JP5669771B2 - Gas turbine combustor - Google Patents

Description

  The present invention relates to a gas turbine combustor, and more particularly, to a gas turbine combustor suitable for one configured to supply fuel and air as a plurality of coaxial jets into a combustion chamber.

In gas turbine power plants that use fossil resources as fuel, active use of hydrogen-containing fuels has been attempted as a means of reducing emissions of carbon dioxide (CO ₂ ), which causes global warming. Since hydrogen-containing fuels emit less CO ₂ during combustion, in recent years, it has been studied to effectively use coke oven gas produced as a by-product at steelworks or off-gas produced as a by-product at refineries. .

In addition, in an integrated coal gasification combined cycle (IGCC) that generates electricity by gasifying coal, which is an abundant resource, a system that collects and stores carbon in the fuel supplied to the gas turbine (C C S: the carbon Capture and Storage), is being studied to reduce CO ₂ emissions by converting carbon content in the hydrogen.

  In the case of a by-product gas, the fuel as described above contains 30% to 60% of hydrogen, and the coal gasification gas that is the fuel of the IGCC plant contains 25% to 90% of hydrogen. Therefore, in gas turbine power plants, the momentum for using such hydrogen-containing fuel is increasing.

  Since the hydrogen contained in the fuel as described above has a wide flammable range and a high combustion speed, there is a concern that a high-temperature flame is formed near the wall surface in the combustion chamber and the reliability of the combustor is impaired.

  As a means for preventing the high-temperature flame from being locally formed, a method of dispersing the fuel and burning it uniformly in the combustion chamber is effective.

  As a method for improving the dispersibility of fuel to prevent the formation of a high-temperature flame and reducing the NOx emission amount, there is one described in Patent Document 1. In Patent Document 1, a plurality of fuel nozzles and a plurality of air holes are provided, and a plurality of burners for injecting a fuel flow and an air flow formed around the fuel flow into a combustion chamber are arranged to disperse the fuel. A combustor is described that enhances the temperature and prevents the formation of hot flames.

JP 2009-133508 A

  However, when the hydrogen-containing fuel is burned by the burner described in Patent Document 1, the combustible air-fuel mixture flowing into the wake formed behind the burner structure becomes an ignition source, causing pressure fluctuations, and continuously There is concern about the possibility of falling into an unstable combustion state called combustion oscillation in which pressure waves are generated. This combustion vibration consumes the repeated fatigue life of the combustor and causes a decrease in reliability.

  The present invention has been made in view of the above-described points, and an object of the present invention is to provide a gas turbine combustor that suppresses generation of combustion vibration and improves reliability.

In order to achieve the above object, a gas turbine combustor according to the present invention is located in a combustion chamber to which fuel and air are supplied and an upstream side wall surface of the combustion chamber, and a plurality of air holes are formed in concentric rows. A gas turbine including a plurality of burners each including the plurality of fuel nozzles and the plurality of air holes, and a plurality of burners including the plurality of fuel nozzles and the plurality of air holes. In the combustor, a central burner is disposed on the central axis of the combustor, and a plurality of outer peripheral burners are disposed around the central burner, and the outer peripheral burner is disposed from the reference position adjacent to the central burner. Whether the distance between the tip of the fuel nozzle and the combustion chamber side surface of the air hole plate is configured to sequentially increase in the circumferential direction of the air hole plate,
Alternatively, a central burner is disposed on the central axis of the combustor, and a plurality of outer peripheral burners are disposed around the central burner, and the outer peripheral burner is located at a reference position adjacent to the central burner from the fuel nozzle. Is configured such that the length of the air hole plate sequentially decreases in the circumferential direction of the air hole plate.

  ADVANTAGE OF THE INVENTION According to this invention, generation | occurrence | production of combustion vibration can be suppressed and the gas turbine combustor which improved reliability can be obtained.

It is a lineblock diagram showing the outline of the gas turbine plant provided with the gas turbine combustor of the present invention. It is a fragmentary sectional perspective view which shows the burner part in the reference example 1 of the gas turbine combustor of this invention. FIG. 3 is a front view of FIG. 2. FIG. 3 is a cross-sectional development view showing a positional relationship between a fuel nozzle length in a two-row air hole of Reference Example 1 shown in FIG. 2 and a combustion chamber side of an air hole plate. It is sectional drawing which shows the burner part in a prior art (comparative example) with the flow of the air-fuel | gaseous mixture formed in the downstream, and a flame. It is a cross-sectional developed view showing the positional relationship between the fuel nozzle length and the combustion chamber side of the air hole plate in the 2-row air hole of the prior art (comparative example), and a figure showing the fluctuation of the pressure fluctuation and the equivalent ratio of the coaxial jet. FIG. 3 is a cross-sectional development view showing the positional relationship between the fuel nozzle length in the second row air holes of Reference Example 1 shown in FIG. 2 and the combustion chamber side of the air hole plate, and a view showing pressure fluctuations and fluctuations in the equivalent ratio of coaxial jets. is there. It is sectional drawing which shows the combustion chamber side part of the air hole plate in Example 1 of the gas turbine combustor of this invention. It is a front view of Fig.8 (a). It is a front view of the air hole plate for demonstrating arrangement | positioning of the outer periphery burner in Example 1. FIG. It is a figure which shows the relationship between the fuel nozzle length of the outer periphery burner structure in Example 1, and the circumferential direction position of an air hole plate.

Hereinafter, embodiments of the gas turbine combustor of the present invention will be described with reference to the drawings. In the following description, the same reference numerals are used for the same components.
[ Reference Example 1]
First, a schematic configuration of a gas turbine plant including the gas turbine combustor of the present invention will be described with reference to FIG.

  As shown in FIG. 1, the gas turbine plant 1 combusts an air compressor 2 that sucks and compresses air 101 from the atmosphere, compressed air 102 compressed by the air compressor 2, and gas fuel 200, and generates combustion gas 110. The combustor 3 to be generated, the gas turbine 4 driven by the combustion gas 110 generated in the combustor 3, the generator 6 that generates electric power using the rotational power of the gas turbine 4, and the gas turbine that starts the gas turbine 4 The starting motor 7 is schematically configured. Reference numeral 10 denotes an outer cylinder, 12 denotes a liner, 13 denotes a combustor end cover, 103 denotes cooling air, and 111 denotes exhaust gas.

  The combustor 3 includes a burner 8. The burner 8 includes an air hole plate 20 provided with a plurality of air holes 21 for guiding the compressed air 102 a compressed by the air compressor 2 to the combustion chamber 5, and a gas. A plurality of fuel nozzles 22 for injecting fuel 200 into the air holes 21, and the plurality of air holes 21 and the plurality of fuel nozzles 22 are in a state where one fuel nozzle 22 is close to the same axis in one air hole 21. Are arranged in a one-to-one correspondence. Reference numeral 300 denotes an end cover side surface of the air hole plate 20, and 301 denotes a combustion chamber side surface of the air hole plate 20.

  The plurality of fuel nozzles 22 are connected to a fuel distributor 23, and a system of gas fuel 200 supplied to the fuel nozzles 22 can be distributed to each fuel nozzle 22 by the fuel distributor 23.

  Further, the gas fuel 200 is branched into two systems downstream of the fuel cutoff valve 60, and passes through the fuel pressure adjusting valves 61a and 62a and the fuel flow rate adjusting valves 61b and 62b in the respective systems. It is supplied to the nozzle 22. In this embodiment, the fuel is distributed to the two systems, but it may be distributed to a larger number of systems. If the fuel system is distributed to a plurality of systems in this way, the degree of freedom of operation can be expanded by increasing the number of systems.

In the combustor 3 of this reference example , hydrogen-containing fuels such as coke oven gas, refinery off-gas, or coal gasification gas can be used as the gas fuel 200, including liquefied natural gas (LNG). Applicable to all gas fuels.

2 and 3 show details of the burner 8 in Reference Example 1 of the gas turbine combustor of the present invention. 3 is an observation of the air hole plate 20 shown in FIG. 1 from the downstream (front) side, and FIG. 2 shows the air hole plate 20 having three rows of air hole groups shown in FIG. 2 is cut along the pitch circle of the second-row air hole group indicated by the alternate long and short dash line, and shows the positional relationship between the second-row air holes 52 and the fuel nozzle 22 described later.

As shown in FIG. 3, the air holes 21 formed in the air hole plate 20 are arranged on a plurality of concentric circles centered on the axis of the combustor 3. In this reference example , the air holes 21 face outward from the center of the burner 8. The first row air holes 51, the second row air holes 52, and the third row air holes 53 are composed of three rows of air hole groups.

The feature of the burner 8 in this reference example is that the distance (Li1 to Li7) between the tip of the fuel nozzle 22 and the position of the combustion chamber side surface 301 (air hole outlet position) in each row differs in the circumferential direction. That is. That is, in this reference example , in each row, the distance (Li1 to Li7) between the tip of the fuel nozzle 22 and the position of the combustion chamber side surface 301 (air hole outlet position) gradually changes in the circumferential direction, and the reference position It is configured to increase (become longer) as it goes from 70 to the θ direction (direction from θ1 to θ7). In other words, the axial length of the fuel nozzle 22 gradually changes in the circumferential direction and becomes shorter from the reference position 70 toward the θ direction (direction from θ1 to θ7).

FIG. 4 shows the relationship between the length of the fuel nozzle 22 in the second row air holes 52 and the air hole outlet position. As shown in FIG. 4, in this reference example , the distance (Li1 to Li6) between the tip of the fuel nozzle 22 located in the air hole 21 and the position of the combustion chamber side surface 301 (air hole outlet position) is the reference position. It increases from 70 to the θ direction (direction from θ1 to θ6). In other words, the axial length (Ln1 to Ln6) of the fuel nozzle 22 is shortened from the reference position 70 in the θ direction (direction from θ1 to θ6).

Next, the operation and effect in Reference Example 1 will be described in comparison with the prior art.

  First, FIG. 5 shows a schematic view of the flow of the air-fuel mixture and the flame formed downstream of the burner 8 of the prior art (comparative example). As shown in the figure, in the prior art, the axial lengths of the fuel nozzles 22 are all the same, and the tip of the fuel nozzle 22 located in the air hole 21 and the position of the combustion chamber side surface 301 (air hole The distance to the exit position is all equal.

  In such a prior art configuration, the air hole on the combustion chamber side surface 301 of the air hole plate 20 and the air hole gap formed in the air hole plate 20 sandwiched between the air holes are circulated called a wake. A low flow velocity region 90 with vortices is formed. Since hydrogen has a high combustion speed as described above, there is a possibility that the flame surface 83a may approach the vicinity of the burner 8 like the flame surfaces 83b and 83c due to some disturbance. When the flame surface 83a approaches the burner 8, the low flow velocity region 90 entrains the combustible air-fuel mixture from the mainstream coaxial jet by the wake that is the circulation vortex. May ignite.

  The ignition of the air-fuel mixture generates a pressure wave, and the pressure in the wake (low speed region 90), the air hole 21 and the outlet of the fuel nozzle 22 increases instantaneously. When the pressure at the outlet of the fuel nozzle 22 increases, the fuel supply differential pressure decreases, and the ratio of the fuel flow rate to the fuel flow rate and the air flow rate (fuel-air ratio) decreases. Under the fuel lean condition in which the fuel-air ratio decreases, the combustion speed decreases as the fuel-air ratio decreases on the flame surface, so the flame surface moves backward. When the flame surface retreats downstream, the drop in the fuel supply differential pressure is eliminated, and the fuel-air ratio increases again. Since the combustion speed increases with an increase in the fuel-air ratio on the flame surface, the flame surface again approaches the vicinity of the air hole plate 20. At this time, the combustible air-fuel mixture present in the low flow velocity region 90 is ignited, and the above phenomenon is repeated to change the flame position, resulting in an unstable combustion state called combustion oscillation in which pressure fluctuations periodically occur.

  From the above principle of combustion vibration generation, the characteristic frequency of combustion vibration is inversely proportional to the distance L from the tip of the fuel nozzle 22 to the combustion chamber side surface 301 of the air hole plate 20.

In the prior art, since the distance L from the tip of the fuel nozzle 22 in each air hole 21 to the combustion chamber side surface 301 of the air hole plate 20 is equal, the frequency of pressure fluctuations generated in each air hole 21 is equal to each other. .

  6 expands the second-row air holes 52 and the second-row fuel nozzles 22 along the pitch circle of the second-row air hole group shown by the one-dot chain line in FIG. The ratio variation is shown.

  The waveform of the pressure fluctuation generated in the air hole 21 opening at θ1 and the equivalent ratio fluctuation of the coaxial jet is illustrated in the upper left of FIG. 6, and the equivalent ratio of the pressure fluctuation generated in the air hole 21 opening in θ6 and the coaxial jet is illustrated in the upper right. The waveform of fluctuation is illustrated.

As shown in the figure, since the distance L from the tip of the fuel nozzle 22 in each air hole 21 to the combustion chamber side surface 301 of the air hole plate 20 is equal, the air holes opened at θ1 and θ6 with respect to the pressure wave It can be seen that the phase of the equivalent ratio variation of 21 is equal. For this reason, when the equivalence ratio fluctuation is maximized, the combustion amount becomes large, and the possibility that the vibration energy becomes large due to the fluctuation of the pressure in the same phase in the entire burner.

  In particular, hydrogen-containing fuels have a higher combustion speed and lower ignition energy than fuels that do not contain hydrogen, such as LNG. Therefore, flames are easy to approach near the burner and easily ignite near the burner, causing pressure fluctuations. The possibility to do is also increased.

Therefore, in this reference example , the characteristic frequency of each air hole 21 is detuned in each row to suppress the occurrence of combustion vibration.

Hereinafter, the effect of this reference example will be described with reference to FIG. 7 expands the second row of air holes 52 and the second row of fuel nozzles 22 along the pitch circle of the second row of air holes shown in FIG. Shows fluctuations.

  As shown in the figure, the distance from the tip of each fuel nozzle 22 to the combustion chamber side surface 301 (air hole outlet) of the air hole plate 20 is Lij (i: row number, j: circumferential air hole number). And Since Lij is different in the circumferential direction of each row, the pressure fluctuation frequency fj (j: circumferential air hole number) of each hole is different.

  The waveform of the pressure fluctuation generated in the air hole 21 opening at θ1 and the equivalence ratio fluctuation of the coaxial jet is illustrated in the upper left of FIG. 7, and the equivalent ratio of the pressure fluctuation generated in the air hole 21 opening in θ6 and the coaxial jet is illustrated in the upper right. The waveform of fluctuation is illustrated.

As shown in the figure, since the pressure fluctuation generated at θ1 and the pressure fluctuation generated at θ6 have different phases, the pressure fluctuation at θ6 does not become the maximum when the pressure fluctuation at θ1 is the maximum, and the pressure wave in the entire burner. Will not overlap and strengthen each other. At the same time, variations in the equivalence ratio of θ1 and θ6 are also different in phase, so that the amount of combustion generated by the equivalence ratio variation of each air hole 21 does not increase and does not reinforce vibration energy.

  Therefore, since the frequency of the pressure fluctuation that grows for each air hole 21 does not overlap and strengthen each other, the amplitude of the pressure fluctuation does not increase. Furthermore, since Lij is different in the circumferential direction of each row, the time for the pressure wave generated by the ignition of the combustible mixture to reach the tip of the fuel nozzle 22 is different, and the phases of the pressure waves are different from each other. Therefore, the pressure waves do not intensify each other, and the combustion vibration is suppressed.

According to such a configuration of the present reference example , the amplitude of the pressure fluctuation does not increase, generation of combustion vibration can be suppressed, and a gas turbine combustor with improved reliability can be obtained.

In this reference example , the length of all the fuel nozzles 22 is changed. However, when the number of fuel nozzles 22 is large, several fuel nozzles 22 having the same length are combined. Even if it is composed of a plurality of units, the basic operation and effects described above are not impaired.

Further, in this reference example, with respect to the second row air holes 52, the distance between the tip of the fuel nozzle 22 and the position of the combustion chamber side surface 301 (air hole outlet position) is changed in the circumferential direction, or the length of the fuel nozzle 22 is increased. Although the structure for changing the circumferential direction of the fuel nozzle 22 has been described, the length of the fuel nozzle 22 may be changed in the circumferential direction by the first row air holes 51 and the third row air holes 53, and the first and second rows. The effects described above can be expected even if the circumferential lengths of the eye air holes 51 and 52 and the first to third air holes 51 to 53 are all changed.
[Example 1 ]
Next, Embodiment 1 of the gas turbine combustor of the present invention will be described with reference to FIGS. 8A, 8B, 9 and 10. FIG.

In this embodiment, a plurality of burners 8 of Reference Example 1 are arranged to constitute one combustor 3. That is, as shown in FIG. 8A and FIG. 8B, the combustor 3 of this embodiment is located at one central burner 32 located at the axial center of the combustor 3 and outside the central burner 32. It consists of six outer peripheral burners 33.

  The central axis of the air holes 21 in each row is inclined in the circumferential direction of the pitch circle of each row, and the flow that has passed through the air holes 21 swirls spirally downstream of the air holes 21 to form a swirling flow. . The swirl direction of the swirl flow formed by the respective outer peripheral burners 33 is counterclockwise as viewed in FIG.

  The feature of this embodiment is that, in each of the outer peripheral burners 33, the distance between the tip of the fuel nozzle 22 and the position of the combustion chamber side surface 301 (air hole outlet position) in each row is the center burner of each burner 8. It is configured to gradually change and increase (become longer) as it proceeds in the turning direction with the region adjacent to 32 as a base point. In other words, the length of the fuel nozzle 22 in the axial direction gradually decreases step by step as it advances in the swivel direction starting from the region adjacent to the central burner 32 of each burner 8.

  FIG. 9 shows a specific arrangement example of the fuel nozzles 22 in the outer peripheral burner 33 in the present embodiment.

  In the example shown in FIG. 9, the outer peripheral burner 33 is regarded as one region for each length of the fuel nozzle 22, the region A adjacent to the central burner 32, the region C adjacent to the liner 12 (see FIG. 1), and the other outer periphery. The area is divided into four areas B and D adjacent to the burner 33.

  FIG. 10 shows the relationship between the lengths of the fuel nozzles 22 in the circumferential direction of the outer burner in the four regions described above.

  As shown in the figure, the length of the fuel nozzle 22 is gradually reduced in the turning direction (θ direction) of the outer peripheral burner 33, with the area adjacent to the central burner 32 being A. That is, the fuel nozzle 22 in the region A is the longest, the region B is shorter than the region A, and the regions C and D are shorter than the region B. In the region D, the length of the region C and the fuel nozzle 22 may be equal.

Also in this embodiment, as in Reference Example 1, the distance from the tip of the fuel nozzle 22 to the combustion chamber side surface 301 of the air hole plate 20 is different in the circumferential direction in each outer peripheral burner 33. . Therefore, similarly to the reference example 1, the outer peripheral burner 33 has different frequency characteristics for each region in the circumferential direction, and pressure and equivalent ratio fluctuations are not synchronized in the entire burner, so that generation of pressure vibration is suppressed. .

Further, in the present embodiment, the following effects can be further obtained by arranging a plurality of the burners 8 of the reference example 1 with the reference position 70 at a portion adjacent to the central burner 32.

That is, as shown in FIG. 10, by changing the length of the fuel nozzle 22 in the circumferential direction in one outer peripheral burner 33, the length of the portion where the fuel and air are mixed inside the air hole is changed to the circumferential region. It changes every time. This length is called the mixing distance. The longer the mixing distance, the longer the coaxial jet burner, the more uniform the air-fuel mixture ejected therefrom, and the smaller the standard deviation of the fuel concentration in the air-fuel mixture. Even air-fuel mixtures having the same equivalent ratio as an average have a minute concentration distribution inside.

  In general, an air-fuel mixture with a large standard deviation in concentration distribution has excellent ignitability and flame propagation characteristics because the thermal decomposition of fuel and the generation of active chemical species are active in locally high concentration regions. High temperature combustion gas masses are formed.

  On the other hand, in an air-fuel mixture with a small standard deviation of the concentration distribution, since the fuel is thin as a whole, the ignition delay is increased and the flame propagation speed is reduced, but a local high-temperature combustion gas mass is hardly generated.

  The area A of the outer burner 33 adjacent to the central burner 32 that bears flame holding has a shorter mixing distance of fuel and air than the other areas of the outer burner 33, and the standard deviation of the fuel concentration in the mixture is large. Therefore, the air-fuel mixture ejected from the coaxial jet burner arranged in the region A has a large concentration deviation as compared with the air-fuel mixture in other regions, and a lump having a locally high equivalence ratio is included in the air-fuel mixture.

  Since the air-fuel mixture having a locally high equivalence ratio as described above is excellent in ignitability and flame propagation, combustion stabilization of the entire combustor can be achieved. Accordingly, the region A of the outer peripheral burner 33 is suitable for receiving heat and active chemical species from the central burner 32 and propagating them to the base point of the outer peripheral burner 33.

  On the other hand, the region B has a longer mixing distance than the region A, and the standard deviation of the fuel concentration is smaller than the region A. However, because it is adjacent to the region A and downstream of the swirl, the flame stability can be kept high by the locally hot combustion gas mass flowing from the region A.

  Further, the fuel nozzle 22 in the region C has the longest mixing distance in each of the outer peripheral burners 33, so that it is burned lean and contributes to NOx reduction. In addition, since the local high temperature portion is unlikely to exist, the liner 12 adjacent to the region C is not overheated, and the reliability of the combustor 3 can be ensured.

  Regions B and D have different fuel nozzle lengths and different synchronization frequencies when pressure fluctuations occur. Therefore, since the pressure fluctuation is detuned between the adjacent outer burners 33, the amplitude of the pressure fluctuation does not increase in the whole burner, and the occurrence of combustion vibration is suppressed.

  DESCRIPTION OF SYMBOLS 1 ... Gas turbine plant, 2 ... Air compressor, 3 ... Combustor, 4 ... Gas turbine, 5 ... Combustion chamber, 6 ... Generator, 7 ... Gas turbine starting motor, 8 ... Burner, 10 ... Outer cylinder, 12 ... liner, 13 ... combustor end cover, 20 ... air hole plate, 21 ... air hole, 22 ... fuel nozzle, 23 ... fuel distributor, 32 ... central burner, 33 ... outer peripheral burner, 51 ... single row air hole, 52 ... second row air holes, 53 ... third row air holes, 60 ... fuel shutoff valve, 61a, 62a ... fuel pressure adjustment valve, 61b, 62b ... fuel flow rate adjustment valve, 70 ... reference position, 83, 83a, 83b 83c ... flame surface, 90 ... low flow velocity region, 101 ... air, 102, 102a ... compressed air, 103 ... cooling air, 110 ... combustion gas, 111 ... exhaust gas, 200, 201, 202 ... gas fuel, 300 ... air Hole plate Ndokaba surface, 301 ... combustion chamber-side surface of the air hole plate.

Claims (6)

A combustion chamber to which fuel and air are supplied; an air hole plate located on an upstream side wall surface of the combustion chamber; and a plurality of air holes formed in a concentric array, and each air hole of the air hole plate In a gas turbine combustor comprising a plurality of fuel nozzles and a plurality of burners comprising the plurality of fuel nozzles and the plurality of air holes,
A central burner is disposed on the central axis of the combustor, and a plurality of outer peripheral burners are disposed around the central burner, and the outer peripheral burner is disposed at a tip end of the fuel nozzle from a reference position adjacent to the central burner. The gas turbine combustor is configured such that the distance between the air hole plate and the surface of the air hole plate on the combustion chamber side sequentially increases in the circumferential direction of the air hole plate. The gas turbine combustor according to claim 1.
The outer peripheral burner has a plurality of air holes formed in the air hole plate inclined in the circumferential direction, and from the reference position on the inner peripheral side of the combustor where the central burner is disposed, the tip of the fuel nozzle and the air A gas turbine combustor, wherein the distance between the hole plate and the combustion chamber side surface is sequentially increased in the direction of inclination of the air hole. The gas turbine combustor according to claim 1 or 2,
The plurality of outer peripheral burners are divided into a region A adjacent to the central burner, a region C adjacent to the liner of the combustor, and regions B and D adjacent to other adjacent outer peripheral burners, respectively. The distance between the tip of the fuel nozzle and the combustion chamber side surface of the air hole plate is the shortest, and the distance between the tip of the fuel nozzle in the region B and the combustion chamber side surface of the air hole plate is shorter than the region A. A gas turbine combustor which is long and is configured such that the distance between the tip of the fuel nozzle in the regions C and D and the combustion chamber side surface of the air hole plate is longer than that in the region B. A combustion chamber to which fuel and air are supplied; an air hole plate located on an upstream side wall surface of the combustion chamber; and a plurality of air holes formed in a concentric array, and each air hole of the air hole plate In a gas turbine combustor comprising a plurality of fuel nozzles and a plurality of burners comprising the plurality of fuel nozzles and the plurality of air holes,
A central burner is disposed on the central axis of the combustor, and a plurality of outer peripheral burners are disposed around the central burner, and the outer peripheral burner extends from a reference position adjacent to the central burner to the length of the fuel nozzle. The gas turbine combustor is configured so that the length of the air hole plate gradually decreases in the circumferential direction of the air hole plate. The gas turbine combustor according to claim 4.
The outer circumferential burner has a length of the fuel nozzle from a reference position on the inner circumferential side of the combustor where the plurality of air holes formed in the air hole plate are inclined in the circumferential direction and the central burner is disposed. A gas turbine combustor configured to be sequentially shortened in an inclination direction of the air hole. The gas turbine combustor according to claim 4 or 5,
The plurality of outer peripheral burners are divided into a region A adjacent to the central burner, a region C adjacent to the liner of the combustor, and regions B and D adjacent to other adjacent outer peripheral burners, respectively. The length of the fuel nozzle is the longest, the length of the fuel nozzle in the region B is shorter than the region A, and the length of the fuel nozzle in the regions C and D is shorter than the region B. A gas turbine combustor characterized by comprising:

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