JP5993046B2 - Multi-fuel compatible gas turbine combustor - Google Patents

Description

  The present invention relates to a multi-fuel compatible gas turbine combustor capable of effectively utilizing a hydrogen-containing fuel while ensuring low emission performance.

  Gas turbine engine combustors are produced by mixing fuel and compressed air in addition to wet-type combustors that inject water or steam into the combustor as a technology for obtaining low emission performance including low NOx. There is known a dry type DLE (Dry Low Emissions) combustor in which the premixed gas is injected into a combustion chamber to perform lean premixed combustion. As fuel for this DLE combustor, hydrocarbon fuels such as natural gas, kerosene and light oil are used.

  By the way, in recent years, it is required to effectively use hydrogen gas generated from a chemical plant or the like as a fuel for a gas turbine combustor. As a gas turbine combustor using hydrogen gas as a fuel, a combustor as disclosed in Patent Document 1 is known.

JP 2011-75174 A

  Gases such as hydrogen have a higher combustion speed than hydrocarbon-based fuels. If a large amount of this gas is mixed with the fuel of the DLE combustor, the flame goes back to the relatively long premixing passage and is heated and damaged. This may cause a phenomenon called backfire. On the other hand, Patent Document 1 uses hydrogen gas as fuel while adopting diffusion combustion to reduce the risk of flashback. That is, Patent Document 1 is not a technique related to lean premixed combustion.

  An object of the present invention is to provide a multi-fuel compatible gas turbine combustor that burns a gas containing hydrogen at a high concentration with low NOx while maintaining good low emission performance by premixed combustion.

  To achieve the above object, a multi-fuel compatible gas turbine combustor according to the present invention supplies a premixed gas containing a first fuel to a first combustion region in a combustion chamber for combustion, and the combustion A reheating burner for supplying a premixed gas containing a second refueling fuel having a composition different from that of the first fuel to burn in a second combustion region downstream of the first combustion region in the room; The first fuel is a hydrocarbon-based gas, and the second fuel is a gas containing hydrogen at a concentration exceeding the stable combustion limit concentration of hydrogen. Here, the term “hydrocarbon-based” includes 60% by volume or more of hydrocarbons, and hydrogen gas refers to a gas having a concentration equal to or lower than the stable combustion limit concentration or a liquid containing 60% by volume or more of hydrocarbons. In addition, the stable combustion limit concentration of hydrogen means that when a premixed gas containing hydrogen is generated in a main burner having a flame holding mechanism and a swirler, backfire occurs and stable combustion is impaired or maintained. The upper limit hydrogen concentration (volume%) that becomes the boundary of. The stable combustion limit concentration of hydrogen is usually 8 to 15% by volume, and is about 10% by volume in this embodiment.

  In this gas turbine combustor, a hydrocarbon-based first fuel having a relatively low combustion speed is supplied to the main burner for supplying the premixed gas to the first combustion region for combustion, and thus backfire occurs. Therefore, good low emission performance can be maintained. On the other hand, when the operating range is expanded to the high output side in response to an increase in engine load, the premixed gas in which air is mixed with the second fuel is burned and supplied from the burner to the second combustion region for combustion. As a result of being able to burn the second fuel containing high-speed hydrogen gas at a low combustion temperature by introducing air, it is possible to burn hydrogen gas with a large amount of NOx generated with low NOx, that is, with low emissions. become. Note that the “different composition” mentioned here means that the main component or element content is different. In addition, since the combustion burner is operated in a state where combustion by the main burner is almost completed and high-temperature combustion gas is generated, the premixed gas injected from the combustion burner can be used without a flame holding mechanism. The combustion reaction is stably promoted by the high-temperature combustion gas. For this reason, there is no risk of flashback even when a gas containing hydrogen exceeding the stable combustion limit concentration is used as the second fuel.

  In the present invention, the reheating burner is preferably a premixing burner that premixes the first fuel and the second fuel with air and supplies them to the second combustion region. Thereby, when either one of the first fuel and the second fuel is insufficient, it can be coped with by mixing air with the fuel that is sufficient and supplying it to the second combustion region. For example, when the by-product hydrogen gas generated in the chemical plant is used as the second fuel, when the second fuel is insufficient due to the operation stop of the chemical plant, the first fuel is replenished and supplied from the burner to the second combustion region. Thus, the required high output operation can be maintained.

  In the present invention, when both the first and second fuels are supplied to the reheating burner, the reheating burner includes a premixing chamber for introducing air and a first fuel for injecting the first fuel into the premixing chamber. It is preferable to have one nozzle and a second nozzle that injects the second fuel into the premixing chamber. Thereby, in the premixing chamber, the first fuel injected from the first nozzle and the second fuel injected from the second nozzle are sufficiently mixed with the air introduced into the premixing chamber, so that a good mixture is obtained. And this premixed gas is supplied to the second combustion region.

  When both the first and second fuels are supplied to the reheating burner, the reheating burner supplies a mixing chamber into which the first fuel and the second fuel are introduced, and a mixed fuel from the mixing chamber. It is preferable to have a premixing chamber for premixing with air. Thus, after the first fuel and the second fuel are introduced into the mixing chamber and mixed in advance, the mixed fuel is guided to the premixing chamber and premixed with the air, so that the first fuel, the second fuel, and the air are mixed. It is possible to generate a premixed gas whose distribution is uniform throughout.

  When supplying both the first and second fuels to the refueling burner, the reheating burner preliminarily mixes the first fuel with air and injects the first fuel, and the second fuel as air and prefuel. It can also be set as the structure which has the 2nd burner which mixes and injects. Thereby, the structure of a 1st burner and a 2nd burner can be simplified.

  In the case where both the first and second fuels are supplied to the additional burner, a first fuel control valve is provided in a main fuel supply passage for supplying the first fuel to the main burner, and the additional fuel is supplied to the additional burner. The first additional fuel supply passage for supplying one fuel is preferably branched from the upstream side of the first fuel control valve in the main fuel supply passage. Thus, the required amount of the first fuel can always be stably supplied to the reheating burner regardless of the fluctuation of the pressure in the main fuel supply passage accompanying the adjustment of the first fuel control valve.

  In the present invention, a pilot burner that injects the first fuel into the first combustion region and diffuses and burns the pilot fuel is provided in a pilot fuel supply passage that supplies the first fuel to the pilot burner when the main burner is in operation. It is preferable to have a pilot sub-passage for introducing the second fuel. As a result, the second fuel containing hydrogen gas is also supplied to the diffusion combustion type pilot burner, so that the combustion in the pilot burner is stabilized by the hydrogen gas having a high combustion temperature.

  Any combination of at least two configurations disclosed in the claims and / or the specification and / or drawings is included in the present invention. In particular, any combination of two or more of each claim in the claims is included in the present invention.

The present invention will be understood more clearly from the following description of preferred embodiments with reference to the accompanying drawings. However, the embodiments and drawings are for illustration and description only and should not be used to define the scope of the present invention. The scope of the invention is defined by the appended claims. In the accompanying drawings, the same reference numerals in a plurality of drawings indicate the same or corresponding parts.
It is a schematic block diagram which shows the gas turbine engine to which the gas turbine combustor of this invention is applied. 1 is a schematic longitudinal sectional view showing a gas turbine combustor according to a first embodiment of the present invention including a fuel supply system thereof. FIG. 3 is an enlarged view of a part of FIG. 2. It is the III-III sectional view taken on the line of FIG. 3A. It is a characteristic view which shows the relationship between the load fluctuation | variation of a gas turbine engine same as the above, and the fuel usage-amount of the 2nd fuel corresponding to this. It is the schematic longitudinal cross-sectional view which showed the gas turbine combustor which concerns on 2nd Embodiment of this invention including this fuel supply system. It is the schematic longitudinal cross-sectional view which showed the gas turbine combustor which concerns on 3rd Embodiment of this invention including this fuel supply system. It is the schematic longitudinal cross-sectional view which showed the gas turbine combustor which concerns on 4th Embodiment of this invention including this fuel supply system.

  Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In the embodiment of the present invention, the gas turbine engine GT to which the gas turbine combustor is applied is a single can type as shown in FIG. 1, but may be a multi can type. The gas turbine engine GT includes a centrifugal compressor 1 that compresses air A taken in from an air inlet 1a, a combustor 2 that supplies fuel to the compressed air A and burns it, and combustion gas from the combustor 2 And a turbine 3 driven by The combustor 2 is disposed so as to protrude substantially in the radial direction with respect to the engine rotation axis C. Combustion gas generated in the combustor 2 is guided to the turbine 3 to rotate the turbine 3, and drives the centrifugal compressor 1 connected to the turbine 3 by the rotating shaft 4 and a load 7 that is a generator, for example. To do. The exhaust gas EG that has passed through the turbine 3 is discharged from the exhaust duct 8 to the outside.

  As shown in FIG. 2, the combustor 2 includes a reverse flow in which the compressed air A and the combustion gas G introduced into the air passage 22 from the centrifugal compressor 1 (FIG. 1) flow in opposite directions in the combustor 2. It is a can type, and a substantially cylindrical combustion cylinder 9 is accommodated in a cylindrical housing H in a concentric arrangement. An air passage 22 for introducing the air A from the centrifugal compressor 1 is formed between the housing H and the combustion cylinder 9, and a combustion chamber 10 is formed inside the combustion cylinder 9. A burner unit (nozzle unit) 11 is attached to the top of the combustion cylinder 9.

  The burner unit 11 uses a hydrocarbon-based fuel containing 60% by volume or more of hydrocarbons as the first fuel F1. This hydrocarbon fuel is natural gas here. The hydrocarbon fuel includes, in addition to natural gas, gas fuel such as natural gas mixed with about 5% hydrogen, or liquid fuel such as kerosene and light oil. The burner unit 11 includes a main burner 12 that injects and burns a premixed gas M1 containing a premixed first fuel F1 supplied from a first fuel supply source 18 into a first combustion region S1 in the combustion chamber 10; And a pilot burner 13 for directly injecting the first fuel F1 into the first combustion region S1 and diffusing and burning it.

  Further, in the combustion cylinder 9, the second fuel F2 and the first fuel for replenishment supplied from the second fuel supply source 19 to the second combustion region S2 downstream of the first combustion region S1 in the combustion chamber 10 are provided. A reheating burner 20 is provided that combusts both the first fuel F1 from the supply source 18 by premixing with the air A and injecting it. Each reheating burner 20 traverses the air passage 22 between the housing H and the combustion cylinder 9, and a plurality, for example, 2 to 12, are provided at equal intervals in the circumferential direction of the combustion cylinder 9. As the second fuel F2, a gas having a composition different from that of the first fuel F1 and containing hydrogen at a concentration exceeding the stable combustion limit concentration, for example, a concentration exceeding 10% by volume is used. The hydrogen concentration of the second fuel F2 is preferably 20% by volume or more, and more preferably 30% by volume or more. This hydrogen-containing gas is, for example, hydrogen gas alone (100% by volume) or a gas obtained by mixing hydrogen gas with an inert gas such as methane gas, propane gas, or nitrogen.

  The main burner 12 is disposed so as to surround the outer periphery of a cylindrical pilot burner 13. The main burner 12 has an annular outer wall 121 having an L-shaped cross section and an annular inner wall 122, and a premixing passage 14 is formed between the outer wall 121 and the inner wall 122. The upstream end of the premixing passage 14 opens outward in the radial direction, and a plurality of main fuel nozzles 17 are equidistantly spaced in the circumferential direction of the main burner 12 outward of the opened annular air inlet 14a. Is arranged in. A plurality of fuel injection holes (not shown) for injecting the first fuel F1 toward the air intake port 14a are formed in a portion of the main fuel nozzle 17 facing the air intake port 14a, and the air intake port 14a. Is provided with a swirler 25 that swirls the inflowing air to promote premixing with the first fuel F1. The diffusion combustion type pilot burner 13 is disposed in the inner space of the inner wall 122.

  As shown in FIG. 3A, the follow-up burner 20 is formed by connecting a fuel introduction block 20a and an air-fuel mixture injection cylinder 20b with a plurality of guide pieces 20c to each other, and is not shown in the housing H. The tip of the air-fuel mixture injection cylinder part 20 b is inserted through an insertion hole 41 provided in the combustion cylinder 9 and protrudes into the combustion chamber 10. An air inlet 43 provided with a guide piece 20c is formed between the collar 20ba of the air-fuel mixture injection cylinder 20b and the bottom wall 20n of the fuel introduction block 20a. The air inlet 43 communicates with the premixing chamber 21 formed by the inner peripheral surface of the air-fuel mixture injection cylinder portion 20b and the outer surface of the bottom wall 20n.

  The fuel introduction block 20 a includes a first fuel introduction passage 20 d for introducing the first fuel F 1 from the first fuel supply source 18 from the radially outer side of the combustor 2, and a second fuel from the second fuel supply source 19. A second fuel introduction passage 20e for introducing F2 from the radially outer side of the combustor 2, an annular first fuel chamber 20f for storing the first fuel F1 from the first fuel introduction passage 20d, and a second fuel introduction passage. A cylindrical second fuel chamber 20g for storing the second fuel F2 from 20e is provided. The fuel introduction block 20a further includes a first nozzle 20h comprising a plurality of small holes for injecting the first fuel F1 in the first fuel chamber 20f into the premixing chamber 21 on the bottom wall 20n, and a second fuel chamber 20g. A second nozzle 20i having a plurality of small holes for injecting the second fuel F2 into the premixing chamber 21;

  The guide piece 20c is arranged concentrically with the cylindrical air-fuel mixture injection cylinder portion 20b opposite to the fuel introduction block 20a, and in the vicinity of the outer peripheral edge of the fuel introduction block 20a in the circumferential direction as shown in FIG. 3B. A plurality (for example, 12) are provided at equal intervals. The first nozzle 20h of the fuel introduction block 20a is located slightly between the adjacent two guide pieces 20c and slightly closer to the axis C1 of the fuel introduction block 20a than the guide pieces 20c. Accordingly, the first fuel F1 shown in FIG. 3A is injected from the first nozzle 20h toward the air flow of the compressed air A flowing in from the air inlet 43. From the second nozzle 20i, the second fuel F2 is injected toward the central portion of the premixing chamber 21 in the direction of the axis C1. Thereby, the smooth mixing of the first fuel F1 and the second fuel F2 and the compressed air A is promoted. Since the compressed air A flowing in from the air inlet 43 is deflected by 90 ° after passing through the guide piece 20c, turbulent flow is generated, thereby promoting mixing with the first fuel F1 and the second fuel F2.

  Next, the operation will be described. The flow rate of the first fuel F1 supplied from the first fuel supply source 18 shown in FIG. 2 is adjusted by the first fuel control valve 23, and then from the main fuel nozzle 17 to the air intake port 14a of the premixing passage 14. It is injected towards. The injected first fuel F1 is introduced into the premixing passage 14 while being swirled by the swirler 25 together with the compressed air A flowing from the air passage 22 into the air intake port 14a. The gas is premixed while flowing, and is ejected from the annular premixed gas outlet 24 into the combustion chamber 10 as the premixed gas M1.

  When the gas turbine engine GT is started, the first fuel control valve 23 is closed, only the second fuel control valve 27 is opened, and the first fuel F1 of the first fuel supply source 18 turns the second fuel control valve 27 on. Then, the fuel is injected from the pilot burner 13 into the combustion chamber 10 and diffused and burned by ignition by a spark plug (not shown). During normal operation, while continuing the supply of the first fuel F1 from the pilot burner 13, the premixed gas M1 injected from the main burner 12 into the combustion chamber 10 is premixed and burned using the flame as a seed flame. In the upstream portion of the combustion chamber 10, a first combustion region S1 is formed. The main burner 12 and the pilot burner 13 are controlled so that the air-fuel ratio (air flow rate / fuel flow rate) becomes a preferable predetermined value.

  This first combustion region S1 is capable of reducing NOx, CO and the like by performing lean premix combustion of the first fuel F1, and a relatively low combustion speed hydrocarbon in the main burner 12 for premix combustion. Since the first fuel F1 of the system is supplied, good low emission performance can be maintained because no backfire occurs.

  A second combustion region S2 in which the premixed gas M2 injected from the reheating burner 20 is premixed and combusted is formed on the downstream side of the first combustion region S1 in the combustion chamber 10. The reheating burner 20 is supplied from the second fuel supply source 19 through the third fuel control valve 28, and from the first fuel supply source 18 through the fourth fuel control valve 29. Both of the one fuel F1 is premixed with the compressed air A to generate a premixed gas M2, which is supplied to the second combustion region S2.

  The second combustion region S2 is formed in order to expand the operating range to the high output side according to the fluctuation of the operating load of the gas turbine engine GT, and the increase in the operating load of the gas turbine engine GT is a constant value. 2, both the third fuel control valve 28 and the fourth fuel control valve 29 in FIG. 2 are adjusted so as to open by an opening corresponding to the fluctuation of the operating load, and the second fuel supply source 19 or the second fuel control valve 29 is adjusted. A required amount of the second fuel F <b> 2 and the first fuel F <b> 1 are supplied from the one fuel supply source 18 to the reheating burner 20. As is apparent from FIG. 4, the usage amount of the second fuel F2 also increases as the operating load of the engine GT increases, so that the hydrogen gas that is not sufficiently utilized at that time at the high load is removed from the combustor 2. It can be used in large quantities as the second fuel F2. In this case, the flame holding performance of the first combustion region S1 is ensured by the main burner 12 and the pilot burner 13 regardless of the amount of the second fuel F2 supplied in the second combustion region S2.

  In the reheating burner 20, the first fuel F1 and the second fuel F2 respectively stored in the first fuel chamber 20f and the second fuel chamber 20g are injected into the premixing chamber 21 from the first nozzle 20h and the second nozzle 20i. After being mixed, it is premixed with the compressed air A flowing into the premixing chamber 21 from the air passage 22 through the air inlet 43. Thereby, in the premixing chamber 21, the 1st fuel F1 and the 2nd fuel F2 are fully mixed with the compressed air A introduced from the air passage 22, and the favorable premixed gas M2 is produced | generated. The premixed gas M2 is supplied from the mixed gas injection cylinder portion 20b to the second combustion region S2 in the combustion cylinder 9 and premixed and combusted.

  Here, when only the second fuel F2 is supplied to the reheating burner 20, the second fuel F2 containing hydrogen gas having a high combustion speed can be burned at a low combustion temperature by introducing the compressed air A. Hydrogen gas with a large amount of NOx generated can be burned with low NOx. Further, the reheating burner 20 is operated in a state where combustion by the main burner 12 and the pilot burner 13 is almost completed and high-temperature combustion gas G is generated, and therefore, the premixed gas injected from the reheating burner 20 is used. In M2, the combustion reaction is stably promoted by the high-temperature combustion gas G without a flame holding mechanism. For this reason, there is no risk of backfire even when a fuel such as hydrogen is used as the second fuel F2.

  In this combustor 2, when the second fuel F2 is insufficient, it can be coped with by adding the first fuel F1. For example, when the by-product hydrogen gas generated in the chemical plant is used as the second fuel F2, the fourth fuel control valve 29 is opened to open the first fuel when the second fuel F2 is insufficient due to the operation stop of the chemical plant. The first fuel F1 of the supply source 18 can be supplied from the reheating burner 20 to the second combustion region S2, and the required high output operation can be maintained.

  By the way, it is known that backfire is generated from a relatively low-speed place such as a boundary layer of a burner wall surface or a backflow region. As is apparent from the above description, the reheating burner 20 does not require a flame holding mechanism and does not include a swirler or a flame holder that generates a reverse flow region, and therefore has extremely high resistance to back fire from the reverse flow region. . By reducing the fuel concentration in the vicinity of the boundary layer, that is, in the vicinity of the inner peripheral surface of the air-fuel mixture injection cylinder portion 20b, the reverse of the boundary layer generated in the vicinity of the inner peripheral surface is achieved by the arrangement of the fuel injection holes of the reheating burner 20. Resistance to fire can be increased. For this reason, in the reheating burner 20 of this embodiment, it is possible to use a relatively high concentration of hydrogen gas as fuel without backfire, while adopting a lean premixed combustion method. .

  FIG. 5 shows a second embodiment of the present invention. In this figure, the same or corresponding parts as those in FIG. The gas turbine combustor 2A of the second embodiment is different from the gas turbine combustor 2 of FIG. 2 only in the configuration of the reheating burner 20A. In other words, the reheating burner 20A directly introduces the mixed fuel into the mixing chamber 20j without storing the first fuel F1 from the first fuel introduction passage 20d and the second fuel F2 from the second fuel introduction passage 20e. Generate. The mixed fuel is injected from the mixing chamber 20j through the third nozzle 20k to the premixing chamber 21, and is premixed with the compressed air A flowing in from the air passage 22 to generate the premixed gas M2. Similar to the first embodiment, the premixing chamber 21 is formed between the inner surface of the air-fuel mixture injection cylinder portion 20b and the bottom wall 20n of the fuel introduction block 20a that are coupled to each other via a plurality of guide pieces 20c. ing.

  In the reheating burner 20 of the first embodiment, the first fuel F1 and the second fuel F2 are once stored in the first fuel chamber 20f and the second fuel chamber 20g, respectively, and then premixed in which the compressed air A is introduced. While the first fuel F1 and the second fuel F2 are injected into the chamber 21 to generate the premixed gas M2, in the second embodiment, the first fuel F1 and the second fuel F2 are fed into the mixing chamber 20j. After the introduction and generation of the mixed fuel in advance, the mixed fuel is injected into the premixing chamber 21 to generate the premixed gas M2. Therefore, as a result of promoting the mixing of the two fuels F1, F2, a more uniform premixed gas M2 is obtained.

  FIG. 6 shows a third embodiment of the present invention. In this figure, the same or corresponding parts as those in FIG. The gas turbine combustor 2B of the third embodiment is different from the gas turbine combustor 2 of FIG. 2 in that the reheating burner 20B of FIG. 6 is provided separately for the first fuel F1 and the second fuel F2. The first burner 201 and the second burner 202 are arranged in two stages. The first burner 201 introduces a fuel chamber 20m for introducing the first fuel F1 from a single first fuel introduction passage 20i, and introduces the first fuel F1 in the fuel chamber 20m from the third nozzle 20k to generate compressed air A and And a premixing chamber 21 for premixing.

  The second burner 202 has the same structure, and the second fuel F2 is introduced into the fuel chamber 20m from the second fuel introduction passage 20i. The first fuel F1 is supplied to the first burner 201 via the fourth fuel control valve 29, and the second fuel F2 is supplied to the second burner 202 via the third fuel control valve 28. The first additional fuel supply passage 31 for supplying the first fuel F1 is branched from the upstream side of the first fuel control valve 23 in the main fuel supply passage 30 provided with the first fuel control valve 23. Further, in the gas turbine combustor 2B, when the second fuel F2 is insufficient, the fifth fuel control valve 32 is opened, and the first fuel F1 of the first fuel supply source 18 is supplied to the second fuel through the check valve 33. The first fuel F 1 and the second fuel F 2 from the second fuel supply source 19 are mixed by the mixer 34 and supplied to the second burner 202.

  In the gas turbine combustor 2 </ b> B of this embodiment, since the first additional fuel supply passage 31 is connected to the main fuel supply passage 30 on the upstream side of the first fuel control valve 23, the adjustment of the first fuel control valve 23 is performed. Regardless of the fluctuation in the pressure of the main fuel supply passage 30 accompanying the above, the required amount of the first fuel F1 can always be stably supplied to the additional burner 20B.

  FIG. 7 shows a fourth embodiment of the present invention. In this figure, the same or corresponding parts as those in FIG. The gas turbine combustor 2C according to the fourth embodiment includes a plurality of reheating burners 20C in FIG. 7 having the same structure as the first burner 201 and the second burner 202 provided in the third embodiment in FIG. A pilot burner 13A that is provided and capable of supplying the second fuel F2 is provided. The second fuel F2 is introduced into the pilot fuel supply passage 37 for supplying the first fuel F1 to the pilot burner 13A through the second fuel control valve 27 and the check valve 38 through the sixth fuel control valve 39 when the main burner 12 is operated. The pilot sub passage 40 is connected. The check valve 38 allows only the flow of the first fuel F1 to the pilot burner 13A and the additional burner 20C. The gas turbine combustor 2C is provided with a fifth fuel control valve 32, a check valve 33, and a mixer 34 equivalent to those provided in the third embodiment (FIG. 6).

  In the gas turbine combustor 2C of this embodiment, in addition to the first fuel F1 being supplied through the second fuel control valve 27 and the check valve 38, the second fuel F2 containing hydrogen gas is the sixth fuel control. Since the fuel is supplied to the pilot burner 13A through the valve 39, the combustion in the pilot burner 13A is stabilized by the hydrogen gas having a high combustion temperature.

  As described above, the preferred embodiments have been described with reference to the drawings. However, those skilled in the art will readily understand various changes and modifications within the obvious scope by looking at the present specification. Accordingly, such changes and modifications are to be construed as within the scope of the invention as defined by the appended claims.

2, 2A, 2B, 2C Combustor 10 Combustion chamber 12 Main burner 13, 13A Pilot burner 14 Premixing passage 20, 20A, 20B Reheating burner 23 First fuel control valve 30 Main fuel supply passage 31 First additional fuel supply Passage 37 Pilot fuel supply passage 40 Pilot sub-passage S1 First combustion region S2 Second combustion region 201 First burner 202 Second burner M1, M2 Premixed gas

Claims (5)

A main burner for supplying a premixed gas containing the first fuel to the first combustion region in the combustion chamber and burning it;
A reheating burner for supplying and burning a premixed gas containing a second fuel having a composition different from that of the first fuel to a second combustion region downstream of the first combustion region in the combustion chamber;
The first fuel is hydrocarbon-based, and the second fuel is a gas containing hydrogen at a concentration exceeding the stable combustion limit concentration of hydrogen,
The reheating burner, said first fuel and the second fuel Ri Ah in premixed burner and supplying the mixed air and pre said second combustion zone,
The reheating burner is a gas turbine combustor having a mixing chamber into which the first fuel and the second fuel are introduced, and a premixing chamber in which the mixed fuel from the mixing chamber is premixed with air . 2. The gas turbine combustor according to claim 1, wherein the refueling burner includes a fuel introduction block in which the mixing chamber is formed, and a mixer-injected cylinder portion with a collar, which is an air inlet to the premixing chamber. Are coupled to each other through a plurality of guide pieces provided in the
The air inlet is formed between the collar of the mixer injection cylinder and the bottom wall of the fuel introduction block,
A gas turbine combustor in which the premixing chamber is formed by an inner peripheral surface of the mixer injection cylinder and an outer surface of the bottom wall, and the air inlet is in communication with the premixing chamber. A main burner for supplying a premixed gas containing the first fuel to the first combustion region in the combustion chamber and burning it;
A reheating burner for supplying and burning a premixed gas containing a second fuel having a composition different from that of the first fuel to a second combustion region downstream of the first combustion region in the combustion chamber;
The first fuel is hydrocarbon-based, and the second fuel is a gas containing hydrogen at a concentration exceeding the stable combustion limit concentration of hydrogen,
The reheating burner is a premixing burner that premixes the first fuel and the second fuel with air and supplies them to the second combustion region,
The reheating burner is a gas turbine combustor having a first burner that premixes and injects the first fuel with air, and a second burner that premixes and injects the second fuel with air.   The gas turbine combustor according to any one of claims 1 to 3, wherein a first fuel control valve is provided in a main fuel supply passage for supplying the first fuel to the main burner, and the refueling burner includes the first fuel control valve. A gas turbine combustor in which a first additional fuel supply passage for supplying a first fuel branches from an upstream side of the first fuel control valve in the main fuel supply passage. A main burner for supplying a premixed gas containing the first fuel to the first combustion region in the combustion chamber and burning it;
A reheating burner for supplying and burning a premixed gas containing a second fuel having a composition different from that of the first fuel to a second combustion region downstream of the first combustion region in the combustion chamber;
The first fuel is hydrocarbon-based, and the second fuel is a gas containing hydrogen at a concentration exceeding the stable combustion limit concentration of hydrogen,
The reheating burner is a premixing burner that premixes the first fuel and the second fuel with air and supplies them to the second combustion region,
A pilot burner that diffuses and burns the first fuel by injecting the first fuel into the first combustion region, and the second fuel is introduced into a pilot fuel supply passage that supplies the first fuel to the pilot burner when the main burner is operated A gas turbine combustor having a pilot sub-passage.

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