JP2015034649A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of reducing the NOx concentration of a diffusion combustor by controlling a shape of flame formed in a burner.SOLUTION: In a gas turbine combustor 3 including a cylindrical combustion chamber 9 for mixing fuel and air and burning it, and a burner 300 disposed at the upstream side of the combustion chamber 9, injecting the fuel and the air into the combustion chamber, and holding the flame, the burner 300 has a plurality of fuel injection holes 403 and a plurality of air injection holes 401. The plurality of fuel injection holes 403: are disposed on the inner side in the radial direction, of the burner 300 with respect to the plurality of air injection holes 401; have inward angles relative to a shaft center axis of the gas turbine combustor; and inject the fuel toward the radial center of the burner 300.

Description

  The present invention relates to a gas turbine combustor, and more particularly to a diffusion combustion type gas turbine combustor that injects fuel and air from separate flow paths into a combustion chamber.

  In recent years, from the viewpoints of reducing power generation costs, effective use of resources, and prevention of global warming, effective use of hydrogen-containing fuels including hydrogen such as coke oven gas by-produced at steelworks and off-gas produced as a by-product at refineries To be considered.

  For example, when a hydrogen-containing fuel is used in a gas turbine power plant, the hydrogen-containing fuel is effective as a measure for preventing global warming because it emits less carbon dioxide (CO2) during combustion. In the integrated coal gasification combined cycle (IGCC), which generates gas by gasifying abundant resources, a system that collects and stores the carbon in the hydrogen-containing fuel supplied to the gas turbine. (Carbon Capture and Storage: CCS) has been established to further reduce CO2 emissions.

  In such an IGCC plant, the fuel composition changes depending on the charcoal type, gasifier load, CCS operating conditions, and the like, so a combustor that can cope with the change in the fuel composition is required. In order to change the fuel composition, a diffusion combustion system in which fuel and air are injected and mixed into combustion chambers from separate flow paths and burned is effective.

  A fuel injection device capable of improving the combustion efficiency and ignitability / flame holding properties of a pilot injection valve that controls diffusion combustion, and discloses a burner structure that injects fuel in the axial center direction of the combustor (for example, , See Patent Document 1).

JP 2012-251742 A

  In a hydrogen-containing fuel, for example, when the hydrogen content increases, the combustion speed representing the flammability of the fuel increases, so in the premixed combustion method in which the fuel and air are premixed and burned, the flame is increased as the combustion speed increases. The risk of backflow (backfire) into the premixer increases and reliability decreases. On the other hand, when the hydrogen content decreases and the combustion speed decreases, the flame tends to become unstable because the flow rate of the premixed gas is too high. Therefore, in a gas turbine power plant in which the fuel composition changes during operation, it is extremely difficult to cope with the premixed combustion method.

  On the other hand, since the diffusion combustor injects fuel and air into the combustion chamber from separate flow paths, no premixed gas is formed in the burner for injecting fuel and air, and the fuel composition changes. There is no flashback. In addition, since diffusion combustion has a wider stable combustion range than premixed combustion, stable combustion is possible even if the composition of the fuel supplied in the plant changes.

  However, in the diffusion combustor, when the fuel and air injected from the burner are mixed in the combustion chamber, a region where the theoretical mixing ratio is formed in the mixing process of the fuel and air is formed, and accordingly, a high temperature region is generated. Get higher. In particular, in a burner, it is common to swirl fuel and air, create a negative pressure near the center of the burner in the radial direction by swirling flow, and hold a flame by circulation of high-temperature combustion gas (circulation gas region). However, when a flame approaches the burner and a high-temperature combustion gas region is generated in the vicinity of the burner, a high-temperature combustion gas region is formed to the downstream of the combustion chamber through the circulation gas region, and the NOx concentration increases. In particular, the influence is significant in the combustion of hydrogen-containing fuel.

  In order to reduce the NOx concentration, water or steam, and in IGCC, nitrogen generated when producing oxygen necessary for the oxidizer of the gasifier is injected into the combustor to reduce the above-mentioned high temperature region. Is generally done. In order to inject a medium necessary for NOx reduction into the combustor, it is necessary to increase the medium to a pressure higher than the combustor pressure, and there is a problem that the plant efficiency is reduced due to the consumption of power required for the pressure increase.

  The present invention has been made based on the above-mentioned matters, and an object of the present invention is to provide a gas turbine combustor capable of controlling the flame shape formed in the burner and reducing the NOx concentration of the diffusion combustor. It is.

  In order to solve the above problems, for example, the configuration described in the claims is adopted. The present application includes a plurality of means for solving the above-described problems. For example, a cylindrical combustion chamber for mixing and burning fuel and air, and a combustion chamber located upstream of the combustion chamber. In a gas turbine combustor including a burner for injecting the fuel and the air into a room and holding a flame, the burner includes a plurality of fuel injection holes and a plurality of air injection holes, and the plurality of fuel injection holes. The hole is disposed radially inward of the burner with respect to the plurality of air injection holes, has an inward angle with respect to the axial center of the gas turbine combustor, and injects the fuel in the radial center direction of the burner. Features.

  According to the present invention, in the diffusion burner, fuel is injected from the fuel injection hole on the inner peripheral side of the air swirler, and an inward angle is provided in the fuel injection hole so that the injection can be performed in the axial center direction of the combustion chamber. A thin diffusion flame can be formed. In addition, by injecting fuel toward the axial center of the combustion chamber, a diffusion flame can be formed at a downstream position slightly away from the burner, so that the air around the burner can be actively involved in the flame, Low NOx combustion is possible. As a result, the flow rate of the injection medium such as water, steam or nitrogen can be reduced, which can contribute to the improvement of plant efficiency.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic configuration diagram illustrating a side sectional view of a main part of a first embodiment of a gas turbine combustor according to the present invention together with a schematic diagram of an entire gas turbine plant. It is the front view which looked at the burner which constitutes a 1st embodiment of the gas turbine combustor of the present invention from the combustion chamber side. It is sectional drawing which looked at the burner shown in FIG. 2 from the AA arrow. It is the schematic block diagram which represented the sectional side view of the principal part of the burner which comprises 1st Embodiment of the gas turbine combustor of this invention with the situation figure which shows the flow of the combustion gas in a combustion chamber. It is the front view which looked at the burner which comprises 2nd Embodiment of the gas turbine combustor of this invention from the combustion chamber side. It is the schematic block diagram which represented the sectional side view of the principal part of the burner which comprises 2nd Embodiment of the gas turbine combustor of this invention with the situation figure which shows the flow of the combustion gas in a combustion chamber. It is the front view which looked at the conventional burner which does not have the fuel injection inward angle which comprises the conventional gas turbine combustor from the combustion chamber side. It is the schematic block diagram which represented the sectional side view of the principal part of the conventional burner which does not have the fuel injection inward angle which comprises the conventional gas turbine combustor with the situation figure which shows the flow of the combustion gas in a combustion chamber.

  Embodiments of a gas turbine combustor according to the present invention will be described below with reference to the drawings.

  FIG. 1 is a schematic configuration diagram showing a side sectional view of an essential part of a first embodiment of a gas turbine combustor of the present invention together with a schematic diagram of an entire gas turbine plant. In this embodiment, liquid fuel such as light oil is used for starting the gas turbine, and a mixed gas of H 2 and CO (coal gasification gas such as IGCC or coke oven gas) is used as the main fuel.

  The gas turbine 5 includes a compressor 2, a combustor 3, a turbine 4, a generator 6, a starter motor 8, and the like. In the gas turbine 5, the air 101 sucked from the atmosphere by the compressor 2 is compressed, and the combustion air 102 is supplied to the combustor 3. In the combustor 3, the combustion air 102 from the compressor 2 and the gas turbine start fuel (here, light oil) 15 are ignited to generate the combustion gas 140 and supply it to the turbine 4. The turbine 4 is supplied with rotational power by supplying the combustion gas 140, and the rotational power of the turbine 4 is transmitted to the compressor 2 and the generator 6. The rotational power transmitted to the compressor 2 is used as compression power, and the rotational power transmitted to the generator 6 is converted into electric energy.

  The combustor 3 includes an outer cylinder 10 that is a pressure vessel formed in a substantially cylindrical structure, an end cover 14 provided at an end of the outer cylinder 10, and a combustion chamber liner 12 that forms a combustion chamber 9 in the outer cylinder 10. And a flow sleeve 11 which is disposed inside the outer cylinder 10 and on the outer peripheral side of the combustion chamber liner 12 and forms an annular space between the inner peripheral surface and the outer peripheral surface of the combustion chamber liner 12. A burner 300 is disposed on the inner side of the end cover 14 upstream of the combustion chamber 9 to inject fuel and air into the combustion chamber 9 to hold a flame.

Combustion air 102 supplied to the combustor 3 flows in the space between the flow sleeve 11 and the combustion chamber liner 12, and cools the combustion chamber 9 while the combustion chamber 9 is cooled by the air holes 13 provided in the side wall of the combustion chamber liner 12. Supplied in. Further, the combustion air 102 that has flowed through the space between the flow sleeve 11 and the combustion chamber liner 12 enters the combustion chamber 9 from the cooling air hole 200a provided in the louver 200 at the upstream end of the combustion chamber 9 as cooling air 102b. Supplied.
The combustion air 102 supplied to the burner 300 is supplied into the combustion chamber 9 as air 102a from the air injection hole 401 through an air introduction hole 401a provided in an air swirler described later.

  The burner 300 includes a starting oil nozzle 501 at the center in the radial direction, a gas injection hole 403 on its outer periphery, and an air injection hole 401 (air swirler 400) on its outer periphery. In general, when using gas fuel containing hydrogen, a fuel nozzle body 125 is provided with a system of starting fuel 15 such as light oil and a system of atomized air 25 for atomizing the starting fuel 15, and the reliability at the time of gas turbine ignition. Improves sex. The fuel nozzle body 125 is provided with a system of gas fuel 203 provided with a fuel cutoff valve 71 and a fuel flow rate adjustment valve 61, and is connected to the gas injection hole 403. After the operation to the partial load with the light oil fuel from the starting fuel system 15, the flow rate of the gas fuel 203 is increased at the same time as the flow rate of the light oil fuel is decreased, and finally the operation mode is switched to the gas-only firing operation mode. .

  Next, the burner structure will be described with reference to FIGS. FIG. 2 is a front view of the burner constituting the first embodiment of the gas turbine combustor of the present invention as viewed from the combustion chamber side, and FIG. 3 is a cross-sectional view of the burner shown in FIG. FIG. 4 is a schematic configuration diagram showing a side sectional view of the main part of the burner constituting the first embodiment of the gas turbine combustor of the present invention together with a situation diagram showing the flow of combustion gas in the combustion chamber. is there. 2 to 4, the same reference numerals as those shown in FIG. 1 are the same parts, and detailed description thereof is omitted.

  As shown in FIG. 2, the burner 300 according to the present embodiment has a starting oil nozzle 501 disposed in the axial center portion of the combustion chamber 9 and eight gas injection holes 403 disposed on the outer periphery thereof. An air swirler 400 is disposed on the outer periphery of the gas injection hole 403, and the eight air injection holes 401 are provided in the air swirler 400. As shown in FIG. 3, the air injection hole 401 is provided with a turning angle α. As a result, the air 102a ejected from the air nozzle hole 401 is swirled, so that a negative pressure is generated in the center portion in the radial direction of the burner 300 to form a region (circulation gas region) where the combustion gas circulates.

  Returning to FIG. 2, the gas injection hole 403 has a turning angle β and an inward angle θ. As a result, the gas fuel 203 is injected in the radial center direction of the burner 300 while turning. Here, the swirl angle β is defined by the center on the gas inlet side of the gas nozzle hole 403 and the center on the gas outlet side with respect to the line connecting the center on the gas inlet side of the gas nozzle hole 403 and the axial center of the combustion chamber 9. Is the angle formed by the line connecting the two. Further, the inward angle θ is an angle formed by a line connecting the center on the gas inlet side of the gas injection hole 403 and the center on the gas outlet side with respect to the axial direction of the combustion chamber 9. The turning angle β is set so that the turning angle at which the gas fuel turns and the turning angle of the air generated by the turning angle α of the air nozzle hole 401 are in the same direction.

  In FIG. 4, as described above, the air 102 a supplied to the burner 300 is ejected from the air injection hole 401 to the combustion chamber 9 through the air hole introduction hole 401 a of the air swirler 400. A swirling component is given to the air 102a. As a result, the central portion in the radial direction of the burner 300 has a negative pressure, and the circulating gas region 30 is formed. Since the circulating gas region 30 continuously applies heat from the flame to the gas fuel 203 and air 102a supplied to the burner 300, the flame 250 is continuously formed and the flame is held.

  In this embodiment, the gas injection hole 403 is provided with an inward angle θ. By providing the inward angle θ, the gas fuel 203 is injected into the central portion in the radial direction of the burner 300, and the flame 250 is held from the position where the jets of the fuels merge to increase the fuel concentration. Since the fuel is injected in the radial center direction of the burner, the flame 250 can be prevented from spreading outside the burner 300, and a thin diffusion flame can be formed. The position P, which becomes the flame holding base point by injecting the fuel in the central direction, is located in the downstream direction of the distance L from the burner surface.

  When the burner 300 is viewed from the axially downstream side in the combustion chamber 9, the combustion gas 35 including the cooling air 102 b of the louver 200 is circulated around the outer periphery of the burner 300 by the jet of air and fuel injected from the burner 300. doing. The temperature of the combustion gas 35 is lower than the temperature of the flame 250. By forming a narrow diffusion flame slightly downstream from the burner 300, the combustion gas 35 circulating around the burner can be entrained in the flame 250. As a result, the flame temperature can be lowered, so that the NOx concentration can be lowered.

  Next, for comparison with the present embodiment, a conventional burner having no fuel injection inward angle will be described with reference to FIGS. 7 is a front view of a conventional burner that does not have a fuel injection inward angle that constitutes a conventional gas turbine combustor as viewed from the combustion chamber side, and FIG. 8 does not have a fuel injection inward angle that constitutes a conventional gas turbine combustor. It is the schematic block diagram which represented the sectional side view of the principal part of the conventional burner with the situation figure which shows the flow of the combustion gas in a combustion chamber. 7 and 8, the same reference numerals as those shown in FIGS. 1 to 4 are the same parts, and detailed description thereof is omitted.

  The conventional burner 300C shown in FIG. 7 is different from the burner 300 of the present embodiment shown in FIG. 2 only in that the gas injection hole 403C has a swivel angle β but no inward angle θ, and is otherwise the same. It is a configuration. The gas fuel 203 spreads outward in the radial direction of the burner while swirling, and is mixed with the air 102a supplied from the air swirler 400 and burned.

  As shown in FIG. 8, a flame 250 is formed by mixing the injected gaseous fuel 203 and air 102a in the combustion chamber. A part of the combustion gas generated from the formed flame 250 is taken into the circulating gas region 30 and continuously gives heat to the gas fuel 203 and the air 102a along the surface of the burner 300C. Since the combustion gas taken into the circulation gas region 30 flows along the vicinity of the surface of the burner 300C, the temperature near the surface of the burner 300C increases, and the flame 250 is formed close to the burner 300C.

  In the portion where the flame 250 is formed close to the burner 300C surface, the low-temperature combustion gas 35 circulated on the outer peripheral side of the burner 300C becomes slow. As a result, the flame temperature does not decrease, and low NOx combustion becomes difficult.

  In the present embodiment, a thin diffusion flame can be formed by providing the gas injection hole 403C with an inward angle. Moreover, the low-temperature circulating gas around the burner generated by the influence of the jet injected from the burner is caught in this flame. Because of these synergistic effects, the flame temperature can be lowered, so the NOx concentration can be lowered.

Next, the operation method of the embodiment of the gas turbine combustor of the present invention will be described with reference to FIG.
The start of the gas turbine 5 is driven by external power such as a starting motor 8. By holding the rotational speed of the gas turbine 5 at the rotational speed corresponding to the ignition condition of the combustor 3 by the starter motor 8, the combustion air 102 necessary for ignition is supplied to the combustor 3, and the ignition condition is satisfied. .

  By supplying the burner 300 with light oil as the starting fuel 15 and atomized air 25 for atomizing the light oil, ignition in the combustor 3 is possible. After ignition of the combustor 3, combustion gas 140 is generated and supplied to the turbine 4. When the flow rate of the light oil, which is the starting fuel 15, increases, the turbine 4 increases in speed and reaches the specified rotational speed. .

  After the gas turbine 5 reaches the no-load rated speed, the generator 6 is placed in parallel with the power system, and the inlet combustion gas temperature of the turbine 4 and the generator output (load) are increased by increasing the flow rate of light oil. Under partial load conditions, it is possible to switch the fuel from light oil to a mixed gas of H2 and CO. Generally, the gas oil flow rate is decreased and the gas fuel 203 flow rate is increased at a constant gas turbine load condition, and the gas is exclusively operated. Switch modes.

  After the operation mode is switched to the gas-only firing operation, it is possible to increase the load up to the rated load by increasing the flow rate of the gas fuel 203. In addition, after switching to gas-only firing, a thin diffusion flame is formed in the burner 300, and low NOx combustion becomes possible.

  In the present embodiment, the example in which light oil is used as the starting fuel has been described. However, the same effect can be obtained by using a high calorie fuel such as LNG as the starting fuel. In addition, when ignition with a mixed gas of H 2 and CO is easy, the burner can be configured without using the starting oil nozzle 501 such as light oil or LNG.

  According to the first embodiment of the gas turbine combustor of the present invention described above, in the diffusion burner 300, the gas fuel 203 is injected from the gas injection hole 401 on the inner peripheral side of the air swirler 400, and the gas injection Since the inward angle is provided in the hole 401 so that the injection can be performed in the axial center direction of the combustion chamber 9, a thin diffusion flame 250 can be formed. In addition, by injecting fuel in the axial center direction of the combustion chamber 9, the diffusion flame 250 can be formed at a downstream position slightly away from the burner 300, so that the air around the burner can be actively involved in the flame, Low NOx combustion by the diffusion flame 250 is possible. As a result, the flow rate of the injection medium such as water, steam or nitrogen can be reduced, which can contribute to the improvement of plant efficiency.

  Hereinafter, a second embodiment of the gas turbine combustor of the present invention will be described with reference to the drawings. FIG. 5 is a front view of a gas turbine combustor according to a second embodiment of the present invention as viewed from the combustion chamber side, and FIG. 6 is a gas turbine combustor according to the second embodiment of the present invention. It is the schematic block diagram which represented the sectional side view of the principal part of the burner which combines with the situation figure which shows the flow of the combustion gas in a combustion chamber. 5 and 6, the same reference numerals as those shown in FIG. 1 to FIG. 4 are the same parts, and detailed description thereof is omitted.

  The second embodiment of the gas turbine combustor according to the present invention shown in FIG. 5 and FIG. 6 is configured with almost the same equipment as the first embodiment, but the following configuration is different. In the present embodiment, a swirler capable of injecting a part of the fuel 203 is provided on the outer periphery of the air swirler 400 of the first embodiment. In the present embodiment, the swirler having the air swirler 400 of the burner 300 is referred to as an inner swirler 201, and the swirler provided on the outer periphery is referred to as an outer swirler 202. The outer swirler 202 is provided with eight second gas injection holes 404. Thus, in the present embodiment, the first fuel injected from the gas injection hole 403 of the inner peripheral swirler 201 and the second fuel injected from the second gas injection hole 404 of the outer peripheral swirler 202 are divided. The fuel can be injected into the combustion chamber 9.

  The gas turbine combustor according to the present invention is characterized in that fuel is injected toward the axial center of the combustion chamber 9, a flame holding point is formed at a downstream position slightly away from the burner 300, and mixing with ambient air is promoted. Therefore, it is effective for realizing low NOx combustion for a fuel having a high combustion rate and good reactivity. However, when the composition of the fuel supplied to the gas turbine changes depending on the gasifier load and the type of coal as in the IGCC plant, a gas turbine combustor that can cope with the composition change is required.

  In particular, when the gasifier load is lower than the rated load, the combustible components contained in the gas are reduced and the inert components are increased as compared to the rated load, so the heat generation is reduced and the combustibility is reduced. When the entire amount of fuel is supplied only from the inner swirler 201, the fuel ejection flow rate increases as the fuel flow rate increases. In addition, since the reactivity of the fuel also decreases as the calorific value decreases, the flame holding ability decreases.

  In the gas turbine combustor of the present embodiment, the first fuel is injected from the gas injection hole 403 of the inner peripheral swirler 201 and is injected from the outer peripheral swirler 202 even if the heat generation amount is reduced during operation of the gas turbine. Since the flow rate of the second fuel to be increased is increased, the flow velocity of the first fuel injected from the inner swirler 201 can be reduced. As a result, stable combustion is possible even when the heat generation amount is reduced.

  As shown in FIG. 6, the burner 300 is provided with an outer peripheral swirler 202 on the outer side of the inner peripheral swirler 201. A first system 51 of gas fuel 203 provided with a fuel shut-off valve 71 and a fuel flow rate adjustment valve 61 is connected to the gas injection hole 403 of the inner peripheral swirler 201. A second system 52 of gas fuel 203 provided with a fuel cutoff valve 72 and a fuel flow rate adjustment valve 62 is connected to the second gas injection hole 404 of the outer peripheral swirler 202. By adjusting the fuel flow rate adjustment valve 61 of the first system 51 and the fuel flow rate adjustment valve 62 of the second system 52, the flow rate of fuel supplied to the gas injection holes of each swirler can be controlled. Further, although not shown, a calorific value detection means for detecting a decrease in the calorific value of the fuel is provided.

  For example, when the calorific value of the fuel decreases as the gasifier load decreases, it is necessary to increase the fuel flow rate in order to maintain the output of the gas turbine 5. At this time, if the entire fuel flow rate increased from the inner swirler 201 is injected, the fuel injection flow rate increases and unstable combustion is likely to occur.

  In the present embodiment, when a decrease in the calorific value of the fuel is detected, a part of the fuel is injected from the outer swirler 202, so that the fuel flow speed of the inner swirler 201 can be optimized. Further, at this time, heat is transferred from the inner and outer peripheral flames due to the formation of the outer peripheral flame 251, so that stable combustion is possible.

  As described above, when the amount of heat generated by the fuel changes during operation of the gas turbine 5, it is possible to perform low NOx combustion while maintaining stable combustion by adjusting the ratio of the fuel flow rate supplied to the inner and outer swirlers. Become.

  According to the second embodiment of the gas turbine combustor of the present invention described above, the same effect as that of the first embodiment can be obtained.

  Further, according to the above-described second embodiment of the gas turbine combustor of the present invention, even when the amount of heat generated by the fuel changes during operation of the gas turbine 5, low combustion is maintained while maintaining stable combustion. NOx combustion becomes possible.

  In addition, this invention is not limited to an above-described Example, Various modifications are included. For example, the above-described embodiments have been described in detail for easy understanding of the present invention, and are not necessarily limited to those having all the configurations described. Each of the above-described configurations, functions, processing units, processing means, and the like may be realized by hardware by designing a part or all of them with, for example, an integrated circuit. Each of the above-described configurations, functions, and the like may be realized by software by interpreting and executing a program that realizes each function by the processor.

2 Compressor 3 Combustor 4 Turbine 5 Gas turbine 6 Generator 8 Starter motor 9 Combustion chamber 10 Outer cylinder 11 Flow sleeve 12 Combustion chamber liner 14 End cover 15 Start-up fuel 25 Spray air 30 Circulating gas region 35 Combustion gas 61 Fuel Flow control valve 71 Fuel shutoff valve 101 Air 102 Combustion air 102a Air 102b Cooling air 140 Combustion gas 200 Louver 200a Cooling air hole 201 Inner circumferential swirler 202 Outer swirler 203 Gas fuel 250 Flame 300 Burner 400 Air swirler 401 Air injection hole 401a Air Introduction hole 403 Gas injection hole 404 Second gas injection hole 501 Oil nozzle

Claims (5)

A gas turbine combustor comprising a cylindrical combustion chamber for mixing and burning fuel and air, and a burner located upstream of the combustion chamber for injecting the fuel and air into the combustion chamber to hold a flame In
The burner has a plurality of fuel injection holes and a plurality of air injection holes,
The plurality of fuel injection holes are disposed radially inward of the burner with respect to the plurality of air injection holes, have an inward angle with respect to the axis of the gas turbine combustor, and the fuel in the radial center direction of the burner A gas turbine combustor characterized by injecting. The gas turbine combustor according to claim 1.
The gas turbine combustor, wherein the plurality of fuel injection holes and the plurality of air injection holes each have a turning angle, and the turning angles of the fuel and the air are in the same direction. The gas turbine combustor according to claim 1 or 2,
The burner includes a first swirler provided with the plurality of air injection holes and the plurality of fuel injection holes, and a plurality of second fuel injection nozzles that are disposed on an outer peripheral side of the first swirler and inject a part of the fuel. A second swirler provided with a hole,
The gas turbine combustor, wherein the swirling direction of the plurality of air injection holes of the first swirler and the swirling direction of the plurality of second fuel injection holes of the second swirler are the same direction. The gas turbine combustor according to claim 3.
A first fuel system for supplying fuel to the first swirler; a second fuel system for supplying fuel to the second swirler; a first flow rate adjusting valve provided in the first fuel system; A second flow rate adjusting valve provided in the fuel system; and a heat generation amount change detecting means of the fuel,
The opening of the first flow rate adjustment valve and the opening of the second flow rate adjustment valve are adjusted and supplied to the first and second swirlers according to the change in the heat generation amount detected by the heat generation amount change detection means. A gas turbine combustor characterized by controlling a fuel flow rate ratio. The gas turbine combustor according to claim 3 or 4,
A gas nozzle, such as a starting oil nozzle or LNG, is arranged inside the fuel nozzle hole of the first swirler in the radial direction so that the starting fuel and the main gas fuel can be supplied independently. Turbine combustor.

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