JP5178790B2 - Fuel control method and fuel control apparatus for gas turbine combustor for gas turbine using high humidity air - Google Patents

Description

  The present invention relates to a fuel control method and a fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine that stably operates a low-NOx gas turbine combustor mounted on a high-humidity air-utilizing gas turbine.

  In Japanese Patent Laid-Open No. 2008-175098, which is a well-known example, moisture is added to a gas turbine working fluid (air) and humidified, and the heat energy of the gas turbine exhaust gas is recovered by the humidified air, thereby improving the output and efficiency. In a high-humidity air-utilizing gas turbine power plant that aims to improve, a technique relating to fuel control is disclosed that makes it possible to maintain flame stability while ensuring low NOx performance of the combustor before and after the start of moisture addition.

  In general, when the rotational speed rises at the time of starting the gas turbine, the compressor intake air flow rate and the vibration characteristics of the rotating body change, so that the system tends to become unstable due to disturbance compared to after reaching the rated rotational speed. Even in high-humidity air-based gas turbine plants, if water addition is started while the rotational speed is increasing, disturbance will be given to the gas turbine. Therefore, to ensure the stability at startup, after reaching the rated rotational speed It is desirable to start adding water in the partial load state.

  On the other hand, the nitrogen oxide (NOx) generated in the gas turbine combustor is mostly thermal NOx generated by oxidation of nitrogen in the air when using a fuel having a low nitrogen content such as natural gas, kerosene, and light oil. It is. Since the generation of thermal NOx is highly temperature-dependent, generally in gas turbines using these fuels, the reduction in flame temperature is the basic idea of the low NOx combustion method.

  As a measure for reducing the flame temperature, premixed combustion in which fuel and air are mixed in advance and then burned is known. In addition, when the combustion air is heated by the regenerator as in a high-humidity air-utilizing gas turbine plant, the flame temperature is appropriately controlled while reducing the NOx reduction while preventing spontaneous combustion of the fuel. For this purpose, as disclosed in Japanese Patent Application Laid-Open No. 2008-175098, a technique for injecting and burning fuel and air into a gas turbine combustion chamber as many small-diameter coaxial jets is effective. is there.

  In such a gas turbine combustor that achieves low NOx, it is important to adjust the fuel-air ratio, which is the ratio of the fuel flow rate to the air flow rate, within a predetermined range in order to achieve both low NOx performance and flame stability. is there.

  Japanese Patent Application Laid-Open No. 07-189743 discloses a known example of a low NOx gas turbine combustor used in a general gas turbine, such as a change in the opening of a compressor inlet guide valve, an atmospheric temperature change, A technique for adjusting the ratio of the fuel flow rate to the gas turbine combustor and the air flow rate based on the change in the air flow rate due to the pressure change and the change in the fuel flow rate due to the change in the fuel temperature and the heat generation amount of the fuel is disclosed. ing.

JP 2008-175098 A JP 07-189743 A

  When moisture addition is started in a high-humidity air-based gas turbine plant, the moisture in the combustion air increases in the gas turbine combustor, so the combustion heat of the fuel is deprived of moisture and the flame temperature decreases. The amount of NOx generated decreases. Moreover, since the flow rate of the turbine working fluid increases due to the addition of moisture, the flame temperature also decreases and the amount of NOx generated decreases when the fuel decreases in order to keep the rotational speed constant.

  Further, since the amount of recovered heat in the regenerator is reduced due to a decrease in the temperature of the flame combusted in the gas turbine combustor, the temperature of the flame is also reduced due to a decrease in the combustion air temperature, and the amount of NOx generated is reduced.

  By starting the addition of moisture in this way, (1) increase in moisture, (2) decrease in fuel, and (3) decrease in air temperature simultaneously advance the flame temperature, so that the amount of NOx generated decreases. On the contrary, the stability of the flame becomes worse.

  Therefore, if the distribution of air to be supplied to the gas turbine combustor is set in consideration of moisture addition in advance, the premixing section at the head of the gas turbine combustor will prevent the flame from blowing out under high humidity conditions. Or the air flow rate supplied to a coaxial jet part can be set appropriately.

  However, in the gas turbine combustor in which the distribution of air to be supplied to the gas turbine combustor is set in this way, the flame temperature becomes high contrary to the above before the start of moisture addition, so that the stability of the flame is ensured. However, the amount of NOx generated tends to increase.

  That is, in the high-humidity air-utilizing gas turbine, a large change in conditions occurs in the NOx generation and flame stability of the gas turbine combustor before and after the start of moisture addition. Further, it is considered that there is a delay until the water is actually added to the combustion air when the gas turbine is increased due to valve control or the volume of the system after the start of water addition.

  Further, it is considered that there is a delay before the humidity of the combustion air decreases for the same reason when the gas turbine is loaded. Control means that stably burns the gas turbine combustor with low NOx is also required against such a change in conditions.

  Therefore, as disclosed in Japanese Patent Application Laid-Open No. 2008-175098, a part of the combustion part of the gas turbine combustor having a plurality of combustion parts to which fuel is individually supplied is held more flame than the other combustion parts. Combustion section (combustion section with air holes that give a swirl component to the air flow) with excellent heat resistance, and the combustion gas temperature in the combustion section with excellent flame holding performance is increased for a predetermined period after the start of humidification. Combustion stability after humidification can be ensured by controlling the fuel by setting the ratio of the fuel supplied to the combustion section with excellent flame-holding property so that the combustion gas temperature is higher than the start temperature. it can.

  In the case where the stability of combustion is ensured by applying the technology of the control device as disclosed in Japanese Patent Application Laid-Open No. 07-189743 to such a change in humidity, the moisture in the compressed air is reduced. It is conceivable to measure and control the fuel flow rate based on the measured value.

  However, the air at the outlet of the humidifier is at a high temperature of about 100 ° C. under a saturated condition, and when a humidity sensor is installed at the outlet of the humidifier, there is a possibility that the humidity measurement by the humidity sensor has a large error. In addition, although the air at the regenerator outlet is not saturated, it has a high temperature of 450 ° C. to 650 ° C. When the humidity sensor is installed, there is a problem that the humidity sensor at the regenerator outlet requires high heat resistance.

  Therefore, in a high-humidity air-utilizing gas turbine plant, low NOx and combustion stability are reduced against changes in combustion air humidity that cause significant changes in NOx generation and combustion stability of the combustor after the start of moisture addition. A compatible gas turbine combustor control means is required.

  It is an object of the present invention to provide a gas turbine in the event of a transient condition change to NOx generation and flame stability of a gas turbine combustor after the start of moisture addition to the humidifier of a high humidity air-utilizing gas turbine. It is an object of the present invention to provide a fuel control method and a fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine capable of stably combusting the combustor with low NOx.

A fuel control method for a gas turbine combustor for a gas turbine using high-humidity air according to the present invention includes a compressor, and a gas turbine combustor that generates combustion gas by burning fuel using compressed air compressed by the compressor. A turbine driven by combustion gas generated in the gas turbine combustor, a humidifier that humidifies the compressed air that is compressed by the compressor and supplied to the gas turbine combustor, and water that is supplied to the humidifier A gas turbine combustor for a high-humidity air-utilizing gas turbine equipped with a regenerative heat exchanger that heats the exhaust gas with exhaust gas exhausted from the turbine, wherein the gas turbine combustor includes a plurality of fuel nozzles for supplying fuel, Combustion that has a plurality of combustion sections configured with a plurality of air flow paths that supply combustion air, and that has better flame holding properties than some of the other combustion sections in some of the plurality of combustion sections Forming part In the fuel control method for a gas turbine combustor, the compressed air obtained by estimating the fuel ratio setting for supplying fuel to the combustion section having excellent flame holding properties from the internal temperature of the humidifier and the internal pressure of the humidifier And controlling the flow rate of the fuel supplied to the plurality of combustion portions of the gas turbine combustor.
A fuel control method for a gas turbine combustor for a high-humidity air-utilizing gas turbine according to the present invention includes a compressor and gas turbine combustion that generates fuel by burning fuel using compressed air compressed by the compressor. , A turbine driven by combustion gas generated in the gas turbine combustor, a humidifier that humidifies compressed air that is compressed by the compressor and supplied to the gas turbine combustor, and supplies the humidifier A gas turbine combustor for a high-humidity air-utilizing gas turbine having a regenerative heat exchanger for heating water with exhaust gas exhausted from the turbine, wherein the gas turbine combustor includes a plurality of fuel nozzles for supplying fuel And a plurality of combustion parts that are formed in an air hole plate so as to be coaxial with the fuel nozzle and supply combustion air, and the plurality of combustion parts installed Of these, the fuel control of the gas turbine combustor in which the combustion part located on the inner peripheral side of the air hole plate forms a combustion part having better flame holding properties than the other combustion parts located on the outer peripheral side of the air hole plate In the method, the fuel ratio for supplying fuel to the combustion section having excellent flame holding properties is set based on the air humidity of the compressed air estimated from the internal temperature of the humidifier and the internal pressure of the humidifier. And controlling the flow rate ratio of the fuel supplied to the plurality of combustion portions of the gas turbine combustor.

A fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine according to the present invention includes a compressor and a gas turbine combustor that generates combustion gas by burning fuel using compressed air compressed by the compressor. A turbine driven by combustion gas generated in the gas turbine combustor, a humidifier that humidifies the combustion air compressed by the compressor and supplied to the gas turbine combustor, and the humidifier A high-humidity air-utilizing gas turbine having a regenerative heat exchanger for heating water with exhaust gas exhausted from the turbine, wherein the gas turbine combustor supplies a plurality of fuel nozzles for supplying fuel and combustion air A plurality of combustion sections configured with a plurality of air flow paths, and forming a combustion section having better flame holding properties than the other combustion sections in some of the plurality of installed combustion sections Gas turbine A fuel control apparatus for a burn unit, a fuel control system for supplying fuel to a plurality of the combustion section of the gas turbine combustor,
Bias for calculating the bias amount of the fuel ratio supplied to the combustion part of the gas turbine combustor having excellent flame holding properties based on the combustion air humidity estimated from the internal air temperature of the humidifier and the internal pressure of the humidifier A plurality of combustion units of the gas turbine combustor, comprising: a computing unit; and a fuel flow rate ratio setting unit that calculates a fuel ratio to be supplied to the combustion unit having excellent flame holding properties based on an output of the bias computing unit. It is characterized by controlling the flow rate of the supplied fuel.

The fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine according to the present invention is a gas turbine combustion that generates a combustion gas by burning fuel using compressed air compressed by the compressor. , A turbine driven by the combustion gas generated in the gas turbine combustor, a humidifier that humidifies the combustion air compressed by the compressor and supplied to the gas turbine combustor, and the humidifier A high-humidity air-utilizing gas turbine having a regenerative heat exchanger for heating water to be exhausted with exhaust gas exhausted from the turbine, wherein the gas turbine combustor includes a plurality of fuel nozzles for supplying fuel, and the fuel nozzle And a plurality of air holes configured with a plurality of air holes for supplying combustion air formed on the air hole plate so as to be coaxial with the air hole plate. In the fuel control device for a gas turbine combustor, in which a combustion portion having a flame holding property superior to other combustion portions located on the outer peripheral side of the air hole plate is formed in the combustion portion located on the inner peripheral side of the gas hole plate. A fuel control device that supplies fuel to a plurality of combustion sections of a turbine combustor is a gas having excellent flame holding properties based on combustion air humidity estimated from the internal air temperature of the humidifier and the internal pressure of the humidifier. A bias calculator for calculating the bias amount of the fuel ratio supplied to the combustion section of the turbine combustor;
A fuel flow rate ratio setting device for calculating a fuel ratio supplied to the combustion section having excellent flame holding properties based on an output of the bias calculator, and a fuel flow ratio setting device for supplying fuel to the plurality of combustion sections of the gas turbine combustor; It is characterized by controlling the flow rate ratio.

  In accordance with the present invention, when a transient condition change occurs in the NOx generation and flame stability of the gas turbine combustor after the start of moisture addition to the humidifier of the high humidity air-utilizing gas turbine, A fuel control method and a fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine capable of stably combusting the combustor with low NOx can be realized.

1 is a system diagram showing a schematic configuration of a high-humidity air-utilizing gas turbine equipped with a gas turbine combustor according to a first embodiment of the present invention. 1 is a partial structural diagram showing the configuration of a fuel nozzle installed in a gas turbine combustor that is a first embodiment of the present invention. The front view which shows the air hole plate which comprises the combustion part installed in the gas turbine combustor of 1st Example shown in FIG. The characteristic view showing an example of the operating method of the high-humidity air utilization gas turbine provided with the gas turbine combustor of 1st Example of this invention. The characteristic view showing another example of the operating method of the high-humidity air utilization gas turbine provided with the gas turbine combustor of 1st Example of this invention. The control block diagram which shows the structure of the fuel control apparatus by the gas turbine combustor of 1st Example of this invention. The system diagram which shows schematic structure of the high-humidity air utilization gas turbine provided with the gas turbine combustor which is 2nd Example of this invention. The characteristic view showing an example of the operating method of the high-humidity air utilization gas turbine provided with the gas turbine combustor of 2nd Example of this invention. The control block diagram which shows the structure of the fuel control apparatus by the gas turbine combustor of 2nd Example of this invention. The system diagram which shows schematic structure of the high-humidity air utilization gas turbine provided with the gas turbine combustor which is 3rd Example of this invention. The characteristic view showing an example of the operating method of the high humidity air utilization gas turbine provided with the gas turbine combustor of 3rd Example of this invention. The characteristic view showing other examples of the operating method of the high humidity air utilization gas turbine provided with the gas turbine combustor of the 3rd example of the present invention. The control block diagram which shows the structure of the fuel control apparatus by the gas turbine combustor of 3rd Example of this invention.

  A fuel control method and a fuel control device for a gas turbine combustor which is an embodiment of the present invention installed in a high-humidity air-utilizing gas turbine will be described below with reference to the drawings.

  A fuel control method and a fuel control apparatus for a gas turbine combustor according to a first embodiment of the present invention installed in a high-humidity air-utilizing gas turbine will be described with reference to FIGS.

  FIG. 1 is a system diagram showing the overall configuration of a high-humidity air-utilizing gas turbine in which a gas turbine combustor according to a first embodiment of the present invention is installed.

  In FIG. 1, a high-humidity air-utilizing gas turbine for power generation includes a compressor 1 that compresses air, and a gas turbine combustor that generates fuel by burning fuel using the compressed air compressed by the compressor 1. 2, a turbine 3 driven by combustion gas generated in the gas turbine combustor 2, a humidifier 4 that humidifies the compressed air that is compressed by the compressor 1 and supplied to the gas turbine combustor 2, The regenerative heat exchanger 5 is configured to heat the water supplied to the humidifier 4 with the exhaust gas exhausted from the turbine 3, and the generator 20 is rotated by the output of the turbine 3 to obtain electric power.

  The gas turbine combustor 2 is stored in a combustor casing 7 and a combustor cover 8. A fuel nozzle 9 is installed at the head of the gas turbine combustor 2, and a substantially cylindrical combustor liner 10 that separates combustion air and combustion gas is grounded downstream of the fuel nozzle 9. .

  The high-humidity air-utilizing gas turbine is provided with an intake spray device 27 that sprays water 300 onto the gas turbine intake air 100 at the inlet of the compressor 1. The water 300 supplied to the intake spray device 27 is water 300 that has been subjected to water treatment by the water purification device 26 and whose flow rate has been adjusted by the spray water amount control valve 310.

  Then, the high-pressure air 102 obtained by compressing the suction air 101 (atmospheric pressure) after the water 300 is sprayed by the intake spray device 27 flows through the gap between the transition piece 12 and the transition piece flow sleeve 13, and the transition piece. 12 is convectively cooled to become extracted air 103.

  The extracted air 103 is cooled to near 100 ° C. by the air cooler 28 to become the humidifier inflow air 110 and is supplied to the humidifier 4.

  The humidifier inflow air 110 is added with moisture in the humidifier 4 to become humidified air 104. As a method for humidifying air, humidification by a wet wall tower or a humidification tower is known.

  In the upper part of the humidifier 4, a thermometer for measuring the internal temperature 500 of the humidifier and a pressure gauge for measuring the internal pressure 600 of the humidifier are installed in order to monitor the soundness of the gas turbine using the high humidity air. Is done.

  The humidified air 104 to which moisture has been added by the humidifier 4 is guided to the regenerative heat exchanger 5, and is heated by the heat exchange with the exhaust gas 107 exhausted from the turbine 3 in the regenerative heat exchanger 5, and the high-temperature air 105. It is injected into the combustor casing 7 of the gas turbine combustor 2.

  The air flowing in the combustor casing 7 in the gas turbine combustor 2 flows through the generally annular space outside the combustor liner 10 toward the combustor head, and is used for convective cooling of the combustor liner 10 on the way. Is done.

  Further, part of the high-temperature air 105 flows into the combustor liner 10 from the cooling holes provided in the combustor liner 10 and is used for film cooling. The remaining high-temperature air 105 (36 in the A portion in the figure) flows into the combustor liner 10 through an air hole 32 to be described later, is used for combustion together with the fuel ejected from the fuel nozzle 31, and the high-temperature combustion gas 106. Is sent to the turbine 3.

  The low-pressure exhaust gas 107 discharged from the turbine 3 after working in the turbine 3 recovers the thermal energy held by the exhaust gas 107 in the regenerator 5 and then recovers the water located downstream of the regenerator 5. After passing through the device 24, the exhaust gas is exhausted from the exhaust tower 25 to the atmosphere as low-temperature exhaust gas 109.

  Further, the water in the exhaust gas 108 is recovered by the water recovery device 24 on the downstream side of the regenerator 5. In this figure, a method of collecting water by spraying water on the flue and aggregating and dropping the water in the exhaust gas 108 is adopted as a method of water recovery.

  The driving force obtained by the turbine 3 driven by the high-temperature combustion gas 106 is transmitted to the compressor 1 and the generator 20 connected to the turbine 3 through the shaft 21. A part of the driving force is used to pressurize the suction air by rotating the compressor 1. Further, the generator 20 converts this driving force into electric power.

  The water recovered from the bottoms of the water recovery device 24 and the humidifier 4 is reused as spray water to the water recovery device 24 or humidified water to the humidifier 4.

  The power generation amount MW of the generator 20 that is the output of the high-humidity air-utilizing gas turbine for power generation is controlled by opening and closing the fuel flow rate adjusting valves 211 to 214 that adjust the fuel flow rate supplied to the gas turbine combustor 2. On the other hand, the amount of humidification to the air supplied to the gas turbine combustor 2 is controlled by opening / closing a humidifier water supply valve 312 that adjusts the amount of humidified water to the humidifier 4.

  2 and 3 are a partial sectional view showing the structure of the fuel nozzle 9 constituting the combustion section installed in the gas turbine combustor 2 according to the first embodiment of the present invention, and a front view showing the air hole plate 33. FIG. It is.

  In the gas turbine combustor 2 of the present embodiment, as shown in FIGS. 2 and 3, a large number of fuel nozzles 31 arranged in an annular shape are attached to the fuel nozzle header 30 of the combustor cover 8. A structure in which an air hole plate 33 having a large number of annularly arranged air holes 32 forming an air flow path corresponding to each of the fuel nozzles 31 is attached to the combustor cover 8 via a support 34. It has become.

  The plurality of fuel nozzles 31 and the plurality of air holes 32 respectively installed corresponding to the fuel nozzles 31 are arranged so as to be substantially concentric with an annular shape. As shown, a coaxial jet of a fuel jet 35 at the center of the air hole 32 formed in the air hole plate 33 and an air jet 36 flowing into the air hole 32 around the fuel jet 35 is formed. ing.

  Due to the coaxial jet structure described above, the fuel-air is not mixed in the air hole 32, so that the fuel is not ignited even when the combustion air is hot like the high-humidity air-utilizing gas turbine. A highly reliable gas turbine combustor 2 can be obtained without melting the hole plate 33.

  Further, by forming a large number of such coaxial jets, the interface between the fuel and air is increased and mixing is promoted, so that the amount of NOx generated in the gas turbine combustor 2 can be suppressed.

  FIG. 3 is a front view of the air hole plate 33 constituting the gas turbine combustor 2 of this embodiment as viewed from the downstream side of the combustor. In the gas turbine combustor 2 of the present embodiment, a large number of air holes 32 (and a fuel nozzle 31 that is paired with the air holes 32 (not shown)) are radially outer peripheral sides of the air hole plate 33. Eight annular air hole arrays are arranged concentrically on the side.

  As for the burner forming the combustion part of the gas turbine combustor 2, the four rows (first row to fourth row) on the center side are the F1 burner forming the combustion portion of the first group (F1), and the fifth row is the first row. The F2 burner forming the second group (F2) combustion part, the outer two rows (sixth and seventh rows) are the F3 burner forming the third group (F3) combustion part, and the outermost periphery (eighth row) are F4 burners forming the combustion part of the fourth group (F4) are divided into groups, and as shown in FIG. 2, flanges (41 to 41) provided on the header 30 for each group of F1 burners to F4 burners. 44) The fuel systems are divided into groups so that fuel can be supplied from the fuel nozzle 31 through 44).

  By adopting such a fuel system grouping structure, it becomes possible to perform fuel staging in which the number of fuel nozzles that supply fuel is changed stepwise in response to changes in the flow rate of fuel supplied to the gas turbine combustor 2. Combustion stability of the gas turbine combustor 2 during partial load operation is enhanced and NOx reduction is possible.

  Further, the air holes 32 of the air hole plate 33 that constitutes the F1 burner forming the four central rows (F1) of the combusting section are angled in the pitch circle tangential direction (α ° in FIG. 3, 15 ° in this embodiment). ), The entire air flow flowing down the air hole 32 is swirled, and the flame is stabilized by the generated circulating flow.

  In the F2 burner to F4 burner disposed on the outer peripheral side of the F1 burner, the flame is stabilized by the combustion heat of the central F1 burner. Therefore, when humidification is started in the high-humidity gas turbine and the humidity of the combustion air increases, the flow rate of fuel supplied to the F1 burner of the gas turbine combustor 2 is increased, and the locally high-temperature portion is reduced. By providing, the combustion stability of F1 flame improves.

  Although the fuel flow rate of the burners after the F2 burner is decreased by the increase in the F1 fuel, the flame is stabilized by the combustion heat of the F1 burner, so that the combustion stability is ensured as the whole burner.

  An example of the operation method of the high-humidity air-utilizing gas turbine to which the fuel control method and fuel control device of the gas turbine combustor 2 of the present embodiment are applied will be described with reference to the characteristic diagrams shown in FIGS. .

  The horizontal axis of the characteristic diagram of the operation method of the high-humidity air-utilizing gas turbine in FIG. 4 is the time from the start of startup, and the vertical axis is the rotational speed, power generation amount, air flow rate, humidifier supply water amount 301, humidified air 104 from the top. The humidity and the humidifier internal temperature 500 are respectively shown.

  Also, the horizontal axis of the operation method of the high-humidity air-utilizing gas turbine in FIG. 5 is the time from the start of the start as in FIG. 4, the vertical axis is the combustion temperature from the top, the total fuel flow rate, and fuel to the F1 burner to F4 burner. It is a schematic representation of the individual fuel flow rate (F1 flow rate to F4 flow rate) of each fuel system to be supplied.

  4 and 5, the period a is the speed increase period from the start to the rated speed, the period b is the load increasing period during the start of the gas turbine, and the period c is the load after the end of the start. Represents the follow-up operation period. The increased load period b is divided into a first moisture-free addition period b1, a moisture addition amount change period b2, and a moisture addition amount constant period b3.

  In the operation method of the gas turbine combustor 2 by the fuel control device of the gas turbine combustor 2 of the present embodiment, first, the gas turbine combustor at the time of ignition and acceleration with a relatively small fuel flow rate according to a command from the control device 400. Operation is performed by burning only the F1 burner located on the axial center side of No. 2 (that is, supplying fuel only to the fuel system 201 in FIG. 2), and the speed is increased to near the rated load no-load condition. This single combustion of the F1 burner will be referred to as ¼ mode in the following description.

  Next, in the subsequent load increase process (period b), fuel is supplied to the F2 burner installed on the outer peripheral side of the F1 burner of the gas turbine combustor 2, and the operation is performed at F1 + F2. That is, fuel is supplied to the fuel systems 201 and 202, and each fuel flow rate is adjusted by adjusting the opening degree of the flow control valves 211 and 212 installed in the fuel systems 201 and 202, respectively, according to a command from the control device 400. Control. This time is called a 2/4 mode.

  Next, a state in which fuel is supplied to the fuel system 203 for supplying fuel to the F3 burner installed on the outer peripheral side of the F2 burner of the gas turbine combustor 2 and the F3 burner is ignited is referred to as a 3/4 mode. In the process so far, moisture has not been added to the humidifier 4 of the high-humidity air-utilizing gas turbine (b1). That is, the humidifier water supply valve 311 for adjusting the flow rate of water supplied to the humidifier 4 of the high-humidity air utilization gas turbine shown in FIG. 1 is fully closed, and is regenerated by the opening degree of the humidifier bypass valve 312. The amount of water flowing through the feed water superheater 12 installed on the downstream side of the heat exchanger 5 is controlled.

  Further, the increase in the fuel flow rate during this period is achieved by adjusting the opening degree of the flow rate control valves 211, 212, and 213 so that the gas turbine power generation amount increases according to the load increase rate determined in the start-up plan of the gas turbine. The fuel flow rate supplied to the F2 burner and the F3 burner is controlled. The fuel flow distribution of each fuel system 201 to 203 supplied to the F1 burner, F2 burner, and F3 burner is a ratio determined so that the combustion of the gas turbine combustor 2 is stable and the generated NOx is minimized. Supplied.

  In the fuel control method and fuel control apparatus for the gas turbine combustor 2 of the present embodiment, the addition of moisture to the humidifier 4 of the high-humidity air-utilizing gas turbine is started in this 3/4 mode. In response to the humidification start command, the air cooler side humidifier water supply valve 312 is opened, and water at a flow rate corresponding to the opening degree is injected into the humidifier 4 (period b2). At the same time, the air cooler side humidifier bypass valve 313 is controlled so that the amount of water flowing through the air cooler 28 becomes a predetermined value, and the opening degree is decreased and finally the fully closed state.

  After that, the amount of water flowing through the air cooler 28 is adjusted to a predetermined value by controlling the opening degree of the air cooler side humidifier water supply valve 312 (periods b2 to b3).

  At this time, the fuel flow rate is controlled so that the gas turbine power generation amount increases in accordance with the load increase rate determined in the gas turbine startup plan. Among them, since the F1 fuel plays a major role in ensuring combustion stability, it is necessary to set the ratio of the F1 flow rate to the total fuel flow rate to be larger after the start of humidification than before the start of humidification.

  Judgment based on the F1 combustion temperature is effective in determining the optimum F1 flow rate ratio for ensuring combustion stability. The combustion temperature can be calculated from the combustion air temperature, the combustion air humidity, and the ratio of fuel flow to air flow (fuel / air ratio).

  From the experimental results of the inventors' high-humidity air-utilizing gas turbine pilot plant, it is known that the humidified air 104 is saturated. Therefore, in the fuel control device 400 of the gas turbine combustor 2 of the present embodiment, the humidified air 104 is saturated at the humidifier internal air temperature 500, so the humidity of the humidified air 104 is obtained indirectly. If the pressure of the humidified air 104 is equal to or higher than the saturated water vapor pressure, the combustion air humidity is obtained from the following equation (1).

Hm (vol%) = P _sat / P _total × 100: (1)
Here, Hm (vol%): humidity, P _total : humidifier internal pressure 600, P _sat : saturated water vapor pressure. The saturated water vapor pressure can be obtained from the vapor table.

  That is, based on the measured values of the humidifier internal air temperature 500 and the humidifier internal pressure 600 by the saturation humidity calculator included in the F1 bias calculator 404 constituting the fuel control device 400, the calculation formula of the above formula (1) is obtained. Used to calculate the combustion air humidity.

  Since the F1 bias calculator 404 can calculate the combustion temperature from the calculated combustion air humidity, the calculated combustion temperature is compared with the F1 combustion temperature necessary for ensuring the combustion stability of the gas turbine combustor 2. Thus, the F1 bias 415 that is the F1 bias flow rate necessary for ensuring the combustion stability can be obtained.

  The calculation method of the combustion air humidity by the F1 bias calculator 404 in the fuel control device 400 of the gas turbine combustor 2 of the present embodiment is the humidifier supply supplied to the humidifier 4 by the humidifier water supply amount control valve 312. In addition to the period during which the amount of water 301 is constant (period b3 in FIG. 4), the humidifier water supply amount 301 changes from the fully closed state to the specified opening degree until the humidifier water supply amount control valve changes to several tens of seconds. Is effective for calculating the combustion air humidity even during a period of several minutes (period b2 in FIG. 4).

  Therefore, the combustion stability of the gas turbine combustor 2 is calculated by calculating an appropriate F1 bias 415 by the F1 bias calculator 404 even for a transient humidity change of the combustion air due to a change in the humidifier water supply amount 301. Can be secured.

  When the power generation amount or the turbine exhaust gas temperature reaches a predetermined amount, the start of the high-humidity gas turbine is completed, and thereafter, the load follows the load by increasing / decreasing the fuel flow rate according to the increase / decrease of the load (period c). . During high load operation, the fuel flow rate of the F4 burner installed on the outermost periphery of the gas turbine combustor 2 is mainly increased or decreased.

  At this time, the fuel / air mixture supplied to the F4 burner is mixed with the combustion gas of the F1 to F3 burner and becomes high temperature, so that the oxidation reaction of the fuel proceeds and high combustion efficiency can be obtained.

  In addition, since the air distribution is set so that the temperature after the completion of combustion becomes equal to or lower than the temperature at which NOx generation becomes significant, combustion with almost zero NOx generation from the F4 burner becomes possible. In addition, since the reaction is completed even with a very small amount of fuel introduced into the F4 burner, continuous fuel switching is possible, improving operability.

  An example of the control block of the fuel control device 400 that controls the fuel of the gas turbine combustor 2 of the present embodiment is shown in FIG.

  As shown in FIG. 6, the fuel control device 400 for controlling the fuel of the gas turbine combustor 2 of the present embodiment includes a subtractor 401, a fuel flow rate controller 402, a fuel flow rate ratio setting unit 403, and an F1 bias setting. 404, database 405, and actual fuel controller 407.

  In the fuel control device 400, the subtractor 401 obtains the difference between the load command MWD given so as to follow a predetermined power generation amount increase rate and the actual power generation amount MW, and the load command MWD obtained by the subtractor 401 is obtained. The fuel flow rate command value 410 to be supplied to the gas turbine combustor 2 is calculated by the fuel flow rate controller 402 based on the difference between the actual power generation amount MW.

  Based on the fuel flow rate command value 410 calculated by the fuel flow rate controller 402, each fuel flow rate ratio (411 to 414) of the fuel supplied to the F1 burner to F4 burner installed in the gas turbine combustor 2 by the fuel flow rate ratio setting unit 403 ) Respectively.

  On the other hand, in the F1 bias calculator 404, the equation (1) is calculated by the saturation humidity calculator included in the F1 bias calculator 404 based on the measured values of the humidifier internal air temperature 500 and the humidifier internal pressure 600. Use to calculate the saturation humidity of the combustion air.

  Next, the F1 bias calculator 404 calculates a combustion air temperature corresponding to the calculated saturation humidity of the combustion air, and is necessary for ensuring the calculated combustion air temperature and the combustion stability of the gas turbine combustor 2. By comparing the F1 combustion temperature, the F1 bias 415, which is the F1 bias flow rate necessary for ensuring combustion stability, is obtained.

  The database 405 includes steam table data necessary for obtaining the saturation humidity of combustion air, and F1 fuel flow data necessary for ensuring combustion stability of F1 with respect to combustion air temperature, combustion air humidity, and combustion air flow rate. To a value corresponding to the saturation humidity is provided to the F1 bias calculator 404 as a bias value.

  In the fuel flow rate ratio setting unit 403, the fuel flow rate command value 410 calculated by the fuel flow rate controller 402 is used as an input value, and the F1 burner to F4 burner installed in the gas turbine combustor 2 are referred to while referring to the value of the F1 bias 415. Each fuel flow rate ratio (411 to 414) of the supplied fuel is calculated.

  The actual fuel controller 407 receives the fuel flow rate ratios (411 to 414) of the F1 burner to F4 burner and the fuel flow rate command value 410 calculated from the fuel flow rate command value 410, and the flow rate or valve of each combustion system of the F1 to F4 burners. Opening of the fuel flow rate control valves 211 to 214 that respectively calculate and output the opening degrees (211 to 214) and adjust the flow rate of the fuel supplied to the F1 burner to the F4 burner installed in the gas turbine combustor 2. It is configured to control the degree.

  Thus, the fuel control device 400 of the gas turbine combustor 2 according to the present embodiment shown in FIG. 6 can increase the F1 flow rate during the period b2 indicated by the solid line in the characteristic diagram of FIG. Here, the dotted line indicating the decrease in the F1 flow rate in the period b2 is the F1 flow rate when the F1 bias 415 according to the present embodiment is not applied. In this case, the combustion stability of the gas turbine combustor 2 is reduced due to the F1 combustion temperature being decreased. Will result in a situation where

  In contrast, the F1 bias 415 calculated by the F1 bias calculator 404 in the fuel control device 400 of the gas turbine combustor 2 according to this embodiment is input to the fuel flow rate ratio setting unit 403 and supplied to the gas turbine combustor 2. By controlling the fuel, as shown by the solid line in FIG. 5, when the F1 flow rate in the period b2 is increased, the F1 combustion temperature can be maintained at a predetermined temperature. As a result, the combustion stability of the gas turbine combustor 2 can be maintained. Can be realized.

  In the calculation of the F1 bias calculator 404, the saturated humidity of the humidified air 104 is obtained even if the humidifier internal temperature 500 and the humidifier internal pressure 600 are substituted with the measured values of the temperature and pressure of the humidified air 104. Can do.

  In addition, there may be a case where there is a time delay until the water is actually added to the combustion air after the start of the water addition due to the volume held by the system such as the humidifier bypass valve 312 and the piping. At that time, the actual combustion air humidity is estimated in consideration of the first order lag with respect to the combustion air humidity obtained from the measured values of the humidifier internal temperature 500 and the humidifier internal pressure 600 by the calculation of the F1 bias calculator 404. For example, the NOx reduction of the gas turbine combustor 2 and the securing of combustion stability can be achieved at the same time.

  At the time of gas turbine descending load, it is considered that there is a delay until the combustion air humidity follows the humidifier supply water amount 301 in the humidifier 4 depending on the volume held by the system such as the piping. It is particularly effective to estimate the combustion air humidity.

  According to this embodiment, when a transient condition change occurs in the NOx generation and flame stability of the gas turbine combustor after the start of moisture addition to the humidifier of the high-humidity air-utilizing gas turbine, A fuel control method and a fuel control apparatus for a gas turbine combustor for a gas turbine using high humidity air that can stably burn the turbine combustor with low NOx can be realized.

  A fuel control method and a fuel control apparatus for a gas turbine combustor according to a second embodiment of the present invention installed in a high-humidity air-utilizing gas turbine will be described with reference to FIGS.

  The fuel control device of the gas turbine combustor of the present embodiment has the same basic configuration as the fuel control device of the gas turbine combustor of the first embodiment, so the description common to both is omitted. Only the differences will be described below.

  The difference between the F1 bias calculator 404 in the fuel control device 400 of the gas turbine combustor 2 of this embodiment and the fuel control device of the gas turbine combustor 2 of the first embodiment is that the measured value of the humidifier internal temperature 500 is different. Instead, the saturated humidity of the humidified air 104 is obtained from any one of the measured values of the humidifier supply water temperature 501, the humidifier circulating water temperature 502, and the humidifier inflow air temperature 503.

  In the high-humidity air-utilizing gas turbine, in order to ensure the soundness of the plant, measurement of the humidifier supply water temperature 501, the humidifier circulating water temperature 502, and the humidifier inflow air temperature 503 are essential items. The saturated humidity of the humidified air 104 is obtained from the temperature of each part.

  Further, even when the humidifier internal temperature 500 is measured, as a backup, the humidifier supply water temperature 501, the humidifier circulating water temperature 502, and the humidifier inflow air temperature 503 are used instead of the humidifier internal temperature 500. There is an advantage in that any one of the measured values can be used.

  FIG. 8 is a characteristic diagram showing an example of the operation method of the high-humidity air-utilizing gas turbine to which the fuel control method and fuel control device of the gas turbine combustor of the present embodiment is applied. In the characteristic diagram of FIG. FIG. 4 shows the humidity and the humidifier shown in the characteristic diagram of the operation method of the high-humidity air-utilizing gas turbine to which the fuel control method and fuel control device of the gas turbine combustor of the first embodiment shown in FIG. The internal temperature 500 (reprinted), the humidifier supply water temperature 501, the humidifier circulating water temperature 502, and the humidifier inflow air temperature 503 were compared side by side.

  According to the inventors' experiment using a pilot plant for a high-humidity air-utilizing gas turbine, in the operating method of the high-humidity air-utilizing gas turbine shown in FIGS. 4 and 5 of the first embodiment, a humidifier The supply water temperature 501, the humidifier circulating water temperature 502, and the humidifier inflow air temperature 503 were proportional to the temperature inside the humidifier 500 and time.

  An example of a control block of the fuel control device 400 that controls the fuel of the gas turbine combustor 2 of the present embodiment is shown in FIG.

  In the control block of the fuel control device 400 for controlling the fuel of the gas turbine combustor 2 of this embodiment shown in FIG. 9, the humidifier supply water temperature 501, the humidifier circulating water temperature 502, the increase Although it has the structure which added the function which estimates the humidifier internal temperature 500 'from the humidifier inlet air temperature 503, the other structure is the same as the control block of the fuel control apparatus 400 of 1st Example.

  According to the fuel control device 400 for controlling the fuel of the gas turbine combustor 2 of the present embodiment, the humidifier internal temperature 500 or the humidity increase in the database 405 is performed by the saturation humidity calculator included in the F1 bias calculator 404. Combustion air is generated by the humidifier tower internal air temperature 500 ′ estimated from any one of the heater supply water temperature 501, the humidifier circulating water temperature 502, and the humidifier inlet air temperature 503, and the humidifier internal pressure 600. As with the fuel control device 400 of the first embodiment, the gas turbine combustor after adding moisture to the humidifier 4 is calculated from the calculation result of the combustion air temperature calculated from the saturation humidity of the combustion air. In the characteristic diagram of FIG. 5 that secures the combustion stability of 2, an increase in the F1 flow rate during the period b2 indicated by the solid line can be realized.

  Further, the combustion stability of the gas turbine combustor 2 is also applied to a transient humidity change of combustion air due to a change in the humidifier water supply amount 301 supplied to the humidifier 4 as in the first embodiment. Can be secured.

  According to this embodiment, when a transient condition change occurs in the NOx generation and flame stability of the gas turbine combustor after the start of moisture addition to the humidifier of the high-humidity air-utilizing gas turbine, A fuel control method and a fuel control apparatus for a gas turbine combustor for a gas turbine using high humidity air that can stably burn the turbine combustor with low NOx can be realized.

  A fuel control method and a fuel control apparatus for a gas turbine combustor according to a third embodiment of the present invention installed in a high-humidity air-utilizing gas turbine will be described with reference to FIGS.

  Since the basic configuration of the gas turbine combustor control method and control device of the present embodiment is the same as that of the gas turbine combustor control method and control device of the first embodiment, a description common to both of them is given. Are omitted, and only the differences are described below.

  The fuel control device 400 of the gas turbine combustor 2 of the present embodiment is that the feed water heater 22 is installed downstream of the regenerative heat exchanger 5 that recovers heat from the gas turbine exhaust gas 107. This is different from the fuel control device of the combustor 2. The feed water heater 22 further recovers thermal energy from the exhaust gas 107 after passing through the regenerative heat exchanger 5 and heats the water supplied to the humidifier 4 to increase the thermal efficiency of the high humidity air-utilizing gas turbine. Has the advantage of improving.

  In the fuel control device 400 of the gas turbine combustor 2 of the present embodiment, the humidifier internal temperature 500, the humidifier supply water temperature 501, the humidifier circulating water temperature 502, the humidifier inflow air temperature 503, the air cooler. At least one point of the feed water temperature 504 on the side and the feed water temperature 505 on the feed water heater side and the humidifier internal pressure 600 are measured.

  A characteristic diagram showing an example of an operation method of a high-humidity air-utilizing gas turbine to which the fuel control method and the fuel control device of the gas turbine combustor 2 of the present embodiment are applied will be described with reference to FIGS.

  The horizontal axis of the characteristic diagram of FIG. 11 is the time from the start of the start as in the characteristic diagram of FIG. 4, and the vertical axis is the rotational speed, power generation amount, air flow rate, humidifier supply water amount from the top (humidification on the feed water heater side) Humidifier supply water amount 305), humidity of humidifier air 104, humidifier internal temperature 500, humidifier supply water temperature 501, humidifier circulating water temperature 502, humidifier The inflow air temperature 503, the supply water temperature 504 on the air cooler side, and the supply water temperature 505 on the feed water heater side are shown.

  Here, humidifier internal temperature 500, humidifier supply water temperature 501, humidifier circulating water temperature 502, humidifier inflow air temperature 503, air cooler side supply water temperature 504, feed water heater side supply water temperature 505 shows that the temperature changes in the same manner with respect to the time because it is known from the pilot plant experiment of the high-humidity air-utilizing gas turbine of the inventors.

  In addition, the horizontal axis of the characteristic diagram of FIG. 12 schematically represents the time from the start of startup as in the characteristic diagram of FIG. 11, and the vertical axis schematically represents the combustion temperature, fuel flow rate, and individual fuel flow rate of each of the F1 to F4 systems from the top. It is a thing. In addition, period a represents a speed increasing period from start to reach the rated speed, period b represents an increased load period during start of the gas turbine, and period c represents a load following operation period after the end of start. The increased load period b is divided into a first moisture-free addition period b1, a moisture addition amount change period b2, and a moisture addition amount constant period b3.

  Unlike the characteristic diagram showing the operation method of the high-humidity air-utilizing gas turbine in the case of the first embodiment, the moisture addition amount change period b2 is set in the humidifier 4 in the high-humidity air-utilizing gas turbine of the present embodiment. On the other hand, since two water supply systems that join and supply water are provided, the supply water 305 on the air cooler side is added after the supply water 303 on the water supply heater side is added. The flow of operation of the high-humidity air-utilizing gas turbine until the addition of moisture to the humidifier 4 is the same as in the first embodiment.

  In the operation method of the high-humidity air-utilizing gas turbine in the case of the present embodiment, in response to the humidification start command, the feed water heater-side humidifier feed valve 315 is first opened, and the feed water at a flow rate corresponding to the opening is supplied to the humidifier 4 Water is poured into the water. At the same time, the feed water heater bypass valve 314 is controlled so that the amount of water flowing through the feed water heater 22 becomes a predetermined value, and the opening degree is decreased and finally the fully closed state.

  Thereafter, the amount of water flowing through the feed water heater 22 is adjusted to a predetermined value by controlling the opening of the feed water heater side humidifier feed valve 315. Subsequently, the air cooler-side humidifier water supply valve 312 is opened, and water with a flow rate corresponding to the opening degree is injected into the humidifier 4.

  At the same time, the air cooler bypass valve 313 is controlled so that the amount of water flowing through the air cooler 28 becomes a predetermined value, while decreasing the opening degree and finally becomes a fully closed state. After that, the amount of water flowing through the air cooler 28 is adjusted to a predetermined value by controlling the opening degree of the air cooler side humidifier water supply valve 312 (periods b2 to b3).

  Also in this embodiment, in order to obtain the F1 fuel flow rate necessary for ensuring the combustion stability of the gas turbine combustor 2 after humidification by the humidifier 4, the F1 bias calculator 404 provided in the fuel control device 400 is used. The saturation humidity of the combustion air is obtained by a saturation humidity calculator. As described in the first embodiment, the humidity of the humidified air 104 can be obtained from the humidifier internal temperature 500 and the humidifier internal pressure 600.

  Alternatively, according to the fuel control device 400 for controlling the fuel of the gas turbine combustor 2 of the present embodiment, the humidifier supply water temperature 501, the humidifier circulating water temperature 502, the humidifier inlet air temperature 503, the air cooling. Saturated humidity inherent in the F1 bias calculator 404 provided in the fuel control device 400 in the same manner as in the second embodiment from one measured value of the water supply side water temperature 504 and the water supply heater side supply water temperature 505 Is used to estimate the humidifier internal temperature 500 ′, calculate the saturation humidity (combustion air humidity) of the humidified air 104 from the estimated humidifier internal temperature 500 ′ and the humidifier internal pressure 600, and calculate the combustion The combustion temperature may be calculated from the air humidity.

  As a result, similarly to the fuel control device 400 of the gas turbine combustor 2 of the first and second embodiments, the combustion stability of the gas turbine combustor 2 is ensured even after moisture is added to the humidifier 4. The increase in the F1 flow rate during the period b2 indicated by the solid line in the characteristic diagram of FIG.

  When the feed water heater 28 is provided as in the high-humidity air-utilizing gas turbine to which the fuel / fuel control device 400 of the gas turbine combustor 2 of the present embodiment is applied, in addition to the water temperature measurement location of the second embodiment, Fuel control is also possible by measuring the water temperature of the water supply system of the feed water heater 28, which is advantageous in that the choices of measurement points are widened.

  In the control block of the fuel control apparatus 400 for controlling the fuel of the gas turbine combustor 2 of this embodiment shown in FIG. 13, the humidifier internal temperature 500 or the humidifier supply water temperature 501 and the humidifier in the database 405 are used. A humidifier internal temperature 500 ′ estimated from any one of a circulating water temperature 502, a humidifier inlet air temperature 503, an air cooler side supply water temperature 504, and a feed water heater side supply water temperature 505, The saturation humidity of the combustion air is calculated by the humidifier internal pressure 600, and the calculation result of the combustion air temperature calculated from the saturation humidity of the combustion air is used similarly to the fuel control device 400 of the first embodiment and the second embodiment. Even after moisture is added to the humidifier 4, an increase in the F1 flow rate during the period b <b> 2 indicated by the solid line in the characteristic diagram of FIG. 5 that ensures the combustion stability of the gas turbine combustor 2 can be realized.

  Further, the gas turbine combustor is also applied to the transient humidity change of the combustion air due to the change of the humidifier water supply amount 301 supplied to the humidifier 4 in the same manner as in the first and second embodiments. 2 combustion stability can be secured.

  The operation method of the high-humidity air-utilizing gas turbine after reaching the period b3 is the same operation as in the first embodiment.

  In the present embodiment, the case where the fuel control device for the gas turbine combustor of the present embodiment is applied to the high-humidity air-utilizing gas turbine having the configuration including the air cooler 28 and the feed water heater 22 has been described. In the case of a configuration that does not include the air cooler 28 in the configuration, the same operation method of the high-humidity air-utilizing gas turbine is possible. In that case, in addition to the humidifier internal temperature 500, the humidity (combustion air humidity) of the humidified air 104 can be obtained by the humidifier circulating water temperature 502, the feed water heater side feed water temperature 505, and the humidifier feed water temperature 501. It ’s fine.

  According to this embodiment, when a transient condition change occurs in the NOx generation and flame stability of the gas turbine combustor after the start of moisture addition to the humidifier of the high-humidity air-utilizing gas turbine, A fuel control method and a fuel control apparatus for a gas turbine combustor for a gas turbine using high humidity air that can stably burn the turbine combustor with low NOx can be realized.

  The present invention is applicable to a fuel control method and a fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine.

  1: compressor, 2: combustor, 3: turbine, 4: humidifier, 5: regenerative heat exchanger, 7: combustor casing, 8: combustor cover, 9: fuel nozzle, 10: combustor liner, 11: liner flow sleeve, 12: transition piece, 13: transition piece flow sleeve, 20: generator, 21: shaft, 22: feed water heater, 23: flue, 24: water recovery device, 25: exhaust pipe, 26 : Water purification device, 27: Intake spray device, 28: Air cooler, 30: Fuel header, 31: Fuel nozzle, 32: Air hole, 33: Air hole plate, 35: Fuel jet, 36: Air jet, 51: F1 fuel flange, 52: F2 fuel flange, 53: F3 fuel flange, 54: F4 fuel flange, 100: gas turbine intake air (atmospheric pressure), 101: intake air (large Pressure), 102: high pressure air, 103: extraction air, 104: humidified air, 105: high temperature air, 106-109: exhaust gas, 110: humidifier inflow air, 200: fuel, 201: F1 fuel, 202: F2 Fuel: 203: F3 fuel, 204: F4 fuel, 210: Fuel cutoff valve, 211: F1 fuel control valve, 212: F2 fuel control valve, 213: F3 fuel control valve, 214: F4 fuel control valve, 300: Compressor Intake spray water, 301: Humidifier supply water, 302, 304: Bypass water, 303, 305: Supply water, 310: Spray water amount control valve, 312: Humidifier water supply control valve, 313: Humidifier bypass valve 314: Humidifier bypass valve, 315: Humidifier water supply control valve, 401: Subtractor, 402: Fuel flow controller, 403: Fuel flow ratio setting device, 404: F1 bias setting device, 405 Database, 407: Actual fuel flow controller, 410: Fuel flow command value, 411: F1 fuel ratio, 412: F2 fuel ratio, 413: F3 fuel ratio, 414: F4 fuel ratio, 415: F1 bias, 500: Humidification Internal temperature, 501: Humidifier supply water temperature, 502: Humidifier circulation water temperature, 503: Humidifier inflow air temperature, 504: Humidifier supply water temperature, 505: Humidifier supply water temperature, 600 : Humidifier internal pressure.

Claims (6)

A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine driven by the combustion gas generated by the gas turbine combustor, and a compressor that compresses High humidity air use comprising a humidifier that humidifies compressed air supplied to the gas turbine combustor and a regenerative heat exchanger that heats water supplied to the humidifier with exhaust gas exhausted from the turbine A gas turbine combustor for a gas turbine,
The gas turbine combustor is provided with a plurality of combustion sections each including a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air, and some of the plurality of combustion sections installed In the fuel control method of the gas turbine combustor, in which the combustion part has a combustion part having better flame holding properties than the other combustion parts,
The setting of the fuel ratio for supplying fuel to the combustion portion having excellent flame holding properties is set based on the air humidity of the compressed air estimated from the internal temperature of the humidifier and the internal pressure of the humidifier, A fuel control method for a gas turbine combustor for a high-humidity air-utilizing gas turbine, comprising controlling a flow rate of fuel supplied to a plurality of combustion portions of the gas turbine combustor. A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine driven by the combustion gas generated by the gas turbine combustor, and a compressor that compresses High humidity air use comprising a humidifier that humidifies compressed air supplied to the gas turbine combustor and a regenerative heat exchanger that heats water supplied to the humidifier with exhaust gas exhausted from the turbine A gas turbine combustor for a gas turbine,
The gas turbine combustor includes a combustion section including a plurality of fuel nozzles for supplying fuel and a plurality of air holes for supplying combustion air formed in an air hole plate so as to be coaxial with the fuel nozzle. Among the plurality of installed combustion parts, the combustion part having a better flame holding property than the other combustion parts located on the outer peripheral side of the air hole plate in the combustion part located on the inner peripheral side of the air hole plate In the fuel control method of the gas turbine combustor forming
The setting of the fuel ratio for supplying fuel to the combustion portion having excellent flame holding properties is set based on the air humidity of the compressed air estimated from the internal temperature of the humidifier and the internal pressure of the humidifier, A fuel control method for a gas turbine combustor for a high-humidity air-utilizing gas turbine, comprising controlling a flow rate of fuel supplied to a plurality of combustion portions of the gas turbine combustor. In the fuel control method of the gas turbine combustor for the high-humidity air-utilizing gas turbine according to claim 1 or 2,
From the temperature of the supply water supplied to the humidifier, the water temperature of the circulation system for resupplying the surplus water of the humidifier to the humidifier, and the temperature of the air flowing into the humidifier, the inside of the humidifier Estimate the air temperature,
From the estimated air temperature inside the humidifier and the internal pressure of the humidifier, the humidity of the combustion air is estimated,
A gas turbine for a high-humidity air-utilizing gas turbine, characterized in that a fuel ratio supplied to the combustion section having excellent flame holding properties installed in a gas turbine combustor is controlled based on the estimated humidity of combustion air. Combustor fuel control method. A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine driven by the combustion gas generated by the gas turbine combustor, and a compressor that compresses And a humidifier that humidifies the combustion air supplied to the gas turbine combustor and a regenerative heat exchanger that heats the water supplied to the humidifier with the exhaust gas exhausted from the turbine. A gas turbine,
The gas turbine combustor is provided with a plurality of combustion sections each including a plurality of fuel nozzles for supplying fuel and a plurality of air flow paths for supplying combustion air, and some of the plurality of combustion sections installed In the fuel control device of the gas turbine combustor, in which the combustion part is formed in the combustion part with a better flame holding property than the other combustion parts,
A fuel control device that supplies fuel to a plurality of combustion sections of the gas turbine combustor,
Bias for calculating the bias amount of the fuel ratio supplied to the combustion part of the gas turbine combustor having excellent flame holding properties based on the combustion air humidity estimated from the internal air temperature of the humidifier and the internal pressure of the humidifier An arithmetic unit;
A fuel flow rate ratio setting device for calculating a fuel ratio supplied to the combustion section having excellent flame holding properties based on an output of the bias calculator, and a fuel flow ratio setting device for supplying fuel to the plurality of combustion sections of the gas turbine combustor; A fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine, wherein the flow rate ratio is controlled. A compressor, a gas turbine combustor that burns fuel using compressed air compressed by the compressor to generate combustion gas, a turbine driven by the combustion gas generated by the gas turbine combustor, and a compressor that compresses And a humidifier that humidifies the combustion air supplied to the gas turbine combustor and a regenerative heat exchanger that heats the water supplied to the humidifier with the exhaust gas exhausted from the turbine. A gas turbine,
The gas turbine combustor includes a combustion section including a plurality of fuel nozzles for supplying fuel and a plurality of air holes for supplying combustion air formed in an air hole plate so as to be coaxial with the fuel nozzle. Among the plurality of installed combustion parts, the combustion part having a better flame holding property than the other combustion parts located on the outer peripheral side of the air hole plate in the combustion part located on the inner peripheral side of the air hole plate In the fuel control device of the gas turbine combustor forming
A fuel control device that supplies fuel to a plurality of combustion sections of the gas turbine combustor,
Bias for calculating the bias amount of the fuel ratio supplied to the combustion part of the gas turbine combustor having excellent flame holding properties based on the combustion air humidity estimated from the internal air temperature of the humidifier and the internal pressure of the humidifier An arithmetic unit;
A fuel flow rate ratio setting device for calculating a fuel ratio supplied to the combustion section having excellent flame holding properties based on an output of the bias calculator, and a fuel flow ratio setting device for supplying fuel to the plurality of combustion sections of the gas turbine combustor; A fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine, wherein the flow rate ratio is controlled. The fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine according to claim 4 or 5,
A fuel control device that supplies fuel to a plurality of combustion sections of the gas turbine combustor,
The increase from the temperature of the supply water supplied to the humidifier as the bias calculator, the water temperature of the circulation system for resupplying the surplus water of the humidifier to the humidifier, and the temperature of the air flowing into the humidifier. Estimate the air temperature inside the humidifier, estimate the humidity of the combustion air from the estimated air temperature inside the humidifier and the internal pressure of the humidifier, and add it to the gas turbine combustor based on the estimated humidity of the combustion air. A fuel control device for a gas turbine combustor for a high-humidity air-utilizing gas turbine, wherein a bias amount of a fuel ratio supplied to the installed combustion portion having excellent flame holding properties is calculated.

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