JP5159741B2 - Control device for gas turbine combustor and control method for gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a control device for a gas turbine combustor, which avoids a problem in the reliability of the gas turbine combustor caused by a variation in the concentration of hydrogen in fuel and also maintains low NOx combustion performance. <P>SOLUTION: A burner provided to the gas turbine combustor includes a pilot burner performing diffusion combustion bearing flame stabilizing of the whole combustor and a plurality of the main burner provided on the peripheral side of the pilot burner and performing premixed combustion for performing low NOx combustion. A pilot fuel supply system supplying fuel to the pilot burner and the main fuel supply system supplying fuel to the main burners are provided. At least the main fuel system supplying fuel to the main burners is provided with a hydrogen concentration detector detecting the concentration of hydrogen contained in fuel. A controller is installed for controlling the distribution of the flow rate of fuel supplied to the pilot burner through the pilot fuel supply system and the flow rate of fuel supplied to the main burners through the main fuel supply system, based on the detected concentration of hydrogen. <P>COPYRIGHT: (C)2011,JPO&amp;INPIT

Description

  The present invention relates to fuel flow control of a gas turbine combustor installed in a gas turbine plant, and more particularly to a control device for a premixed combustion type gas turbine combustor operated by a fuel containing hydrogen in the fuel composition, and the gas turbine combustor. Relates to the control method.

In recent years, from the viewpoint of reducing power generation costs and effective use of resources, as well as preventing global warming, off-gas generated at petroleum refineries and coke oven gas (COG) generated by iron-making processes (COG) are abbreviated. The by-product gas containing hydrogen (H ₂ ) is required to be effectively used as a fuel for a gas turbine combustor used in a power generation gas turbine.

  In addition, a coal gasification power plant (IGCC: Integrated coal Gasification Combined Cycle, hereinafter abbreviated as IGCC) that generates electricity by gasifying abundant resources of coal with oxygen is used from the viewpoint of preventing global warming. A system for separating and recovering carbon content in fuel supplied to gas turbines in Japan is being studied both at home and abroad. In addition, from the viewpoint of global environmental protection, there is a strong demand for improving the power generation efficiency of coal gasification power plants and reducing pollutant emissions.

  In these gas turbine power plants, 30% to 60% of the fuel components are produced by refinery off-gas and COG, and in the IGCC plant with carbon dioxide separation and recovery, most of the fuel components are hydrogen. Since hydrogen has a high burning rate, the flame may approach the combustor structure in the gas turbine combustor and cause reliability problems.

  In addition to refinery off-gas and COG, the IGCC plant also has a large change in hydrogen concentration due to changes in the carbon dioxide recovery rate. Therefore, the combustion speed increases depending on the situation, and the flame approaches the gas turbine structure. Measures to cope with causing this problem are required.

  Among the above problems, as an example of a technique for coping with a change in the hydrogen concentration, Japanese Patent Application Laid-Open No. 2007-113487 discloses a hydrogen gas that contains hydrogen in the fuel composition. A technique for maintaining a stable combustion in a combustor by avoiding misfire of a gas turbine by supplying a necessary amount of gas to a fuel gas is disclosed.

JP 2007-113487 A

  However, the technique disclosed in Japanese Patent Application Laid-Open No. 2007-113487 maintains a necessary minimum output when the gas turbine load suddenly drops, and is a technique for dealing with fluctuations in hydrogen concentration over a wide load range. Is not disclosed.

  Since hydrogen has a high burning rate, it is likely to cause reliability problems when the flame formed in the gas turbine combustor approaches the combustor structure.

  Even if the gas turbine combustor is designed so that the flame does not approach the structure of the gas turbine combustor, not only the refinery off-gas and COG, but also the IGCC plant changes the carbon dioxide recovery rate. Therefore, it is required to cope with the approach of the flame to the structure of the gas turbine combustor according to the change state of the hydrogen concentration.

  As a combustion method to ensure the reliability of the gas turbine combustor against changes in the hydrogen concentration contained in the fuel gas, 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. However, in this combustion method, a flame is formed with respect to the air-fuel mixture that is most combustible, so that the flame temperature becomes high and the amount of nitrogen oxide (NOx) emission tends to increase.

  From the viewpoint of protecting the global environment, in addition to reducing carbon dioxide, it is also important to reduce NOx, which is the main cause of acid rain and photochemical smog, and it is a gas that responds to a wide range of hydrogen concentration fluctuations and performs low NOx combustion. A combustion method for a turbine combustor is required.

  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 becomes leaner than the stoichiometric mixture ratio and supplied to the gas turbine combustor is effective. In this method, since the air-fuel mixture in the combustible range is formed before flowing into the combustion chamber of the gas turbine combustor, the position of the flame formed in the combustion chamber changes when the hydrogen concentration contained in the fuel gas changes. This approach increases the potential for gas turbine combustor reliability problems.

  The object of the present invention is to use a gas turbine combustor in which the hydrogen concentration in the fuel varies, and the flame formed due to the variation in the hydrogen concentration approaches the structure of the gas turbine combustor. It is an object of the present invention to provide a premixed combustion type gas turbine combustor control device and a gas turbine combustor control method capable of avoiding causing reliability problems and maintaining low NOx combustion performance.

A control device for a gas turbine combustor according to the present invention is a control device for a gas turbine combustor comprising a burner that burns a fuel containing hydrogen in a fuel composition and a starting fuel that does not contain hydrogen in the fuel composition. The burner provided in the combustor is a pilot burner that performs diffusion combustion for holding the flame of the entire gas turbine combustor, and a main burner that is installed on the outer peripheral side of the pilot burner and performs premixed combustion that performs low NOx combustion A fuel system for supplying fuel to the burner of the gas turbine combustor, a pilot fuel supply system for supplying startup fuel that does not contain hydrogen to the pilot burner, and hydrogen for the fuel composition to the main burner A main fuel supply system for supplying the fuel containing the fuel, and the main burner is connected to a plurality of fuel nozzles and the fuel nozzles. A plurality of air holes formed in the air plate are coaxially configured to configure a coaxial nozzle burner disposed on the inner peripheral side and the outer peripheral side of the main burner, and the main fuel supply system includes the An inner peripheral main fuel supply system for supplying fuel to the coaxial nozzle burner on the inner peripheral side of the main burner, and an outer peripheral main fuel supply system for supplying fuel to the coaxial nozzle burner on the outer peripheral side of the main burner, A hydrogen concentration detector for detecting the hydrogen concentration contained in the fuel is provided in the main fuel system, and the main burner is connected to the main burner through the outer main fuel supply system based on the value of the hydrogen concentration contained in the fuel detected by the hydrogen concentration detector. The flow rate of fuel supplied to the coaxial nozzle burner on the outer peripheral side and the coaxial nozzle burner on the inner peripheral side of the main burner through the inner peripheral main fuel supply system Characterized in that installed a control device for controlling the distribution of the flow rate of the fuel supplied.

The control device for the gas turbine combustor of the present invention includes a coal gasification furnace that generates coal gas from coal, a shift reactor that generates carbon dioxide and hydrogen from the coal gas generated in the coal gasification furnace, and a coal gas An IGCC plant with carbon dioxide recovery comprising a gas turbine having a gas turbine combustor that combusts coal gasified fuel containing coal gas produced in a chemical reactor and hydrogen produced in a shift reactor, In a control apparatus for a gas turbine combustor comprising a fuel containing hydrogen and a burner that burns a starting fuel that does not contain hydrogen in the fuel composition, the burner provided in the gas turbine combustor is used for flame holding of the entire gas turbine combustor. A pilot burner that performs diffusion combustion, and a main burner that is installed on the outer peripheral side of the pilot burner and performs premixed combustion that performs low NOx combustion And a fuel system that supplies fuel to the pilot burner as a fuel system that supplies fuel to the burner of the gas turbine combustor, and a fuel that contains hydrogen in the fuel composition in the main burner. The main burner has a plurality of fuel nozzles and a plurality of air holes formed in an air plate corresponding to the fuel nozzles, and the main burner is configured to be coaxial. A coaxial nozzle burner arranged on the inner peripheral side and the outer peripheral side of the main fuel supply system, the main fuel supply system is an inner peripheral main fuel supply system for supplying fuel to the coaxial nozzle burner on the inner peripheral side of the main burner, An outer peripheral main fuel supply system that supplies fuel to a coaxial nozzle burner on the outer peripheral side of the main burner, and the main fuel system The hydrogen concentration detector for detecting the concentration of hydrogen contained in the fuel is provided, wherein the hydrogen concentration detector in the outer circumferential side of the main burner through the outer peripheral side main fuel supply system based on the value of the hydrogen concentration in the fuel detected coaxial A control device is provided for controlling distribution of the flow rate of fuel supplied to the nozzle burner and the flow rate of fuel supplied to the coaxial nozzle burner on the inner peripheral side of the main burner through the inner peripheral side main fuel supply system. And

In the gas turbine combustor control method according to the present invention, a plurality of burners provided in the gas turbine combustor are installed on the outer peripheral side of the pilot burner that performs diffusion combustion for holding the flame of the entire gas turbine combustor. And a main burner that performs premixed combustion that performs low NOx combustion, and in the method for controlling a gas turbine combustor that burns fuel containing hydrogen in the fuel composition by the burner, the burner provided in the gas turbine combustor Is composed of a pilot burner that performs diffusion combustion that bears flame holding of the entire gas turbine combustor, and a main burner that performs premixed combustion that performs low-NOx combustion by installing a plurality of pilot burners on the outer peripheral side of the pilot burner, As a fuel system for supplying fuel to the burner of the gas turbine combustor, the pilot burner is supplied with startup fuel that does not contain hydrogen in the fuel composition. A pilot fuel supply system and a main fuel supply system for supplying fuel containing hydrogen in the fuel composition to the main burner, and the main burner is formed in an air plate corresponding to the plurality of fuel nozzles and the fuel nozzles A plurality of air holes formed coaxially and configured by a coaxial nozzle burner disposed on an inner peripheral side and an outer peripheral side of the main burner, and the inner peripheral side of the main burner as the main fuel supply system An inner peripheral main fuel supply system for supplying fuel to the coaxial nozzle burner, and an outer peripheral main fuel supply system for supplying fuel to the coaxial nozzle burner on the outer peripheral side of the main burner. detecting a concentration of hydrogen contained in the fuel by providing the hydrogen concentration detector, concentrated hydrogen contained in the fuel detected by the hydrogen concentration detector The flow rate of fuel supplied to the coaxial nozzle burner on the outer peripheral side of the main burner through the outer peripheral side main fuel supply system based on the value of, and the coaxial nozzle burner on the inner peripheral side of the main burner through the inner peripheral side main fuel supply system A control device for controlling distribution with the flow rate of the supplied fuel is provided.

  According to the present invention, when a fuel with varying hydrogen concentration contained in fuel is used in a gas turbine combustor, the flame formed due to the variation in hydrogen concentration approaches the structure of the gas turbine combustor. Thus, it is possible to realize a premixed combustion type gas turbine combustor control device and a gas turbine combustor control method capable of avoiding a problem in reliability and maintaining low NOx combustion performance.

BRIEF DESCRIPTION OF THE DRAWINGS The schematic block diagram of the gas turbine power plant to which the control apparatus of the gas turbine combustor which is 1st Example of this invention is applied. The detailed block diagram of the control apparatus of the gas turbine combustor which is 1st Example shown in FIG. FIG. 3 is a control characteristic diagram showing a change in fuel flow rate with respect to a gas turbine operating rotational speed and a gas turbine load when controlled by the control device for the gas turbine combustor according to the first embodiment shown in FIG. 2. The characteristic view which shows the condition of the change of distribution of the fuel supply quantity with respect to the change of the hydrogen concentration in the rated load at the time of controlling by the control apparatus of the gas turbine combustor which is 1st Example shown in FIG. The schematic block diagram of the gas turbine power plant to which the control apparatus of the gas turbine combustor which is 2nd Example of this invention is applied. The detailed block diagram of the control apparatus of the gas turbine combustor which is 2nd Example shown in FIG. The schematic block diagram of the gas turbine power plant to which the control apparatus of the gas turbine combustor which is 3rd Example of this invention is applied. The detailed block diagram of the control apparatus of the gas turbine combustor which is 3rd Example shown in FIG. The characteristic view which shows the condition of the change of the fuel distribution of the outer periphery of a main burner with respect to the change of the hydrogen concentration in the rated load at the time of controlling by the control apparatus of the gas turbine combustor which is 3rd Example shown in FIG. The schematic block diagram of the IGCC plant with a carbon dioxide recovery to which the control apparatus of the gas turbine combustor which is 4th Example of this invention is applied. The detailed block diagram of the control apparatus of the gas turbine combustor which is the 4th Example shown in FIG.

  A gas turbine combustor control apparatus and a gas turbine combustor control method according to an embodiment of the present invention will be described below with reference to the drawings.

  A gas turbine combustor control apparatus and a gas turbine combustor control method according to a first embodiment of the present invention will be described with reference to FIGS. 1, 2, and 3. FIG. 1 is a schematic diagram showing the configuration of a gas turbine power plant to which a control device for a gas turbine combustor according to a first embodiment of the present invention is applied.

  In FIG. 1, a gas turbine power plant takes in and compresses outside air by a compressor 5 and introduces compressed air 10 compressed by the compressor 5 to a casing 7 of the gas turbine to be used as combustion air 12 in a gas turbine combustor 1a. The high-temperature and high-pressure combustion gas 13 generated by burning the fuel 14 and the combustion air 12 supplied from the outside by the gas turbine combustor 1a is caused to flow into the turbine 6 to extract the rotational power, thereby generating power. The machine 30 is driven to generate electricity.

  In the gas turbine combustor 1 a, a combustor liner 3 that forms a combustion chamber 1 is installed inside a combustor outer cylinder 2, and fuel 14 and combustion air 12 are fed into the combustor liner 3. It has a cylindrical structure that is combusted in the combustion chamber 1 to form a high-temperature and high-pressure combustion gas 13.

  The combustor liner 3 of the gas turbine combustor 1a is in contact with the turbine 6 by a combustor tail cylinder 4 installed to smoothly connect a cylindrical combustor outlet and a stationary blade inlet shape of the turbine 6. .

  Combustion air 12 used for combustion of the gas turbine combustor 1a is supplied through an annular space formed between the combustor outer cylinder 2 and the combustor liner 3, and the combustion air 12 of the gas turbine combustor 1a is supplied. It is dammed by the combustor end cover 8 provided at the tip of the head, and flows into the pilot burner and the main burner 23 from the combustion air holes opened in the outer periphery of the combustor liner 3.

  The fuel 14 containing hydrogen used for combustion in the gas turbine combustor 1a is distributed from the outside of the combustor end cover 8 to the pilot burner 22 and the main burner 23 through a distribution channel provided inside the end cover 8.

  In the gas turbine combustor 1a shown in the present embodiment, a pilot burner 22 adopting a diffusion combustion method is installed in the center, and a plurality of main burners 23 adopting a premix combustion method are arranged on the outer peripheral side of the pilot burner 22. It has a structure.

  The fuel 14 containing hydrogen is pressurized to a pressure higher than the combustor pressure by the fuel compressor 101 and supplied to the fuel supply system 14 a provided with the shut-off valve 103.

  The hydrogen concentration of the fuel 14 containing hydrogen is detected by the hydrogen concentration detecting means 102 provided in the fuel supply system 14a that supplies the fuel 14 pressurized by the fuel compressor 101, and the detected hydrogen concentration detection value of the fuel 14 is detected. Is input to the fuel supply control device 100 that controls the combustion of the gas turbine combustor 1a.

  The fuel supply system 14a is divided into a pilot fuel supply system 122 for supplying fuel to the pilot burner 22 adopting the diffusion combustion method and a main fuel supply system 123 for supplying fuel to the main burner 23 adopting the premixed combustion method. Then, the fuel 14 containing hydrogen is supplied.

  The pilot fuel supply system 122 is provided with a pilot fuel pressure adjustment valve 105 and a pilot fuel flow rate adjustment valve 106 located downstream thereof.

  Similarly, the main fuel supply system 123 is provided with a main fuel supply pressure adjusting valve 107 and a main fuel flow rate adjusting valve 108 located downstream thereof.

  In order to control the combustion of the gas turbine combustor 1a by the control device 100, based on a command signal (details will be described later) calculated by the control device 100, a pilot fuel pressure adjustment valve 105 and a pilot fuel flow rate adjustment valve The amount of fuel supplied to the pilot burner 22 through the pilot fuel supply system 122 is controlled by adjusting the opening of the fuel 106, and the amounts of the main fuel pressure adjusting valve 107 and the main fuel flow adjusting valve 108 are adjusted to adjust the main fuel. The flow rate of the fuel supplied to the main burner 23 through the supply system 123 is controlled.

  In the gas turbine combustor 1a of the present embodiment, the shutoff valve 103 is independently installed in the fuel supply system 14a in order to ensure the emergency shutoff response of the fuel 14, but in order to simplify the fuel supply system, the fuel shutoff is performed. The function of the valve 103 may be provided to the pilot fuel pressure adjustment valve 105 and the main fuel pressure adjustment valve 107.

  FIG. 2 is a block diagram showing details of a control device for controlling the combustion of the gas turbine combustor provided in the gas turbine power plant according to the first embodiment shown in FIG.

  The control device 100 for controlling the combustion of the gas turbine combustor 1a shown in FIG. 2 is provided with a reference fuel flow rate calculator 305. The reference fuel flow rate calculator 305 uses the operation command signal 301 and the rotational speed of the gas turbine. A fuel flow command value is calculated from a state relative to a target operating state determined with reference to the signal 302, and the pilot fuel pressure adjusting valve 105 and the pilot are calculated based on the fuel flow command value calculated by the reference fuel flow rate calculator 305. The flow rate of the fuel supplied to the pilot burner 22 and the main burner 23 of the gas turbine combustor 1a by adjusting the opening of the fuel flow rate adjusting valve 106, the main fuel pressure adjusting valve 107 and the main fuel flow rate adjusting valve 108, respectively. Controlling the combustion of the gas turbine combustor 1a of the gas turbine power plant by adjusting Gas turbine speed and the power load is operated to control the desired state Te.

  More specifically, one of the reference gas turbine input fuel signal 306 calculated and output by the reference fuel flow rate calculator 305 provided in the control device 100 based on the operation command signal 301 and the gas turbine speed signal 302 is: The pilot fuel supply signal 315 is input to a pilot fuel limiter 314 that constitutes a calculation system for calculating, and the pilot fuel supply signal 315 calculated by the pilot fuel limiter 314 is output, and the main fuel supply The main fuel supply signal 325 calculated by the main fuel limiter 321 is input to the reference main fuel flow rate calculator 307 and the main fuel limiter 321 constituting the calculation system for calculating the signal 325. .

  In order to calculate the pilot fuel supply signal 315, the hydrogen concentration signal 304 detected by the hydrogen concentration detector 102 provided in the fuel supply system 14a shown in FIG. The reference gas turbine input fuel signal correction value 309 calculated by the bias calculator 308 and the reference gas turbine input fuel signal 306 calculated by the reference fuel flow rate calculator 305 are added by the adder 310 to be included in the fuel 14. Then, a gas turbine input fuel signal 311 is calculated in which the variation in the fuel heat generation amount accompanying the change in the hydrogen concentration is corrected.

  The subtractor 312 further subtracts the main fuel supply signal 325 calculated by the reference main fuel flow rate calculator 307 and the main fuel limiter 321 from the gas turbine input fuel signal 311 added by the adder 310 to supply pilot fuel. The pilot fuel supply source signal 313 is input to a pilot fuel limiter 314 installed in the control device 100, and the pilot fuel supply signal 315 is calculated by the operation of the pilot fuel limiter 314. The pilot fuel limiter 314 performs a correction operation so that the pilot fuel supply signal becomes a value between the upper limit and the lower limit of the pilot fuel supply signal determined by the hydrogen concentration of the fuel 14, and the pilot fuel supply signal 315 is output from the pilot fuel limiter 314. It is configured to do.

  Then, based on the calculated pilot fuel supply signal 315, a command signal is transmitted from the control device 100 to the pilot fuel pressure adjustment valve 105 and the pilot fuel flow rate adjustment valve 106 installed in the pilot fuel supply system 122, and these pilot fuel pressures are transmitted. The flow rate of fuel supplied to the pilot burner 22 through the pilot fuel supply system 122 is controlled by adjusting the opening degrees of the adjustment valve 105 and the pilot fuel flow rate adjustment valve 106.

  The hydrogen concentration bias 329 with respect to the pilot fuel limiter 314 is configured to be calculated by a pilot fuel limit correction value calculator 328 installed in the control device 100 with the hydrogen concentration signal 304 as an input and input to the pilot fuel limiter 314. Yes.

  On the other hand, the other of the reference gas turbine input fuel signal 306 calculated and output by the reference fuel flow rate calculator 305 provided in the control device 100 is the reference main fuel flow rate installed to calculate the main fuel supply signal 325. The reference main fuel flow rate calculator 307 calculates the reference main fuel flow rate 316 based on the reference gas turbine input fuel signal 306.

  Further, the hydrogen concentration signal 304 obtained by detecting the hydrogen concentration in the fuel 14 by the hydrogen concentration detector 102 is input, the main fuel flow rate correction value 318 calculated by the main fuel hydrogen concentration bias calculator 317, and the reference main fuel flow rate 316. Are added by the adder 319 to calculate the main fuel source flow rate 320 in which the variation in the fuel heat generation amount accompanying the change in the hydrogen concentration is corrected.

  In the main burner 23 adopting the premixed combustion method, the fuel 14 and the combustion air 12 are mixed in advance and then supplied to the gas turbine combustion chamber 1 of the gas turbine combustor 1a. There is an upper limit value and a lower limit value in the flow rate, and the range is narrower than that of the pilot burner 22 adopting diffusion combustion.

  Since the range in which this stable combustion state is obtained changes depending on the hydrogen concentration contained in the fuel 14, the main fuel flow rate calculated based on the main fuel supply source flow rate 320 by the main fuel limiter 321 installed in the control device 100. Is input to the high concentration hydrogen concentration signal 304 detected by the hydrogen concentration detector 102 so that the fuel flow rate is within the above stable range, and burned by the main fuel stable range calculator 326 installed in the control device 100. The main fuel stable range bias 327 obtained by calculating the stable range is input to the main fuel limiter 321 and the corrected main fuel flow rate signal 322 is calculated.

  Since the range in which the main burner 23 of the gas turbine combustor 1a can be stably operated is narrow as described above, the comparator 323 installed in the control device 100 with reference to the gas turbine operation plan and the gas turbine operation rotational speed 302 is used. It is determined whether or not the main burner 23 can be operated. If the main burner 23 is operable, the main fuel flow rate signal 322 is switched by the signal switch 324 and the main fuel supply signal 325 is switched from the control device 100. Output as command signal.

  The fuel supplied to the main burner 23 through the main fuel supply system 123 by adjusting the opening of the main fuel pressure adjusting valve 107 and the main fuel flow rate adjusting valve 108 of the gas turbine combustor 1 a based on the main fuel supply signal 325. Control the flow rate.

FIG. 3 is a control characteristic diagram showing changes in the fuel flow rate with respect to the gas turbine operating rotational speed and the gas turbine load when controlled by the control device of the gas turbine combustor according to the first embodiment shown in FIG. ing. From the characteristic diagram of FIG. 3, the main burner 23 of the gas turbine combustor 1a employing the premixed combustion method as described above has a narrower range that can be stably operated than the pilot burner 22 employing the diffusion combustion method. fuel flow rate of the fuel 14 supplied to the gas turbine combustor 1a activates the gas turbine combustor 1a rotational speed of the gas turbine with speed increasing up to the rated pilot burner 22 alone until it reaches a predetermined flow rate value Gf _SW .

Then, the operation of the gas turbine combustor 1a up to the rated load after the fuel flow rate of the supplied fuel 14 increases from the flow rate value Gf _SW is applied to the main burner 23 with a small NOx emission amount employing the premixed combustion method. The fuel supply Gf _M occupies most, and the pilot burner 22 is configured to supply the minimum fuel flow rate Gf _P necessary for flame holding.

  FIG. 4 is a characteristic diagram showing a change in the distribution of the fuel supply amount with respect to the change in the hydrogen concentration at the rated load when controlled by the control device 100 for the gas turbine combustor according to the first embodiment shown in FIG. .

  4 is the hydrogen concentration contained in the fuel 14, and the vertical axis is supplied to the pilot burner 22 out of the fuel 14 supplied to the entire pilot burner 22 and main burner 23 of the gas turbine combustor 1a. The ratio of the fuel to be used is shown as the pilot fuel ratio.

  In the characteristic diagram of FIG. 4, when the hydrogen concentration contained in the fuel 14 is low, the combustion speed is slow, and the position of the flame formed in the gas turbine combustion chamber 1 of the gas turbine combustor 1 a is in the gas turbine combustion chamber 1. If the flame is not held stronger, the flame will blow out and problems such as generating a large amount of unburned emissions may occur.

  For this reason, when the hydrogen concentration contained in the fuel 14 is low, a bias is applied so that more fuel is supplied to the pilot burner 22 adopting the diffusion combustion method, and as a result, the pilot fuel ratio increases to PM_a.

  However, in this case, the concentration of hydrogen contained in the fuel 14 is low, so that not only the NOx emission amount in the main burner 23 adopting the premixed combustion method is small, but also the diffusion burnup type pilot burner 22 causes the concentration of flame. Since the degree decreases, the NOx emission amount does not increase greatly.

  As the concentration of hydrogen contained in the fuel 14 increases, the combustion speed increases, so the position of the flame formed in the gas turbine combustion chamber 1 gradually moves to the upstream side in the gas turbine combustion chamber 1, so that it can be blown out. The sex becomes smaller.

  Therefore, more fuel is supplied to the main burner 23 adopting the premixed combustion method, and the fuel supply is reduced to the pilot burner 22 adopting the diffusion combustion method. The fuel flow rate for flame holding can be reduced to PM_b, and the amount of fuel burned in the diffusion combustion type pilot burner 22 under the condition that the combustion is the easiest is reduced, so that the NOx emission is further reduced.

  When the hydrogen concentration signal 304 in the fuel 14 detected by the hydrogen concentration detector 102 decreases, the reference gas turbine input fuel signal correction value 309 is calculated by the input fuel hydrogen concentration bias calculator 308 provided in the control device 100. Then, the reference gas turbine input fuel signal correction value 309 is added by the adder 310 to the reference gas turbine input fuel signal 306 calculated by the reference fuel flow rate calculator 305, so that the hydrogen concentration contained in the fuel 14 is increased. The gas turbine input fuel signal 311 is calculated by correcting the fluctuation of the fuel heat generation amount accompanying the decrease in the fuel gas.

  The corrected gas turbine input fuel signal 311 is subtracted by the subtractor 312 from the main fuel supply signal 325 calculated by the reference main fuel flow rate calculator 307 and the main fuel limiter 321 and converted into a pilot fuel supply source signal 313, This pilot fuel supply source signal 313 is input to the pilot fuel limiter 314, and the pilot fuel supply signal 315 is determined by the operation of the pilot fuel limiter 314 and the pilot fuel supply signal determined by the operating state of the gas turbine and the hydrogen concentration of the fuel 14 The pilot fuel limiter 314 performs a correction operation so that the value is between the upper limit and the lower limit, and a pilot fuel supply signal 315 is output from the pilot fuel limiter 314.

  When the hydrogen concentration signal 304 in the fuel 14 detected by the hydrogen concentration detector 102 increases, the main fuel hydrogen concentration bias calculator 317 provided in the control device 100 calculates the main fuel flow rate correction value 318, An adder 319 adds the main fuel flow rate correction value 318 to the reference main fuel flow rate 316 calculated by the reference main fuel flow rate calculator 307 based on the reference gas turbine input fuel signal 306 to reduce the hydrogen concentration. A main fuel source flow rate 320 is calculated by correcting the accompanying fuel heat generation amount fluctuation.

  Next, the main fuel stable range bias obtained by calculating the stable range of combustion by the main fuel stable range calculator 326 so that the main fuel original flow rate 320 becomes the fuel flow rate within the above stable range by the main fuel limiter 321. 327 is input to calculate the corrected main fuel flow rate signal 322, and the comparator 323 calculates the main fuel flow rate signal 322 via the signal switch 324 based on the determination of whether or not the main burner 23 can be operated. As 325, it outputs from the said control apparatus 100 as a command signal.

  That is, when the hydrogen concentration signal 304 in the fuel 14 is decreased by the control as described above, the input fuel hydrogen is compared with the reference gas turbine input fuel signal 306 calculated by the reference fuel flow rate calculator 305. A gas turbine input fuel signal 311 obtained by adding the reference gas turbine input fuel signal correction value 309 calculated by the concentration bias calculator 308 is obtained, and the pilot fuel supplied to the pilot burner 22 via the pilot fuel supply source signal 313 is obtained. The pilot fuel supply signal 315 is a command, and the pilot fuel supply signal 315 is increased.

  Further, the main fuel flow rate correction value 318 calculated by the main fuel hydrogen concentration bias calculator 317 is added to the reference main fuel flow rate 316 calculated by the reference main fuel flow rate calculator 307 based on the reference gas turbine input fuel signal 306. Thus, a main fuel source flow rate 320 is obtained, which becomes a main fuel supply signal 325 that serves as a command for the main fuel supplied to the main burner 23, and acts to decrease the main fuel supply signal 325.

  As a result, the fuel ratio of the pilot fuel supply signal 315 to the main fuel supply signal 325 increases, so that the combustion of the gas turbine combustor can be controlled within the stable combustion range even when the hydrogen concentration in the fuel decreases. Thus, stable combustion of the gas turbine combustor can be realized.

  On the other hand, when the hydrogen concentration signal 304 in the fuel 14 detected by the hydrogen concentration detector 102 increases, the main fuel stable range calculator 326 provided in the control device 100 calculates the stable combustion range. A fuel stable range bias 327 is calculated, and the main fuel stable range bias 327 is input to the main fuel limiter 321 to obtain a corrected main fuel flow rate signal 322.

  The main fuel flow rate signal 322 is output as a main fuel supply signal 325 via a signal switch 324, and the main fuel supply system 123 is based on the main fuel supply signal 325 output from the signal switch 324 of the control device 100. The flow rate of the fuel supplied to the main burner 23 through the main fuel supply system 123 is controlled by adjusting the opening degree of the main fuel pressure adjustment valve 107 and the main fuel flow rate adjustment valve 108 installed in the main fuel supply system 123.

  Further, when the hydrogen concentration signal 304 in the fuel 14 detected by the hydrogen concentration detector 102 increases, the pilot fuel limiter hydrogen that adjusts the combustion balance by the pilot fuel limit correction value calculator 328 provided in the control device 100. A concentration bias 329 is calculated, and this pilot fuel limiter hydrogen concentration bias 329 is input to the pilot fuel limiter 314 and between the upper limit and the lower limit of the pilot fuel supply signal determined by the operating condition in the pilot fuel limiter 314 The pilot fuel supply signal 315 is calculated and output so as to be a value.

  Based on the pilot fuel supply signal 315 output from the pilot fuel limiter 314 of the control device 100, the opening degrees of the pilot fuel pressure adjustment valve 105 and the pilot fuel flow rate adjustment valve 106 installed in the pilot fuel supply system 122 are adjusted. Thus, the flow rate of the fuel supplied to the pilot burner 22 through the pilot fuel supply system 122 is also controlled to decrease.

  That is, when the hydrogen concentration signal 304 in the fuel 14 is increased by the control as described above, the reference gas turbine calculated by the reference main fuel flow rate calculator 307 based on the reference gas turbine input fuel signal 306 is used. The main fuel stable range bias 327 obtained by calculating the stable range of combustion by the main fuel stable range calculator 326 is input to the input fuel signal 306 to calculate the main fuel flow rate signal 322, and the comparator 323 Since the main fuel flow signal 322 becomes the main fuel supply signal 325 via the signal switch 324 based on the determination as to whether or not the burner 23 can be operated, the main fuel supply signal 325 works to increase.

  Further, the pilot fuel limit for adjusting the combustion balance calculated by the pilot fuel limit correction value calculator 328 with respect to the pilot fuel supply source signal 313 based on the reference gas turbine input fuel signal 306 calculated by the reference fuel flow rate calculator 305. The hydrogen concentration bias 329 is input to the pilot fuel limiter 314, and the pilot fuel supply source signal is adjusted so that the pilot fuel limiter 314 has a value between the upper limit and the lower limit of the pilot fuel supply signal determined by the operating state. Since the pilot fuel supply signal 315 is calculated and output based on 313, the pilot fuel supply signal 315 functions to decrease.

  As a result, the fuel ratio of the pilot fuel supply signal 315 to the main fuel supply signal 325 decreases, so that when the hydrogen concentration in the fuel increases, the position of the combustion flame of the gas turbine combustor moves downstream in the combustion chamber. It is possible to ensure the reliability of the gas turbine combustor.

  By the way, when the hydrogen concentration contained in the fuel 14 supplied to the gas turbine combustor 1a becomes higher than a certain level, the position of the flame formed in the gas turbine combustion chamber 1 in the main burner 23 adopting the premixed combustion method is changed to the burner. In order to avoid the occurrence of reliability problems in the main burner 23, the fuel concentration (or hydrogen concentration) in the air-fuel mixture of the main burner 23 is set to be lower than the limit value. It is necessary to suppress to the lower side.

  Therefore, in the control device 100 of the gas turbine combustor 1a according to the embodiment of the present invention described above, when the hydrogen concentration contained in the fuel 14 exceeds a predetermined value, the configuration described above is used. Control is performed to limit the amount of fuel flow supplied to the main burner 23 of the gas turbine combustor 1a.

  As a result of such control, the fuel ratio of the pilot burner 22 again increases to PM_c. However, even in this case, the amount of fuel burned in the main burner 23 is limited due to the reliability of the gas turbine combustor 1a. It is ensured within an acceptable range, and it becomes possible to suppress the NOx emission amount significantly lower than when all the same fuel is treated by a diffusion combustion burner.

  According to this embodiment, when a fuel having a varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, the flame formed due to the variation in the hydrogen concentration becomes a structure of the gas turbine combustor. It is possible to realize a premixed combustion type gas turbine combustor control device and a gas turbine combustor control method capable of avoiding close proximity and causing reliability problems and maintaining low NOx combustion performance.

  Next, a gas turbine combustor control apparatus and a gas turbine combustor control method according to a second embodiment of the present invention will be described with reference to FIGS.

  FIG. 5 is a schematic view showing a configuration of a gas turbine power plant to which a control device for a gas turbine combustor according to a second embodiment of the present invention is applied.

  The basic configuration of the gas turbine combustor control device of the present embodiment is the same as that of the gas turbine combustor control device of the first embodiment of the present invention shown in FIGS. The description of the operation is omitted, and only different configurations will be described below.

  In the control apparatus for the gas turbine combustor according to the second embodiment shown in FIG. 5, the starter 15 is started with another fuel that does not contain hydrogen and has a stable composition for the pilot burner 23. The starting fuel 15 is supplied through a pilot fuel supply system 122 provided with a starting fuel cutoff valve 104 and a starting fuel pressure adjusting valve 105 and a starting fuel flow rate adjusting valve 106 on the downstream side of the starting fuel cutoff valve 104. This is different from the control device for the gas turbine combustor of the first embodiment.

  FIG. 6 is a block diagram showing details of a control device for controlling the combustion of the gas turbine combustor provided in the gas turbine power plant according to the second embodiment shown in FIG.

  In the control device 100a for controlling the combustion of the gas turbine combustor 1a shown in FIG. 6, since the starting fuel 15 of the gas turbine combustor 1a does not contain hydrogen and has a stable fuel composition, it is installed in the control device 100a. The reference fuel flow rate calculator 305a can simultaneously calculate the pilot fuel source flow rate 315a and the reference main fuel flow rate 316 in accordance with the gas turbine operation status.

  In the control device 100a of this embodiment shown in FIG. 6, the input fuel for calculating the reference main fuel flow rate calculator 307 and the reference gas turbine input fuel signal correction value 309 in the control device 100 of the first embodiment shown in FIG. The hydrogen concentration bias calculator 308 is not provided.

  In the control device 100a of this embodiment, the main fuel supply signal 325 calculated by the main fuel limiter 321 constituting the calculation system for calculating the pilot fuel supply signal 315c is used as a gain calculator 330 in consideration of the heat generation amount of the fuel. Is converted into a pilot fuel flow rate correction value 331 for a change in gas turbine input heat generation amount in consideration of a change in fuel heat generation amount due to a change in hydrogen concentration, and a subtractor 332 converts the correction value 331 from the pilot fuel source flow rate 315a. The pilot fuel supply source signal 315b is obtained by subtraction.

  The pilot fuel supply source signal 315b is corrected by the pilot fuel limiter 314b to a value between the upper limit and the lower limit of the pilot fuel supply signal determined by the operating state, and is output as a pilot fuel supply signal 315c. Based on the signal 315c, the opening amounts of the pilot fuel pressure adjusting valve 105 and the pilot fuel flow rate adjusting valve 106 are changed to control the fuel flow rate supplied to the pilot burner 22.

  On the other hand, the reference main fuel flow rate 316 is calculated by the reference fuel flow rate calculator 305a constituting the calculation system for calculating the main fuel supply signal 325. As with the control device 100 of the first embodiment, the main fuel flow rate correction value calculated by the main fuel hydrogen concentration bias calculator 317 based on the hydrogen concentration signal 304 detected by the hydrogen concentration detector 102 provided in the fuel supply system 14a. 318 and the reference main fuel flow rate 316 are added by an adder 319 to obtain a main fuel source flow rate 320 in which a variation in fuel heat generation amount due to a change in hydrogen concentration is corrected.

  Further, the main fuel source flow rate 320 is corrected by the main fuel limiter 321 by the main fuel stability range bias 327 calculated by the main fuel stability range calculator 326 based on the hydrogen concentration signal 304, and the main fuel flow rate signal 322 is calculated. To do.

  When the signal switch 324 is operable, the main fuel flow rate signal 322 is output as a command signal from the control device 100a as the main fuel supply signal 325 as the main fuel supply signal 325.

  Based on the main fuel supply signal 325 passed through the signal switch 324, the opening degree of the main fuel pressure adjustment valve 107 and the main fuel flow rate adjustment valve 108 of the gas turbine combustor 1a is adjusted, and the main fuel supply system 123 is connected to the main fuel supply signal 123. The flow rate of fuel supplied to the burner 23 is controlled.

  In the control device 100a of this embodiment, when the hydrogen concentration signal 304 in the fuel 14 decreases, the main fuel hydrogen concentration bias calculator 317 with respect to the pilot fuel source flow 315a calculated by the reference fuel flow calculator 305a. The main fuel source flow rate 320 is obtained by adding the main fuel flow rate correction value 318 calculated in (4), which becomes a main fuel supply signal 325 that serves as a command for the main fuel to be supplied to the main burner 23, and this main fuel supply signal 325. Work to reduce.

  As a result, the fuel ratio of the main fuel supply signal 325 to the pilot fuel supply signal 315c decreases, so that the combustion of the gas turbine combustor can be controlled within the stable combustion range even when the hydrogen concentration in the fuel decreases. The stable combustion of the gas turbine combustor can be realized.

  On the other hand, when the hydrogen concentration signal 304 in the fuel 14 increases, the stable range of combustion is calculated by the main fuel stable range calculator 326 with respect to the reference main fuel flow rate 316 calculated by the reference fuel flow rate calculator 305a. The main fuel stable range bias 327 obtained by calculating the above is input to the main fuel limiter 321 to calculate the main fuel flow rate signal 322, and the comparator 323 is used to determine whether the main burner 23 can be operated or not. Since the main fuel flow signal 322 is output as the main fuel supply signal 325 via, the main fuel supply signal 325 is increased.

  The main fuel supply signal 325 calculated by the main fuel limiter 321 passes through the gain calculator 330 taking into consideration the heat generation amount of the fuel, and takes into account the variation in the fuel heat generation amount due to the change in the hydrogen concentration. It is converted into a pilot fuel flow rate correction value 331 for fluctuations in the input heat generation amount, and is input to the pilot fuel limiter 314b as a pilot fuel supply source signal 315b for correction to obtain the pilot fuel supply signal 315c.

  Further, a pilot fuel limiter hydrogen concentration bias 329 for adjusting the combustion balance calculated by the pilot fuel limit correction value calculator 328 with respect to the pilot fuel original flow rate 315a calculated by the reference fuel flow rate calculator 305a is provided with a pilot fuel limiter 314b. The pilot fuel supply signal 315c is calculated based on the pilot fuel supply signal 315b so that the pilot fuel limiter 314b has a value between the upper limit and the lower limit of the pilot fuel supply signal determined by the operating state. Therefore, the pilot fuel supply signal 315 is decreased.

  As a result, the fuel ratio of the pilot fuel supply signal 315c to the main fuel supply signal 325 decreases, so that when the hydrogen concentration in the fuel increases, the position of the combustion flame of the gas turbine combustor moves downstream in the combustion chamber. It is possible to ensure the reliability of the gas turbine combustor.

  Thus, the control can be simplified by operating the pilot burner 22 with the starting fuel having no fuel composition fluctuation. In addition to high-calorie gas fuels such as natural gas and propane gas, oil fuels such as kerosene, light oil, and A heavy oil may be used as the starting fuel.

  According to this embodiment, when a fuel having a varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, the flame formed due to the variation in the hydrogen concentration becomes a structure of the gas turbine combustor. It is possible to realize a premixed combustion type gas turbine combustor control device and a gas turbine combustor control method capable of avoiding close proximity and causing reliability problems and maintaining low NOx combustion performance.

  Next, a gas turbine combustor control apparatus and a gas turbine combustor control method according to a third embodiment of the present invention will be described with reference to FIGS. FIG. 7 is a schematic diagram showing the configuration of a gas turbine power plant to which a control device for a gas turbine combustor according to a third embodiment of the present invention is applied.

  The control apparatus for the gas turbine combustor of the present embodiment has the same basic configuration as the control apparatus for the gas turbine combustor of the second embodiment of the present invention shown in FIGS. The description of the operation is omitted, and only different configurations will be described below.

  In the gas turbine combustor 1a according to the third embodiment shown in FIG. 7, the main burner 23 has a small diameter in which a large number of fuel nozzles 25 and a large number of air holes opened in the air hole plate 24 are arranged coaxially. The small-diameter coaxial nozzle is formed as an assembled main burner 23, and a plurality of the assembled main burners 23 are disposed around the pilot burner 22 so that the fuel is structurally preliminarily formed. The structure of the main nozzle provided in the gas turbine combustor 1 of the second embodiment is different from that of NOx by increasing the dispersibility of air and reducing NOx.

  The coaxial nozzle burner, which is a plurality of main burners 23 provided in the present embodiment, is a burner composed of a large number of coaxial jets of fuel and air, and the degree of mixing of fuel and air is determined according to the shape of the air nozzle and the shape of the fuel nozzle. Can be adjusted.

  Further, in each of the plurality of main burners 23, the flame holding ability of the burner alone can be adjusted by mixing and jetting the innermost coaxial jet facing the central axis of the coaxial nozzle burner. It is possible to make the coaxial jet flow at the innermost peripheral part have a flame holding function.

  The plurality of main burners 23 adjust the mixing of fuel and air so as to enhance the flame holding function as described above, so that the position where the mixture in the combustible range is formed is far from the structure of the coaxial nozzle burner. It is possible to design in a place, and the tolerance for the flame approach can be increased for the coaxial nozzle on the inner peripheral side of each main burner 23.

  Therefore, in the gas turbine combustor 1a of the present embodiment, the fuel containing hydrogen is constituted by the inner peripheral side main fuel supply system 123a supplied to the inner circumference side of the coaxial nozzle constituting each main burner 23, and each main burner 23. Branching to the outer peripheral main fuel supply system 124a supplied to the outer peripheral side of the coaxial nozzle constituting each main burner 23, the distribution of the supplied fuel can be adjusted.

  The fuel 14 containing hydrogen supplied to the inner peripheral side of the coaxial nozzle constituting the main burner 23 is an inner peripheral main fuel pressure adjusting valve 107a installed in the inner peripheral main fuel supply system 123a, an inner peripheral main fuel flow rate. The fuel nozzle 25 is led from the inner peripheral space of the fuel distributor 26 provided in the main burner 23 through the regulating valve 108a to the joint port of the combustor end cover 8 and passing through the flow path inside the end cover 8. It passes through the air hole plate 24 through the air hole and passes through the air hole plate 24 to be jetted into the combustion chamber 1 as a jet coaxial with the air.

  Similarly, the fuel 14 containing hydrogen supplied to the outer peripheral side of the coaxial nozzle constituting the main burner 23 is also connected to the outer peripheral main fuel pressure regulating valve 107b, the outer peripheral main fuel, installed in the outer peripheral main fuel supply system 124a. The fuel nozzle 25 is led from the outer peripheral side space of the fuel distributor 26 provided in the main burner 23 through the flow rate adjusting valve 108 b to the joint port of the combustor end cover 8, passing through the flow path inside the end cover 8. It passes through the air hole plate 24 through the air hole and passes through the air hole plate 24 to be jetted into the combustion chamber 1 as a jet coaxial with the air.

  FIG. 8 is a block diagram showing details of a control device 100b for controlling the combustion of the gas turbine combustor 1a provided in the gas turbine power plant according to the third embodiment shown in FIG.

  In the control apparatus 100b for controlling the combustion of the gas turbine combustor 1a shown in FIG. 8, the starting fuel 15 of the gas turbine combustor 1a is the same as in the second embodiment. Therefore, the reference fuel flow rate calculator 305a installed in the control device 100b can simultaneously calculate the pilot fuel source flow rate 315a and the reference main fuel flow rate 316 according to the gas turbine operating condition.

  The control device 100b for controlling the combustion of the gas turbine combustor 1a of this embodiment shown in FIG. 8 does not include the reference main fuel flow rate calculator 307 in the control device 100 of the first embodiment shown in FIG. A main inner / outer / periphery ratio calculator 333 that calculates the fuel ratio 334 between the inner and outer circumferences of each main burner 23, and a main inner / outer / periphery fuel that calculates a main inner peripheral fuel supply signal 336 and a main outer peripheral fuel supply signal 337. The flow rate calculator 335 is newly provided.

  In the gas turbine combustor 1a of the present embodiment, as described above, each main burner 23 is constituted by the coaxial nozzle in which the fuel nozzle 25 and the air hole opened in the air hole plate 24 are arranged coaxially. In addition to having the function of holding the flame in itself, the inner peripheral side of the coaxial nozzle adjusts the mixing and has the function of holding the flame, so that the tolerance for the flame approach is widened.

  Therefore, in the control device 100b of the present embodiment, it is possible to perform low NOx combustion while ensuring reliability by adjusting the fuel distribution inside the main burner with respect to the change in the hydrogen concentration, and the fuel supplied to the pilot burner is It is sufficient to ensure the minimum combustion stability of the entire combustor.

  Therefore, in the control device 100a that controls the combustion of the gas turbine combustor 1a of the present embodiment, in the control system that calculates the pilot fuel supply signal 315c, the pilot fuel source flow rate 315a is determined by the pilot fuel limiter 314 according to the operating state. Only by correcting the fuel supply signal to a value between the upper limit and the lower limit, it can be output as the pilot fuel supply signal 315c, and the control can be greatly simplified.

  On the other hand, in the control system for calculating the main fuel supply signal, the reference main fuel flow rate 316 calculated by the reference fuel flow rate calculator 305 a is added to the main fuel flow rate correction value 318 calculated by the main fuel hydrogen concentration bias calculator 317. The main fuel source flow rate 320 corrected by the change in the fuel heat generation amount due to the change in the hydrogen concentration and corrected by the main fuel stable range calculator 326 and the main fuel limiter 321 is corrected. As the signal 322, the main fuel flow rate signal 322 is output as the main fuel supply signal 325 if the signal switch 324 is operable, and the fuel flow rate 0 is output if the operation is not possible.

  Thereafter, the fuel ratio 334 between the inner peripheral side and the outer peripheral side in the main burner 23 is calculated by the main inner / outer peripheral ratio calculator 333, and the fuel ratio 334 between the inner peripheral side and the outer peripheral side is calculated as the main inner / outer peripheral fuel flow rate. The main fuel supply signal 335 and the main outer fuel supply signal 337 are calculated by multiplying the main fuel supply signal 325 by the device 335, and the main inner fuel supply signal 336 and the main outer fuel supply signal 337 are calculated. The flow rate of the fuel supplied to the inner peripheral side and the outer peripheral side of the coaxial nozzle which is the main burner 23 is controlled based on the supply signal 337, respectively.

  In the control device 100b of the present embodiment, when the hydrogen concentration signal 304 in the fuel 14 decreases, the combustion on the inner peripheral side of the coaxial nozzle that is the main burner 23 in order to ensure stable combustion of the gas turbine combustor 1a. The inner peripheral side so that the fuel flow rate supplied through the inner peripheral main fuel supply system 123a is larger than the fuel flow rate supplied through the outer peripheral main fuel supply system 124a so that the ratio is higher than the outer peripheral combustion ratio. The opening degree of the main fuel pressure adjusting valve 107a and the inner peripheral main fuel flow rate adjusting valve 108a, and the outer peripheral main fuel pressure adjusting valve 107b and the outer peripheral main fuel flow rate adjusting valve 108b are controlled by the control device 100b, respectively. The combustion ratio on the inner peripheral side of 23 is increased.

  Next, until the hydrogen concentration signal 304 in the fuel 14 increases and the hydrogen concentration reaches about 48%, the combustion ratio on the inner peripheral side of the coaxial nozzle that is the main burner 23 of the gas turbine combustor 1a is on the outer peripheral side. The inner peripheral main fuel pressure regulating valve is set so that the fuel flow rate supplied through the inner peripheral main fuel supply system 123a is smaller than the fuel flow rate supplied through the outer peripheral main fuel supply system 124a so as to be lower than the combustion ratio. The opening degree of the outer peripheral side main fuel flow rate adjusting valve 107a and the outer peripheral side main fuel flow rate adjusting valve 107b and the outer peripheral side main fuel flow rate adjusting valve 108b is controlled by the control device 100b, respectively. Increase the combustion ratio.

  Further, when the hydrogen concentration signal 304 in the fuel 14 increases and the hydrogen concentration exceeds a predetermined concentration (for example, about 48%), the position of the flame formed in the combustion chamber of the gas turbine combustor 1a is combusted. In order to move to the downstream side of the chamber and ensure the reliability of the gas turbine combustor, the inner peripheral side is set so that the combustion ratio on the inner peripheral side of the coaxial nozzle which is the main burner 23 is higher than the combustion ratio on the outer peripheral side. The inner peripheral main fuel pressure adjustment valve 107a and the inner peripheral main fuel flow adjustment valve 108a, so that the fuel flow supplied through the main fuel supply system 123a is greater than the fuel flow supplied through the outer main fuel supply system 124a. In addition, the opening degree of the outer peripheral side main fuel pressure adjusting valve 107b and the outer peripheral side main fuel flow rate adjusting valve 108b is controlled by the control device 100b, respectively. Increasing the combustion ratio of the inner circumferential side of 23.

  In addition, although description was abbreviate | omitted about the effect | action of each calculating unit which comprises the control apparatus 100b of the gas turbine combustor 1a of a present Example, the control apparatus 100 of the gas turbine combustor 1a shown in FIG. 2 and FIG. Refer to the operation of each computing unit constituting the control device 100a of the gas turbine combustor 1a shown.

  FIG. 9 shows a change in the distribution of the fuel supply amount on the inner and outer periphery of the main burner with respect to the change in the hydrogen concentration at the rated load when controlled by the control device 100b of the gas turbine combustor 1a according to the third embodiment shown in FIG. FIG.

  The horizontal axis in FIG. 9 is the concentration of hydrogen contained in the fuel 14, and the vertical axis is the ratio of the fuel on the inner peripheral side that holds the flame holding out of the total fuel supplied to the main burner 23 of the gas turbine combustor 1a. Is shown as the fuel ratio for flame holding.

  In the characteristic diagram of FIG. 9, when the hydrogen concentration is low, the combustion speed is slow, and the flame is flowed downstream of the combustor, so if the flame is not held stronger, the flame will blow out and generate a large amount of unburned emissions. May cause problems.

  For this reason, when the hydrogen concentration contained in the fuel 14 is low, a bias is applied so as to supply more fuel to the inner peripheral side that bears flame holding, and as a result, the flame holding fuel ratio increases to IO_a.

  However, in this case, the concentration of hydrogen contained in the fuel 14 is low, so that not only the NOx emission amount in the entire main burner is small, but also the inner peripheral main burner responsible for flame holding has a certain degree of low NOx combustibility. Because of the coaxial nozzle structure, the NOx emission is smaller than that of the first embodiment.

  As the concentration of hydrogen contained in the fuel 14 increases, the combustion speed increases, so the position of the flame formed in the gas turbine combustion chamber 1 gradually moves to the upstream side in the gas turbine combustion chamber 1, so that it can be blown out. The flame holding fuel flow rate can be reduced to IO_b, and the exhaust NOx is further reduced.

  Further, when the concentration of hydrogen contained in the fuel 14 is increased, the flame comes close to the burner structure on the outer peripheral side of the coaxial nozzle constituting the main burner 23, which causes a reliability problem in the main burner. In order to avoid this, it is necessary to suppress the fuel concentration (or hydrogen concentration) in the air-fuel mixture on the outer peripheral side of the coaxial nozzle burner below a certain limit value.

  For this reason, as a result of the restriction | limiting of the fuel flow volume supplied to the outer peripheral side of a coaxial nozzle, the flame holding fuel ratio will increase to IO_c again. However, even in this case, the inner peripheral side of the coaxial nozzle that constitutes the main burner 23 that holds the flame holding has a coaxial nozzle structure that can obtain a certain degree of low NOx combustibility. Even small.

  According to this embodiment, when a fuel having a varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, the flame formed due to the variation in the hydrogen concentration becomes a structure of the gas turbine combustor. It is possible to realize a premixed combustion type gas turbine combustor control device and a gas turbine combustor control method capable of avoiding close proximity and causing reliability problems and maintaining low NOx combustion performance.

  Next, a gas turbine combustor control apparatus and a gas turbine combustor control method according to a fourth embodiment of the present invention will be described with reference to FIGS.

  FIG. 10 is a schematic diagram showing the configuration of a gas turbine power plant to which a gas turbine combustor 1a according to a fourth embodiment of the present invention is applied.

  The control device for the gas turbine combustor of the present embodiment has the same basic configuration as the control device for the gas turbine combustor of the third embodiment of the present invention shown in FIGS. The description of the operation is omitted, and only different configurations will be described below.

  FIG. 10 shows an embodiment of an IGCC plant with carbon dioxide recovery equipped with a gas turbine combustor 1a according to the present invention, and a fuel supply system that supplies the compressor 5, the turbine 6, the generator 30, and the gas turbine combustor 1a. It is the schematic block diagram which showed.

  The gas turbine combustor 1a and its control device 11c provided in the IGCC plant with carbon dioxide recovery of the present embodiment are the control device for the gas turbine combustor 1a of the third embodiment of the present invention shown in FIGS. Since the basic configuration is the same as that of 100b, description of the configuration and operation common to both will be omitted, and only different configuration will be described below.

  In FIG. 10, the IGCC plant with carbon dioxide recovery first starts the gas turbine to a certain load with the starting fuel, and generates the coal gasification furnace 202 that generates coal gas from coal and the coal gasification furnace 202. A coal gasification gas purification device 203 for purifying the coal gas produced, a shift reactor 206 for producing carbon dioxide and hydrogen from the coal gas produced in the coal gasification furnace 202, and a recovery of the carbon dioxide produced in the shift reactor 206 By starting the operation of each device of the carbon dioxide recovery device 207, the coal gasification fuel 21 containing hydrogen is supplied to the gas turbine combustor 1a of the gas turbine.

  In the gasification of coal, first, oxygen 17 and coal 16 refined by the oxygen production apparatus 201 are converted into gas mainly composed of carbon monoxide and hydrogen in the coal gasification furnace 202, and impurities and the like are removed in the gas purification apparatus 203. Coal gasification gas 18 is produced. A part of the produced coal gasification gas 18 is supplied as the coal gasification fuel 21 to the gas turbine fuel supply systems 123a and 124a that reach the gas turbine combustor 1a via the hydrogen concentration detection means 102a and the flow rate adjustment valve 205. A part of the coal gasification gas 18 is led to the shift reactor 206 via the flow rate adjustment valve 206, and the remaining gas is burned in the gas processing furnace 209.

  In the shift reactor 206, water vapor 19 is supplied to the coal gasification gas 18 to cause a shift reaction, and carbon monoxide in the composition is converted into carbon dioxide and hydrogen, which is sent to the carbon dioxide recovery device 207. And the high hydrogen concentration coal gasification gas 20 is purified.

  A part of the high hydrogen concentration coal gasification gas 20 is also supplied as the coal gasification fuel 21 to the gas turbine fuel supply systems 123a and 124a that reach the gas turbine combustor 1a via the hydrogen concentration detection means 102b and the flow rate adjustment valve 208. The remaining gas is burned in the gas processing furnace 209.

  When the coal gasification fuel 21 is supplied, the starting fuel 15 is replaced with the coal gasification fuel 21. Therefore, the pilot fuel supply system 122 and the pilot fuel supply system 122 branched from the gas turbine fuel supply system 123a are provided in the pilot fuel supply system 122. A starting fuel pilot burner fuel shut-off valve 104a for adjusting the fuel supplied to the pilot burner 22, a starting fuel pilot burner fuel pressure adjusting valve 105a, and a starting fuel pilot burner fuel flow rate adjusting valve 106a are installed. The gas turbine fuel supply system 122b branched from the turbine fuel supply system 123a includes a coal gasification fuel pilot burner fuel cutoff valve 104b for adjusting the fuel supplied to the pilot burner 22, and a coal gasification fuel pilot burner fuel pressure adjustment valve. 105b and coal Gasification fuel pilot burner fuel flow rate regulating valve 106b are installed.

  A plurality of installed main burners 23 employ coaxial nozzle burners in the same manner as the main burner 23 of the gas turbine combustor 1a of the third embodiment. The fuel supply system 123a is provided with an inner peripheral main fuel pressure adjustment valve 107a and an inner peripheral main fuel flow rate adjustment valve 108a, and the outer peripheral main fuel supply system 124a is provided with an outer peripheral main fuel pressure adjustment valve 107b and an outer peripheral main. A fuel flow control valve 108b is installed.

  The coal gasified fuel 21 is guided to the joint port of the combustor end cover 8 through the inner peripheral main fuel supply system 123a and the outer peripheral main fuel supply system 124a, and passes through the flow path inside the end cover 8. Then, the fuel is ejected from the outer peripheral side space of the fuel distributor 26 of each main burner 23 toward the air hole opened in the air hole plate 24 through the fuel nozzle 25 and is jetted into the combustion chamber 1 as a jet coaxial with the air. And is configured to burn.

  FIG. 11 is a configuration diagram showing details of a control device 100c that controls the gas turbine combustor 1a provided in the IGCC plant with carbon dioxide recovery of the present embodiment.

  Since a plurality of fuels are switched in the IGCC plant with carbon dioxide recovery, the reference gas flow calculator 305c installed in the control device 100c refers to the operation command signal 301 and the rotation speed signal 302 of the gas turbine, and the reference gas turbine. In addition to the input fuel signal 306, a pilot input heat amount 315d, which is a signal indicating the amount of heat necessary for the fuel supplied to the pilot burner 22 when switching from the starting fuel to the coal gasification fuel, is calculated.

  The pilot burner input heat amount signal 315d is converted into the starting pilot fuel source flow rate 315a by the starting fuel flow rate calculator 343, and the starting fuel pilot fuel supply signal 315c is calculated in the same manner as the control device 100b shown in the second embodiment.

  That is, the main fuel supply signal 325 taking into account the variation in the fuel heat generation amount due to the change in the hydrogen concentration contained in the fuel is converted into a pilot fuel flow rate fluctuation of the gas turbine input heat generation amount by the gain calculator 330 considering the heat generation amount of the fuel. By converting to a correction value and subtracting by the subtracter 332, the starting fuel pilot fuel source flow 315a is used as the starting fuel pilot fuel flow signal 315e.

The starting fuel pilot fuel flow signal 315e is corrected by the pilot fuel limiter 314b so as to be a value between the upper limit and the lower limit of the pilot fuel supply signal determined by the operating state, and is output as a pilot fuel supply signal 315c. Under the present circumstances, unlike each control apparatus 100, 100a, 100b shown in Examples 1-3, the fuel containing the hydrogen produced | generated in the IGCC plant with a carbon dioxide recovery is the fuel which mixed the coal gasification fuel from which hydrogen concentration differs Therefore, the hydrogen concentration 304 of the fuel that is actually supplied to the gas turbine combustor 1a is the coal gas detected from the hydrogen concentration detecting means 102a installed in the system that is directly supplied from the gas purification device 203 to the gas turbine. Coal gas hydrogen concentration signal 338, coal gasification gas flow rate signal 339 of the same system, and CO ₂ recovered coal gas hydrogen concentration signal obtained from hydrogen concentration detection means 102b installed in the system supplied from carbon dioxide recovery device 207 340, can be calculated by the supply of hydrogen concentration calculator 342 by entering the CO ₂ recovery after coal gas flow signal 341 of the same strain , To obtain a hydrogen concentration 304 of the fuel.

  Since the coal gasification fuel 21 from the coal gasification furnace 202 is not generated at the time of starting the IGCC plant with carbon dioxide recovery, the start-up fuel pilot fuel supply signal 315c is not corrected at the initial start-up time. Used as a flow rate indication value of 15.

  When the coal gasification furnace 202 starts and the coal gasification fuel 21 starts to be generated, the fuel supply to the gas turbine combustor 1a switches the fuel supplied from the start fuel 15 to the coal gasification fuel 21 to the pilot burner 22. Do the driving.

  At this time, similarly to the control device 100 shown in the first embodiment, the reference gas turbine input fuel signal correction value 309 calculated by the input fuel hydrogen concentration bias calculator 308 with the hydrogen concentration signal 304 as an input and the reference fuel flow rate calculation are calculated. The reference gas turbine input fuel signal 306 calculated in the unit 305c is added by the adder 310 to calculate the gas turbine input fuel signal 311 in which the fluctuation of the fuel heat generation amount due to the change in the hydrogen concentration is corrected.

  Further, the subtractor 312 subtracts the main fuel supply signal 325 from the gas turbine input fuel signal 311 to convert it into a pilot fuel supply source signal 313, and the pilot fuel limiter 314 determines the upper and lower limits of the pilot fuel supply signal determined by the operating state. The pilot fuel supply signal 315 is corrected so as to be a value between the pilot fuel supply signal 315 and the pilot fuel pressure adjustment valve 105b installed in the pilot fuel supply system 122b and the pilot fuel flow rate adjustment based on the pilot fuel supply signal 315 The flow rate of the coal gasification fuel supplied to the pilot burner 22 is controlled by changing the opening degree of the valve 106b.

  On the other hand, in the control system that calculates the main fuel supply signal, the reference main fuel flow rate 316 calculated by the reference fuel flow rate calculator 305c is used in the same manner as the control devices 100, 100a, and 100b shown in the first to third embodiments. The main fuel flow rate correction value 318 calculated by the main fuel hydrogen concentration bias calculator 317 is added by the adder 319, and the main fuel stable flow rate 320 is obtained as a main fuel source flow rate 320 corrected for fluctuations in the amount of heat generated by the change in hydrogen concentration. As the calculated value in the range calculator 326 and the main fuel flow rate signal 322 corrected by the main fuel limiter 321, the main fuel flow rate signal 322 is used if the signal switch 324 is operable, and the fuel flow rate is determined if it is not operable. An operation of outputting 0 as the main fuel supply signal 325 is performed.

Thereafter, a fuel ratio for supplying fuel to the inner peripheral side and the outer peripheral side of each main burner 23 of the gas turbine combustor 1a is calculated by the main inner / outer peripheral ratio calculator 335 and multiplied by the main fuel supply signal 325. Thus, the main inner peripheral fuel supply signal 336 and the main outer peripheral fuel supply signal 337 are obtained in the same manner as in the control device 100b shown in the third embodiment.

  In the control apparatus 100c of the present embodiment, when the hydrogen concentration signal 338 or 341 in the coal gasification fuel 21 decreases, the coaxial nozzle that is the main burner 23 is used to ensure stable combustion of the gas turbine combustor 1a. The fuel flow rate supplied through the inner peripheral side main fuel supply system 123a is higher than the fuel flow rate supplied through the outer peripheral side main fuel supply system 124a so that the combustion ratio on the inner peripheral side becomes higher than the combustion ratio on the outer peripheral side. The opening degree of the inner peripheral side main fuel pressure adjusting valve 107a and the inner peripheral side main fuel flow rate adjusting valve 108a, and the outer peripheral side main fuel pressure adjusting valve 107b and the outer peripheral side main fuel flow rate adjusting valve 108b are respectively controlled by the control device 100b. Then, the combustion ratio on the inner peripheral side of the main burner 23 is increased.

  Next, until the hydrogen concentration signal 338 or 341 in the coal gasified fuel 21 increases and the hydrogen concentration reaches a predetermined value (for example, about 48%), the coaxial nozzle which is the main burner 23 of the gas turbine combustor 1a. The fuel flow rate supplied through the inner peripheral main fuel supply system 123a is smaller than the fuel flow rate supplied through the outer peripheral main fuel supply system 124a so that the combustion ratio on the inner peripheral side is lower than the combustion ratio on the outer peripheral side. Further, the opening degree of the inner peripheral main fuel pressure adjusting valve 107a and the inner peripheral main fuel flow rate adjusting valve 108a, and the outer peripheral main fuel pressure adjusting valve 107b and the outer peripheral main fuel flow rate adjusting valve 108b are respectively controlled by the control device 100b. By controlling, the combustion ratio on the outer peripheral side of the main burner 23 is increased.

  Further, when the hydrogen concentration signal 338 or 341 in the coal gasified fuel 21 increases and the hydrogen concentration exceeds a predetermined concentration (for example, about 48%), it is formed in the combustion chamber of the gas turbine combustor 1a. In order to move the flame position downstream of the combustion chamber and ensure the reliability of the gas turbine combustor, the combustion ratio on the inner peripheral side of the coaxial nozzle as the main burner 23 is made higher than the combustion ratio on the outer peripheral side. Further, the inner peripheral main fuel pressure adjustment valve 107a and the inner peripheral main fuel are adjusted so that the fuel flow rate supplied through the inner peripheral main fuel supply system 123a is larger than the fuel flow rate supplied through the outer peripheral main fuel supply system 124a. The opening degree of the flow rate adjusting valve 108a, the outer peripheral side main fuel pressure adjusting valve 107b, and the outer peripheral side main fuel flow rate adjusting valve 108b is adjusted by the control device 100b. Control to raise the combustion ratio of the inner circumferential side of the main burner 23.

  As a result, the fuel ratio of the main fuel supply signal 325 to the pilot fuel supply signal 315c decreases, so that the combustion of the gas turbine combustor can be controlled within the stable combustion range even when the hydrogen concentration in the fuel decreases. The stable combustion of the gas turbine combustor can be realized.

  According to this embodiment, when a fuel having a varying hydrogen concentration contained in the fuel is used in a gas turbine combustor, the flame formed due to the variation in the hydrogen concentration becomes a structure of the gas turbine combustor. It is possible to realize a premixed combustion type gas turbine combustor control device and a gas turbine combustor control method capable of avoiding close proximity and causing reliability problems and maintaining low NOx combustion performance.

  The present invention relates to a fuel flow control of a gas turbine combustor installed in a gas turbine plant, in particular, a control device for a premixed combustion type gas turbine combustor operated by a fuel containing hydrogen in the fuel composition and a gas turbine combustor. Applicable to control method.

1: gas turbine combustor, 1a: gas turbine combustion chamber, 2: combustor outer cylinder, 3: combustor liner, 4: combustor tail cylinder, 5: compressor, 6: turbine, 7: vehicle compartment, 8: Combustor end cover, 10: compressed air, 11: cooling air, 12: combustion air, 13: combustion gas, 14: fuel, 14a: fuel supply system, 15: starting fuel, 16: coal, 17: oxygen 18 : Coal gasification gas, 19: Water vapor, 20: High hydrogen concentration (after CO ₂ recovery) Coal gasification gas, 21: Coal gasification fuel, 22: Pilot burner, 23: Premixed combustion system main burner, 24: Air Hole plate, 25: Fuel nozzle, 26: Fuel distributor, 100: Control device, 101: Fuel compressor, 102, 102a, 102b: Hydrogen concentration detection means, 103: Shut-off valve, 104: Fuel shut-off valve for activation, 105 : Pyro Fuel pressure regulating valve, 105a: starting fuel pilot fuel pressure regulating valve, 105b: hydrogen containing pilot fuel pressure regulating valve, 106: pilot fuel flow regulating valve, 106a: starting fuel pilot fuel regulating valve, 106b: hydrogen containing Fuel pilot fuel flow rate adjustment valve 107: Main fuel supply pressure adjustment valve 107a: Inner peripheral side main fuel pressure adjustment valve 107b: Outer peripheral side main fuel pressure adjustment valve 108: Main fuel flow rate adjustment valve 108a: Inner peripheral side Main fuel flow rate adjustment valve 108b: Outer peripheral side main fuel flow rate adjustment valve 122, 122b: Pilot fuel supply system 123: Main fuel supply system 123a: Inner peripheral side main fuel supply system 124a: Outer peripheral side main fuel supply system 201: Oxygen production equipment, 202: Coal gasification furnace, 203: Coal gasification gas purification equipment 204, 205: Flow rate adjusting valve, 206: Shift reactor, 207: Carbon dioxide recovery device, 208: Flow rate adjusting valve, 209: Gas processing furnace, 301: Operation command signal, 302: Gas turbine rotation speed signal, 303: Gas turbine operation plan line, 304: hydrogen concentration signal, 305, 305a, 305b: reference fuel flow rate calculator, 306: reference gas turbine input fuel signal, 307: reference main fuel flow rate calculator, 308: input fuel hydrogen concentration bias calculation 309: Reference gas turbine input fuel signal correction value, 310: Adder, 311: Gas turbine input fuel signal, 312: Subtractor, 313: Pilot fuel supply source signal, 314: Pilot fuel limiter, 315: Pilot fuel Supply signal, 315a: Pilot fuel source flow rate, 315b: Pilot fuel supply source signal, 3 5c: Startup fuel pilot fuel supply signal, 315d: Pilot burner input heat amount signal, 315e: Startup fuel pilot fuel flow signal, 316: Reference main fuel flow rate, 317: Main fuel hydrogen concentration bias calculator, 318: Main fuel flow rate Correction value, 319: adder, 320: main fuel source flow rate, 321: main fuel limiter, 322: main fuel flow rate signal, 323: comparator, 324: signal switcher, 325: main fuel supply signal, 326: main Fuel stable range calculator, 327: Main fuel stable range bias, 328: Pilot fuel limit correction value calculator, 329: Pilot fuel limiter hydrogen concentration bias, 330: Gain calculator, 331: Pilot fuel flow rate calorific value correction Value, 332: subtractor, 333: main inner / outer circumference ratio calculator, 334: memory Inner / outer periphery ratio signal, 335: Main inner / outer periphery fuel flow rate calculator, 336: Main inner periphery side fuel supply signal, 337: Main outer periphery side fuel supply signal, 338: Coal gasification gas hydrogen concentration signal, 339: Coal gasification Gas flow rate signal, 340: Coal gas hydrogen concentration signal after CO ₂ recovery, 341: Coal gas flow rate signal after CO ₂ recovery, 342: Supply hydrogen concentration calculator.

Claims (3)

In a control device for a gas turbine combustor including a fuel containing hydrogen in a fuel composition and a burner that burns a starting fuel that does not contain hydrogen in the fuel composition,
The burner provided in the gas turbine combustor is a pilot burner that performs diffusion combustion for holding the flame of the entire gas turbine combustor, and a plurality of the burners that are installed on the outer peripheral side of the pilot burner to perform premixed combustion that performs low NOx combustion. Consists of a main burner and
As a fuel system for supplying fuel to the burner of the gas turbine combustor, a pilot fuel supply system for supplying starter fuel not containing hydrogen in the fuel composition to the pilot burner, and a fuel containing hydrogen in the fuel composition to the main burner Each main fuel supply system is arranged,
In the main burner, a plurality of fuel nozzles and a plurality of air holes formed in an air plate corresponding to the fuel nozzles are coaxially arranged and arranged on the inner peripheral side and the outer peripheral side of the main burner. Consists of a nozzle burner,
The main fuel supply system includes an inner peripheral main fuel supply system that supplies fuel to the coaxial nozzle burner on the inner peripheral side of the main burner, and an outer peripheral main fuel supply system that supplies fuel to the coaxial nozzle burner on the outer peripheral side of the main burner. And
A hydrogen concentration detector for detecting the hydrogen concentration contained in the fuel is provided in the main fuel system,
The flow rate of the fuel supplied to the coaxial nozzle burner on the outer peripheral side of the main burner through the outer peripheral main fuel supply system based on the value of the hydrogen concentration contained in the fuel detected by the hydrogen concentration detector, and the inner peripheral main fuel A control device for a gas turbine combustor, characterized in that a control device for controlling the distribution of the flow rate of fuel supplied to the coaxial nozzle burner on the inner peripheral side of the main burner through a supply system is installed .
Coal gasifier that generates coal gas from coal, shift reactor that generates carbon dioxide and hydrogen from coal gas generated in the coal gasifier, and coal gas and shift reactor that generate in coal gasifier An IGCC plant with a carbon dioxide recovery having a gas turbine having a gas turbine combustor that burns coal gasified fuel containing hydrogen, the fuel composition containing hydrogen and the fuel composition not containing hydrogen In a control device for a gas turbine combustor including a burner for burning a starting fuel,
The burner provided in the gas turbine combustor is a pilot burner that performs diffusion combustion for holding the flame of the entire gas turbine combustor, and a plurality of the burners that are installed on the outer peripheral side of the pilot burner to perform premixed combustion that performs low NOx combustion. Consists of a main burner and
As a fuel system for supplying fuel to the burner of the gas turbine combustor, a pilot fuel supply system for supplying starter fuel not containing hydrogen in the fuel composition to the pilot burner, and a fuel containing hydrogen in the fuel composition to the main burner Each main fuel supply system is arranged,
In the main burner, a plurality of fuel nozzles and a plurality of air holes formed in an air plate corresponding to the fuel nozzles are coaxially arranged and arranged on the inner peripheral side and the outer peripheral side of the main burner. Consists of a nozzle burner,
The main fuel supply system includes an inner peripheral main fuel supply system that supplies fuel to the coaxial nozzle burner on the inner peripheral side of the main burner, and an outer peripheral main fuel supply system that supplies fuel to the coaxial nozzle burner on the outer peripheral side of the main burner. And
A hydrogen concentration detector for detecting the hydrogen concentration contained in the fuel is provided in the main fuel system,
The flow rate of the fuel supplied to the coaxial nozzle burner on the outer peripheral side of the main burner through the outer peripheral main fuel supply system based on the value of the hydrogen concentration contained in the fuel detected by the hydrogen concentration detector, and the inner peripheral main fuel A control device for a gas turbine combustor, characterized in that a control device for controlling the distribution of the flow rate of fuel supplied to the coaxial nozzle burner on the inner peripheral side of the main burner through a supply system is installed . The burner provided in the gas turbine combustor is a pilot burner that performs diffusion combustion for holding the flame of the entire gas turbine combustor, and a main burner that is installed on the outer peripheral side of the pilot burner and performs premixed combustion that performs low NOx combustion. In a control method of a gas turbine combustor that burns fuel containing hydrogen in the fuel composition with the burner,
The burner provided in the gas turbine combustor is a pilot burner that performs diffusion combustion for holding the flame of the entire gas turbine combustor, and a plurality of the burners that are installed on the outer peripheral side of the pilot burner to perform premixed combustion that performs low NOx combustion. It consists of a main burner and
As a fuel system for supplying fuel to the burner of the gas turbine combustor, a pilot fuel supply system for supplying starter fuel not containing hydrogen in the fuel composition to the pilot burner, and a fuel containing hydrogen in the fuel composition to the main burner Each main fuel supply system is arranged,
In the main burner, a plurality of fuel nozzles and a plurality of air holes formed in an air plate corresponding to the fuel nozzles are coaxially arranged and arranged on the inner peripheral side and the outer peripheral side of the main burner. It consists of a nozzle burner,
As the main fuel supply system, an inner peripheral main fuel supply system that supplies fuel to the coaxial nozzle burner on the inner peripheral side of the main burner, and an outer peripheral side main fuel supply system that supplies fuel to the coaxial nozzle burner on the outer peripheral side of the main burner And are arranged,
Detecting the hydrogen concentration contained in the fuel by a hydrogen concentration detector provided in the main fuel system,
The flow rate of the fuel supplied to the coaxial nozzle burner on the outer peripheral side of the main burner through the outer peripheral main fuel supply system based on the value of the hydrogen concentration contained in the fuel detected by the hydrogen concentration detector, and the inner peripheral main fuel A control method for a gas turbine combustor, wherein a control device is provided for controlling distribution of a flow rate of fuel supplied to a coaxial nozzle burner on an inner peripheral side of the main burner through a supply system .

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