JP5372814B2 - Gas turbine combustor and operation method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor that achieves both suppression of NOx discharge and securement of combustion stability. <P>SOLUTION: The gas turbine combustor includes a mixing chamber for mixing fuel and air; a mixing chamber forming member for forming the mixing chamber; a plurality of first air holes provided in the mixing chamber forming member and supplying air into the mixing chamber; and a plurality of first fuel nozzles for jetting fuel toward the first air holes. A second air hole is disposed at a position for making air flow flowing therein, take along more of fuel jetted from the first fuel nozzles into the mixing chamber as the jetting speed of the fuel jetted from the first fuel nozzles becomes lower. <P>COPYRIGHT: (C)2011,JPO&amp;INPIT

Description

  The present invention relates to a gas turbine combustor and an operation method.

  One of the combustion methods of a gas turbine combustor is a premixed combustion method. The premix combustion method is a method in which fuel and air are mixed in advance in a premixer and then burned in a combustion chamber. By mixing fuel and air in advance and burning, local high temperature regions can be suppressed and thermal NOx can be reduced. One example of a combustor that employs a premixed combustion burner is a combination with a diffusion combustion type burner that injects fuel directly into a combustion chamber and burns it. This is to ensure combustion stability from low load to high load.

  As an example of a combustor in which a premixed combustion burner and a diffusion combustion burner are combined, in Patent Document 1, a diffusion combustion burner is disposed as a pilot burner that holds a flame at the axial center position of the combustor. A combustor arranged to surround the perimeter is described. With this configuration, the effect of reducing NOx by the premixed combustion burner and the effect of improving the combustion stability by the diffusion combustion burner can be obtained. Patent Document 1 describes a technique for improving the combustion stability over a wide load range by controlling the combustion ratio between the diffusion combustion burner and the premixed combustion burner.

  In Patent Document 2, as a combustor for complying with strict NOx emission control, a hollow conical mixing chamber that expands in the ejection direction, and a plurality of air introductions for introducing combustion air into the mixing chamber A combustor having a pilot burner with a hole and a gaseous fuel nozzle for ejecting gaseous fuel substantially coaxially with the air introduction hole is described. Generally, in a combustor in which a diffusion combustion burner and a premixed combustion burner are combined, most of the NOx emission amount is occupied by a pilot burner which is a diffusion combustion burner. On the other hand, in the combustor described in Patent Document 2, mixing of fuel and air in the pilot burner is promoted to achieve low NOx.

JP-A-7-280267 JP 2007-064625 A

  In recent years, regulations on exhaust gases have been becoming more stringent year by year from the viewpoint of protecting the global environment, and further reduction of NOx emissions has been demanded. In the combustor described in Patent Document 1, a diffusion combustion burner is adopted as a pilot burner in order to ensure combustion stability over a wide load range. Therefore, in order to satisfy recent strict environmental regulations, it is necessary to take measures to suppress the NOx emission in the diffusion combustion burner.

  As one measure for that, it is conceivable to use the combustor of Patent Document 2. The combustor of Patent Document 2 uses a pilot burner that has a better mixing action of air and fuel than a general diffusion combustion burner. The combustor disclosed in Patent Document 2 can significantly reduce the amount of NOx emissions compared to the combustor in which the pilot burner disclosed in Patent Document 1 includes a diffusion combustion burner. However, when the combustor of Patent Document 2 is used, the following problems can be considered.

  In a combustor that combines a diffusion combustion burner and a premixed combustion burner, as the combustion load increases, the proportion of fuel supplied to the premixed combustion burner (hereinafter referred to as the premixed combustion ratio) is increased to reduce NOx emissions. Drive in a controlled manner. When the premixed combustion ratio is increased to reduce NOx, the flow rate of fuel supplied to the pilot burner decreases. If it does so, the ratio (henceforth a fuel-air ratio) of the fuel with respect to the air of a pilot burner also becomes small. In this case, there is a possibility that the combustion stability may be impaired due to the blow-off of the flame due to a local decrease in the flame temperature. On the other hand, when the fuel supply ratio to the pilot burner is increased to increase combustion stability (when the premixed combustion ratio is lowered), the NOx emission amount is not sufficiently suppressed.

  An object of the present invention is to provide a gas turbine combustor that achieves both NOx emission suppression and combustion stability.

In order to solve the above problems, the present invention provides a mixing chamber for mixing fuel and air, a mixing chamber forming member for forming the mixing chamber, and air in the mixing chamber provided in the mixing chamber forming member. A plurality of first air holes for supplying fuel, a plurality of first fuel nozzles for injecting fuel toward the first air holes, and an injection speed of fuel injected by the first fuel nozzles decreases. , in a position to flow the air flow into the second air hole is accompanied more fuel injected from the first fuel nozzle to the mixing chamber, the second air holes are arranged, the The second air hole is provided at a position that is in phase with respect to the circumferential direction of the first fuel nozzle and the mixing chamber .

  According to the present invention, it is possible to provide a gas turbine combustor that achieves both NOx emission suppression and combustion stability.

It is side sectional drawing of the pilot burner of 1st Example of this invention. It is AA sectional drawing of the burner shown to Fig.1 (a). It is sectional drawing which showed typically the flow of the air and fuel in a burner at the time of the driving | operation of the 1st Example of this invention. It is sectional drawing which showed typically the flow of the air and fuel in a burner at the time of the driving | operation of the 1st Example of this invention. 1 is a schematic configuration diagram schematically illustrating an overall configuration of a gas turbine plant including a first embodiment of the present invention. It is the figure which showed the NOx characteristic with respect to the gas turbine load of the 1st Example of this invention and a comparison technique. It is the figure which showed the NOx characteristic with respect to the pre-mixing combustion ratio of the 1st Example of this invention and a comparison technique. It is a burner sectional view of the 2nd example of the present invention. It is AA sectional drawing of the burner shown to Fig.5 (a). It is a sectional side view which shows the 3rd Example of this invention. It is side sectional drawing which shows the 4th Example of this invention.

  Hereinafter, embodiments of the gas turbine combustor of the present invention will be described with reference to the drawings.

  First, a first embodiment of the present invention will be described below with reference to FIGS.

  FIG. 3 is a schematic configuration diagram schematically showing the overall configuration of the gas turbine plant provided with the first embodiment of the present invention. As shown in FIG. 3, the gas turbine plant of the present embodiment mixes a compressor 200 that compresses air to generate high-pressure combustion air, combustion air 100 introduced from the compressor 200, and fuel. Combustor 202 that burns to generate combustion gas 150 and turbine 201 to which combustion gas 150 generated by this combustor 202 is introduced. In addition, the shafts of the compressor 200, the turbine 201, and the generator 203 are connected.

  The combustor 202 includes an inner cylinder 206 that burns combustion air 100 and fuel for combustion to generate a combustion gas 150, a transition piece 207 that guides the combustion gas 150 from the inner cylinder 206 to the turbine 201, An outer cylinder 204 that houses the cylinder 206 and the transition piece 207, an end cover 205, an ignition plug 210 that is supported by the outer cylinder 204 and ignites in the inner cylinder 206, and the like. The inner cylinder 206 has a cylindrical shape. On the upstream side of the inner cylinder 206, the pilot burner 1 is provided on the axis of the inner cylinder 206, and a plurality of premixed combustion burners 208 are arranged around it.

  The left figure of Fig.1 (a) shows the sectional side view of the pilot burner 1 which is the 1st Example of this invention. The right figure of Fig.1 (a) is the figure which looked at the pilot burner 1 from the combustion chamber side. FIG.1 (b) is AA sectional drawing of the right figure of Fig.1 (a). The pilot burner 1 includes a mixing chamber forming member 20 that forms a hollow conical mixing chamber 2 for promoting mixing of fuel and air, an air introduction hole 4 that introduces combustion air 100 into the mixing chamber 2, and an air introduction A plurality of holes 5 are provided. The air introduction holes 4 and 5 are provided in the mixing chamber forming member 20. The air introduction hole 5 is arranged on the outer peripheral side with respect to the central axis of the mixing chamber 2 than the air introduction hole 4. The air introduction holes 4 and 5 are formed so that the introduction angle of the combustion air 100 is deflected in the circumferential direction of the mixing chamber 2 in order to generate a swirling flow inside the mixing chamber 2.

  Further, the pilot burner 1 is provided with a liquid fuel nozzle 8 for injecting liquid fuel on the upstream side in the axial direction inside the mixing chamber 2. On the outer periphery of the liquid fuel nozzle 8, a gaseous fuel manifold 9, a gaseous fuel nozzle 6, and a gaseous fuel nozzle 7 as an outer peripheral side fuel nozzle are installed. The gaseous fuel nozzles 6 and 7 are arranged so as to inject fuel toward the opposed air introduction holes 4 and 5, respectively.

  The mixing chamber forming member 20 is provided with an air introduction hole 3 for supplying a part of the combustion air 100 to the mixing chamber 2 as the combustion air 109. The air introduction hole 3 is arranged at a position where the distance between the fuel injection port of the gaseous fuel nozzle 6 and the fuel injection port of the gaseous fuel nozzle 6 is closer than the distance between the fuel injection port of the gaseous fuel nozzle 6 and the air introduction hole 4. The distance referred to here is the length of the line segment connecting the point on the end surface of the air nozzle hole on the fuel nozzle side and the point on the end face of the fuel injection port so as to be the shortest. The air introduction hole 3 is provided so as to supply the combustion air 109 to the axial center side of the mixing chamber 2 from the position where the air introduction hole 4 supplies the combustion air. Furthermore, the air introduction hole 3 is arrange | positioned in the position used as the same phase about the circumferential direction of the gaseous fuel nozzle 6 and the mixing chamber 2, as shown in FIG.1 (b).

  Detailed events that occur in the combustor of the present embodiment having the above-described configuration will be described below. FIG. 2 is a detailed cross-sectional view of the pilot burner 1 in the present embodiment, and schematically shows the flow of the gaseous fuel 101 and the combustion air 100. FIG. 2 (a) shows the flow of gaseous fuel under conditions where the gaseous fuel flow rate is high, and FIG. 2 (b) shows the flow of gaseous fuel under conditions where the gaseous fuel flow rate is low.

  Under conditions where the gas turbine load is low, the fuel is burned only by the pilot burner 1 having high combustion stability. For this reason, the flow rate of the gaseous fuel supplied to the pilot burner 1 is sufficiently large under conditions of a low gas turbine load. On the other hand, under conditions with a high gas turbine load, the ratio of fuel supplied to the premixed combustion burner 208 is increased in order to suppress NOx emissions. If it does so, the ratio of the gaseous fuel supplied to the pilot burner 1 will decrease, and flow volume will become small.

  Since the cross-sectional area of the fuel flow path of the gaseous fuel nozzles 6 and 7 is constant regardless of the supplied fuel flow rate, the flow rate of the gaseous fuel flowing in the gaseous fuel nozzles 6 and 7 is substantially proportional to the fuel supply flow rate. That is, when the fuel supply flow rate is high, the flow rate of the fuel injected from the gaseous fuel nozzles 6 and 7 is high, and when the fuel supply flow rate is low, the flow rate of the fuel injected from the gaseous fuel nozzles 6 and 7 is low. Become.

  The air introduction hole 3 is arranged so that the distance between the fuel injection hole of the gaseous fuel nozzle 6 and the air introduction hole 3 is closer than the distance between the fuel injection hole of the gaseous fuel nozzle 6 and the air introduction hole 4. ing. Therefore, the gaseous fuel 104 injected from the gaseous fuel nozzle 6 is affected by the flow of the combustion air 109 flowing into the air introduction hole 3 before reaching the air introduction hole 4 provided in the fuel injection direction.

  In the present embodiment, the air introduction hole 3 is disposed at a position that is in phase with respect to the circumferential direction of the gaseous fuel nozzle 6 and the mixing chamber 2. Therefore, the gaseous fuel 104 injected from the gaseous fuel nozzle 6 toward the air introduction hole 4 passes immediately above the air introduction hole 3. The flow of the combustion air 109 becomes stronger as the position is closer to the air introduction hole 3. Therefore, the gaseous fuel 104 is strongly influenced by the combustion air 109 by passing immediately above the air introduction hole 3. Further, since the diameter of the air introduction hole 3 is traversed, the time affected by the combustion air 109 is also increased. Therefore, the gaseous fuel 104 can flow into the air introduction hole 3 more effectively.

  Under low load conditions where the flow rate of fuel supplied to the pilot burner 1 is large, the ejection speed of the gaseous fuel ejected from the gaseous fuel nozzles 6 and 7 is fast. Therefore, as shown in FIG. 2A, the gaseous fuel 104 penetrates the flow of the combustion air 109 flowing into the air introduction hole 3 and is injected almost coaxially with the combustion air 100 from the air introduction hole 4. In this case, the fuel and air are mixed inside the air introduction holes 4 and 5, and further mixing is further promoted by vortices generated when the fuel and air are ejected from the air introduction holes 4 and 5. Due to this two-stage mixing promotion effect, a fuel / air mixture 106 is generated inside the mixing chamber 2. This air-fuel mixture 106 is a so-called lean air-fuel mixture that has a small amount of locally overconcentrated fuel due to the two-stage mixing. By mixing the fuel and air in this way, it is possible to suppress the occurrence of a local high temperature region and to reduce the NOx emission amount.

  On the other hand, in the high load condition where the flow rate of fuel supplied to the pilot burner 1 is small as shown in FIG. 2B, the injection speed of the fuel injected from the gaseous fuel nozzles 6 and 7 is slow and the penetration force of the fuel jet is weak. . Therefore, the gaseous fuel 104 injected from the gaseous fuel nozzle 6 is accompanied by the combustion air 109 flowing toward the air introduction hole 3 and flows into the mixing chamber 2 from the air introduction hole 3. As a result, fuel is supplied to the axial center of the mixing chamber 2. In addition, the gaseous fuel 104 injected from the gaseous fuel nozzle 6 is strongly influenced by the combustion air 109 flowing into the air introduction hole 3 as the injection speed decreases.

  The gaseous fuel 104 is also affected by the air flow flowing into the air introduction hole 4. However, in the combustor of the present embodiment, the distance between the fuel injection port of the gaseous fuel nozzle 6 that is the first fuel nozzle and the air introduction hole 3 that is the second air hole is equal to the fuel injection port of the gaseous fuel nozzle 6. The air introduction hole 3 is disposed at a position closer to the distance from the air introduction hole 4 that is the first air hole. Therefore, the smaller the fuel injection speed, the more gaseous fuel 104 flows from the air introduction hole 3 into the mixing chamber 2.

  The mixing chamber of the combustor of the present embodiment has a shape that expands toward the downstream side in the axial direction. Further, a swirl angle is given to both the air introduction hole 4 as the first air hole and the air introduction hole 5 as the outer peripheral side air hole so as to generate a swirl flow in the mixing chamber 2.

  In this way, if a swirl angle is applied to at least one of the air introduction hole 4 or the air introduction hole 5, a swirl component can act on the combustion air 100 flowing in from the air introduction holes 4 and 5, and the influence of centrifugal force is exerted. A flow toward the outer peripheral side of the mixing chamber 2 can be formed. Thereby, mixing with the combustion air 100 and the gaseous fuel 104 which flowed in from the air introduction hole 3 is suppressed. As a result, a fuel rich mixture 107 is generated at the axial center of the mixing chamber 2. Due to the combustion of the air-fuel mixture 107, a high-temperature small flame 500 is formed at the axial center of the pilot burner 1. When this high-temperature flame becomes an anchor, the blow-off of the flame can be suppressed, and the combustion stability can be improved.

  In the operation described above, there is a concern that the amount of NOx emissions increases by the amount of high temperature flame formed. However, the premixed combustion ratio is high under high load conditions, and most of the NOx discharged from the combustor is occupied by NOx discharged by the premixed combustion burner 208. Compared with the total amount of NOx discharged by the premixed combustion burner 208, the amount of increase in NOx resulting from the formation of a high-temperature flame is small. That is, the influence of the increase in the NOx emission amount due to the provision of the air introduction hole 3 on the total amount of NOx discharged from the combustor is sufficiently small.

  FIG. 4 shows the NOx emission characteristics of the gas turbine combustor of this embodiment. (A) shows the NOx emission characteristics with respect to the gas turbine load, and (b) shows the NOx emission characteristics with respect to the premixed combustion ratio under the rated load conditions. It is shown. Here, the combustor described in Patent Document 1 is shown as Comparative Technology 1, and the combustor described in Patent Document 2 is shown as Comparative Technology 2.

  As shown in FIG. 4A, in the combustor including the pilot burner of the present embodiment and the comparative technique 2, the comparative technique 1 is performed under the low load condition (up to point A) of the pilot burner alone combustion where the fuel flow rate is increased. As a result, NOx emissions can be reduced. This is because the combustion characteristics of the burner described above are different, and the NOx emission in the pilot burner is suppressed by promoting the mixing of fuel and air.

  Moreover, in FIG.4 (b), it turns out that each burner shows the tendency for NOx emission amount to fall by raising a premix combustion ratio. Here, the point that satisfies the target value (point a) of the NOx emission amount is the point b in the combustor of the comparative technique 1 and the point c in the comparative technique 2 and the combustor of the present embodiment. The difference between the point b and the point c is due to the reduction of NOx emissions by promoting the mixing of fuel and air in the pilot burner described above.

  On the other hand, as the premixed combustion ratio increases, the flow rate of the fuel supplied to the diffusion combustion burner decreases, and the flame blows out eventually. The d, e, and f points indicating the flame blow-off points also differ depending on the pilot burner. In the comparative technique 2 (point e), which has the lowest flame blow-off point, the flame temperature is lowered by diluting the fuel in the air-fuel mixture generated in the mixing chamber, so that the flame blows off at a low premixed combustion ratio. Indicates. On the other hand, according to the combustor of the present embodiment, under the condition that the fuel flow rate of the pilot burner is reduced, the effect of being able to form a small flame 500 having a high flame temperature at the axial center portion of the pilot burner, a high premixed combustion ratio Driving is possible.

  Normally, NOx emission characteristics and blow-off characteristics vary depending on atmospheric conditions (temperature and humidity). Therefore, in order to ensure the combustion stability, it is preferable that the range of the premixed combustion ratio from the point where the target value of NOx can be satisfied to the point where the flame blows out is ensured widely. In the combustor of the present embodiment, the range (between cf: z) can be ensured wider than between b and d in comparison technique 1: x and between c and e in comparison technique 2: y. That is, it can be said that the combustion stability of the combustor is high.

  As described above, according to the combustor of the present embodiment, the NOx emission amount is reduced under the low load condition where the fuel flow rate supplied to the pilot burner 1 is increased, while the fuel flow rate is reduced under the high load condition. Combustion stability can be improved, and a more reliable combustor can be provided.

  Next, a second embodiment of the present invention will be described with reference to FIG. The left figure of Fig.5 (a) shows the sectional side view of the pilot burner 1 in the 2nd Example of this invention. The right figure of Fig.5 (a) is the figure which looked at the pilot burner 1 from the combustion chamber side. FIG.1 (b) is AA sectional drawing of the right figure of Fig.1 (a).

  The basic configuration of this embodiment is the same as that of the first embodiment. The difference between this embodiment and the first embodiment is that, as shown in FIG. 5B, the second air introduction hole 3 so that the swirl acts on the combustion air 109 flowing in from the second air introduction hole 3. Is formed by deflecting α degrees in the circumferential direction of the mixing chamber 2.

  In the combustor shown in the present embodiment, the combustion air 109 flowing from the second air introduction hole 3 is swirled inside the mixing chamber 2. A circulating flow is formed by the swirling flow generated in this way, and the small flame 500 can be further stabilized as compared with the first embodiment. As a result, even when the amount of fuel supplied to the pilot burner 1 is smaller, it is possible to suppress the blow-off of the flame, and it is possible to operate at a higher premixed combustion ratio than in the first embodiment. Therefore, combustion stability is further improved by increasing the operating margin, and a highly reliable combustor can be provided.

  Next, a third embodiment of the present invention will be described with reference to FIG. FIG. 6 is a side sectional view of the pilot burner 1 in the third embodiment of the present invention.

  The basic components of this embodiment are the same as those of the first embodiment. The difference between the present embodiment and the first embodiment is that the hole area of the air introduction hole 3 is smaller than the hole area of the air introduction holes 4 and 5.

  In the combustor shown in the present embodiment, the amount of air flowing from the second air introduction hole 3 can be reduced. Therefore, under a high load condition where the fuel flow rate of the diffusion combustion burner is small, an air-fuel mixture having a high fuel concentration can be generated by the axial center portion of the mixing chamber 2, and the flame temperature of the small flame 500 can be made higher.

  As a result, it is possible to operate at a premixed combustion ratio higher than that of the first embodiment, and the combustion stability is further improved by increasing the operating margin, and a highly reliable combustor can be provided. Although there is a concern about the increase in NOx emission due to the high temperature of the small flame 500 of the pilot burner 1, the increase in NOx can be offset by further increasing the premixed combustion ratio by utilizing the expanded operating margin. Therefore, the NOx emission amount does not increase significantly.

  Further, if the structure of the present embodiment and the turning structure of the second embodiment are combined, further performance improvement can be expected.

  Next, a fourth embodiment of the present invention will be described with reference to FIG. The side sectional view of the pilot burner 1 in the 4th example of the present invention is shown.

  The basic components of this embodiment are the same as those of the first embodiment. The difference between the present embodiment and the first embodiment is that the fuel supply system of the gaseous fuel nozzle 6 facing the air introduction hole 4 and the gaseous fuel nozzle 7 facing the air introduction hole 5 is divided and each system is divided. Are provided with flow control valves 303 and 305 and fuel cutoff valves 304 and 306. In the present embodiment, a control device 307 is provided as means for controlling these valves.

  In the combustor shown in the present embodiment, depending on the gas turbine load, the operation of supplying fuel only to the gaseous fuel nozzle 6, the operation of supplying fuel to the gaseous fuel nozzle 7, and the gaseous fuel nozzles 6 and 7 Operation to supply fuel becomes possible. Furthermore, the fuel distribution between the gaseous fuel nozzles 6 and 7 can also be adjusted. In particular, the ability to adjust the relative flow rates of the gaseous fuel nozzles 6 and 7 contributes to an increase in the degree of freedom in operating the combustor. This is because the formation of the small flame 500 can be adjusted more freely.

  In this embodiment, the gas fuel nozzle on the inner peripheral side of the burner is used as the first gas fuel nozzle 6 and the gas fuel nozzle on the outer peripheral side is used as the second gas fuel nozzle 7, so that the fuel is divided into two fuel supply systems. However, the control may be performed for each of the other combinations or each nozzle. Further, this embodiment may be combined with the second and third embodiments.

DESCRIPTION OF SYMBOLS 1 Pilot burner 2 Mixing chamber 3,4,5 Air introduction hole 6,7 Gas fuel nozzle 20 Mixing chamber formation member 100 Combustion air 101 Gas fuel 103 Flame 200 Compressor 201 Turbine 202 Combustor 203 Generator 206 Inner cylinder 207 Transition piece 208 Premixed combustion burner

Claims (6)

A mixing chamber for mixing fuel and air;
A mixing chamber forming member for forming the mixing chamber;
A plurality of first air holes provided in the mixing chamber forming member for supplying air into the mixing chamber;
A plurality of first fuel nozzles for injecting fuel toward the first air holes;
In a gas turbine combustor having
The mixing chamber forming member has a second air hole for supplying air to the axial center side of the mixing chamber from the first air hole,
As the injection speed of the fuel injected by the first fuel nozzle decreases, the air flow flowing into the second air hole becomes more mixed with the fuel injected from the first fuel nozzle into the mixing chamber. The second air hole is arranged at a position to be introduced ,
The gas turbine combustor, wherein the second air hole is provided at a position that is in phase with respect to the circumferential direction of the first fuel nozzle and the mixing chamber .   The gas turbine combustor according to claim 1.
  The cross-sectional area of the second air hole is smaller than the cross-sectional area of the first air hole
Combustor characterized by that.   The gas turbine combustor according to claim 1 or 2,
  A plurality of outer peripheral fuel nozzles provided on the outer peripheral side with respect to the central axis of the mixing chamber from the first fuel nozzle;
  An outer peripheral air hole provided in the mixing chamber forming member in the same number as the outer peripheral fuel nozzle so as to face the outer peripheral fuel nozzle;
  And a control device capable of controlling a relative flow rate of the fuel supplied to the first fuel nozzle and the fuel supplied to the outer peripheral fuel nozzle.
Combustor characterized by that.   The gas turbine combustor according to any one of claims 1 to 3,
  A second fuel nozzle for injecting fuel into the mixing chamber at an axially upstream portion in the mixing chamber;
Combustor characterized by that.   The gas turbine combustor according to any one of claims 1 to 4, wherein:
  The mixing chamber has a shape that expands toward the downstream side in the axial direction,
  At least one of the first air hole and the outer peripheral side air hole is configured to generate a swirling flow in the mixing chamber.
Combustor characterized by that.   In the gas turbine combustor according to any one of claims 1 to 5,
  The second air hole is configured to generate a swirling flow in the mixing chamber.
Combustor characterized by that.

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