JP3673009B2 - Gas turbine combustor - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a gas turbine combustor, and in particular, a fuel supply unit for injecting fuel into a combustion chamber can be applied to both liquid fuel and gaseous fuel types, and liquid fuel and gaseous fuel can be used together. The present invention relates to a gas turbine combustor that reduces NOx concentration in gas turbine exhaust gas by selecting a seed.
[0002]
[Prior art]
In gas turbine plants and combined cycle power plants, a plurality of gas turbine combustors are incorporated between the air compressor and the gas turbine, and the combustion gas generated by the gas turbine combustor is guided to the gas turbine. The gas turbine is driven.
[0003]
In recent years, gas turbine plants and combined cycle power plants have been increasing the temperature of the combustion gas in the gas turbine combustor (increasing the temperature of the gas turbine inlet) to improve turbine thermal efficiency. Along with this, the NOx concentration in the gas turbine exhaust gas also increases and has a great influence on the environment. Therefore, a technique for reducing the NOx concentration in the gas turbine exhaust gas is currently being sought.
[0004]
The main factor of NOx generation in the gas turbine combustor is local increase in temperature of the combustion gas in the gas turbine combustor, and the NOx generation amount depends on the combustion gas temperature of the gas turbine combustor. A large amount of NOx is generated when high temperature diffusion combustion is performed when fuel and air are in a state close to the fuel-air ratio 1 while fuel and air are diffusely mixed and burned in the gas turbine combustor.
[0005]
Conventionally, methods for keeping NOx generated in a gas turbine combustor low include a lean premixed combustion method in which air is added to fuel in advance to burn it in a lean fuel state, or water or steam that is injected into the combustion gas A steam injection combustion system has already been proposed.
[0006]
In the gas turbine combustor to which the lean premixed combustion zone is applied, the head side of the combustion chamber is divided into a first stage combustion region, and the downstream side of the head is divided into a second stage combustion region. A relatively small amount of fuel is injected into the combustion chamber to generate a high-temperature combustion gas. This combustion gas is used as a flame (fire type), and a large amount of lean premixed fuel is injected into the second stage combustion region. By preventing the generation of NOx, the generation of NOx was kept low. In this case, the pilot fuel supply unit that injects the liquid fuel into the first stage combustion region includes a combustion air nozzle that concentrically surrounds the pilot fuel nozzle and atomizes the liquid fuel, and is finely divided by the combustion air nozzle. The combusted liquid fuel was burnt by diffusion. The main fuel supply unit for injecting liquid fuel into the second stage combustion region includes a main fuel nozzle and a premixing duct, respectively, and adds air to the liquid fuel injected from the main fuel nozzle in the premixing duct. As a result, a premixed fuel in a lean state was used to generate combustion gas for driving a gas turbine.
[0007]
[Problems to be solved by the invention]
In recent gas turbine plants and combined cycle power plants, the temperature of the combustion gas in the gas turbine combustor has been increased in order to further improve the turbine thermal efficiency, but as the temperature of the combustion gas increases, There is a need for NOx having a lower generated concentration. In order to further reduce the NOx generation concentration, the amount of liquid fuel injected from the pilot fuel supply unit into the first stage combustion region is made smaller than before, and the remaining amount is all changed from the main fuel supply unit to the first level. It has become necessary to produce combustion gases with a lean liquid fuel that is injected into a two-stage combustion zone.
[0008]
However, in the conventional lean premixed combustion method, when the liquid fuel injected from the pilot fuel supply unit to the first stage combustion region is reduced more than before, the lean liquid injected from the main fuel supply unit to the second stage combustion region There was a problem that liquid fuel was blown out while generating combustion gas with fuel. For this reason, there is a limit to reducing the amount of liquid fuel injected from the pilot fuel supply unit to the first stage combustion region, and the advent of a gas turbine combustor that suppresses the NOx concentration generation amount by the lean premixed combustion method lower than before. Has come difficult.
[0009]
The present invention has been made based on such circumstances, and allows the liquid fuel from the pilot fuel supply section injected into the first stage combustion region to be freely switched to the gaseous fuel, To provide a gas turbine combustor in which the liquid fuel from the main fuel supply section injected into the second stage combustion region can be freely switched to the gaseous fuel so that the NOx generation concentration is lower than the conventional one. Objective.
[0010]
Another object of the present invention is to provide a gas turbine combustor in which gaseous fuel can be used in combination with liquid fuel from a pilot fuel supply unit injected into the first stage combustion region.
[0011]
[Means for Solving the Problems]
In order to achieve the above object, a gas turbine combustor according to the present invention has a combustion chamber formed in a combustor liner as a first stage combustion on the combustor liner head side. A pilot fuel supply section for injecting pilot fuel into the first stage combustion area, and a second stage combustion area. A main fuel supply unit for injecting main fuel premixed in a lean fuel state, the pilot fuel supply unit injecting a pilot fuel nozzle for injecting pilot fuel, and injecting a first pilot fuel First pilot fuel nozzle and second pilot nose that selectively injects liquid fuel, gaseous fuel, or air according to the first pilot fuel type injected by the first pilot fuel nozzle Each of the third pilot fuel nozzles for injecting the third pilot fuel, and the main fuel supply section includes a plurality of main fuel nozzles for injecting the main fuel, and each of the main fuel nozzles. And a premixing duct for adding air to the main fuel to make the fuel lean, and a fuel passage for selectively supplying either the liquid fuel or the gaseous fuel to the main fuel supply unit . In the gas turbine combustor, the main fuel supply unit includes a fuel outlet extending from a fuel injection port of the main fuel nozzle, a guide wall that forms an inclined path at the fuel outlet, and a head of the inclined path. And a flat spray portion formed from the portion toward the downstream side .
[0023]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, an embodiment of a gas turbine combustor according to the present invention will be described with reference to the drawings.
[0024]
FIG. 1 is a partially cutaway schematic cross-sectional view of a gas turbine combustor according to the present invention.
[0025]
The gas turbine combustor indicated by reference numeral 1 is formed in a long cylindrical shape as a whole, and a plurality of gas turbine combustors, for example, six, eight, etc. are installed between an air compressor and a gas turbine of a gas turbine plant.
[0026]
The gas turbine combustor 1 has a structure in which a cylindrical combustor liner 3 is accommodated in a combustor outer cylinder 2 and a combustion chamber 6 is formed inside by the combustor liner 3. Further, the combustor liner 3 is provided with a flow sleeve 7 that forms an air passage 5 between the combustor outer cylinder 2 and compressed air of air compression (not shown) is compressed by the flow sleeve into the combustion chamber. 6 is directed to the head side for combustion and in the middle of the combustion chamber 6 for dilution of the combustion gas temperature.
[0027]
The combustion chamber 6 formed by the combustor liner 3 is formed in a horizontal bell shape on the head side, and gradually expands toward the downstream side to form a cylindrical chamber, and the downstream side is a transition piece. (Not shown). The combustion chamber 6 is divided into a first-stage combustion region 6a on the head side and a second-stage combustion region 6b on the wake side adjacent to the first-stage combustion region 6a .
[0028]
On the head side of the combustor liner 3, a pilot fuel supply unit 8 for injecting the pilot fuel A into the first stage combustion region 6a is provided. The pilot fuel supply unit 8 serves as a pilot fuel supply unit. A pilot fuel nozzle 9 is installed. A main fuel supply unit 10 for injecting the main fuel B into the second stage combustion region 6b is provided outside the pilot fuel nozzle 9. The main fuel supply unit 10 includes a main fuel nozzle 11 and a premixing duct 12 as main fuel supply means. The pilot fuel nozzle 9 and the main fuel nozzle 11 are installed on a head plate 13 that covers the opening of the combustor outer cylinder 2. The head plate 13 is recessed in a stepped manner, and a plurality of main fuel nozzles 11 are installed at each step portion, and concentration is performed so that the plurality of main fuel nozzles 11 approach the pilot fuel nozzle 9. .
[0029]
The pilot fuel nozzle 9 surrounds the first pilot fuel nozzle 14 using the pilot liquid fuel A such as light oil or kerosene and the first pilot fuel nozzle 14 in the center, and the first pilot fuel nozzle 9 The second pilot fuel nozzle 15 and the second pilot fuel nozzle 15 that selectively use one of fluids of liquid fuel, gaseous fuel, and air according to the fuel used by 14 and the second pilot fuel nozzle 15 are concentrically surrounded, for example It is composed of a third pilot fuel nozzle 16 that uses a pilot fuel C such as LNG, and a swirler 17 provided around the third pilot fuel nozzle 16, and the pilot fuel A or C is jetted as a swirling flow.
[0030]
As shown in FIG. 2, the first pilot fuel nozzle 14 is provided with a fuel inlet 18 at one end and a fuel outlet 19 at the other end and extending in the axial direction, and a narrow passage 21 communicating with the fuel passage 20. And a turning / turning passage 22 that applies a turning flow to the pilot fuel A flowing through the narrow passage 21 simultaneously with a turning, and a fuel outlet 19 that communicates with the turning / turning passage 22 and gradually reduces the opening area. Yes.
[0031]
The second pilot nozzle 15 is configured to be applicable to any fluid of liquid fuel, gaseous fuel, and liquid fuel atomization air, and is a fluid supplied from a manifold (not shown) via a fluid inlet 23, such as a liquid. A fluid passage 24 that guides air for fuel micro-flow, and a fluid swirler 25 that is provided on the downstream side of the fluid passage 24 and is configured in a ring shape that provides a swirling flow along the circumferential direction of the passage wall. And a contracted flow passage 26 that accelerates the fluid toward the downstream side of the fluid swirler 25, and a pilot fuel A that is injected from the fuel outlet 19 by the fluid accompanied by the increased speed and swirl flow at the downstream end of the contracted flow passage 26. Respectively, and a fluid outlet 26a that is injected into the first stage combustion region 6a.
[0032]
The third pilot fuel nozzle 16 is provided on the outer peripheral side of the fluid passage 24 of the second pilot nozzle 15, and receives pilot fuel C, for example, gaseous fuel such as LNG, through a fuel inlet 27 from a fuel supply unit (not shown). The fuel passage 28 to be guided, the fuel contraction passage 29 that gradually decreases the opening area toward the downstream side of the fuel passage 28, and the drilling from the oblique direction of the downstream end of the fuel contraction passage 29 toward the swirler 17. The fuel injection port 30 is provided.
[0033]
On the other hand, the main fuel nozzle 11 and the premixing duct 12 constituting the main fuel supply unit 10 are arranged in order from the outside of the pilot fuel nozzle 9 in order from the first main fuel nozzle 11a, the first premixing duct 12a, and the first. The two main fuel nozzles 11b, the second premixing duct 12b, the third main fuel nozzle 11c, the third premixing duct 12c, the fourth main fuel nozzle 11d, and the fourth premixing duct are divided into multi-stages, respectively. The premixing ducts 12a, 12b,... Are brought close to the pilot fuel nozzle 9 to prevent the combustion gas from blowing off. The main fuel supply unit 10 supplies main fuel B, for example, liquid fuel, to the main fuel nozzles 11 partitioned into the main fuel nozzles 1a, 11b,... Via the fuel valve 31 and the fuel manifold 32. A first main fuel passage 33 is provided. An annular fuel header 34 is provided in the head plate 13 in the first main fuel passage 33.
[0034]
The fuel header 34, second main fuel passage 35 that extends in a direction intersecting the axial direction is provided, the fuel changeover valve 36 to the second main fuel passage 35, via the fuel manifold 37 main use fuels, such as gas fuel, thereby making it possible to supply switched to the main fuel B.
[0035]
The premixing duct 12 divided into the first premixing duct 12a, the second premixing duct 12b,... Is provided with a swirl vane 38 on the inlet side, and a throttle passage 39 for turning toward the combustor liner 3 from the middle. Form. The throttle passage 39 is formed as a passage that gradually decreases the opening area from the upstream side toward the downstream side. Further, an air outlet 40 for guiding the compressed air in the air passage 5 into the combustion chamber 6 is provided at a connection portion of the premixing duct 12 to the combustor liner 3.
[0036]
The main fuel nozzle 11 partitioned into the first main fuel nozzle 11a, the second main fuel nozzle 11b,... Is connected via a fuel header 34 formed in the head plate 13, as shown in FIG. A fuel outlet 44 connected to the fuel guide path 42 of the protruding rib 41 and provided integrally with the fuel injection port 43 is provided.
[0037]
The fuel blow-out port 44 is, for example, a main fuel B (liquid fuel) injected from the fuel injection port 43 through an extremely thin film 45 and a main fuel by a pressing force of compressed air a from the top 45a of the ramp 45. A spraying section 46 is provided for atomizing B and evaporating the atomized main fuel B during scattering. The spray portion 46 has a flat surface.
[0038]
The fuel outlet 44 is provided with a guide wall 45 b for guiding the main fuel B injected from the fuel injection port 43 to the spray portion 46. It is to be noted that the slant path 45 is preferably at an angle of 5 ° or more with respect to the axis of the fuel injection port 43 in view of flowing the main fuel B as an extremely thin film, and the top 45a of the slant path 45 is a pressing force of the compressed air a. It is desirable to install it slightly behind the inlet of the premixing duct 12 in order to effectively use this.
[0039]
Next, the operation will be described.
[0040]
The operation of the gas turbine combustor 1 is controlled according to the operation of the gas turbine plant. From the fuel ignition to the initial load of the gas turbine, the pilot fuel A, for example, the pilot fuel A is supplied to the first pilot fuel nozzle 14 of the pilot fuel supply unit 8. Liquid fuel is supplied. As shown in FIG. 2, the pilot fuel A supplied to the first pilot fuel nozzle 14 is accelerated while flowing through the fuel passage 20 and the narrow passage 21 from the fuel inlet 18, and swirls by the turning / turning passage 22. A flow is applied to turn, and after turning, the fuel is injected from the fuel outlet 19.
[0041]
On the other hand, the second pilot nozzle 15 uses fuel air when the first pilot fuel nozzle 14 uses liquid fuel.
[0042]
The air supplied to the fluid inlet 23 of the second pilot nozzle 15 is given a swirling flow by the fluid swirler 25 through the fluid passage 24, and is accelerated by the contraction passage 26. After the acceleration, the air is supplied from the fuel outlet 19. When the swirling flow is given to the liquid fuel to be sprayed and atomized and ejected from the fluid outlet 26a, it reacts with the compressed air swirled from the swirler 17 and diffused in the first stage combustion region 6a (FIG. 1). Combustion takes place.
[0043]
In this embodiment, liquid fuel is used for the first pilot fuel nozzle 14 and air is used for the second pilot nozzle 15. However, gaseous fuel is supplied to the second pilot nozzle 15. Alternatively, diffusion combustion may be performed in combination with the liquid fuel of the first pilot fuel nozzle 14. In addition, the liquid fuel supplied to the first pilot fuel nozzle 14 is cut and the liquid fuel is supplied to the second pilot nozzle 15 while the gaseous fuel is supplied to the third pilot fuel nozzle 16. 15 and 16 may be used together to perform diffusion combustion. In this case, as shown in FIG. 2, the third pilot fuel nozzle 16 supplies gaseous fuel to the fuel inlet 27 and increases the speed when flowing from the fuel passage 28 to the fuel contraction passage 29. When ejected from the fuel injection port 30, it reacts with the compressed air swirled from the swirler 17 and given a large swirl flow. The liquid fuel ejected from the fuel injection port 30 by the large swirl flow provided from the swirler 17 is subjected to diffusion combustion while mixing swirl.
[0044]
As the gas turbine load increases from the initial load, as shown by the broken line in FIG. 4, the pilot fuel A, for example, liquid fuel, supplied to the first pilot fuel nozzle 14, After being narrowed down to several percent, as shown by the broken line, the fuel is continuously supplied as a combustion gas generation fire type (flame) as a constant fuel consumption. As the amount of pilot fuel A is decreased, main fuel B, for example, liquid fuel is supplied to the main fuel nozzle 11 of the main fuel supply unit 10 instead.
[0045]
The main fuel nozzle 11 of the main fuel supply unit 10 is partitioned into a first main fuel nozzle 11a, a second main fuel nozzle 11b, a third main fuel nozzle 11c, and a fourth main fuel nozzle 11d. .. In the order of the main fuel nozzles 11a, 11b,..., As shown by the solid line in FIG. 4, the pilot fuel B is gradually supplied to the fuel valve 31, the fuel manifold 32, and the first main fuel passage 33. As shown in FIG. 4, the main fuel B is increased in accordance with the increase in the gas turbine load as a fuel input flow in a range in which the premixed combustion gas is not blown out. It becomes the total amount of the solid line shown by.
[0046]
As shown in FIG. 3, the main fuel B supplied to the main fuel nozzle 11 passes from the fuel injection port 43 to the fuel outlet 44 through the first main fuel passage 33, the fuel header 34, and the fuel guide passage 42. When ejected, it flows in the form of an ultrathin film by means of a ramp 45 defined in the guide wall 45b, and flows from the top 45a to the flat spray section 46 by the pressing force (shearing force) of the compressed air a. Since it is atomized and evaporated while the atomized main fuel B is scattered, a premixed fuel in a homogeneous fuel lean state is generated in the premixing duct 12.
[0047]
The premixing duct 12 is divided into a first premixing duct 12a, a second premixing duct 12b, a third premixing duct 12c, and a fourth premixing duct 12d corresponding to the main fuel nozzles 11a, 11b,. The premixed fuel in a homogeneous fuel lean state is supplied from the main fuel nozzles 11a, 11b,.
[0048]
The homogeneous fuel lean premixed fuel supplied to each premixing duct 12a, 12b,... Is given a swirling flow by swirl vanes 38, and further accelerated by a throttle passage 39, in the second stage combustion region 6b. The diffusion combustion gas from the pilot fuel nozzle 9 is burned as a fire type (flame).
[0049]
A throttle passage 39 for each premixing duct 12a, 12b,... Is connected to the combustion chamber 6 of the combustor liner 3 by turning the passage, but is formed in a bell shape so as to be very close to the pilot fuel nozzle 9. Are concentrated on the head side of the combustion chamber 6 of the combustor liner 3, there is no fear that the combustion gas will blow off when the premixed combustion gas is generated. Further, since the throttle passage 39 accelerates the premixed fuel to generate the premixed combustion gas, there is no possibility of backfire. Therefore, even if the premixed fuel is burned in the second stage combustion region 6b of the combustion chamber 6, a stable premixed combustion gas having almost little NOx concentration can be obtained.
[0050]
Further, the premixed combustion gas has a relatively high temperature and may burn the combustor liner 3. However, a plurality of air outlets 40 are formed around the connection portion of the throttle passage 39 to the combustor liner 3, and the compressed air a is forcibly blown out in a film shape. There is no risk of burning.
[0051]
In the present embodiment, it has been described that the liquid fuel is supplied to the main fuel nozzle 11 of the main fuel supply unit 10 to obtain the premixed combustion gas having almost little NOx concentration. The main fuel nozzle 11 is configured to be able to supply gaseous fuel instead of liquid fuel.
[0052]
As shown in FIG. 1, the main fuel supply unit 10 includes a first main fuel nozzle 11 a in which the main fuel nozzle 11 is partitioned from the fuel switching valve 36 via the second main fuel passage 35 and the fuel header 34. , The main fuel D (gaseous fuel) is supplied to the second main fuel nozzle 11b, the third main fuel nozzle 11c, and the fourth main fuel nozzle 11d in the order shown in FIG. The main fuel D supplied in order to the main fuel nozzles 11a, 11b,... Is given a swirl flow by the swirl vanes 38 of the premixing ducts 12a, 12b,. The premixed combustion gas is obtained by being injected from the throttle passage 39 into the second stage combustion region 6b. Therefore, since the main fuel supply unit 10 is configured to be able to apply gaseous fuel, the main fuel supply unit 10 can generate premixed combustion gas having a lower NOx concentration than liquid fuel.
[0053]
5 and 6 are experimental data showing characteristics of NOx concentration and CO concentration generated in the operation of the gas turbine combustor 1 according to the present invention. From this data, the NOx concentration is determined by temporarily narrowing down the pilot fuel A injected from the pilot fuel nozzle 9 of the pilot fuel supply unit 8 and injecting it from the main fuel nozzle 11 of the main fuel supply unit 10 instead. Although it becomes a little higher before supplying the main fuel B, it can be seen that after the main fuel B is introduced, the concentration becomes almost stable and almost no CO concentration is generated.
[0054]
【The invention's effect】
As described above, the gas turbine combustor according to the present invention includes the pilot fuel nozzle for injecting the pilot fuel into the first stage combustion nozzle, the first pilot fuel nozzle, the second pilot fuel nozzle, the third It is divided into each of the pilot fuel nozzles and can be applied to both fuel types, liquid fuel and gaseous fuel. By using multiple fuels and using them in combination, it achieves diffusion combustion with excellent combustion stability, The main fuel nozzle for injecting the main fuel into the second stage combustion region is provided with a fuel passage applicable to both fuel types, liquid fuel and gaseous fuel, to increase the use of the fuel, and to the fuel spray port The fuel outlet is composed of a ramp and a flat spray port, the thickness of the fuel collected in the spray section through the ramp is reduced, and the fuel is made atomized by the compressed air pressure to the reduced thickness. Since evaporated in scattering of the fuel is atomized, it is possible to produce a premixed fuel of a homogeneous fuel-lean state, I generation coupled with homogeneous fuel lean state premixed fuel, in a diffusion combustion It is possible to achieve premixed combustion with almost no NOx concentration by reducing the pilot fuel.
[Brief description of the drawings]
FIG. 1 is a partially cutaway schematic cross-sectional view showing an embodiment of a gas turbine combustor according to the present invention.
FIG. 2 is an external view with a partially cut section of a pilot fuel nozzle of a gas turbine combustor according to the present invention.
FIG. 3 is a partial sectional view of a main fuel nozzle of a gas turbine combustor according to the present invention.
FIG. 4 is a graph showing each fuel distribution in the gas turbine combustor according to the present invention.
FIG. 5 is a graph showing the NOx concentration with respect to the gas turbine load of the gas turbine combustor according to the present invention.
FIG. 6 is a graph showing the CO concentration with respect to the gas turbine load of the gas turbine combustor according to the present invention.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Gas turbine combustor 2 Combustor outer cylinder 3 Combustor liner 4 Flow sleeve 5 Air passage 6 Combustion chamber 6a First stage combustion area 6b Second stage combustion area 8 Pilot fuel supply part 9 Pilot fuel nozzle 10 Main fuel Supply unit 11 Main fuel nozzle 11a First main fuel nozzle 11b Second main fuel nozzle 11c Third main fuel nozzle 11d Fourth main fuel nozzle 12 Premixing duct 12a First premixing duct 12b Second premixing Duct 12c Third premixing duct 12d Fourth premixing duct 13 Head plate 14 First pilot fuel nozzle 15 Second pilot fuel nozzle 16 Third pilot fuel nozzle 17 Swirler 18 Fuel inlet 19 Fuel outlet 20 Fuel passage 21 Narrow Passage 22 Turning / swirl passage 23 Fluid inlet 24 Fluid passage 25 Fluid swirler 26 Shrinkage passage 26a Fluid outlet 27 Fuel inlet 28 Fuel passage 29 Fuel shrinkage passage 30 Fuel injection port 31 Fuel valve 32 Fuel manifold 33 First main fuel passage 34 Fuel header 35 Second main fuel passage 36 Switching valve 37 Fuel manifold 38 Swivel wing 39 Restriction passage 40 Air outlet 41 Projecting rib 42 Fuel guide passage 43 Fuel injection port 44 Fuel outlet 45 Slope 45a Top 45b Guide wall 46 Spray part

Claims (1)

The combustion chamber formed in the combustor liner is divided into a first stage combustion region on the combustor liner head side and a second stage combustion region on the downstream side of the first stage combustion region. A pilot fuel supply unit for injecting pilot fuel into the stage combustion region; and a main fuel supply unit for injecting main fuel premixed in a lean fuel state into the second stage combustion region, respectively . The fuel supply unit includes a pilot fuel nozzle that injects pilot fuel, a first pilot fuel nozzle that injects first pilot fuel, and a first pilot fuel type that is injected by the first pilot fuel nozzle. One is divided into a second pilot nozzle that selectively injects one of liquid fuel, gaseous fuel, and air, and a third pilot fuel nozzle that injects third pilot fuel. The main fuel supply section includes a plurality of main fuel nozzles that inject main fuel, and a premix duct that faces each of the main fuel nozzles and adds air to the main fuel to make the fuel lean. In the gas turbine combustor having a fuel passage for selectively supplying either the liquid fuel or the gaseous fuel to the main fuel supply unit, the main fuel supply unit is a fuel injection port of the main fuel nozzle. The fuel outlet is provided with a guide wall that forms an oblique path at the fuel outlet, and a flat spray portion that is formed from the head of the oblique path toward the downstream side. Gas turbine combustor.

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