JP5614893B2 - Gas turbine combustor and coal gasification combined power plant - Google Patents

Description

  The present invention relates to a gas turbine combustor and a coal gasification combined power plant, and more particularly, to a gas turbine combustor and a coal gasification combined power plant that burns a fuel containing hydrogen as a fuel composition.

  When gas fuel containing hydrogen as a composition component is used in a gas turbine combustor, since the combustion speed of hydrogen is high, the flame formed in the gas turbine combustor approaches the combustor structure and is reliable. May cause problems.

  As a combustion method to ensure the reliability of the gas turbine combustor for the fuel containing hydrogen, only the fuel is directly injected into the combustion chamber of the gas turbine combustor and the fuel and air are mixed in the combustion chamber. Although the method is effective, in this combustion method, a flame is formed in a state where it is most easily combusted, so that the flame temperature becomes high and the amount of nitrogen oxide (NOx) emission tends to increase.

  On the other hand, in order to perform low NOx combustion, a premixed combustion method in which fuel and air are mixed in advance so that the fuel and air become leaner than the stoichiometric mixing ratio and supplied to the gas turbine combustor is effective. In the mixed combustion method, since the mixture in the combustible range is formed before it flows into the combustion chamber of the gas turbine combustor, the position of the flame formed in the combustion chamber when the hydrogen concentration contained in the fuel gas changes and increases Is likely to cause reliability problems in the gas turbine combustor as it approaches the structure of the gas turbine combustor. Even when the hydrogen concentration decreases, the lean air-fuel mixture is burned in the combustion chamber, so that the combustion speed and the combustible range fluctuate and the possibility of causing combustion instability increases.

  With a structure in which a large number of coaxial jet nozzles (coaxial jet burners) in which fuel nozzles and air nozzles are coaxially arranged are assembled, fuel and air dispersibility is increased in advance, and the fuel and air are supplied at a short distance. There is a gas turbine combustor that prevents backfire and achieves low NOx combustion by mixing.

  As a gas turbine combustor using such a coaxial jet nozzle (coaxial jet burner), in Patent Document 1, the surface of the air hole plate on the combustion chamber side has a truncated cone shape with the center portion protruding to the combustion chamber downstream side. Thus, the inner peripheral side coaxial jet nozzle group is a burner with high combustion stability, and the outer peripheral side coaxial jet nozzle group is a burner capable of low NOx combustion. Patent Document 1 also discloses a structure in which the top of the air hole plate is recessed to promote stagnation (FIG. 18). Reducing the top of the head and promoting itching enhances flame holding and improves combustion stability. Further, in Patent Document 1, for a fuel containing hydrogen, in order to prevent flame holding around the air hole outlet and prevent the flame from approaching the air hole plate, the air hole plate has a conical shape. (FIG. 27). The conical structure makes the stagnation area of the burner head very small, as opposed to the structure in which the head is depressed.

JP 2011-75172 A

  When gas fuel containing hydrogen as a composition component is used in a gas turbine combustor, since the combustion speed of hydrogen is high, the flame formed in the gas turbine combustor approaches the combustor structure and is reliable. May cause problems. Therefore, when a fuel containing hydrogen is applied to a gas turbine, there is a demand for a technique that can maintain combustion stability and achieve low NOx combustion while ensuring the reliability of the structure.

  Patent Document 1 basically realizes low NOx combustion while maintaining combustion stability for a fuel having a stable composition. Among them, in Patent Document 1, for the fuel containing hydrogen, by making the air hole plate conical, the stagnation region at the top of the burner is made very small, This prevents flame holding and prevents the flame from approaching the air hole plate.

  However, the apex of the cone, which is the central part of the air hole plate, is always exposed to the circulating gas, which is the combustion gas, and is encased in a steady flame having a higher temperature. In the case of a fuel containing hydrogen such as coal gasification fuel, the concentration of water vapor in the combustion gas and steady flame is higher than that of other fuels. Since water vapor is a gas with high emissivity, there is a possibility that the central portion of the air hole plate is locally overheated by radiation when encased in a high-temperature steady flame.

  An object of the present invention is a gas turbine combustor that burns a fuel containing hydrogen in the fuel composition, avoids overheating of the structure of the gas turbine combustor, and maintains combustion stability and low NOx combustion performance. Is to provide a vessel.

  The present invention relates to a gas turbine combustor using a coaxial jet burner that burns a fuel containing hydrogen in the fuel composition, such that the combustion chamber side surface of the burner protrudes from the outer peripheral side toward the center toward the combustion chamber side. And the center of the burner is recessed with an inclination so as to move away from the combustion chamber.

  The gas turbine combustor of the present invention desirably has a structure in which the circulating gas that is part of the combustion gas that circulates toward the stagnation region that occurs near the center of the burner is pushed back downstream of the combustion chamber so as to be away from the burner.

  Moreover, this invention uses the gas turbine combustor of the said structure as a gas turbine combustor of a coal gasification combined cycle power plant.

  ADVANTAGE OF THE INVENTION According to this invention, in the gas turbine combustor which burns the fuel which contains hydrogen in a fuel composition, it becomes possible to avoid overheating of the structure of a gas turbine combustor, and to maintain combustion stability and low NOx combustion performance. .

It is a schematic block diagram of the coal gasification combined cycle power plant provided with the gas turbine combustor which is an Example of the present invention. It is a schematic sectional drawing which shows the structure of the gas turbine combustor of the 1st Example of this invention. It is the fragmentary sectional view which looked at the air plate of the several main porous coaxial jet burner installed in the gas turbine combustor of the 1st Example of this invention from the combustion chamber side. FIG. 3 is a partial view showing air holes of an air plate formed in a main porous coaxial jet burner of the gas turbine combustor of the first embodiment shown in FIG. 2. It is the figure which looked at the air plate provided with the air hole formed in the main porous coaxial jet burner of the gas turbine combustor of the 1st Example shown in FIG. 2 from the combustion chamber side. It is a situation figure of the flow near the air hole of the fluid which flows through the fuel nozzle and air hole which constitute the main porous coaxial jet burner installed in the gas turbine combustor of the example of the present invention. FIG. 2 shows a fuel nozzle composing the main porous coaxial jet burner of the gas turbine combustor according to the first embodiment of the present invention shown in FIG. 2, a fluid jetted from the air hole to the combustion chamber, and a flow of the combustion gas in the combustion chamber. FIG. It is a schematic sectional drawing which shows the structure of the gas turbine combustor of the 2nd Example of this invention. It is the fragmentary sectional view which looked at the air plate of the several main porous coaxial jet burner installed in the gas turbine combustor of the 2nd Example of this invention from the combustion chamber side. It is a fragmentary view which shows the air hole of the air plate formed in the main porous coaxial jet burner of the gas turbine combustor of the 2nd Example shown in FIG. It is the figure which looked at the air plate provided with the air hole formed in the main porous coaxial jet burner of the gas turbine combustor of the 2nd Example shown in FIG. 8 from the combustion chamber side. FIG. 9 is a situation diagram showing the flow of combustion gas in the combustion chamber and the fuel nozzle that constitutes the main porous coaxial jet burner of the gas turbine combustor of the second embodiment shown in FIG. is there. FIG. 13 shows the flow of the combustion gas in the combustion chamber and the fuel nozzle that constitutes the main porous coaxial jet burner of the gas turbine combustor of the second embodiment shown in FIG. It is a figure which shows the distribution range of the air-fuel | gaseous mixture from the 1st coaxial jet burner part in the position of the cross section X of the situation figure shown. FIG. 13 shows the flow of the combustion gas in the combustion chamber and the fuel nozzle that constitutes the main porous coaxial jet burner of the gas turbine combustor of the second embodiment shown in FIG. It is a figure which shows the distribution range of the air-fuel | gaseous mixture from the 1st coaxial jet burner part in the position of the cross section Y of the situation figure shown. FIG. 13 shows the flow of the combustion gas in the combustion chamber and the fuel nozzle that constitutes the main porous coaxial jet burner of the gas turbine combustor of the second embodiment shown in FIG. It is a figure which shows the change with respect to the distance from the air hole plate exit of the pressure in the burner central axis of the situation figure shown.

  First, before describing the embodiments of the present invention in detail, in order to facilitate understanding of the present invention, the outline of the present invention will be described in comparison with FIG. 18 of Patent Document 1 having a structure similar to the present invention. To do.

  In the present invention, the combustion chamber side surface of the burner has an inclination that protrudes toward the combustion chamber side from the outer peripheral side toward the central portion, and the central portion of the burner is recessed with an inclination so as to move away from the combustion chamber. As a specific configuration example, an air hole plate positioned on the upstream side of the combustion chamber to which fuel and air are supplied and having a plurality of air holes, and coaxially arranged with respect to the air holes of the air hole plate, the air holes In a gas turbine combustor that includes a plurality of perforated coaxial jet burners comprising a plurality of fuel nozzles for supplying a fuel containing hydrogen in the fuel composition to each other and that is disposed in the gas turbine combustor that burns the fuel containing hydrogen in the fuel composition The porous coaxial jet burner has an inclination such that the combustion chamber side surface of the porous coaxial jet burner protrudes from the outer peripheral side toward the central portion toward the combustion chamber side, and the central portion of the porous coaxial jet burner moves away from the combustion chamber. In this way, the concave shape is recessed with an inclination.

  By making the combustion chamber side surface of the burner have an inclination that protrudes toward the combustion chamber from the outer periphery toward the center, the inner periphery coaxial jet nozzle becomes a burner with high combustion stability, and the outer periphery coaxial jet The nozzle can be a burner capable of low NOx combustion. Furthermore, by using a structure in which the central portion of the burner is recessed with an inclination so as to move away from the combustion chamber, overheating of the central portion of the burner can be avoided.

  FIG. 18 of Patent Document 1 discloses a structure similar to the present invention. However, Patent Document 1 realizes low NOx combustion while maintaining combustion stability for a fuel having a stable composition, including the structure disclosed in FIG. And in patent document 1, with respect to the fuel containing hydrogen, by making the air hole plate into a conical shape, the stagnation region at the top of the burner is made very small, and the flame around the air hole outlet is reduced. This prevents flame holding and prevents the flame from approaching the air hole plate. That is, in Patent Document 1, for the fuel containing hydrogen, in particular, the air hole as shown in FIG. 27 is opposite to the structure in which the top of the head is recessed to promote stagnation as shown in FIG. The plate has a conical shape to reduce the stagnation region at the top of the burner.

  The present invention specializes in a gas turbine combustor that burns fuel containing hydrogen. In contrast to Patent Document 1 (FIG. 27), the center of the porous coaxial jet burner is inclined in a concave shape so as to be away from the combustion chamber. It has a recessed structure. By adopting a structure in which the central part of the combustion chamber side surface of the multi-hole coaxial jet burner is recessed with an inclination so as to move away from the combustion chamber, it is possible to avoid the risk that the central part of the burner is wrapped in a steady flame, Since the central part of the burner is recessed in a concave shape so as to move away from the combustion chamber with an inclination angle, the angle at which the steady flame is viewed from the surface of the central part of the burner is reduced, so that the heat flow flowing into the central part of the burner by radiation Since the bundle can be suppressed, the risk that the burner central portion is overheated can be further reduced.

  And in this invention, it has a structure which pushes back the circulating gas which is a part of combustion gas which circulates toward the stagnation area | region produced in the burner center vicinity back to a combustion chamber downstream so that it may keep away from a burner. As a result, overheating of the burner center can be avoided more reliably.

  Moreover, the combustion chamber side surface of the multi-hole coaxial jet burner has an inclination that protrudes from the outer peripheral side toward the center toward the combustion chamber side, so that a low flow velocity vortex (wake) formed near the outlet of the air hole It can suppress the growth and reduce the risk of the flame adhering to the wake, and the flow from the outer peripheral side toward the central stagnation region along the inclination of the combustion chamber side surface of the multi-hole coaxial jet burner is generated. Since the flow pushes the flame back downstream, the flame is less likely to adhere to the downstream.

  Hereinafter, a gas turbine combustor, a gas turbine combustor fuel supply apparatus, a gas turbine combustor fuel supply method, and a power plant using the gas turbine combustor according to embodiments of the present invention will be described with reference to the drawings.

  FIG. 1 is a schematic configuration diagram of an integrated coal gasification combined cycle (IGCC) including a gas turbine plant having a gas turbine combustor according to a first embodiment of the present invention (IGCC). It is. From the viewpoint of preventing global warming, IGCC is studying a system for separating and recovering carbon in gasified fuel supplied to a gas turbine combustor both at home and abroad. The IGCC shown in FIG. 1 is a coal gasification combined cycle (CCS-IGCC) plant with a carbon dioxide separation and recovery device.

  The coal gasification furnace 202 is charged with the oxygen 17 from the oxygen production apparatus 201 to gasify the coal 16. The pre-refining coal gasification gas 18 generated in the coal gasification furnace 202 is collected and desulfurized by the coal gasification gas purification device 203 and then supplied to the shift reactor 206 via the flow rate adjustment valve 204. In the shift reactor 206, the water vapor 20 is added to convert CO in the coal gasification gas into CO2 by a shift reaction. And CO2 in coal gasification gas is collect | recovered in the carbon dioxide recovery apparatus 207, and high hydrogen concentration (after CO2 collection | recovery) coal gasification gas 21 is manufactured. The fuel supply systems 122b, 123a, 123b include pre-carbon dioxide recovery coal gasification gas 19 from the pre-carbon dioxide recovery coal gasification gas supply system 120 and high hydrogen concentration coal from the high hydrogen concentration coal gasification gas supply system 121. Gasified gas 21 is supplied as coal gasified fuel 22 through shutoff valve 103. The coal gasification gas supply system 120 before carbon dioxide recovery is provided with a hydrogen concentration detection means 102a and a flow rate adjustment valve 205. The high hydrogen concentration coal gasification gas supply system 121 is provided with a hydrogen concentration detection means 102 b and a flow rate adjustment valve 208. Coal gasification gas that is not used as the coal gasification fuel 22 is discharged through the gas processing furnace 209. When the high hydrogen concentration coal gasification gas 21 in which CO2 is recovered is supplied as the coal gasification fuel 22, most components of the fuel are hydrogen.

  The gas turbine plant driven by the coal gasification fuel 22 containing hydrogen in the fuel composition burns the compressed air 10 compressed by sucking outside air by the compressor 5 into the gas turbine combustor 9 via the passenger compartment 7. It is supplied as working air 12 and injected into the combustion chamber 1 together with the coal gasification fuel 22 from the main porous coaxial jet burner 53 installed in the gas turbine combustor 9 and burned. Further, the gas turbine plant drives the high-temperature and high-pressure combustion gas 13 generated by burning the gasification fuel 22 in the gas turbine combustor 9 into the turbine 6 to drive the rotational power of the turbine 6 to the generator 501. Take out as power. Although not shown, steam is generated by the high-temperature exhaust gas from the gas turbine, and the steam turbine is driven by this steam to generate electric power.

  The gas turbine combustor of the present invention includes a coke oven gas (COG) and a blast furnace gas (BFG), which are by-product gases containing hydrogen, obtained from an iron manufacturing plant, in addition to the IGCC as described above. Gas), converter gas (LDG: Linzer Donawitz Gas), or a gas turbine that uses these gas mixtures as fuel, or a gas that uses hydrogen as a by-product gas, such as a naphtha cracking plant at a petroleum refinery It can be applied to turbines. In these by-product gases, 30 to 60% of the fuel component is hydrogen.

  In this way, when fuel with varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, overheating of the structure is avoided without being affected by variations in hydrogen concentration over a wide load range, and reliability is improved. It is important to maintain high combustion stability and low NOx combustion performance.

  Next, the structure of the gas turbine combustor which is the first embodiment of the present invention will be described. 2 is a cross-sectional view showing a schematic structure of the gas turbine combustor shown in FIG. 1, and FIGS. 3 to 5 show a porous coaxial jet burner installed in the gas turbine combustor shown in FIGS. It is a figure which shows the air hole plate of the wall-shaped member which formed the air hole to perform. 6 shows a gas turbine combustor described in FIGS. 1 and 2, a single fuel nozzle constituting a multi-hole coaxial jet burner, and a multi-hole coaxial jet burner arranged corresponding to the single fuel nozzle. It is an enlarged view which shows the mode of the flow of the fluid in the vicinity of the single air hole formed in the air hole plate which comprises.

  The gas turbine combustor 9 includes a combustor outer cylinder 2 installed on the outer peripheral side, a combustor liner 3 installed inside the combustor outer cylinder 2, and a combustor connected to the downstream side of the combustor liner 3. A cylindrical structure having a tail cylinder 4 is formed, and a cylindrical combustion chamber 1 for burning coal gasification fuel 22 and combustion air 12 is formed inside the combustor liner 3. The combustor tail cylinder 4 is a component that smoothly communicates between the outlet of the cylindrical combustor liner 3 and the stationary blade inlet of the fan-shaped turbine 6.

  Combustion air 12 used for combustion of the coal gasification fuel 22 in the combustion chamber 1 of the gas turbine combustor 9 is supplied through a space between the combustor outer cylinder 2 and the combustor liner 3 of the gas turbine combustor 9. However, it is dammed by the combustor end cover 8 provided at the head of the gas turbine combustor 9, and a part of the combustion air 12 is formed in the air hole plate 54 constituting the main porous coaxial jet burner 53. The air hole 55 is supplied.

  Further, another part of the combustion air 12 flows into the combustion chamber 1 as cooling air 11 from a large number of air holes opened in the wall surface of the combustor liner 3 and is generated in the combustion chamber 1 of the gas turbine combustor 9. The high-temperature and high-pressure combustion gas 13 cools the structure such as the combustor liner 3 so that it is not overheated.

  The coal gasification fuel 22 supplied to the gas turbine combustor 9 passes through the distribution flow path of the fuel distributor 57 provided inside the end cover 8 from the outside of the combustor end cover 8, and each of the main porous coaxial jet burners 53. The fuel nozzles 56 are respectively distributed.

  The coal gasification combined power plant with carbon dioxide recovery shown in the present embodiment is a coal gas from the outside until the coal gasification furnace 202 is operated and the coal gasification fuel 22 is supplied to the gas turbine plant. It is necessary to start the gasification furnace 202 by starting the gas turbine plant with fuel different from the gasification gas 22 to generate electric power and thermal energy. For this reason, this embodiment has a fuel supply system 122a that supplies the starting fuel 15 for starting the coal gasification combined power plant.

  As shown in FIGS. 1 and 5, the gas turbine combustor 9 of the present embodiment includes a pilot burner 50 having an activation fuel injection nozzle 51 at the center of the combustor axis, and includes an outer peripheral side of the combustor axis. A structure in which five main porous coaxial jet burners 53 having a porous coaxial jet burner structure are arranged around the pilot burner 50 is adopted.

  For this reason, the fuel supply system 122a for supplying the starter fuel 15 as pilot fuel to the pilot burner 50 of the gas turbine combustor 9 before the start of the gasification furnace 202 is disposed, and the starter fuel 15 is supplied to the fuel supply system 122a. A starting fuel pilot burner fuel cutoff valve 104a, a starting fuel pilot burner fuel pressure adjustment valve 105a, and a starting fuel pilot burner fuel flow rate adjustment valve 106a are installed.

  Further, if a multi-hole coaxial jet burner structure is adopted for the pilot burner, a gas turbine combustor capable of performing lower NOx combustion can be configured. In this embodiment, the coal gasification fuel 22 is also supplied to the pilot burner 50, and after the gasification furnace 202 is operated, the pilot burner 50 is also operated by the coal gasification fuel 22. For this reason, after the gasification furnace 202 is started, a fuel supply system 122b for supplying the coal gasification fuel 22 as pilot fuel to the pilot burner 50 installed in the gas turbine combustor 9 is provided. A coal gasification fuel pilot burner fuel shut-off valve 104b, a coal gasification fuel pilot burner fuel pressure adjustment valve 105b, and a coal gasification fuel pilot burner fuel flow adjustment valve 106b are installed in 122b, respectively, for adjusting the flow rate of the coal gasification fuel 22. Has been.

  Each of the plurality of main perforated coaxial jet burners 53 installed in the gas turbine combustor 9 is a fuel that supplies coal gasification fuel 22 as fuel to the first coaxial jet burner portion 53a provided on the inner peripheral side thereof. A supply system 123a is provided, and an inner peripheral main fuel pressure adjustment valve 107a and an inner peripheral main fuel flow adjustment valve 108a for adjusting the flow rate of the coal gasification fuel 22 are respectively installed in the fuel supply system 123a. .

  Further, each of the plurality of main porous coaxial jet burners 53 installed in the gas turbine combustor 9 has a second coaxial jet burner provided on the outer peripheral side (the outer peripheral side of the first coaxial jet burner portion 53a). A fuel supply system 123b for supplying the coal gasification fuel 22 as fuel is disposed in the section 53b. The fuel supply system 123b includes an outer peripheral main fuel pressure adjustment valve 107b for adjusting the flow rate of the coal gasification fuel 22, and an outer peripheral side. A main fuel flow rate adjusting valve 108b is installed. In FIG. 1, fuel supply systems 123 a and 123 b for supplying the coal gasification fuel 22 to one main perforated coaxial jet burner 53 are illustrated for simplification of the drawing.

  The porous coaxial jet burner constituting the main porous coaxial jet burner 53 is a burner that forms a large number of fuel / air coaxial jets, and the degree of mixing of the fuel and air is determined by the air nozzle constituting the main porous coaxial jet burner 53. And the shape of the fuel nozzle can be adjusted.

  Further, the flame holding ability of each main porous coaxial jet burner 53 can be adjusted by mixing and jetting direction of the coaxial jet of the first coaxial jet burner portion 53a installed on the inner peripheral side of each main porous coaxial jet burner 53. Therefore, the coaxial jet of the first coaxial jet burner portion 53a can have a flame holding function.

  Further, in the combustion chamber 1, the mixing of fuel and air is adjusted by the first coaxial jet burner portion 53 a on the inner peripheral side of each main porous coaxial jet burner 53 so as to enhance the flame holding function. The position where the combustible air-fuel mixture is formed can be designed at a position away from the structure of each main perforated coaxial jet burner 53 in the downstream direction of the combustion chamber of the gas turbine combustor 9. For the coaxial nozzle, a large margin for the flame approach can be taken.

  Therefore, in the gas turbine combustor 9 of the present embodiment, in the main porous coaxial jet burner 53 constituting the main burner, the first coaxial jet burner portion 53a installed on the inner peripheral side and the second coaxial jet burner portion 53a installed on the outer peripheral side. The fuel system is divided into a fuel supply system 123a and a fuel supply system 123b so that the coal gasification fuel 22 is supplied independently to the coaxial jet burner 53b, and the fuel supply system 123a and the fuel supply system 123b are supplied. The fuel distribution and the flow rate of each fuel can be adjusted. The distribution of the fuel supplied to the fuel supply system 123a and the fuel supply system 123b and the adjustment of the flow rate of each fuel are adjusted as described in Patent Document 1, for example.

  A part of the coal gasification fuel 22 supplied to the main perforated coaxial jet burner 53 is guided to the joint of the combustor end cover 8 of the gas turbine combustor 9 through the fuel supply system 123a. Further, the other part of the coal gasified fuel 22 is led to the connection port of the combustor end cover 8 of the gas turbine combustor 9 through the fuel supply system 123b. Each coal gasified fuel 22 thus guided passes through the flow path inside the end cover 8 as shown in FIG. 2, and the fuel nozzle constituting the main porous coaxial jet burner 53 from the outer peripheral side space of the fuel distributor 57. 56 is jetted toward the air hole 55 opened in the air hole plate 54, and is jetted coaxially with the air from the main porous coaxial jet burner 53 into the combustion chamber 1 of the gas turbine combustor 9 for combustion. .

  FIG. 6 shows the tip of a single fuel nozzle 56 constituting one coaxial jet burner among a large number of coaxial jet burners constituting the main porous coaxial jet burner 53 installed in the gas turbine combustor 9, and air It is the schematic which expanded and showed the air hole 55 of the hole plate 54. FIG. A coaxial jet burner is a burner in which a fuel flow path and a flow path of an oxidant such as air are arranged substantially concentrically so as to jet in substantially the same direction.

  In the coaxial jet burner shown in FIG. 6, the air hole plate 54 is disposed between one fuel nozzle 56 constituting the main porous coaxial jet burner 53 and the combustion chamber 1. The fuel nozzle 56 is disposed substantially coaxially with the air hole 55 on the upstream side of the air hole 55 formed in the air hole plate 54, and the coal gasified fuel 22 ejected from the fuel nozzle 56 flows into the center of the air hole 55. Is configured to do. Further, the combustion air 12 is drawn into the upstream side of the air hole plate 54, and the combustion air 12 supplied from the upstream side of the air hole plate 54 is also air from the outer peripheral side of the fuel nozzle 56. It flows into the hole 55. At this time, the combustion air 12 flows from a wide space formed on the upstream side of the air hole plate 54 into an air hole 55 in a narrow space formed in the air hole plate 54.

  Therefore, in the air hole 55, the fuel flow and the annular air flow formed on the outer peripheral side of the fuel flow cause the vortex generated downstream of the fuel nozzle 56 and the combustion air 12 at the inlet of the air hole to abruptly flow. A coaxial jet that flows down including a fine turbulent structure such as a separation vortex due to contraction is formed.

  The fuel flow and the air flow that have passed through the air hole 55 of the air hole plate 54 are ejected at once into the combustion chamber 1 in a space larger than the air hole 55, and the vortex limited in the narrow space of the air hole 55 is greatly expanded. As it collapses, the fuel flow and air flow rapidly mix in the combustion chamber 1 to form an air-fuel mixture 42 as shown in FIG.

  As described above, when the plurality of air holes 55 coaxial with the plurality of fuel nozzles 56 are arranged in the air hole plate 54 and the fuel nozzle 56 is arranged on the upstream side of the air holes 55, the air flows into the combustion chamber 1. Since fuel disperses rapidly, the degree of mixing of fuel and air increases, allowing rapid mixing over short distances.

  In the main perforated coaxial jet burner 53 having such a configuration, the fuel flow flows through the center of the air hole 55 constituting the coaxial jet burner, and the air flow flows around the fuel flow. In the very vicinity, a mixture in the combustible range is not formed. Further, since mixing proceeds in the air hole 55 and in a very narrow region immediately after flowing into the combustion chamber 1, the flame is difficult to approach the vicinity of the air hole plate 54, and the gas turbine combustor 9 has high reliability. Has characteristics.

  Next, one of the five main perforated coaxial jet burners 53 installed in the gas turbine combustor 9 of the present embodiment is extracted, and the fuel flow and air flow are extracted using FIGS. 7, 3, 4, and 5. Explain the flow situation.

  5 is a view of the air hole plate 54 as viewed from the combustion chamber 1 side, and FIG. 3 is a view of one of the main porous coaxial jet burners 53 surrounded by the one-dot chain line of the air hole plate 54 shown in FIG. 4 is a cross-sectional view cut in a direction perpendicular to the fuel nozzle side plane, and FIG. 4 is extracted with attention paid to one of the main perforated coaxial jet burners 53 surrounded by a one-dot chain line in the air hole plate 54 shown in FIG. The figure is shown. The shaded area in FIG. 4 is a portion where the combustion chamber side surface of the air hole plate 54 has an inclined surface that protrudes toward the combustion chamber side with an inclination angle α0 from the outer peripheral side toward the central portion. There is a hatched area with a downward slanting oblique line, which is a portion that is recessed in a concave shape so that the center of the burner moves away from the combustion chamber with an inclination angle α1.

  Further, in FIG. 5, the position of the combustor liner 3 positioned on the outer side downstream of the air hole plate 54 on the fuel nozzle side is indicated by a broken line. FIG. 7 shows a fuel nozzle, a fluid jetted from the air hole to the combustion chamber, and a combustion gas in the combustion chamber for one of the main porous coaxial jet burners 53 surrounded by the one-dot chain line of the air hole plate 54 shown in FIG. FIG.

  In the positional relationship between the fuel nozzle 56 and the air hole 55 constituting the coaxial jet burner of the main porous coaxial jet burner 53 of the present embodiment shown in FIG. 7, a first installed on the inner peripheral side of the main porous coaxial jet burner 53. The central axis of the burner innermost peripheral air hole 55-1 serving as the coaxial jet burner portion 53a is inclined in the circumferential direction of the pitch circle in which the air hole is disposed with respect to the burner central axis. FIG. 4 is a partial cross-sectional view of the air hole plate 54 cut along one central axis of the burner innermost peripheral air hole 55-1 serving as the first coaxial jet burner portion 53a. As shown in FIG. 4, the central axis of the burner innermost peripheral air hole 55-1 serving as the first coaxial jet burner portion 53a is inclined in the circumferential direction of the pitch circle in which the air hole is arranged with respect to the burner central axis. Therefore, the fuel flow 41-1 and the air flow of the inner peripheral fuel ejected from the innermost peripheral air hole 55-1 serving as the first coaxial jet burner portion 53a are the central axis of the innermost peripheral air hole 55-1. Is injected into the combustion chamber 1 with a swirling component in the tangential direction of the pitch circle in which air holes are arranged, and is rapidly mixed by the above-described mechanism to become an air-fuel mixture 42-1.

  Since the innermost peripheral air hole 55-1 serving as the first coaxial jet burner portion 53a has a turning angle θ inclined in the circumferential direction as shown in FIG. The injected air-fuel mixture 42-1 turns into a swirl flow 46 that flows downstream while spirally swirling inside the combustion chamber 1, and flows out downstream while expanding the swirl diameter inside the combustion chamber 1.

  The swirling flow that flows down while expanding in this way induces a pressure gradient in the opposite direction on the central axis of the swirling, so that the combustion gas generated by the reaction in the flame 45 in the swirling flow as shown in FIG. A part of 44 circulates as a circulating gas 43 toward a stagnation region 49 generated in the vicinity of the center of the burner, and gives activation energy to the air-fuel mixture 42-1 flowing from the innermost peripheral air hole 55-1. It functions as an ignition source that maintains the combustion reaction. As a result, a stable conical steady flame 45 is formed inside the combustion chamber 1.

  The air hole plate 54 of the main porous coaxial jet burner 53 installed in the gas turbine combustor 9 of the present embodiment shown in FIG. 7 has an inclination angle with the surface on the combustion chamber side from the outer peripheral side toward the center as shown in FIG. It has a structure that protrudes toward the combustion chamber with α0. In the vicinity of the outlet of the air hole 55, the fuel and air that have flowed down the air hole 55 at high speed suddenly jet into a wide space and are not restrained by the wall surface of the air hole. The plate 54 grows in the normal direction 65 of the combustion chamber side surface. In the present embodiment, since the combustion chamber side surface of the air hole plate 54 protrudes toward the combustion chamber side with an inclination angle α0 from the outer peripheral side toward the central portion, the second air hole 55-2 on the outer peripheral side is formed. The fuel and air that has flowed down are structured to enter at an angle with respect to the space in which the wake 48 on the combustion chamber side surface of the air hole plate 54 is to grow. For this reason, the wake 48 generated near the combustion chamber side surface of the air hole plate 54 cannot grow greatly. If a large low flow velocity vortex exists on the surface of the air hole plate 54, in the case of a fuel containing hydrogen such as the coal gasified fuel 22, a flame is held in the wake 48 and the air hole plate 54 may overheat. Occurs. In this embodiment, the combustion chamber side surface of the air hole plate 54 protrudes toward the combustion chamber side with an inclination angle α0 from the outer peripheral side toward the central portion, so that the growth of the wake 48 is suppressed. It is possible to reduce the risk of the flame being attached.

  Further, if the surface of the air hole plate 54 on the combustion chamber side is flat, a wake grows, and a pressure recovery point due to the wake flows between the air hole plate outer peripheral region and the stagnation region 49 at the center of the air hole plate 54. Therefore, the air around the air hole plate is only stirred by the wake 48. However, by causing the combustion chamber side surface of the air hole plate 54 to protrude, growth of the wake is suppressed as described above, so that a forward pressure gradient from the outer periphery of the air hole plate toward the central stagnation region 49 is created. As shown in FIG. 2, since the accompanying flow 40 in which the surrounding gas is entrained toward the stagnation point is generated, it becomes difficult for the flame to adhere to the wake 48 of the air hole outlet.

  However, if the combustion chamber side surface of the air hole plate 54 only protrudes toward the combustion chamber side with an inclination angle α0 from the outer peripheral side toward the central part, the air hole plate 54 faces the stagnation region 49 near the burner center. The central portion of the gas is protruded, is always exposed to the circulating gas 43 which is the high-temperature combustion gas 44, and is encased in the steady flame 45 having a higher temperature. In the case of a fuel containing hydrogen such as the coal gasification fuel 22, the water vapor concentration in the combustion gas 44 and the steady flame 45 is higher than that of other fuels. Since water vapor is a gas with a high emissivity, the central portion of the air hole plate 54 is at a high risk of being overheated by radiation when it is encased in the high temperature steady flame 45. Therefore, in this embodiment, as shown in FIG. 3, the burner central portion has a structure that is recessed in a concave shape so as to move away from the combustion chamber with an inclination angle α 1, so that the burner central portion has a steady flame 45. I try to avoid the danger of being enveloped.

  Furthermore, since the central portion of the burner is recessed in a concave shape so as to move away from the combustion chamber with an inclination angle α1, the angle at which the stationary flame 45 is viewed from the surface of the central portion of the burner is reduced, so that the central portion of the burner is irradiated by radiation. Since the inflowing heat flux can be suppressed, the risk of overheating of the burner center is further reduced.

  On the other hand, on the outer peripheral side of the main porous coaxial jet burner 53, a row of outer peripheral air holes 55-2 serving as the second coaxial jet burner portion 53b installed on the outer peripheral side of the first coaxial jet burner portion 53a is arranged. Has been. The air hole central axis of the outer peripheral side air hole 55-2 is parallel to the burner central axis. Accordingly, the fuel flow 41-2 and the air flow of the outer peripheral fuel ejected from the outer peripheral air hole 55-2 serving as the second coaxial jet burner portion 53b are injected into the combustion chamber 1 in parallel to the burner central axis, and the above-described mechanism. Thus, the mixture is rapidly mixed to become the air-fuel mixture 42-2, and merges with the flame 45 that goes straight in the combustion chamber and spreads conically.

  At this joining position, activation energy is applied from the combustion gas 44 generated by the combustion of the air-fuel mixture 42-1 ejected from the innermost peripheral air hole 55-1 serving as the first coaxial jet burner 53a, and the combustion reaction is performed. The flame 45 propagates inside the gas mixture 42-2.

  As described above, the air-fuel mixture 42-2 from the outer peripheral air hole 55-2 serving as the second coaxial jet burner 53b is a combustion gas generated by the combustion reaction of the air-fuel mixture 42-1 from the innermost air hole 55-1. Since 44 is used as the ignition source, the start position of the combustion reaction is downstream from the air hole plate 54, and combustion is performed in a more advanced state of mixing, so that more uniform and low NOx combustion is possible.

  In addition, although the air hole 55 formed in the air hole plate 54 shown in the gas turbine combustor 9 of the present embodiment is only an air hole having a circular cross section, the air hole may be formed in a shape other than a circular shape (for example, a rectangular slot). To do.

  According to the present embodiment, when a fuel with varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, it is reliable to avoid overheating of the structure without being affected by variations in the hydrogen concentration over a wide load range. It is possible to achieve a gas turbine combustor that maintains high combustion stability and can exhibit low NOx combustion performance.

  A gas turbine combustor which is a second embodiment of the present invention will be described. The gas turbine plant having the gas turbine combustor according to the second embodiment of the present invention is also a coal gasification combined power plant similar to the first embodiment, and the configuration and operation method of the plant is the first implementation. Similar to the example.

  In the second embodiment, in particular, in order to more reliably avoid overheating of the burner central portion, the circulating gas that is a part of the combustion gas circulated toward the stagnation region generated in the vicinity of the burner central portion is used. The main feature is that it has a structure for pushing back to the downstream side of the combustion chamber so as to be away from the burner (hereinafter referred to as a circulating gas push-back structure).

  FIG. 8 is a sectional view showing a schematic structure of a gas turbine combustor according to a second embodiment of the present invention. FIGS. 9 to 11 are perforated coaxial jet burners installed in the gas turbine combustor shown in FIG. It is a figure which shows the air hole plate of the wall-shaped member in which the air hole which comprises was formed. 11 is a view of the air hole plate 54 as viewed from the combustion chamber 1 side, and FIG. 9 is a view of one of the main porous coaxial jet burners 53 surrounded by the one-dot chain line of the air hole plate 54 shown in FIG. FIG. 10 is a cross-sectional view cut in a direction perpendicular to the surface, and FIG. 10 shows a drawing extracted by paying attention to one of the main porous coaxial jet burners 53 surrounded by a one-dot chain line in the air hole plate 54 shown in FIG. The shaded region in FIG. 10 is a portion where the combustion chamber side surface of the air hole plate 54 has an inclined surface projecting toward the combustion chamber side with an inclination angle α0 from the outer peripheral side toward the central portion. There is a hatched area with a downward slanting oblique line, which is a portion that is recessed in a concave shape so that the center of the burner moves away from the combustion chamber with an inclination angle α1.

  Further, in FIG. 11, the position of the combustor liner 3 positioned on the outer side downstream of the air hole plate 54 on the fuel nozzle side is indicated by a broken line. Further, FIG. 12 shows a fuel nozzle, a fluid jetted from the air hole to the combustion chamber, and a combustion gas in the combustion chamber for one of the main porous coaxial jet burners 53 surrounded by the one-dot chain line of the air hole plate 54 shown in FIG. FIG.

  First, as shown in FIGS. 9 to 11, the main burner 53 of the gas turbine combustor of the second embodiment shown in FIG. 8 has a concave shape so as to be away from the combustion chamber at the center of the main burner with an inclination angle α1. It differs from the first embodiment in that it has a cooling air hole 58 through which only air is ejected in a region that is recessed. That is, the cooling air hole 58 functions as a circulating gas push-back structure. When the cooling air hole 58 for ejecting only air is opened in the recessed area in the center of the burner in this way, the cooling air 11 is ejected toward the stagnation area 49 generated near the center of the burner as shown in FIG. The circulating gas 43 as an ignition source is pushed back from the air hole plate 54 to the first coaxial jet burner 53a, and the circulating gas 43 is diluted to lower the temperature. Due to this effect, the position where the mixture of fuel and air ejected from the first coaxial jet burner 53a ignites moves downstream in the combustor axial direction, and the axial distance between the air hole plate 54 and the steady flame 45 becomes smaller. Since it becomes larger, it is more effective in avoiding overheating of the air hole plate 54. A plurality of cooling air holes may be used.

  Next, in this embodiment, in the main burner 53, as shown in FIGS. 9 to 11, two rows of outer peripheries become the second and third coaxial jet burner portions on the outer peripheral side of the first coaxial jet burner portion 53a. Side air holes 55-2 and 55-3 are arranged.

  As shown in FIG. 9, the inlet pitch circle diameter 61-2 and the outlet pitch circle diameter 63-2 of the second outer peripheral air hole are the inlet pitch circle diameter 61-1 and the outlet pitch circle diameter 63- of the first air hole. Greater than 1 and has a larger circumference. Since the third air hole array is larger than the second air hole array, the number of air holes that can be arranged further increases. Actually, in the present embodiment, only four coaxial jet burners are arranged in the first air hole row, but eight coaxial jet burners are arranged in the second row and 12 coaxial jet burners in the third row. Has been placed.

  Similar to the first embodiment, the air-fuel mixtures 42-2 and 42-3 from the outer peripheral air holes 55-2 and 55-3 are the combustion reaction of the air-fuel mixture 42-1 from the innermost air hole 55-1. Since the combustion gas 44 generated by the above becomes an ignition source, the combustion reaction starts from the downstream side of the air hole plate 54 and burns in a more mixed state, so that more uniform and low NOx combustion is possible. . Therefore, when the present invention is applied to a gas turbine having a larger combustion amount, a coaxial jet that performs low NOx combustion in the main burner by forming third to fourth air hole arrays on the outer peripheral side as necessary. The number of burners increases, and the amount of NOx emissions can be further suppressed.

  Furthermore, in this embodiment, as shown in FIG. 10, the second air hole 55-2 and the third air hole 55-3 constituting the second coaxial jet burner part and the third coaxial jet burner part are air A difference from the first embodiment is that the hole central axis is provided with the turning angles θ2 and θ3 inclined in the circumferential direction of the pitch circle in which air holes are arranged with respect to the burner central axis. Thus, by giving the swirl angles θ2 and θ3 to the outer peripheral air holes 55-2 and 55-3, the reverse pressure gradient induced by the swirl flow can be strengthened, and the flame holding ability of the entire burner can be enhanced. it can.

  Furthermore, in this embodiment, as shown in FIG. 10, the air hole 55-1 constituting the first coaxial jet burner has a concave shape so that the center of the burner moves away from the combustion chamber with an inclination angle α1. Open in the recessed part. The structure in which the air hole 55-1 is opened in the concave portion is also a function as a circulating gas push-back structure. Further, the structure in which the air hole 55-1 is opened in the concave portion has the function of improving the combustion stability as follows.

  That is, as described above, the combustion chamber side surface of the air hole plate 54 has a portion that protrudes toward the combustion chamber side with an inclination angle α0, and wake growth is suppressed. A forward pressure gradient toward the stagnation region 49 is created, and as shown in FIG. 12, an accompanying flow 40 in which surrounding gas is entrained toward the stagnation point is generated. In the first embodiment, the outlet of the air hole constituting the coaxial jet burner opens to an inclined portion projecting toward the combustion chamber with the inclination angle α0, and the air-fuel mixture ejected from each air hole is an accompanying flow 40. Exposed to. For this reason, it may be influenced by surrounding flow conditions such as partially taking in air brought by the accompanying flow. If the air hole 55-1 which comprises the 1st coaxial jet burner part like this example is opened in the part which is dented in the concave shape so that the burner center part may leave the inclination angle α1 from the combustion chamber. Since the first coaxial jet burner portion has an outlet at a position not directly exposed to the accompanying flow, it is not subject to disturbance caused by the accompanying flow, and the burner structure is more excellent in combustion stability.

  Furthermore, in this embodiment, the air holes are arranged on the central axes of the air holes 55-1, 55-2, 55-3 constituting the first coaxial jet burner part and the second and third coaxial jet burner parts. In addition to inclining in the circumferential direction of the outlet pitch circle, the inner inclination angles β1, β2, and β3 are set so that the outlet pitch circle has a jet angle inclined toward the burner center side with respect to the tangent drawn at the air hole outlet position. have. The effect of the internal inclination angle β will be described with reference to FIGS. 13, 14, and 15 for the first coaxial jet burner.

  When the central axis of the air hole 55 constituting the coaxial jet burner has a jet direction inclined to the burner center side with respect to the tangent drawn to the air hole outlet pitch circle, the fuel / air mixture jetted from the coaxial jet burner burns It becomes a swirling jet that spouts into the chamber while reducing the swirling diameter. Taking the first coaxial jet burner as an example, as shown in an enlarged view in FIG. 13, in the cross section X corresponding to the air hole outlet, the air-fuel mixture 42-1 exists at positions separated from each other corresponding to the air hole outlet.

  However, as described above, the first air hole 55-1 is given the internal inclination angle β1 in addition to the swivel angle θ1, and the air-fuel mixture 42-1 is ejected into the combustion chamber while reducing the swirl diameter. At the cross-sectional position Y moved downstream, the turning diameter is reduced so as to be in contact with each other. At this time, since the angular momentum of the jet flow that has been ejected from the air hole is preserved, the turning speed increases in accordance with the reduction of the turning diameter. Therefore, the pressure gradient induced in the burner central axis by the swirling flow that flows down while reducing the swirling diameter has a forward pressure gradient that decreases as the jet flow pressure increases in accordance with the increase in swirling speed. .

  On the other hand, when the cross-sectional position Y is passed, the swirl flow of the air-fuel mixture gradually increases the swirl diameter. The swirling flow that flows down while the swirling diameter increases induces a reverse pressure gradient on the burner central axis as described above. FIG. 15 shows the change in pressure induced on the burner central axis by such a swirling flow with respect to the distance along the burner central axis from the air hole outlet.

  Due to the reverse pressure gradient, a part of the combustion gas 44 of the steady flame 45 circulates as a circulation gas 43 toward a stagnation region 49 generated in the center of the burner. However, as shown in FIG. 15, since a forward pressure gradient is formed in a region upstream of the cross-sectional position Y in the vicinity of the air hole plate 54, the circulating gas 43 cannot be traced upstream from the cross-sectional position Y. Since the circulating gas 43 is an ignition source for the air-fuel mixture 42-1 from the first coaxial jet burner serving as a flame base point, the ignition source does not enter the air hole plate side from the cross-sectional position Y, so that the air hole The steady flame 45 does not enter from the plate 54 to the cross-sectional position Y. Accordingly, the axial distance between the air hole plate 54 and the steady flame 45 becomes larger, which is more effective in avoiding overheating of the air hole plate 54. That is, the inclining angle β has a function as a circulating gas pushback structure. In order to maximize the effect of the circulating gas push-back structure, the maximum height H at which the air hole plate 54 protrudes toward the combustion chamber is set as follows.

The position Y at which the swirling diameter of the air-fuel mixture 42-1 ejected from the first coaxial jet burner changes from reduction to enlargement corresponds to the diameters of the inlet and outlet pitch circles of the first air holes, and the first air. It can be determined from the axial length of the hole and the internal tilt angle. The distance from the air hole inlet to the cross-sectional position Y is λ ₁ , the first air hole inlet pitch circle diameter 61-1 is D _I-1 , the first air hole outlet pitch circle diameter 63-1 is D _E-1 , the axial length 64-1 of the first air hole and L _1, tangent the center axis of the first air holes 55-1 as described above is drawn first air hole outlets pitch circle in the air hole outlet Assuming that the angle formed by the internal inclination angle β ₁ , λ ₁ is expressed by the following equation (1).

If the maximum height H at which the air hole plate 54 protrudes toward the combustion chamber is set to be smaller than the distance λ ₁ , the steady flame 45 does not approach the air hole plate 54 beyond the distance λ ₁ . That is, if the maximum height H that satisfies the following equation (2) and the air hole plate 54 protrudes toward the combustion chamber is taken, the effect of avoiding overheating of the air hole plate 54 can be maximized by this embodiment. .

  The second embodiment described above has several features. As described above, these features have specific effects according to individual configurations. Therefore, it is not essential to have all the features, and it may be a single feature or a combination of several features. In particular, the circulating gas push-back structure has three structures in the present embodiment, but may be a single or a combination of several features.

  According to the present embodiment, when a fuel with varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, it is reliable to avoid overheating of the structure without being affected by variations in the hydrogen concentration over a wide load range. It is possible to achieve a gas turbine combustor that maintains high combustion stability and can exhibit low NOx combustion performance.

  1: Combustion chamber, 2: Combustor outer cylinder, 3: Combustor liner, 4: Combustor tail cylinder, 5: Compressor, 6: Turbine, 7: Cabin, 8: Combustor end cover, 9: Gas turbine Combustor, 10: compressed air, 11: cooling air, 12: combustion air, 13: combustion gas, 14: fuel, 15: fuel for start-up, 16: coal, 17: oxygen, 18: coal gasification gas before purification , 19: Coal gasification gas before carbon dioxide recovery, 20: Water vapor, 21: High hydrogen concentration (after CO2 recovery) coal gasification gas, 22: Coal gasification fuel, 40: Associated flow, 41, 41-1, 41 -2: Main burner fuel, 42, 42-1, 42-2: Mixture, 43: Circulating gas, 44: Combustion gas, 45: Flame, 46: Swirling flow, 47: Circulating flow, 48: Backflow, 49 : Stagnation area, 50: Pilot burner, 51: Fuel injection nozzle for activation, 53 Main perforated coaxial jet burner, 54: Air hole plate, 55, 55-1, 55-2: Air hole, 56: Fuel nozzle, 57: Fuel distributor, 58: Cooling air hole at the center of the burner, 61, 61-1 61-2: Air hole inlet pitch circle diameter, 62, 62-1, 62-2: Air hole diameter, 63, 63-1, 63-2, 63-3: Air hole outlet pitch circle diameter, 64, 64 -1, 64-2, 64-3: Air hole burner axial length, 65: Air hole plate combustion chamber side surface normal (backward growth direction), 100: Fuel supply control device, 101: Fuel compressor, 102, 102a, 102b: hydrogen concentration detection means, 103: shut-off valve, 104a: start-up fuel shut-off valve, 104b: hydrogen-containing pilot fuel shut-off valve, 105a: start-up fuel pilot fuel pressure regulating valve, 105b: hydrogen-containing pilot fuel pressure Regulating valve 106a: Start-up fuel pilot fuel flow rate regulating valve 106b: Hydrogen-containing fuel pilot fuel flow rate regulating valve 107a: Inner circumferential main fuel pressure regulating valve 107b: Outer circumferential main fuel pressure regulating valve 108a: Inner circumferential Side main fuel flow rate adjusting valve, 108b: outer peripheral side main fuel flow rate adjusting valve, 109: check valve, 22a: fuel system, 120: coal gasification gas supply system before carbon dioxide recovery, 121: high hydrogen concentration coal gasification gas Supply system, 122a, 122b, 123a, 123b: Fuel supply system, 201: Oxygen production apparatus, 202: Coal gasification furnace, 203: Coal gasification gas purification apparatus, 204, 205: Flow control valve, 206: Shift reactor 207: carbon dioxide recovery device, 208: flow rate adjustment valve, 209: gas processing furnace, 501: generator.

Claims (8)

A combustion chamber supplied with fuel and air;
An air hole plate located upstream of the combustion chamber and having a plurality of air holes, and a plurality of fuel nozzles arranged coaxially with the air holes and supplying fuel containing hydrogen as a fuel composition to the air holes A gas turbine combustor comprising a multi-hole coaxial jet burner having a plurality of coaxial jet burners,
The porous coaxial jet burner has an inclination such that the combustion chamber side surface of the porous coaxial jet burner protrudes from the outer peripheral side toward the central portion toward the combustion chamber, and the central portion of the porous coaxial jet burner is the combustion chamber A gas turbine combustor characterized in that it is recessed with an inclination so as to move away from it. A combustion chamber supplied with fuel and air;
A plurality of air hole plates that are located upstream of the combustion chamber and have a plurality of air holes, and a plurality of fuel nozzles that are arranged coaxially with the air holes and supply fuel to the air holes. A gas turbine combustor comprising a multi-hole coaxial jet burner having a coaxial jet burner of
The porous coaxial jet burner has an inclination such that the combustion chamber side surface of the porous coaxial jet burner protrudes from the outer peripheral side toward the central portion toward the combustion chamber, and the central portion of the porous coaxial jet burner is the combustion chamber The circulation gas that is a part of the combustion gas that circulates toward the stagnation region that occurs in the vicinity of the central portion of the porous coaxial jet burner is kept away from the central portion of the porous coaxial jet burner. A gas turbine combustor having a structure for pushing back to the downstream side of the combustion chamber.   3. The gas turbine combustor according to claim 2, wherein the pushing-back structure is a cooling air hole that ejects only air to the combustion chamber side provided at a central portion of the porous coaxial jet burner. 4. Combustor.   3. The gas turbine combustor according to claim 2, wherein the structure for pushing back is provided so as to have an opening at a portion where the central portion of the porous coaxial jet burner is recessed with an inclination so as to move away from the combustion chamber. A gas turbine combustor which is the coaxial jet burner.   3. The gas turbine combustor according to claim 2, wherein the perforated coaxial jet burner is disposed on an inner peripheral side that is a central portion of the perforated coaxial jet burner, and includes a plurality of the coaxial jet burners. A plurality of coaxial jet burners and a second coaxial jet arranged on the outer peripheral side of the first coaxial jet burner, which is the outer periphery of the porous coaxial jet burner, each comprising a plurality of the coaxial jet burners A gas turbine combustor comprising: a burner portion, wherein the coaxial jet burner constituting the first coaxial jet burner portion is opened in a hollow portion at a central portion of the porous coaxial jet burner. 3. The gas turbine combustor according to claim 2, wherein the perforated coaxial jet burner is disposed on an inner peripheral side that is a central portion of the perforated coaxial jet burner, and includes a plurality of the coaxial jet burners. A plurality of coaxial jet burners and a second coaxial jet arranged on the outer peripheral side of the first coaxial jet burner, which is the outer periphery of the porous coaxial jet burner, each comprising a plurality of the coaxial jet burners With a burner section,
The pushing back structure inclines the central axis of the air holes constituting the first coaxial jet burner part in the direction of the outlet pitch circle in which the air holes constituting the first coaxial jet burner part are arranged, and the outlet A gas turbine combustor characterized in that the gas turbine combustor is inclined toward a center side of the porous coaxial jet burner from a tangential direction drawn on a pitch circle. 7. The gas turbine combustor according to claim 6, wherein an inlet pitch circle diameter of an air hole row of the first coaxial jet burner portion is D _I-1 , and an outlet pitch circle diameter of the air hole row is D _E-1. the tangent angle to the center axis is drawn in the air hole outlets located at the exit pitch circle of the air hole array of air holes constituting the first coaxial injection burner sections and beta _1, wherein the first coaxial injection burner the axial length of the air holes constituting the part and L _1, the height the air hole plate is protruding up into the combustion chamber side when the H,
A gas turbine combustor characterized in that the height H at which the air hole plate protrudes to the combustion chamber side is such that the relational expression shown in Expression (2) is satisfied.

  A coal gasification combined power plant configured to supply coal gasification gas to a gas turbine combustor as fuel for the gas turbine plant, wherein the gas turbine combustor is the gas turbine according to any one of claims 1 to 7. Coal gasification combined cycle plant using a combustor.

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