is changed in the opposite phase. You can control. In this case, it is necessary to consider the time required for the premixed gas to flow from the outlet of the premixing branch pipe 19 to the outlet of the premixer 8 and the action time including the delay time of the combustion reaction.

As a third embodiment according to the present invention, a multi-burner type combustor provided with a plurality of swirl burners is shown in a central longitudinal sectional view in FIG. The fuel branching device 16 installed inside the premixer 8 has the structure shown in FIG. 2, and changes the flowing direction of the control fuel 21c according to the pressure fluctuation generated near the outlet of the premixer 8. You can Further, a branch pipe for branching the fuel is guided to the inside of the premixer 8 and the outside of the premixer 8, and the outlets of the respective pipes are installed so as to face the flow direction of the surrounding fluid. With such a structure, the control fuel 21
c is branched into the premixer 8 and the main air 12a before flowing into the premixer 8.

The conditions for reducing the combustion oscillation are the same as those described in the first embodiment, but the fuel discharged to the outside of the premixer 8 rides on the main air 12a, and the fuel air inside the premixer 8 is exhausted. The time to affect the ratio also needs to be considered.
For example, by making this action time n / 2 (n: natural number) times the cycle of vibration, the control fuel 21c is directly fed to the premixer 8
When it is discharged into the interior of the premixer, it merges with the control fuel 21c discharged to the outside of the premixer 8 to increase the fuel-air ratio of the premixed gas.

By installing such a fuel branching device 16, it becomes possible to reduce combustion vibration even in a combustor which does not have a special device for generating a diffusion flame.

As described above, in the combustor according to the present invention, the pressure fluctuation generated inside the combustor is used to distribute the fuel discharge direction to the premixer and the diffusion combustion air, whereby the movable part is moved. And does not require electrical control,
It is possible to control the fuel-air ratio of the premixer, thereby reducing combustion oscillation.

Further, by controlling the fuel discharge direction by using the fluctuation of the air flow rate of the premixer caused by the combustion vibration, the combustion vibration can be reduced with a quick response and a simple structure.

By distributing the control fuel discharge direction into the premixer and into the main air flowing into the premixer, the fuel-air ratio control of the premixed air becomes possible, and the device for diffusion combustion, and Combustion vibration can be reduced even in a combustor that does not have diffusion air used for it.

[0053]

As described above, according to the present invention, it is possible to obtain a gas turbine combustor of this type which has a simple structure, is excellent in responsiveness and reliability, and can reduce combustion vibration.

[Brief description of drawings]

FIG. 1 is a vertical side view showing one embodiment of a gas turbine combustor of the present invention.

FIG. 2 is a vertical sectional side view of the fuel branching device installed in the gas turbine combustor of the present invention.

FIG. 3 is a vertical cross-sectional side view of a fuel branching device installed in a gas turbine combustor of the present invention.

FIG. 4 is a characteristic diagram showing changes in the vibration waveform reduced by the present invention.

FIG. 5 is a vertical sectional side view showing another embodiment of the gas turbine combustor of the present invention.

FIG. 6 is a vertical cross-sectional side view of the fuel branching device installed in the gas turbine combustor of the present invention.

FIG. 7 is a vertical cross-sectional side view of the fuel branching device installed in the gas turbine combustor of the present invention.

FIG. 8 is a vertical sectional side view showing another embodiment of the gas turbine combustor of the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Outer cylinder wall, 2 ... Inner cylinder wall, 3 ... Combustion chamber, 4 ... Diffusion swirl burner, 5 ... Swirl blade, 6 ... Diffusion fuel discharge port, 7 ... Diffusion flame, 8 ... Premixer, 9 ... Fuel nozzle 10, ... Flame stabilizer, 1
DESCRIPTION OF SYMBOLS 1 ... Premixed flame, 12a ... Main air flow, 12b ... Diffusion air flow, 12c ... Premixed air flow, 13 ... Combustion gas, 14 ... Compressor, 15 ... Turbine, 16 ... Fuel branching device, 17 ... Fuel supply pipe, 18 ... Pressure conduit, 19 ... Premixing branch pipe, 20 ... Diffusion branch pipe, 21a ... Diffusion fuel flow, 21b ... Premixed fuel flow, 21c ... Control fuel flow, 22 ... Low pressure Vortex area, 23 ... Branch wall.

Claims (11)

[Claims] 1. A gas turbine combustor arranged upstream of a combustion chamber and provided with a premixed combustion burner for combusting gas mixed by the premixer, wherein a fuel injection port in the premixer is provided. A fuel branching means for branching the injected fuel into the inside of the premixer and the outside of the premixer, and providing a pressure guiding pipe connecting the fuel branching means part and the combustion chamber, The opening of the pressure guiding pipe on the fuel branching means side is formed so that the fuel injected into the fuel branching means is branched and supplied to the inside of the premixer as the gas pressure in the combustion chamber increases. Gas turbine combustor. 2. A gas turbine combustor provided with an upstream side of a combustion chamber and provided with a premixed combustion burner for burning gas mixed by the premixer, wherein a fuel nozzle section in the premixer is provided. A fuel branching means for branching the injected fuel into the inside of the premixer and the outside of the premixer, and a pressure guiding pipe connecting the fuel branching means part and the combustion chamber to each other, and The fuel branching means side opening of the pressure guiding pipe is arranged in the vicinity of the fuel nozzle discharge port and in a direction perpendicular to the jetting direction of the fuel nozzle, and the discharge direction of the fuel is changed by the pressure change in the pressure guiding pipe, A gas turbine combustor characterized by being formed so that the flow rate of fuel supplied to the inside of the premixer is controlled. 3. A gas turbine combustor comprising a premixed combustion burner for combusting a gas mixed by a premixer and a diffusion combustion burner for diffusion combustion upstream of the combustion chamber. Is provided at the fuel injection port of the fuel injection means, and a fuel branch means for branching the injected fuel into the premixer and the supply air passage of the diffusion combustion burner is provided, and the fuel branch means and the combustion chamber are provided. A pressure guiding pipe that connects the two is provided, and the fuel branching device side opening of this pressure guiding pipe is connected to the inside of the premixer so that the fuel injected into the fuel branching device becomes higher as the gas pressure in the combustion chamber becomes higher. A gas turbine combustor characterized in that it is formed so as to be supplied in a branched manner. 4. A combustor comprising a premixer for mixing air and fuel to generate a premixed gas, and a combustion chamber located downstream of the premixer for burning the premixed gas. The combustor controls the flow rate of the fuel flowing into the premixer in accordance with the change in the flow rate of the fluid flowing in the combustor, and uses the fluid force of the fluid to control the air and the fuel of the premixed gas mixture. And a means for controlling the degree of mixing of the gas turbine combustor. 5. The means for controlling the degree of mixing has a fuel nozzle for discharging fuel into the fluid at a certain angle with respect to the flowing direction of the fuel, and the fuel discharge direction depends on the flow velocity of the fluid. The gas turbine combustor according to claim 4, wherein the gas turbine combustor is formed so that 6. The gas turbine combustor according to claim 4, wherein the fluid is the air or the premixed gas. 7. A burner for diffusive combustion in a combustion chamber is installed in the combustor, and the direction of discharge of the fuel is controlled by the means for controlling the degree of mixing so that the inside of the premixer and the diffusion combustion are controlled. The gas turbine combustor according to claim 4, 5 or 6, wherein the gas turbine combustor is distributed into the air for use. 8. The means for controlling the degree of mixing is used to distribute the discharge direction of the fuel to the upstream side and the downstream side of the air flow or the premixed air flow.
The gas turbine combustor according to 5 or 6. 9. A premix combustion burner, which is arranged upstream of the combustion chamber and burns the gas mixed by the premixer, wherein the amount of fuel supplied to the premixer depends on the turbine load. In a premixed fuel control method for a gas turbine combustor controlled in accordance with the method, a fuel branch is provided in which a fuel injected into the premixer is branched into a premixer inside and a premixer outside. A means is provided, and the fuel is branched at this branch portion by the gas pressure in the combustion chamber, and the flow rate of the fuel flowing into the premixer is controlled to control the degree of mixture of the air-fuel mixture. Premixed fuel control method for gas turbine combustor. 10. A premix combustion burner, which is arranged upstream of the combustion chamber and burns the gas mixed by the premixer, wherein the amount of fuel supplied to the premixer varies depending on the turbine load. In a premixed fuel control method for a gas turbine combustor controlled in accordance with the method, a fuel branch is provided in which a fuel injected into the premixer is branched into a premixer inside and a premixer outside. And a pressure guiding pipe connecting the fuel branching means and the combustion chamber, the fuel flowing into the premixer by the gas pressure of the combustion chamber conducted through the pressure guiding pipe. A method for controlling premixed fuel for a gas turbine combustor, characterized in that the flow rate of the premixed fuel is controlled to control the degree of mixing of air and fuel in the premixed gas. 11. A premixed combustion burner arranged upstream of the combustion chamber for combusting the gas mixed by the premixer, wherein the amount of fuel supplied to the premixer varies depending on the turbine load. In a premixed fuel control method for a gas turbine combustor controlled in accordance with the method, a fuel branch is provided in which a fuel injected into the premixer is branched into a premixer inside and a premixer outside. And a pressure communication conduit connecting the fuel branching means portion and the combustion chamber to each other, the fuel being branched and supplied to the premixer side via the fuel branching means by the gas pressure in the combustion chamber. A premixed fuel control method for a gas turbine combustor, characterized in that the flow rate is controlled to control the degree of mixing of air and fuel in the premixed gas.