JP3709671B2 - Gas turbine combustor - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a gas turbine combustor, and more particularly to a gas turbine combustor including a first burner that performs diffusion combustion or premix combustion, and a plurality of second burners that perform premix combustion around the first burner.
[0002]
[Prior art]
Gas turbines must operate over a wide power range to accommodate large load changes from startup to rated load. Therefore, it is one of the essential requirements of the gas turbine combustor that the combustion is stable even if the operating conditions such as the air flow rate and the fuel flow rate greatly change from the start to the rated load.
[0003]
On the other hand, in order to reduce the emission amount of nitrogen oxide (hereinafter referred to as NOx) discharged from the gas turbine combustor, a combustion method capable of suppressing the generation of NOx is strongly demanded.
[0004]
As a combustion method with a small amount of exhausted NOx, there is premixed combustion in which fuel and air are mixed in advance before a combustion reaction and then burned. In general, the NOx generation amount increases exponentially as the combustion flame temperature increases. Premixed combustion can prevent the combustion flame temperature from rising locally, so increasing the ratio of air to fuel to make the premixed gas lean reduces the combustion flame temperature and reduces NOx. Emissions can be reduced. Therefore, in order to meet the demand for lower NOx, which is becoming stronger in recent years, the ratio of operation with lean premixed combustion is increasing.
[0005]
However, in general, lean premixed combustion has characteristics that the flame is more easily blown out and combustion vibration is generated than the diffusion combustion in which air and fuel are mixed and burned, and the operation range in which stable combustion is possible is narrow. Therefore, in order to achieve low NOx while ensuring stabilization of combustion, it is necessary to skillfully combine diffusion combustion and lean premixed combustion.
[0006]
In order to stably perform the premix combustion, an annular premix combustion burner is disposed so as to surround the diffusion combustion burner or the diffusion / premix combustion combination burner, or the diffusion combustion burner or the diffusion / premix combustion combination burner is disposed. There are means for holding a premixed flame by a stable diffusion flame by arranging a plurality of premixed combustion burners around, and these are disclosed in JP-A-5-322169 or JP-A-6-129640. Has been described.
[0007]
Further, as a means for stabilizing the premixed flame itself, the flame of the combustion gas is formed by deflecting the flow of the premixed gas of fuel and air in the vicinity of the premixed gas outlet and forming a circulation flow of the combustion gas on the downstream side. It is effective to arrange a flame holder to hold. Therefore, a combustor in which a premixed combustion burner with a flame holder and a pilot burner by diffusion combustion are combined has been proposed. These are described in JP-A-4-103906 or JP-A-5-157239.
[0008]
[Problems to be solved by the invention]
A problem in a combustor that combines a premixed combustion burner and a pilot burner by premixed combustion is that combustion oscillation occurs when the relationship between the two flames becomes unstable. Here, even if the pilot burner is operated only by diffusion combustion, even if it is the case of diffusion / premixed combustion operated by switching between diffusion combustion and premixed combustion according to the load, the same problem Occurs.
[0009]
Conditions under which combustion oscillations occur are extremely complex. Conditions that cause the flame to become unstable if the fuel for diffusion combustion, the premixed gas injection conditions, the supply ratio of the fuel for premixed combustion and the fuel for diffusion combustion are changed, etc. Appears and combustion vibration occurs. In order to suppress the emission of NOx accompanying combustion, it is desirable to make the ratio of the fuel for diffusion combustion as small as possible. However, if combustion vibration occurs under such conditions, the vibration level becomes extremely large.
[0010]
In a combustor in which a conventional premixed combustion burner and a diffusion burner pilot burner are combined, the fuel supply amount ratio of diffusion combustion is increased, and combustion stabilization is achieved by a diffusion combustion flame. Alternatively, the interference between the premixed flame and the diffusion flame is reduced by arranging the combustion chamber for diffusion combustion separately on the upstream side of the combustion chamber for premixed combustion. However, in the burner having such a configuration, the combustion air flow rate for diffusion combustion suppresses the generation of NOx from the diffusion combustion flame, and prevents a high temperature portion from being locally generated and damaging the structural material. Therefore, it must be distributed according to the maximum value of the diffusion fuel supply amount.
[0011]
For this reason, since the flow rate of air supplied from the compressor to the combustor is limited, the ratio of the flow rate of combustion air distributed to the premixer is reduced, the ratio of lean premixed combustion cannot be increased, and the exhaust NOx There was a limit to reducing this. In addition, if the ratio of the fuel for diffusion combustion is reduced in such a combustor, the temperature of the combustion gas due to diffusion combustion decreases, making it difficult to propagate the flame to the premixed flame formed downstream of the diffusion combustion chamber. For this reason, there is a limit to the reduction of exhaust NOx.
[0012]
As one of the methods for solving these problems, the premixed combustion burner and the pilot burner by diffusion combustion are adjacent to each other, and a part of the combustion air of the fuel supplied to the pilot burner is shared with the combustion air of the premixed combustion burner. Combustor structures have been proposed. In this case, as a configuration of the combustor, an annular premixed combustion burner is disposed so as to surround the diffusion pilot burner, or a plurality of premixed combustion burners are disposed around the diffusion pilot burner. Further, when a swirl flow is applied to the gas ejected from the pilot burner, it can be mixed with the air of the premixed combustion burner better. Here, only the combustion air may be applied to the swirl flow, or both the combustion air and the fuel may be applied. In any case, the diffusion combustion fuel is dispersed in the circumferential direction by the swirling flow while being burned, and is mixed with the air ejected from the premixer to continue the combustion. In this combustor configuration, the flow rate of combustion air used only for the combustion of the pilot burner can be reduced, so that the lean premixed combustion ratio can be increased and the exhaust NOx can be reduced.
[0013]
However, on the other hand, in the combustor having the above configuration, when the ratio of the diffusion fuel flow rate is lowered, a condition for generating combustion vibration appears, which is a big problem that hinders the operability and reliability of the gas turbine combustor. . Here, if the diffusion pilot burner is a diffusion / premixed combustion combined burner that performs diffusion combustion when the load is low and switches to premixed combustion when the load increases and the fuel flow rate increases, the ratio of the fuel flow rate of the pilot burner is Exhaust NOx can be reduced without lowering, but in this case as well, a condition in which combustion vibration occurs depending on the fuel ratio of the pilot burner and the premixed combustion burner appears, and the same problem as in the case of the diffusion pilot burner occurs. there were.
[0014]
The object of the present invention is to suppress the formation of an unstable flame in the shear layer at the boundary between the premixed combustion burner and the swirl burner and to reduce the combustion vibration in a wide operating range including combustion conditions that can reduce NOx emissions. An object of the present invention is to provide a gas turbine combustor capable of suppressing generation .
[0015]
[Means for Solving the Problems]
A gas turbine combustor according to the present invention includes a combustion chamber to which fuel and air are supplied, a first burner that ejects fuel into the combustion chamber and swirls the air, and a periphery of the first burner. A plurality of second burners for supplying a premixed mixture of air and fuel to the combustion chamber, and arranged outside the first burner and inside the premixed gas flow of the second burner for combustion An annular partition having a surface inclined with respect to the central axis of the combustion chamber formed so as to have a radial cross-sectional area extending downstream of the chamber, and disposed on the inclined surface of the annular partition with a spacing in the circumferential direction, A plurality of air jets for jetting air in the direction of the central axis of the chamber, and a control means capable of varying the flow rate of the air jetted from the air jets according to the load .
[0016]
Alternatively, the gas turbine combustor of the present invention includes a combustion chamber to which fuel and air are supplied, a first burner that swirls and jets a premixed mixture of fuel and air into the combustion chamber, A plurality of second burners arranged around the burner and supplying a premixed mixture of air and fuel to the combustion chamber, and outside the first burner and inside the flow of the premixed gas in the second burner An annular partition wall having a surface inclined to the central axis of the combustion chamber and having a radial cross-sectional area extending toward the downstream of the combustion chamber, and a circumferentially spaced interval between the inclined surface of the annular partition wall And a plurality of air jets that eject air in the direction of the central axis of the combustion chamber, and control means that can vary the flow rate of the air jetted from the air jets according to the load .
[0017]
Moreover, it is preferable that the said air jet nozzle is arrange | positioned cyclically | annularly centering | focusing on the said 1st burner.
[0018]
Thus, as the first burner, a swirl burner that ejects a swirling flow is used, and the fuel nozzle is disposed in the vicinity of the combustion chamber, and the fuel ejected from the fuel nozzle burns while being mixed with the swirling air flow. A diffusion combustion burner may be used, or a fuel nozzle may be provided on the upstream side of the air flow path separately from the fuel nozzle and operated as a diffusion / premixed combustion combined burner that switches the fuel nozzle to be used according to the load. A so-called premixed combustion burner is applied as the second burner.
[0020]
A gas turbine combustor with a diffusion burner with a swirler and a premixed combustion burner, or a diffusion / premixed combustion burner with a swirler and a premixed combustion burner adjacent to each other depends on the fuel supply ratio to both burners. A condition for generating combustion vibration appears. Such combustion vibration behavior includes the interaction between the region in which the combustion reaction proceeds by the fuel supplied from the burner with swirler and the flame formation region by the fuel supplied from the premixed combustion burner. Is considered to play an important role. That is, although the flame by the burner with a swirler is stable per se, when the amount of fuel supplied to the burner with the swirler decreases, the flame formation region changes and fluctuations occur. In addition, a shear layer is formed at the boundary between the premixed combustion burner and the burner with a swirler, and a flame is formed in the shear layer when the premixed gas exceeds a certain concentration. It has been found that fluctuations occur in the shear layer flame when the amount is reduced. When the fluctuation phase coincides with the phase of change in the combustion reaction of the premixed combustion burner, it is considered that a large combustion vibration is generated corresponding to the frequency of the acoustic system of the combustor.
[0021]
Therefore, the present invention suppresses combustion vibration by suppressing fluctuations in the premixed flame depending on the fuel supply ratio to the burner with swirler. Further, the shear layer flame formed in the shear layer of the premixed combustion burner is prevented from fluctuating.
[0022]
An annular partition wall having a radial cross-sectional area that increases toward the downstream side having an inclined surface is disposed between the swirl burner and the premixed combustion burner. With such a configuration, it is possible to form a reverse flow region accompanying the swirl flow by the swirl burner on the inclined surface of the partition wall, and to start combustion stably from the region. This effect can prevent the shear layer flame formed in the shear layer of the premixed combustion burner to a certain extent, and is particularly effective in the range where the fuel flow rate of the swirl burner is large.
[0023]
However, with such a configuration alone, the effect of preventing the fluctuation of the shear layer flame formed in the shear layer of the premixed combustion burner is not sufficient when the fuel flow rate of the swirl burner is small. This is due to the fact that when the fuel concentration in the backflow region associated with the swirl flow decreases, the combustion start region fluctuates within the backflow region. Therefore, in the present invention, in order to stabilize the combustion start region in the reverse flow region in the range where the fuel flow rate of the swirl burner is small, the partition wall between the adjacent premixed combustion burners is provided with the swirl burner. An air jet opening opened in the direction of the flow path center axis is disposed.
[0024]
With such a configuration, a flame is formed along the air flow ejected from the air outlet, so that the combustion start region does not fluctuate even in a range where the fuel flow rate of the swirl burner is small, and the flame fluctuates. Can be prevented. Here, the air outlet is opened toward the flow path center axis of the swirl burner. Thereby, since an air flow is formed away from the air jet outlet away from the jet direction of the air flow of the adjacent premix combustion burner, the interference between the air flow and the air flow of the premix combustion burner can be avoided, Moreover, it can suppress that the shear layer flame formed in the shear layer of a premixed combustion burner fluctuates. Further, in order to open the air jet outlet in the direction of the center axis of the flow path of the swirl burner, for example, an inclined surface is provided in a partition wall between the adjacent premixed combustion burners, and the inclined surface is opened. Can be achieved. Therefore, in a gas turbine combustor equipped with a diffusion combustion burner and a premixed combustion burner, or a diffusion / premixed combustion combined burner and a premixed combustion burner, in order to increase the lean premixed combustion ratio and reduce exhaust NOx. Even if the air flow rate and the fuel flow rate are changed in a wide range, combustion vibration does not occur and stable combustion is possible.
[0025]
In order to obtain the above-described action satisfactorily, in the combustor, an area where the flow path width becomes narrower from upstream to downstream is formed in the flow path of the air flow or mixed air flow of the swirl burner as necessary. For example, it is preferable to arrange a tapered shape in which the inner diameter of the flow path decreases as it approaches the outlet to the combustion chamber. By doing so, an air flow by the swirl burner can be stably formed on the downstream side of the partition wall, and an air flow from the air outlet can be quickly mixed, so that more stable combustion can be achieved.
[0026]
Here, the shape, arrangement, and number of the air outlets can be adjusted according to the operating conditions of the fuel flow rate of the swirl burner and the premixed combustion burner.
[0027]
When the gas turbine combustor according to the present invention is operated, the swirl burner is first ignited by diffusion combustion, and the premixed combustion burner is ignited after the load increases to some extent. In the present invention, it is possible to operate the swirl burner in the premixed combustion mode at the stage when the load becomes large, and this makes it possible to further reduce exhaust NOx.
[0028]
In the present invention, it is desirable to provide an air flow rate control means capable of varying the flow rate of the air ejected from the air ejection port disposed in the partition wall. This addresses the event that the NOx changes while the flame is stabilized by the air flow ejected from the air outlet. The exhaust NOx varies depending on the air flow rate and fuel flow rate at the boundary surface between the swirl burner and the premixed combustion burner, and the mixed state of both, and the air flow rate ejected from the air jet outlet also affects these.
[0029]
Here, since the air flow rate and the fuel flow rate at the boundary surface change depending on the load of the gas turbine combustor, the influence of the air flow rate ejected from the air outlet on the exhaust NOx changes depending on the load. Therefore, it is desirable that the flow rate of the air ejected from the air outlet is set so that the exhausted NOx does not increase greatly even when the load changes. However, generally, a plurality of gas turbine combustors are arranged around the gas turbine, but the air flow distribution characteristics of the individual combustors may be slightly different. Therefore, by providing an air flow rate control means that can vary the flow rate of the air jetted from the air jet port, it is possible to adjust the individual combustors so that the exhaust NOx does not increase greatly. This adjustment may be performed manually or automatically.
[0030]
Further, as described above, since the influence of the flow rate of air jetted from the air jet port on the exhaust NOx differs depending on the load, it is more effective to make the air flow rate variable according to the load.
[0031]
DETAILED DESCRIPTION OF THE INVENTION
(Example 1)
An embodiment of the present invention will be described with reference to FIGS. 1 is a sectional view of a gas turbine combustor according to the present embodiment, FIG. 2 is a view of FIG. 1 viewed from the downstream side, and FIG. 3 is an enlarged view of a part of FIG. The combustor has a burner with a swirler (hereinafter referred to as a swirl burner) 80 having swirl vanes 2 disposed on the central axis, and a premixer having a ring-shaped flame stabilizer 3 and a premixer 4 on the outer periphery thereof. A combustion burner 90 is arranged. The swirl burner 80 includes the fuel nozzle 1 at the center and an annular air flow path (air nozzle) 13 so as to surround the fuel nozzle 1. The swirl vane 2 is disposed at the tip of the air outlet of the air flow path (air nozzle) 13. In the air flow path (air nozzle) 13, as shown in FIG. 3, a portion 72 is disposed on the outer peripheral side of the flow path so that the inner diameter of the flow path decreases as the nozzle 71 approaches the combustion chamber 70. In this embodiment, the enlarged portion 73 is arranged after the reduced portion 72, but only the reduced portion may be arranged in the flow path and the enlarged portion may be deleted.
[0032]
A partition wall 14 having an inclined surface 75 is provided between the air nozzle 13 of the swirl burner and the jet outlet of the premixed combustion burner 90. In addition, as shown in FIG. 3, the partition wall 14 is provided with an air outlet 11 that opens toward the flow path central axis direction of the swirl burner (the central axis direction of the combustion chamber). In other words, the ejection direction is not parallel to the central axis of the combustor, and is formed so as to approach the central axis as the extension line in the ejection direction moves away from the ejection port. As shown in FIG. 2, eight air outlets 11 are arranged in the circumferential direction in this embodiment, but the number is not particularly limited.
[0033]
In FIG. 1, air 20 compressed by a compressor (not shown) is supplied to the combustor. Fuel 21 is supplied to the fuel nozzle 1 of the swirl burner 80 and is ejected into a swirl flow 30 formed by an ejection air flow 50 of combustion air passing through the swirl vanes 2.
[0034]
On the other hand, the fuel is supplied from the fuel nozzle 10 into the premixer 4, mixed with air, and ejected from the inner and outer periphery of the ring-shaped flame stabilizer 3 as the premixed gas 22. A circulatory flow 40 is formed in the wake of the ring-shaped flame stabilizer 3 to stabilize the premixed flame. A plurality of fuel nozzles 10 are provided as shown in FIG.
[0035]
The gas turbine combustor according to the present embodiment has the following combustion mode depending on the fuel flow rate of the swirl burner.
[0036]
When the fuel flow rate from the swirl burner 80 is large, the fuel ejected from the fuel nozzle 1 is ejected into the swirl flow 30 formed by the jet air flow 50 of the combustion air passing through the swirl vanes 2 and starts combustion. Since the fuel flow rate is large, the combustion reaction continues to be combusted by the jet stream 60 from the air jet 11 arranged on the partition wall 14 and the jet stream 55 from the premixed combustion burner. For this reason, a strong diffusion flame is formed at the center of the combustor, and a stable combustion state is obtained. However, in this case, it is inevitable that the combustion temperature of the flame is locally increased, so the amount of exhausted NOx becomes large.
[0037]
When the fuel flow rate of the swirl burner 80 is small, the fuel flow rate ratio to the premixed combustion burner 90 increases, so the amount of exhausted NOx decreases. At this time, in the present embodiment, a flame is formed along the jet airflow 60 from the air jet 11 arranged on the partition wall 14, so that fluctuation of the combustion flame of the swirl burner 80 is suppressed. Therefore, it is possible to prevent the occurrence of a phenomenon in which an unstable flame is formed in the shear layer at the boundary between the jet air flow 50 of the swirl burner 80 and the jet air flow 55 of the premixed combustion burner 90 to amplify the fluctuation of the premixed flame. The combustion flame can be made to exist independently and stably.
[0038]
According to one embodiment of the present invention, there is an effect that combustion of the premixed flame can be stably performed even if the fuel flow rate of the swirl burner changes with the change of the gas turbine load.
[0039]
(Example 2)
Another embodiment according to the present invention is shown in FIG. Also in the present embodiment, as in the first embodiment, the swirl burner 80 is disposed on the central axis, and the premixed combustion having the ring flame stabilizer 3 and the premixer 4 is spaced by the partition wall 14 on the outer periphery thereof. A burner 90 is arranged. The swirl burner 80 is provided with a fuel nozzle 1 at the center and an annular air nozzle 13 so as to surround it. Further, an air outlet 11 is disposed on the partition wall 14.
[0040]
The difference from the first embodiment is that the fuel nozzle 18 is arranged on the downstream side of the swirl vane 2 of the swirl burner 80. Further, in order to supply fuel to the fuel nozzle 18, the fuel nozzle 1 is a double pipe, and the fuel 19 and 21 can separately control the supply flow rate.
[0041]
Here, the number and location of the fuel nozzles 18 are not particularly limited. Further, the supply of the fuel 19 from the fuel nozzle 18 can be started at any point from the start of the gas turbine to the rated load. In this case, the fuel flow rate 21 from the central portion of the fuel nozzle 1 may be controlled to decrease in accordance with the increase in the supply amount of the fuel 19.
[0042]
The fuel 19 is ejected from the fuel nozzle 18 and rapidly mixed with the air by the swirling air flow by the swirling blades 2, so that it is premixed and vaporized before reaching the combustion region. Therefore, with this configuration, a flame is formed along the air flow ejected from the air outlet, so that the combustion start region does not fluctuate even in a range where the fuel flow rate of the swirl burner is small, and the flame is prevented from fluctuating. it can. Since an air flow from the air outlet is formed away from the jet direction of the air flow of the premix combustion burner, interference between the air flow and the air flow of the premix combustion burner can be avoided, and the premix combustion It can suppress that the shear layer flame formed in the shear layer of a burner fluctuates. Moreover, it is possible to prevent the flame temperature from rising locally, and to suppress the generation of NOx.
[0043]
According to this embodiment, the fuel from the swirl burner can be premixed without forming an unstable flame in the shear layer at the boundary between the premix combustion burner and the swirl burner. is there.
[0044]
(Example 3)
Another embodiment of the present invention will be described with reference to FIGS. FIG. 5 is a sectional view of the gas turbine combustor according to the present embodiment, and FIG. 6 is a view of FIG. 5 viewed from the downstream side.
[0045]
In this embodiment, the swirl burner 80 having swirl vanes 2 is arranged on the central axis in the same manner as in the first and second embodiments. However, eight tubular premixed combustion burners are provided on the outer periphery thereof. 100 is arranged. The premix combustion burner 100 includes a fuel nozzle 101, swirl vanes 102, and a premixer 104. However, the configuration and number of the premix combustion burner 100 are not particularly limited.
[0046]
A partition wall 14 is provided between the air nozzle 13 of the swirl burner 80 and the jet outlet of the premixed combustion burner 100. An air jet 11 is disposed on the partition wall 14.
[0047]
In this embodiment, the premixed combustion burner 100 is sequentially operated as the load increases. Along with this, the fuel flow rate of the swirl burner increases and decreases, but the premixed combustion burner 100 is operated by the same action as described in the first and second embodiments by the air flow from the air outlet 11 arranged on the partition wall 14. An unstable flame is not formed in the shear layer at the boundary between the swirl burner 80 and the occurrence of combustion vibration is suppressed.
[0048]
According to the present embodiment, the tubular premixed combustion burner having the swirl vanes has an effect that the combustion can be stably performed. The partition wall here protrudes downstream from the outlet of the swirl burner 80 and the exit position of the premixed combustion burner, and when viewed from the downstream side along the central axis, the downstream end of the partition wall is the premixed combustion burner. And may be configured to partially overlap.
[0049]
(Example 4)
Another embodiment of the present invention will be described with reference to FIG. In this embodiment, a mechanism (control means) that can change the cross-sectional area of the flow path by inserting the cylinder 201 is disposed in the air flow path 200 that is supplied to the air outlet 11 disposed on the partition wall 14. Here, in the present embodiment, the flow path cross-sectional area is manually changed, but the flow path cross-sectional area may be automatically changed by arranging a drive mechanism.
[0050]
In the present embodiment, when the insertion depth of the cylinder 201 is increased, the flow passage cross-sectional area of the air flow passage 200 is reduced, and pressure loss occurs in this portion. Therefore, the cylinder 201 is supplied to the air outlet 11 disposed on the partition wall 14. Air volume is reduced. Therefore, the flow rate of air from the air outlet 11 can be varied by adjusting the insertion depth of the cylinder 201.
[0051]
Therefore, the insertion depth of the cylinder 201 is adjusted according to the exhaust NOx characteristics of the individual combustors, and the flow rate of air ejected from the air ejection port 11 is adjusted to an optimum value. Since these values vary depending on the flow rate of air flowing into the combustor and the flow rate of supplied fuel, the adjustment values are determined by the characteristics of the individual combustors. If the air channel cross-sectional area is variable during operation, finer adjustment is possible. For example, the ejection air flow rate is controlled by the control means based on, for example, a signal indicating a gas turbine load. As another example, the amount of air ejected is controlled based on the amount of air flowing into the combustor or the fuel flow rate.
[0052]
According to the present embodiment, since the flow rate of the air ejected from the air ejection port can be made variable, it can be adjusted according to the characteristics of the combustor so as to suppress the generation of combustion vibrations and suppress the increase in exhaust NOx. effective.
[0053]
【The invention's effect】
According to the present invention, it is possible to suppress the formation of an unstable flame in the shear layer at the boundary between the premixed combustion burner and the swirl burner and to reduce the combustion vibration in a wide operating range including combustion conditions that can reduce NOx emissions. There is an effect of suppressing the occurrence.
[Brief description of the drawings]
1 is a cross-sectional view of a gas turbine combustor according to an embodiment of the present invention. FIG. 2 is a view of the burner configuration of FIG. 1 as viewed from the downstream side of the combustor.
3 is an enlarged view of a part of FIG.
FIG. 4 is a cross-sectional view of a gas turbine combustor according to another embodiment of the present invention. FIG. 5 is a cross-sectional view of a gas turbine combustor according to still another embodiment of the present invention. The figure seen from the downstream of the vessel.
FIG. 7 is a sectional view of a gas turbine combustor according to still another embodiment of the present invention.
DESCRIPTION OF SYMBOLS 1 ... Fuel nozzle, 2 ... Swirling blade, 3 ... Ring-shaped flame stabilizer, 4 ... Premixer, 10 ... Fuel nozzle, 11 ... Air outlet, 13 ... Air nozzle, 14 ... Partition, 16, 17, 19, DESCRIPTION OF SYMBOLS 21 ... Fuel, 20 ... Air, 22 ... Premixed gas, 30 ... Swirling flow, 40 ... Circulating flow, 50, 55, 60 ... Jetting airflow, 70 ... Combustion chamber, 80 ... Swirling burner, 90 ... Premixed combustion burner, DESCRIPTION OF SYMBOLS 100 ... Premix combustion burner, 101 ... Fuel nozzle, 102 ... Swirling blade, 104 ... Premixer, 200 ... Air flow path, 201 ... Cylinder.

Claims (4)

A combustion chamber supplied with fuel and air;
A first burner for ejecting fuel into the combustion chamber and swirling air;
A plurality of second burners arranged around the first burner for supplying a premixed mixture of air and fuel to the combustion chamber;
It is arranged outside the first burner and inside the premixed gas flow of the second burner, and is formed so as to have a radial cross-sectional area extending downstream of the combustion chamber, and is inclined with respect to the central axis of the combustion chamber An annular partition having a surface;
A plurality of air jets that are disposed on the inclined surface of the annular partition wall in the circumferential direction at intervals, and jet air in the direction of the central axis of the combustion chamber;
A gas turbine combustor comprising control means capable of varying a flow rate of air ejected from the air ejection port according to a load . A combustion chamber supplied with fuel and air;
A first burner that swirls and jets a premixed mixture of fuel and air into the combustion chamber;
A plurality of second burners arranged around the first burner for supplying a premixed mixture of air and fuel to the combustion chamber;
It is arranged outside the first burner and inside the premixed gas flow of the second burner, and is formed so as to have a radial cross-sectional area extending downstream of the combustion chamber, and is inclined with respect to the central axis of the combustion chamber An annular partition having a surface;
A plurality of air jets that are disposed on the inclined surface of the annular partition wall in the circumferential direction at intervals, and jet air in the direction of the central axis of the combustion chamber;
A gas turbine combustor comprising control means capable of varying a flow rate of air ejected from the air ejection port according to a load . The gas turbine combustor according to claim 1 or 2,
The gas turbine combustor, wherein the air outlet is arranged in an annular shape around the first burner. The gas turbine combustor according to claim 1 or 2,
A gas turbine combustor characterized in that a tapered portion whose flow path width narrows from upstream to downstream is formed near the tip of the flow path of the first burner.

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