JP4608154B2 - Gas turbine combustion apparatus and gas turbine provided with the same - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention provides a liner in which a combustion section for burning fuel and a dilution section for diluting combustion exhaust gas discharged from the combustion section with a plurality of dilution air flows from a plurality of dilution air inlets are formed. A plurality of the turbine shafts are arranged side by side so as to surround the turbine shaft,
Each discharge port formed in the downstream end face of each liner is arranged at equal intervals along the rotation direction of the annular turbine blade, and discharges the combustion exhaust gas as a rotational drive source of the turbine blade. It is related with the combustion apparatus for gas turbines comprised in this way, and a gas turbine provided with the same.
[0002]
[Prior art]
The introduction of cogeneration systems that supply both electricity and heat is increasing. As a power generation method in such a cogeneration system, there are a method in which a generator is driven by a gas turbine or a gas engine, a method in which power is generated by a fuel cell, and the like. Such a cogeneration system can be installed in a small-scale and distributed manner for consumers consuming heat such as in regions, buildings, and homes. It can be effectively used for air conditioning and hot water supply.
[0003]
As a power generation method for cogeneration systems, it is desired to use fuel cells with high efficiency, low pollution, and low noise. However, fuel cells still have many problems in terms of price and ease of handling and so on. This point needs to be fully considered.
Therefore, a power generation method using a gas turbine that is low in price, excellent in handleability, and capable of being further reduced in size is drawing attention.
[0004]
A gas turbine used in a cogeneration system or the like is a gas turbine combustion device that burns fuel such as natural gas, kerosene, or light oil supplied inside using combustion air, and combustion in the combustion device. And a turbine blade (rotor blade) that rotates using a combustion exhaust gas discharged from a discharge port of the combustion device as a drive source, and the shaft output of the turbine blade is the above It is used as a drive source for generators.
[0005]
As a combustion apparatus for a gas turbine, a cylindrical liner having a combustion portion that burns fuel inside and having a downstream end surface formed as a discharge port for discharging combustion exhaust gas is used as a rotating shaft of a turbine blade. There is known an annular cylindrical shape in which a plurality of annular cylinders are provided so as to surround the ring. Such a combustion apparatus discharges combustion exhaust gas toward the turbine blades from a plurality of discharge ports arranged in an annular shape along the rotation direction of the turbine blades, thereby rotating the turbine blades.
[0006]
Moreover, the liner provided in such an annular tube type gas turbine combustion apparatus is composed of a cylindrical body cylinder part and a tail cylinder part connected to the downstream side thereof. The combustion part for burning the fuel and the dilution part for diluting the combustion exhaust gas discharged from the combustion part with the dilution air flowing in from a plurality of dilution air inlets, while the tail tube part is A discharge port formed in a flat shape along the rotation direction of the turbine blade is formed at the downstream end portion, and is formed in a tapered shape that guides the combustion exhaust gas discharged from the dilution unit to the discharge port. .
Further, in the dilution section, the combustion exhaust gas is diluted with the dilution air flowing into the liner from a plurality of dilution air inlets formed in the liner, so that the combustion exhaust gas that has been diluted and the temperature is reduced is reduced. The turbine blades can be discharged through the tube portion and the discharge port, and thermal damage to members constituting the liner, such as the tail tube portion and the discharge port, and the turbine blade can be suppressed.
[0007]
[Problems to be solved by the invention]
In the gas turbine combustion apparatus configured in the above-described annular cylindrical shape, the dilution air inlet formed in each liner is symmetrical with respect to the center plane passing through the axis of the turbine blade and the center of the discharge port. When the dilution air inlet is arranged in this way, the temperature distribution of the combustion exhaust gas in the cylindrical cross section of the dilution portion becomes the highest at the center and becomes lower as it goes outward. Then, since the flue gas having the above temperature distribution is guided to the flat discharge port in the dilution section, the temperature distribution of the flue gas at each discharge port is determined by the rotation direction of the turbine blade, that is, the width of the flat discharge port. In the direction, the vicinity of the center of the discharge port becomes the highest temperature position, and the temperature becomes lower as it approaches both ends of the discharge port in the width direction.
[0008]
As described above, when the temperature distribution state of the combustion exhaust gas at the plurality of discharge ports arranged along the rotation direction of the turbine blades reaches the maximum temperature near the center of each discharge port as described above, the highest temperature is obtained. There is a risk that the portion that contacts the combustion gas, for example, the portion corresponding to the center of the discharge port of the nozzle blade (static blade) for rectifying the combustion exhaust gas toward the turbine blade side will be locally hot and thermally damaged. is there.
Therefore, in order to prevent such thermal damage, it is necessary to manufacture the nozzle blades or the like with an expensive heat-resistant material, or to reduce the combustion amount in order to reduce the temperature of the discharged combustion gas as a whole, This is disadvantageous in terms of cost or gas turbine capacity.
[0009]
Therefore, in view of the above circumstances, in a combustion apparatus for a gas turbine configured in an annular cylindrical shape, the temperature distribution state of combustion exhaust gas at a plurality of discharge ports arranged in an annular shape is leveled in a preferable state. The purpose is to establish a technology that can be realized.
[0010]
[Means for Solving the Problems]
[Configuration 1]
The gas turbine combustion apparatus according to the present invention, as described in claim 1, has a combustion part for burning fuel and a combustion exhaust gas discharged from the combustion part flowing in from a plurality of dilution air inlets. A plurality of liners formed with a dilution section that is diluted with dilution air are provided side by side so as to surround the turbine shaft in an annular shape,
Each discharge port formed in the downstream end face of each liner is arranged at equal intervals along the rotation direction of the annular turbine blade, and discharges the combustion exhaust gas as a rotational drive source of the turbine blade. A gas turbine combustion apparatus configured as described above,
The highest temperature position of the combustion exhaust gas at each of the discharge ports is one direction side along the rotation direction from the center of the discharge port with reference to the arrangement pitch interval of the plurality of discharge ports with respect to the rotation direction of the turbine blades The plurality of dilution air inlets are arranged so as to be in positions deviated by 15% or more and 30% or less.
[0011]
[Function and effect]
According to the gas turbine combustion apparatus of the present configuration configured in the annular cylindrical shape, a plurality of dilution air inlets formed on the dilution part side of the liner are appropriately arranged, and the combustion exhaust gas at each discharge port is disposed. The maximum temperature position is biased from the discharge port center to one direction along the turbine blade rotation direction, and the deviation ratio based on the arrangement pitch interval of the plurality of discharge ports with respect to the turbine blade rotation direction at the highest temperature position The maximum temperature position biased in the same direction along the rotation direction of the turbine blades is set to 15% or more so that the dilution air is supplied in a large amount at the adjacent discharge port, and the temperature becomes low. The temperature distribution of the combustion exhaust gas discharged from a plurality of outlets that are close to each other in an annular shape is leveled with a small overall temperature difference, and the maximum temperature of the combustion exhaust gas discharged from the discharge ports is Noz Be set to a temperature below the heat resistant temperature of the members of the wing such as to suppress the thermal damage, by discharging the combustion exhaust gas of sufficient heat, it is possible to improve the power generation output and efficiency.
[0012]
Further, the plurality of dilution air inlets are appropriately arranged, and the deviation rate of the highest temperature position of the combustion exhaust gas at each discharge port is set to 30% or less, so that the highest temperature position is set as described above. Even in the biased position, the temperature of the combustion exhaust gas contacting the end of the discharge port can be made lower than the heat-resistant temperature, and for example, thermal damage such as the wall portion of the tail tube portion can be suppressed.
Therefore, in a preferable state, the combustion apparatus for a gas turbine configured in an annular cylindrical shape that can level the temperature distribution state of the combustion exhaust gas at the plurality of discharge ports arranged in an annular shape over the whole. Can be realized.
[0013]
In order to adjust the deviation ratio in the rotational direction of the turbine blade at the highest temperature position of the combustion exhaust gas at the discharge port, the inflow state of the dilution air in the dilution section is a state where the inflow amount is biased in the width direction, This is possible by adjusting the degree of deviation of the inflow amount.
That is, all or a part of the plurality of dilution air inlets formed in the liner are entirely relative to the center plane passing through the axis of the turbine blade and the center of the discharge port (the center in the width direction of the discharge port). In such a configuration, the inflow state of the dilution air in the dilution section can be made to be a state where the inflow amount is biased, and further, the plurality of dilution air inlets arranged asymmetrically can By appropriately adjusting each positional relationship, it is possible to adjust the deviation of the inflow amount of the dilution air, that is, the deviation ratio of the maximum temperature position of the combustion exhaust gas at the discharge port.
[0014]
[Configuration 2]
According to the gas turbine combustion apparatus of the present invention, as described in claim 2, in addition to the configuration of the gas turbine combustion apparatus having the above-described configuration 1, the steam-containing gas for supplying a steam-containing gas containing steam into the liner. A supply means is provided.
[0015]
[Function and effect]
According to the gas turbine combustion apparatus of this configuration, by providing the steam-containing gas supply means, the steam-containing gas generated using the combustion exhaust gas discharged after rotating the turbine blades is supplied to the combustion section. It is possible to improve the output of the gas turbine, improve the thermal efficiency, and reduce the amount of NOx emissions by mixing it with the fuel to be used or mixing it with the dilution air supplied to the dilution section and supplying it into the liner. .
[0016]
In order to further reduce the NOx emission amount, when the air-fuel mixture is burned in the combustion section, the steam-containing gas may be supplied only to the dilution section.
[0017]
Moreover, if a cogeneration system is configured by a gas turbine that employs a gas turbine combustion device that supplies such a steam-containing gas into the liner, for example, the heat demand on the consumer side fluctuates and is generated. To construct a so-called variable thermoelectric cogeneration system that can supply surplus steam-containing gas into the combustor and convert the steam-containing gas into electrical energy even when the steam-containing gas becomes surplus Can do.
[0018]
[Configuration 3]
According to the gas turbine combustion apparatus of the present invention, as described in claim 3, in addition to the configuration of the gas turbine combustion apparatus having the above-described configuration 1 or 2, the dilution air inflow port has an axial center of the turbine blade. And a plurality of control ports arranged in an asymmetric state with respect to a central plane passing through the center of the discharge port, and a plurality of dilution ports arranged in a symmetric state with respect to the central plane It is configured.
[0019]
[Function and effect]
According to the gas turbine combustion apparatus of the present configuration, the ratio and position of the control port in the plurality of dilution air inlets are appropriately determined, and the highest temperature position of the combustion exhaust gas at the discharge port is preferable. The temperature of the combustion exhaust gas can be lowered uniformly by the dilution air that flows uniformly from the dilution port, and the temperature distribution of the combustion exhaust gas discharged from the plurality of discharge ports Therefore, it may be preferable that the temperature is leveled and the temperature is not higher than the heat resistant temperature.
[0020]
DETAILED DESCRIPTION OF THE INVENTION
Embodiments of a gas turbine combustion apparatus and a gas turbine according to the present invention will be described with reference to the drawings.
The cogeneration system shown in FIG. 1 obtains electric power and heat consumed by consumers such as regions, buildings, and homes. Specifically, the cogeneration system includes a gas turbine 60 that drives natural gas as fuel FG, and power generation that generates electric power EP consumed on the consumer side using the shaft output of the drive shaft 54 of the gas turbine 60. Exhaust heat boiler 80 that generates steam S such as superheated steam (about 450 ° C.) or saturated steam (about 130 ° C.) by exchanging heat between the machine 70 and the combustion exhaust gas EG discharged from the gas turbine 60 and the water W. As the heat consumed on the consumer side, the process steam PS that is a part of the steam S generated by the exhaust heat boiler 80 is supplied to the consumer side.
[0021]
The gas turbine 60 includes a compressor 52 that compresses the air A and a gas turbine combustion device that burns the fuel FG using the air A supplied from the compressor 52, as in a general case. 50 and a turbine blade 53 that is rotationally driven using the combustion exhaust gas EG discharged from the combustion device 50 as a drive source. The compressor 52 and the turbine blade 53 are connected to the drive shaft 54. The shaft output of the drive shaft 53 is used as the driving force of the compressor 52 and the driving force of the generator.
[0022]
In the cogeneration system shown in FIG. 1, steam-containing gas supply means for supplying a control steam CS (an example of a steam-containing gas) containing a part of the steam S generated by the exhaust heat boiler 80 into the combustion device 50. X is provided and will be described in detail later. By supplying this control steam CS into the combustion device 50, the shaft output and thermal efficiency of the gas turbine 60 are improved, and the amount of NOx discharged from the combustion device 50 is reduced. be able to.
Further, since the cogeneration system is configured by the gas turbine 60 including the steam-containing gas supply means X for supplying the control steam CS, which is a part of the steam S, into the combustion apparatus 50, the process on the consumer side Even when the consumption amount of the steam PS fluctuates and the steam S generated in the exhaust heat boiler 80 becomes surplus, the surplus steam S is supplied into the combustion device 50 as the control steam CS, and the control steam CS Is converted into a drive shaft 54 output, that is, a power output of the generator 70, so-called thermoelectric variable type.
[0023]
As shown in FIGS. 2 and 3, the combustion device 50 includes six liners 1 arranged in parallel along the rotation direction of the turbine blades 53 at equal intervals. A cylindrical body 1a having a combustion section 2 for burning the fuel FG injected from the fuel nozzle 5 and a dilution section 3 for diluting the combustion exhaust gas EG discharged from the combustion section 2 with air A is provided. Combustion exhaust gas EG that is formed and discharged from each of the dilution sections 3 circulates in a tapered cylindrical tail cylinder 1b connected to the downstream side of the trunk cylinder 1a. It discharges from the discharge outlet 4 formed in the downstream end surface. The combustion exhaust gas EG discharged from the discharge ports 4 arranged at equal intervals along the annular turbine blade 53 is directed toward the turbine blade 53 by the fixed nozzle blade 8. And jetted to the turbine blade 53 side to rotate the turbine blade 53.
[0024]
Further, as shown in FIG. 3, each discharge port 4 is formed in a flat shape along the rotation direction of the turbine blade 53, and forms an annular shape along the shape of the turbine blade 53 as a whole.
Therefore, the tail tube portion 1b of each liner 1 is formed so as to be tapered in the radial direction of the turbine blade 53 as the wall portion on the drive shaft 54 side is further away from the drive shaft 54 toward the downstream side. The combustion exhaust gas flowing out from the barrel portion 1a is guided to the flat discharge port 4.
[0025]
The plurality of liners 1 are surrounded by a casing 6, and an air flow path 7 through which air A supplied from the compressor 52 flows is formed between each of the liners 1.
On the combustion section 2 side of the liner 1, a plurality of combustion air inlets 10 and 11 are formed for allowing the air A flowing through the air flow path 7 to flow into the combustion section 2 as secondary combustion air. . The combustion device 50 uses the primary combustion air A supplied from the upstream end face of the liner 1 and the combustion air A supplied from the respective combustion air inlets 10 and 11 in the combustion unit 2. Thus, the fuel gas FG is configured to burn.
[0026]
A plurality of dilution air inlets 12 and 13 for allowing the air A flowing through the air flow path 7 to flow into the dilution unit 3 as dilution air are formed on the dilution unit 3 side of the liner 1. In the section 3, the combustion exhaust gas EG discharged from the combustion section 2 is diluted with the dilution air A flowing in from the respective dilution air inlets 12 and 13, and the wall portion of the discharge port 4 or a member on the downstream side thereof. Is discharged to the discharge port 4 side.
[0027]
The steam-containing gas supply means X supplies steam CS1, which is a part of the control steam CS, into the air flow path 7 via the flow rate adjusting valve 23 and the plurality of steam introducing portions 21 formed in the casing 6. It is configured. The steam CS1 supplied in this manner is supplied into the liner 1 through the combustion air inlets 10 and 11 and the dilution air inlets 12 and 13 together with the combustion air A and the dilution air A. Together with the combustion exhaust gas EG, it functions as a rotational drive source for the turbine blades 53. Therefore, the shaft output of the turbine blade 53, that is, the power generation output of the generator 70 can be improved, and further, by adjusting the ratio of the control steam CS to the process steam PS supplied to the consumer side, The system can be a so-called thermoelectric variable type that can adjust the balance between power output and heat output.
The flow rate adjusting valve 23 is adjusted based on the consumption amount of the process steam PS on the consumer side or the consumption amount of electric power.
Further, as the steam CS1 supplied into the air flow path 7 in this way, the superheated steam generated in the exhaust heat boiler 80 or the air compressed and heated by the compressor or the like to the saturated steam generated in the exhaust heat boiler 80. A mixture of these is preferably used.
[0028]
Further, the steam-containing gas supply means X mixes the steam CS2, which is a part of the control steam CS, with the fuel FG supplied to the fuel nozzle 5 through the flow rate adjusting valve 24 and the mixing unit 22 through which the fuel FG flows. Is configured to do. By burning the fuel FG mixed with the control steam CS2 in this way, the temperature rise due to combustion is suppressed, and NOx reduction is realized.
The flow rate adjusting valve 24 is adjusted based on the supply amount of the fuel FG.
As the steam CS2 mixed with the fuel FG in this manner, saturated steam generated in the exhaust heat boiler 80 is preferably used.
[0029]
The downstream end face of each liner 1, that is, the discharge port 4 is externally fitted to a fitting portion 8 a formed on the liner side of the nozzle blade 8.
Further, between the adjacent discharge ports 4, saddles 26 that fill the gaps are respectively provided, and the leakage of the air A from the air flow path 7 directly to the nozzle blade 8 side is suppressed by the saddles 26. .
[0030]
FIG. 4 is a development view in which the barrel portion 1a of the liner 1 is developed by cutting away the innermost line closest to the drive shaft 54. The upper and lower ends become the innermost line, and the center line in the vertical direction is the drive shaft 54. It is the outermost line farthest from.
As shown in FIG. 4, a plurality of combustion air inlets 10 and 11 for allowing combustion air A to flow into the combustion section 2 are formed on the upstream side of the barrel portion 1a, and the combustion air inlet 10 Is a circular hole, and the combustion air inlet 11 is a rectangular hole having a longitudinal axis along the swirl flow of the combustion exhaust gas EG in the combustion section 2. Further, the combustion air inlets 10 and 11 are arranged at equal intervals at six locations in the cylindrical circumferential direction of the liner 1. The combustion air A can be made to flow uniformly.
[0031]
Further, the dilution air inlets 12 and 13 for allowing the dilution air A to flow into the dilution part 3 are formed on the downstream side of the barrel part 1a, that is, in the part close to the end face connected to the tail cylinder part 1b. Yes.
Specifically, the dilution air inlets 12 are circular holes provided at equal intervals in the cylindrical circumferential direction of the liner 1, and each of the dilution air inlets 12 is a drive shaft 54 of the turbine blade. Are arranged symmetrically with respect to the center plane passing through the outermost line of the liner 1. Such a dilution air inlet 12 serves as a so-called dilution port through which the dilution air A can uniformly flow into the dilution section 3.
[0032]
On the other hand, the dilution air inlet 13 is composed of two circular holes 13 a and 13 b that are provided so as to be biased to one side (the lower side in FIG. 4) in the width direction of the liner 1.
That is, the dilution air inlet 13 includes a hole 13a far from the center plane passing through the drive shaft 54 of the turbine blade 53 and the outermost line of the liner 1, and a hole 13b near the center plane. In other words, they are arranged asymmetrically with respect to the center plane and biased to one side across the center plane. The dilution air inlet 13 functions as a so-called control port, and the dilution air A in the dilution section 3 is biased to one side sandwiching the center plane, that is, the side where the hole 13a far from the center plane exists. Therefore, the temperature reduction of the combustion exhaust gas EG flowing to the side where a large amount of dilution air A is supplied becomes greater than that of the other side.
[0033]
The combustion exhaust gas EG to which the dilution air A is supplied in a state of being biased in the same direction along the rotation direction of the turbine blade 53 by the dilution air inlet 13 as the control port, as shown in FIG. Since it is guided to the discharge port 4 side, the temperature distribution state of the combustion exhaust gas EG immediately before discharge at each of the four discharge ports is biased in the same direction along the rotation direction from the maximum temperature position P to the center. It becomes a state.
Further, the maximum temperature position P is set to a value along the rotational direction of the turbine blade 53 from the center of the discharge port 4 by appropriately setting the opening area and position of the dilution air inlet 13 as a control port. The arrangement pitch interval W of the plurality of discharge ports 4 to the direction side (in FIG. 5, the arrangement pitch interval is indicated by a width W connecting the centers of the saddles 26 adjacent in the rotation direction). The bias rate is 15% or more.
[0034]
When the combustion exhaust gas EG in which the maximum temperature position P is biased to one side at an appropriate bias rate is discharged from the respective discharge ports 4, the temperature distribution state of the combustion exhaust gas EG immediately after the discharge is as shown in FIG. In addition, the combustion exhaust gas EG on one side where the maximum temperature position P is biased is reduced in temperature by the combustion exhaust gas EG sufficiently supplied with dilution air A at the discharge port 4 adjacent to the one side and sufficiently cooled. Become. Therefore, since the combustion exhaust gas discharged from the plurality of discharge ports 4 arranged in an annular shape is leveled with a small temperature difference as a whole, the maximum temperature of the combustion exhaust gas discharged from the discharge ports 4 is set. Even if the heat damage is suppressed by setting the temperature lower than the heat resistance temperature of the member such as the nozzle blade 8, the combustion exhaust gas EG having a sufficient amount of heat can be discharged and the power generation output and efficiency can be improved.
[0035]
Furthermore, the above-mentioned deviation ratio of the maximum temperature position P in the temperature distribution of the combustion exhaust gas EG immediately before discharge from the discharge port 4 is set appropriately for the opening area and position of the dilution air inlet 13 as a control port, 30% or less. Therefore, even if the maximum temperature position P is biased as described above, the temperature of the combustion exhaust gas EG contacting the wall portion of the discharge port 4 is set to the heat resistant temperature or less, for example, thermal damage such as the wall portion of the tail tube portion. Can be suppressed.
[0036]
In the above embodiment, the dilution air flow as a dilution port arranged in the dilution section 3 in a symmetric state with respect to the center plane passing through the drive shaft 54 of the turbine blade and the outermost line of the liner 1. The configuration in which both the inlet 12 and the dilution air inflow port 13 as a control port arranged in an asymmetric state with respect to the center plane has been described, but the arrangement position, the number, the total area, etc. If the maximum temperature position of the combustion exhaust gas at the discharge port 4 and the amount of dilution air flowing into the dilution section 3 can be made appropriate, the above-described dilution port can be used. The dilution air inlet 12 may be omitted, and only the dilution air inlet 13 as the control port may be provided in the dilution section 3.
[Brief description of the drawings]
FIG. 1 is a block diagram of a cogeneration system. FIG. 2 is a side sectional view showing a schematic configuration of a gas turbine combustion apparatus. FIG. 3 is a vertical sectional view showing a discharge port arrangement state of the gas turbine combustion apparatus. [Development of the cylinder body of the liner] [Fig. 5] Diagram showing the temperature distribution in the exhaust gas outlet width direction [Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Liner 1a Body cylinder part 1b Cylinder part 2 Combustion part 3 Dilution part 4 Discharge port 5 Fuel nozzle 8 Nozzle blade 10 Combustion air inlet 11 Combustion air inlet 12 Dilution air inlet (dilution port)
13 Air inlet for dilution (control port)
50 Gas Turbine Combustion Device 52 Compressor 53 Turbine Blade 54 Drive Shaft 60 Gas Turbine 70 Generator 80 Exhaust Heat Boiler A Combustion Air FG Fuel EG Combustion Exhaust Gas S Steam CS Control Steam (Steam-containing Gas)
X Steam-containing gas supply means

Claims (4)

A liner in which a combustion section for burning fuel and a dilution section for diluting combustion exhaust gas discharged from the combustion section with a plurality of dilution air inlets from a plurality of dilution air inlets are formed on the turbine shaft. A plurality of juxtaposed so as to surround the ring,
Each discharge port formed in the downstream end face of each liner is arranged at equal intervals along the rotation direction of the annular turbine blade, and discharges the combustion exhaust gas as a rotational drive source of the turbine blade. A gas turbine combustion apparatus configured as described above,
The highest temperature position of the combustion exhaust gas at each of the discharge ports is one direction side along the rotation direction from the center of the discharge port with reference to the arrangement pitch interval of the plurality of discharge ports with respect to the rotation direction of the turbine blades The gas turbine combustion apparatus in which the plurality of dilution air inlets are arranged so that the positions are deviated from 15% to 30%. The combustion apparatus for a gas turbine according to claim 1, further comprising a steam-containing gas supply means for supplying a steam-containing gas containing steam into the liner. A plurality of control ports arranged in an asymmetric state with respect to a center plane passing through the axis of the turbine blade and the center of the discharge port, and the dilution air inlet is symmetric with respect to the center plane The combustion apparatus for gas turbines of Claim 1 or 2 comprised from the several opening for dilution arrange | positioned in a state. A combustion apparatus for a gas turbine according to any one of claims 1 to 3, an annular turbine blade that rotates using combustion exhaust gas discharged from the plurality of discharge ports as a drive source, and air to the combustion apparatus for a gas turbine A gas turbine including a compressor for supplying the gas.

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