JP2014105601A - Gas turbine combustor and method for operating the same - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of securing combustion stability and capable of stably switching fuel even when the composition of hydrogen-containing fuel is varied during switching from starting fuel to the hydrogen-containing fuel.SOLUTION: A gas turbine combustor includes: a burner having a plurality of fuel nozzles for injecting gas fuel to a combustion chamber on the downstream side, and an air hole plate disposed between the fuel nozzles and the combustion chamber and having a plurality of air holes for guiding the compressed air to the combustion chamber which are coaxially arranged with the fuel nozzles on a plurality of concentric circles; a starting fuel nozzle provided in an axial center of the burner and injecting starting fuel; and a control device for fetching a temperature and a heat generation amount of the gas fuel, and calculating a time change rate of a flow rate of the gas fuel and a time change rate of a flow rate of the starting fuel during switching of the fuel from the starting fuel to the gas fuel in a starting process, and outputting a flow rate command signal to a gas fuel flow rate control valve and a starting fuel flow rate control valve.

Description

  The present invention relates to a gas turbine combustor and an operation method thereof.

  In recent years, from the viewpoints of reducing power generation costs, effective use of resources, and prevention of global warming, effective use of hydrogen-containing fuels including hydrogen such as coke oven gas by-produced at steelworks and off-gas produced as a by-product at refineries To be considered.

For example, when a hydrogen-containing fuel is used in a gas turbine power plant, the hydrogen-containing fuel is effective as a measure for preventing global warming because carbon dioxide (Carbon Dioxide: CO ₂ ) emissions during combustion are small. In the integrated coal gasification combined cycle (IGCC), which generates gas by gasifying abundant resources, a system that collects and stores the carbon in the hydrogen-containing fuel supplied to the gas turbine. (Carbon Capture and Storage: CCS) has been established to further reduce CO ₂ emissions.

  On the other hand, since hydrogen contained in the hydrogen-containing fuel has a wide flammable range and a high combustion speed, there is a concern that a high-temperature flame is formed near the wall surface in the combustion chamber of the gas turbine and the reliability of the combustor is impaired. As a means for preventing the local formation of such a high-temperature flame, a method of dispersing the fuel and burning it uniformly in the combustion chamber is effective.

To enhance the dispersibility of the fuel to prevent formation of high-temperature flame, a method for reducing NO _X emissions, comprising a plurality of fuel nozzles and a plurality of air holes, the fuel flow, and formed around the fuel flow A combustor in which a plurality of burners for injecting an air flow into a combustion chamber is arranged is disclosed (for example, see Patent Document 1).

JP 2003-148734 A

  When the hydrogen-containing fuel described above is used as a fuel for a gas turbine, there is a concern that unburned hydrogen-containing fuel may be discharged from the combustor and stay in the turbine on the downstream side if ignition fails in the combustor. Is done. For this reason, in a gas turbine using a hydrogen-containing fuel, ignition is performed with a start-up fuel (for example, oil fuel) that does not contain hydrogen, and the start-up fuel is operated up to a predetermined partial load. It can be considered that the fuel is switched from fuel to hydrogen-containing fuel, and thereafter the load is increased to the rated load with the hydrogen-containing fuel and the operation is continued.

  By the way, the byproduct gas which is a hydrogen-containing fuel contains 30% to 60% of hydrogen, and the coal gasification gas contains 25% to 90% of hydrogen. Moreover, the composition of these hydrogen-containing fuels varies widely depending on the operating conditions and atmospheric conditions of the plant. For this reason, when the composition of the hydrogen-containing fuel changes widely during the switching from the starting fuel to the hydrogen-containing fuel, the state of the flame formed is greatly changed, and there is a concern that the combustion stability is lowered.

  The present invention has been made on the basis of the above-mentioned matters, and its purpose is to change the composition of the hydrogen-containing fuel during the switching of the gas turbine fuel from the starting fuel to the hydrogen-containing fuel. A gas turbine combustor capable of ensuring combustion stability and switching fuel stably and an operation method thereof are provided.

  In order to solve the above problems, for example, the configuration described in the claims is adopted. The present application includes a plurality of means for solving the above-mentioned problems. For example, in the gas turbine combustor that switches the fuel from the starting fuel to the gas fuel during the starting process of the gas turbine, the downstream combustion is performed. A plurality of fuel nozzles for injecting the gaseous fuel into a chamber, and a plurality of air holes installed between the plurality of fuel nozzles and the combustion chamber, for guiding compressed air to the combustion chamber, coaxially with the plurality of fuel nozzles A burner having a plurality of concentrically arranged air hole plates, an activation fuel nozzle provided at the center of the burner for injecting the activation fuel, and supplying the gas fuel to the burner A gas supply pipe, a start-up fuel supply pipe for supplying the start-up fuel to the start-up fuel nozzle, and a gas fuel flow provided in the gas supply pipe for adjusting a supply flow rate of the gas fuel A temperature detection unit that is provided in the control valve, provided in the startup fuel supply pipe and adjusts the supply flow rate of the startup fuel, and provided in the gas supply pipe and that measures the temperature of the gas fuel. A gas meter, a calorimeter for measuring a calorific value of the gas fuel, and a temperature process and a calorific value of the gas fuel measured by the temperature detector and the calorimeter. When the fuel is switched from the starting fuel to the gas fuel in the step, the time change rate of the flow rate of the gas fuel and the time change rate of the start fuel flow rate are calculated, each flow command signal is calculated, and the gas fuel is calculated. And a controller for outputting each flow command signal to the flow control valve and the starting fuel flow control valve.

  According to the present invention, even when the composition of the hydrogen-containing fuel changes during the switching of the gas turbine fuel from the starting fuel to the hydrogen-containing fuel, the combustion stability is ensured and the fuel can be switched stably. it can.

It is a schematic block diagram of the gas turbine plant provided with 1st Embodiment of the gas turbine combustor and its operating method of this invention. It is a characteristic view which shows the flow rate change of the starting fuel and gas fuel with respect to the gas turbine rotation speed and load in 1st Embodiment of the gas turbine combustor of this invention, and its operating method. It is a block diagram which shows the structure of the control apparatus which comprises 1st Embodiment of the gas turbine combustor and its operating method of this invention. It is a characteristic view which shows the fuel switching process of the control apparatus which comprises 1st Embodiment of the gas turbine combustor and its operating method of this invention. It is a flowchart figure which shows the processing content of the control apparatus which comprises 1st Embodiment of the gas turbine combustor and its operating method of this invention. It is a schematic block diagram of the gas turbine plant provided with 2nd Embodiment of the gas turbine combustor and its operating method of this invention. It is a block diagram which shows the structure of the control apparatus which comprises 2nd Embodiment of the gas turbine combustor and its operating method of this invention. It is a characteristic view which shows the fuel switching process of the control apparatus which comprises 2nd Embodiment of the gas turbine combustor of this invention, and its operating method.

  Embodiments of a gas turbine combustor and an operation method thereof according to the present invention will be described below with reference to the drawings.

  FIG. 1 is a schematic configuration diagram of a gas turbine plant provided with a first embodiment of a gas turbine combustor and an operation method thereof according to the present invention. In FIG. 1, the gas turbine plant 1 mainly includes an air compressor 2, a combustor 3, a turbine 4, and a generator 6. The air compressor 2 sucks and compresses air 101 from the atmosphere, generates compressed air 102, and sends the generated compressed air 102 to the combustor 3. The combustor 3 mixes and burns the compressed air 102 generated by the air compressor 2 and the gas fuel 200 or the liquid fuel 210 to generate the combustion gas 110, and the combustion gas 110 is led to the turbine 4.

  The combustion gas 110 guided from the combustor 3 is injected into a moving blade (not shown) through a stationary blade (not shown) in the turbine 4 to rotate the turbine shaft 105. The generator 4 connected to the turbine 4 and the air compressor 2 are driven by the rotational force of the turbine shaft 105. After the energy is recovered by the turbine 4, the combustion gas 110 passes through an exhaust diffuser (not shown) and is discharged to the atmosphere as exhaust 111.

  The generator 4 includes a load detector 50. This load detector 50 monitors the load during operation of the gas turbine. A gas turbine load signal 400 measured by the load detector 50 is input to a control device 500 described later.

  The combustor 3 is formed in a substantially cylindrical structure, and includes a combustor outer cylinder 10 forming a side surface thereof, a combustor end cover 13 provided at an end of the combustor outer cylinder 10, and a combustor end cover 13. A burner 8 provided on the inner side, a main chamber liner 12 that forms an annular space with an inner peripheral surface of the combustor outer cylinder 10 and an outer peripheral surface thereof, gas fuel 200 or liquid fuel 210, and compressed air 102 are mainly used. A combustion chamber 5 for burning inside the chamber liner 12 is provided.

  The burner 8 is disposed inside the combustor end cover 13, and is provided with an oil nozzle 40 located at the axial center of the combustor 3 and a plurality of air holes 21 for guiding the combustion air 102 a to the combustion chamber 5. An air hole plate 20 and a plurality of fuel nozzles 22 arranged on the outer peripheral side of the oil nozzle 40 and upstream of the air hole plate 20 and injecting the gas fuel 200 into the air hole 21 are provided. ing.

  A plurality of air holes 21 provided in the air hole plate 20 and a plurality of fuel nozzles 22 provided in the air hole plate 20 are arranged substantially coaxially in correspondence with each other. The plurality of air holes 21 are arranged on a plurality of concentric circles centering on the axis of the combustor 3, and in the present embodiment, two air hole groups are provided.

  Combustion air 102 a used for combustion among compressed air 102 supplied from the air compressor 2 to the combustor 3 is an annular shape formed by the inner peripheral surface of the combustor outer cylinder 10 and the outer peripheral surface of the main chamber liner 12. , Is dammed by the combustor end cover 13 and flows into the combustion chamber 5 through a plurality of air holes 21 opened in the air hole plate 20.

  A part of the compressed air 102 flows into the combustion chamber 5 from a cooling hole provided in the wall surface of the main chamber liner 12 and becomes cooling air 103 for cooling the main chamber liner 12.

  The plurality of fuel nozzles 22 provided in the burner 8 are connected to a fuel distributor 23 that distributes the gas fuel 200 supplied from the outside of the combustor end cover 13, and the gas fuel 200 ejected from the plurality of fuel nozzles 22. Is supplied to the combustion chamber 5 as a mixed flow while being mixed with the combustion air 102 a by the plurality of air holes 21 provided in the air hole plate 20, and burns in the combustion chamber 5.

  The combustor 3 in the present embodiment can use, as the gas fuel 200, hydrogen-containing fuels such as coke oven gas, refinery off-gas, coal gasification gas, and all gas fuels including natural gas. .

  When hydrogen-containing fuel is used as the fuel gas 200, there is a risk of explosion if ignition fails. For this reason, it is common to use light fuel such as light, kerosene, A heavy oil, or gas fuel such as natural gas or propane as the starting fuel from the time of ignition to a predetermined load. In the present embodiment, until the hydrogen-containing fuel is supplied as the fuel gas 200, oil fuel is supplied as the starting fuel to the oil nozzle 40 installed at the axis of the combustor 3 to start the combustor 3.

  The startup fuel system includes a startup fuel supply pipe 70 that supplies startup fuel 210a from the startup fuel supply source 210 to the oil nozzle 40, a fuel shut-off valve 65 provided in the startup fuel supply pipe 70, and a flow rate adjustment valve. 66. The oil fuel from the starting fuel supply source 210 is led to the joint of the combustor end cover 13 as the starting oil fuel 210a through the starting fuel supply pipe 70, the fuel cutoff valve 65, and the flow rate adjusting valve 66, It passes through the flow path inside the combustor end cover 13 and is ejected to the combustion chamber 5 through the oil nozzle 40.

  The gas fuel system includes a gas supply pipe 71 that supplies the gas fuel 200 a from the gas fuel supply source 200 to the fuel distributor 23, a gas fuel cutoff valve 60 and a gas flow rate adjustment valve 61 provided in the gas supply pipe 71. ing. The hydrogen-containing fuel (gas fuel) 200b from the gas fuel supply source 200 is led to the joint of the combustor end cover 13 as the gas fuel 200a through the gas supply pipe 71, the gas cutoff valve 60, and the gas flow rate control valve 61. Then, it passes through the flow path inside the combustor end cover 13, and is ejected from the fuel distributor 23 through the plurality of fuel nozzles 22 to the combustion chamber 5.

  In the gas fuel system, a calorimeter 600 for measuring the calorific value of the gas fuel 200 b is provided at a portion of the gas supply pipe 71 that connects the gas fuel supply source 200 and the gas cutoff valve 60. Further, a thermometer 602 for measuring the temperature of the gas fuel 200a is provided at a portion of the gas supply pipe 71 that connects the gas flow rate adjusting valve 61 and the connection port of the combustor end cover 13. The calorific value signal 401 of the gas fuel 200 b measured by the calorimeter 600 and the temperature signal 402 of the gas fuel 200 a measured by the thermometer 602 are input to the control device 500.

  The control device 500 takes in the signals 400, 401, and 402 described above, executes a calculation described later based on these signals, and controls the opening degrees of the flow rate control valve 66 and the gas flow rate control valve 61. The flow rates of the gas fuel 200a and the starting oil fuel 210a are adjusted and controlled.

  Next, the fuel flow rate when starting the gas turbine will be described with reference to FIG. FIG. 2 is a characteristic diagram showing changes in the flow rates of the starting fuel 210a and the gas fuel 200a with respect to the gas turbine rotational speed and load in the first embodiment of the gas turbine combustor and the operation method thereof according to the present invention. In FIG. 2, the gas turbine starts from operation with the startup fuel 210 and switches the fuel from the startup fuel 210a to the gas fuel 200a under a predetermined load condition. Here, the starting process of the gas turbine reaches from the ignition to the rated load operation state through the five steps (a) to (e) shown in FIG. The states (a) to (e) in the figure are described below.

(A) Ignition with starting fuel
(B) No-load rated speed (Full Speed No Load: FSNL)
(C) Fuel switching start (partial load condition)
(D) Fuel change completed
(E) Rated load First, the gas turbine is started to rotate, for example, by a starter motor or the like, and is increased to the ignition speed. At this ignition speed, the starting fuel 210a is supplied and ignited (state (a)). Thereafter, the startup fuel 210a is increased to increase the turbine speed to reach the no-load rated speed (FSNL) (state (b)). Thereafter, the generator 6 is arranged in parallel with the power system, and the starting fuel 210 is increased, so that the turbine load reaches a predetermined partial load. Here, the gas turbine can switch the fuel from the start fueling to the gas fueling (state (c)). During fuel switching ((c) to (d)), in order to ensure combustion stability, the starting fuel 210a is gradually decreased and the gas fuel 200a is increased to switch the fuel (state (d)). After completion of the fuel switching, the gas load 200a is further increased to reach the turbine load to the rated load (state (e)).

  Here, the states (a) to (c) are the exclusive combustion state of the startup fuel 210a, and the states (c) to (d) are the mixed combustion state of the startup fuel 210a and the gas fuel 200a. Further, the state (d) to the state (e) are the exclusive combustion state of the gas fuel 200a. When the composition of the gas fuel 200a changes widely during the fuel switching from the state (c) to the state (d), there is a concern that the combustion stability is lowered. An object of the present embodiment is to provide a gas turbine combustor including a control device 500 that can cope with such a change in composition of gas fuel during fuel switching.

  Next, the control apparatus constituting the first embodiment of the gas turbine combustor and the operation method thereof according to the present invention will be described with reference to FIGS. FIG. 3 is a block diagram showing the contents of the control device constituting the first embodiment of the gas turbine combustor and its operating method of the present invention, and FIG. 4 is the first of the gas turbine combustor and the operating method of the present invention. FIG. 5 is a flow chart showing the processing contents of the control device constituting the first embodiment of the gas turbine combustor and the operating method thereof according to the present invention. FIG. 3 to 5, the same reference numerals as those shown in FIGS. 1 and 2 are the same parts, and detailed description thereof is omitted.

  The control device 500 includes a gas turbine load signal 400 detected by the load detector 50, a calorific value signal 401 of the gas fuel 200b detected by the calorimeter 600, and a temperature signal 402 of the gas fuel 200a detected by the thermometer 602. The opening calculated by the calculation unit for the input unit for taking in, the calculation unit for performing calculation processing to be described later based on these signals, the drive unit for the flow rate control valve 66 and the drive unit for the gas flow rate control valve 61 An output unit that outputs a command, for example, a current is provided.

  As shown in FIG. 3, the calculation unit includes a fuel switching adjustment controller 501, a gas fuel adjustment valve controller 502, and a starting fuel adjustment valve controller 503.

The fuel switching adjustment controller 501 performs fuel switching based on the load signal Mw ₀ (400) of the gas turbine, the calorific value signal Q ₀ (401) of the gas fuel 200b, and the temperature signal T ₀ (402) of the gas fuel 200a. The time change rate of the flow rate of the gas fuel 200a and the time change rate of the flow rate of the starting oil fuel 210a are calculated so as to ensure the combustion stability in the meantime. Specifically, a reference value Qs for the calorific value of the gas fuel 200b and a reference value Ts for the temperature of the gas fuel 200a are determined in advance, and the properties (hydrogen-containing composition) of the gas fuel are within a predetermined range of these reference values. is determined in advance the time rate of change of the fuel in the case, the heating value signal Q ₀ of the temperature signals T ₀ and the gas fuel 200b of the detected gas fuel 200a, in accordance with the deviation between these standard values, the time rate of change change.

  Furthermore, the setting of the characteristics of the fuel switching process of the control device 500 will be described with reference to FIG. FIG. 4 shows the change over time of the flow rates of the gas fuel 200a and the starting oil fuel 210a during the fuel switching period from the state (c) to the state (d) shown in FIG. Is the time. tc indicates the time of state (c), and td indicates the time of state (d). Here, (a) of the flow characteristic line of the starting oil fuel 210a is a reference characteristic line, and the time change when the property (hydrogen-containing composition) of the gas fuel 200a described above is within the predetermined range of the reference value. Shows the rate.

Calorific value Q ₀ of fuel gas 200b is lower than the reference value Qs, or if the temperature T ₀ of fuel gas 200a is lower than the reference value Ts, in order to ensure combustion stability in the fuel switching, the low partial It is necessary to supply a lot of heat. Therefore, the increased amount of heat is supplemented by an increase in the flow rate of the starting oil fuel 210a. The fuel switching adjustment controller 501 calculates a flow rate characteristic line (b) in which the flow rate of the starting oil fuel 210a is increased based on the calorific value signal Q ₀ (401) and the temperature signal T ₀ (402).

On the other hand, the calorific value Q ₀ of fuel gas 200b is higher than the reference value Qs, or if the temperature T ₀ of fuel gas 200a is higher than the reference value Ts, in order to ensure combustion stability in the fuel switching, the It is necessary to reduce the amount of heat by a high amount. Therefore, the amount of heat reduction is dealt with by the flow rate reduction of the starting oil fuel 210a. The fuel switching adjustment controller 501 calculates a flow rate characteristic line (c) in which the flow rate of the starting oil fuel 210a is reduced based on the heat generation amount signal Q ₀ (401) and the temperature signal T ₀ (402).

  Returning to FIG. 3, the flow rate change rate signal of each fuel thus calculated is output to the gas fuel control valve controller 502 and the starting fuel control valve controller 503.

  The gas fuel control valve controller 502 calculates the opening command of the gas flow control valve 61 so that the flow rate of the gas fuel 200a changes based on the fuel flow time change rate calculated by the fuel switching control controller 501. This opening degree command is converted into a current signal, for example, and output to the drive unit of the gas flow rate adjustment valve 61.

  The startup fuel control valve controller 503 calculates the opening command of the flow rate control valve 66 so that the flow rate of the startup oil fuel 210a changes based on the fuel flow rate time change rate calculated by the fuel switching adjustment controller 501. To do. This opening degree command is converted into, for example, a current signal and output to the drive unit of the flow rate adjustment valve 66.

Next, the procedure of control of fuel switching by the control device 500 will be described with reference to FIG.
First, the control device 500 includes a gas turbine load signal Mw ₀ (400) detected by the load detector 50, a calorific value signal Q ₀ (401) of the gas fuel 200b detected by the calorimeter 600, and a thermometer 602. The detected temperature signal T ₀ (402) of the gas fuel 200a is taken in (step S1).

Next, the control device 500 determines whether or not the load signal Mw ₀ of the gas turbine is greater than or equal to the load set value Ps determined for starting fuel switching (step S2). If the load signal Mw ₀ of the gas turbine is greater than or equal to the load set value Ps, the process proceeds to (Step S3), and otherwise, the process returns to (Step S1).

Next, the control device 500 calculates a deviation between the calorific value Q ₀ (401) of the captured gas fuel 200b, the temperature signal T ₀ (402) of the gas fuel 200a, and preset reference values Qs and Ts ( Step S3). Specifically, the fuel switching adjustment controller 501 performs the following calculation.
Q ₀ -Qs = α1 (1)
T ₀ -Ts = α2 (2)
Here, α1 is a calorific value deviation and α2 is a temperature deviation.

Next, control device 500 determines whether or not the absolute value of the sum of the deviations calculated in step S3 is equal to or smaller than a predetermined value (step S4). If | K1 × α1 + K2 × α2 |, which is the absolute value of the sum of the deviations, is equal to or smaller than a predetermined value d, the process proceeds to (Step S5), and otherwise, the process proceeds to (Step S6). Specifically, the fuel switching adjustment controller 501 performs the following calculation.
| K1 × α1 + K2 × α2 | ≦ d (3)
Here, K1 is a first rate of change coefficient, and K2 is a second rate of change coefficient. When correcting the increase / decrease in the amount of heat in the gas fuel 200a with the starting fuel 210a, the difference between the calorific value deviation and the temperature deviation is calculated. It is for adjusting the standard. Further, d is a constant for determining whether or not the property (hydrogen-containing composition) of the gas fuel 200a is within a predetermined range of the reference value, and is determined by conducting a test or the like in advance.

  When it is determined in (Step S4) that the absolute value of the sum of the deviations is equal to or less than a predetermined value, control device 500 sets the rate of time change of starting oil fuel 210a during fuel switching to a predetermined reference value. (Step S5). Specifically, the flow rate characteristic line (A), which is the reference characteristic line in FIG.

When it is determined in (Step S4) that the absolute value of the sum of the deviations exceeds the predetermined value, the control device 500 determines the magnitude of the sum of the deviations and the predetermined value (Step S6). If the sum of the deviations exceeds the predetermined value d, the process proceeds to (Step S7). Otherwise, the process proceeds to (Step S8). Specifically, the fuel switching adjustment controller 501 performs the following calculation.
K1 × α1 + K2 × α2> d (4)
When it is determined in (Step S6) that the sum of the deviations exceeds a predetermined value, the control device 500 sets the time change rate of the starting oil fuel 210a in the fuel switching from the predetermined reference value to the starting oil fuel. The value 210a is decreased (step S7). Specifically, the flow rate characteristic line (c) in FIG. 4 is used for control.

  When it is determined in (Step S6) that the sum of the deviations does not exceed the predetermined value, the control device 500 sets the time change rate of the starting oil fuel 210a in the fuel switching from the predetermined reference value. The oil fuel 210a is assumed to increase (step S8). Specifically, the flow rate is controlled by a flow characteristic line (A) in FIG.

  After executing (Step S5) or (Step S7) or (Step S8), the control device 500 outputs an opening degree command to the starting fuel flow rate adjustment valve 66 according to the selected flow rate characteristic line (Step S9). Specifically, in the starting fuel control valve controller 503, an opening degree command for the flow control valve 66 is set so that the flow rate of the starting oil fuel 210a changes based on the time rate of change of the selected flow rate characteristic line. The command signal is output to the drive unit of the flow rate control valve 66.

  The control device 500 outputs an opening degree command to the gas fuel control valve 61 (step S10). Specifically, in the gas fuel control valve controller 502, the opening degree of the gas flow control valve 61 is changed so that the flow rate of the gas fuel 200a changes based on the fuel flow time change rate calculated by the fuel switching adjustment controller 501. A command is calculated, and a command signal is output to the drive unit of the gas flow rate control valve 61. The control device 500 returns after executing (Step S10).

According to the present embodiment, in the gas turbine combustor provided with a so-called coaxial jet cluster burner, when the fuel is switched from the starting oil fuel 210a to the gas fuel 200a, which is a hydrogen-containing fuel, the calorific value Q of the gas fuel 200b. ₀ and the temperature T ₀ of the gas fuel 200a are detected, the amount of heat of the gas fuel 200a is calculated, and the rate of time change is set, so that the composition of the hydrogen-containing fuel of the gas fuel 200a changes during fuel switching. Even so, combustion stability can be ensured and fuel can be switched stably.

  According to the first embodiment of the gas turbine combustor and the operating method of the present invention described above, during the switching of the gas turbine fuel from the starting oil fuel 210a to the gas fuel 200a that is a hydrogen-containing fuel, Even if the composition of the hydrogen-containing fuel of the fuel 200a changes, combustion stability can be ensured and the fuel can be switched stably.

  The second embodiment of the gas turbine combustor and the operation method thereof according to the present invention will be described below with reference to the drawings. FIG. 6 is a schematic configuration diagram of a gas turbine plant provided with a second embodiment of the gas turbine combustor and the operation method thereof according to the present invention. In FIG. 6, the same reference numerals as those shown in FIGS. 1 to 5 are the same parts, and detailed description thereof is omitted.

  In the second embodiment of the gas turbine combustor and the operation method thereof according to the present invention, the configuration of the gas turbine plant is substantially the same as that of the first embodiment, but in the combustor, the first embodiment. The difference is that a plurality of burners are provided and so-called multi-cluster burners are provided.

  In FIG. 6, on the inner side of the combustor end cover 13, one central burner 32 located at the axial center portion of the combustor 3 and a plurality of outer peripheral burners 33 on the outer peripheral portion of the central burner 32 are provided. Yes. The central burner 32 and the outer peripheral burner 33 are disposed on the upstream side of the air hole plate 20 provided with a plurality of air holes 21 for guiding the combustion air 102a to the combustion chamber 5 and gas fuel. A plurality of fuel nozzles 22 for injecting 200a into the air holes 21 are provided.

  In the outer peripheral burner 33, a plurality of air holes 21 provided in the air hole plate 20 and a plurality of fuel nozzles 22 provided in the air hole plate 20 are respectively arranged substantially coaxially. The plurality of air holes 21 are arranged on a plurality of concentric circles centered on the axis of the outer peripheral burner 33, and in the present embodiment, the outer circumferential side of the first row air hole group 51 and the first row air hole group 51. The second row air hole group 52 arranged in the second row and the third row air hole group 53 arranged on the outer periphery of the second row air hole group 52 are provided.

  The plurality of fuel nozzles 22 are connected to a fuel distributor 23 that distributes the gas fuel 200a (202, 203) supplied from the outside of the combustor end cover 13, and the gas fuel 200a ejected from the plurality of fuel nozzles 22 is provided. (202, 203) is supplied to the combustion chamber 5 as a mixed flow while being mixed with the combustion air 102 a through the plurality of air holes 21 provided in the air hole plate 20, and burns in the combustion chamber 5.

  The central burner 32 is disposed on the oil nozzle 40 located at the axial center of the combustor 3 and on the outer peripheral side of the oil nozzle 40 and on the upstream side of the air hole plate 20, and the gas fuel 200a (201) is removed from the air hole. And a plurality of fuel nozzles 22 that inject the fuel toward the inside.

  In the central burner 32, the upstream side of each air hole 21 provided in a plurality in the air hole plate 20 and the plurality of fuel nozzles 22 provided in a plurality are arranged in correspondence with each other. Further, the combustion chamber side surface 301 of the air hole plate 20 is provided with an inclined surface that is inclined concavely toward its central axis. For this reason, the downstream side of each air hole 21 is formed so as to be directed to the axial center of the combustor 3.

Next, a fuel system for supplying the gas fuel 200a to the central burner 32 and the outer peripheral burner 33 of the combustor 3 will be described.
The startup fuel system includes a startup fuel supply pipe 70 that supplies startup fuel 210a from the startup fuel supply source 210 to the oil nozzle 40, a fuel shut-off valve 65 provided in the startup fuel supply pipe 70, and a flow rate adjustment valve. 66. The oil fuel from the starting fuel supply source 210 is led to the joint of the combustor end cover 13 as the starting oil fuel 210a through the starting fuel supply pipe 70, the fuel cutoff valve 65, and the flow rate adjusting valve 66, It passes through the flow path inside the combustor end cover 13 and is ejected to the combustion chamber 5 through the oil nozzle 40.

  The gas fuel system branches into three fuel systems downstream of the gas shut-off valve 60 and a gas supply pipe 71a connecting the gas fuel supply source 200 and the gas shut-off valve 60 to the fuel distributor 23 of the central burner 32. A gas supply pipe 72 for supplying F1 gas fuel 201, and gas supply pipes 73 and 74 for supplying F2 and F3 gas fuels 202 and 203 to the fuel distributor 23 of the outer peripheral burner 33 installed on the outer peripheral side of the central burner, And an F1 gas flow rate adjustment valve 61 a provided in the gas supply pipe 72, an F2 gas flow rate adjustment valve 62 provided in the gas supply pipe 73, and an F3 gas flow rate adjustment valve 63 provided in the gas supply pipe 74. For convenience of explanation, the total of the gas F1 gas fuel 201, the F2 gas fuel 202, and the F3 gas fuel is referred to as a gas fuel 200a.

  In the gas fuel system, a calorimeter 600 for measuring the calorific value of the gas fuel 200b is provided in a gas supply pipe 71a that connects the gas fuel supply source 200 and the gas cutoff valve 60. In addition, a thermometer 601 for measuring the temperature of the F1 gas fuel 201 is provided in the fuel pipe 72 that connects the F1 gas flow rate adjustment valve 61a and the connection port of the combustor end cover 13.

Similarly, a fuel pipe 73 that connects the F2 gas flow rate adjustment valve 62 and the connection port of the combustor end cover 13, and a fuel pipe 74 that connects the F3 gas flow rate adjustment valve 63 and the connection port of the combustor end cover 13. Are provided with a thermometer 602 for measuring the temperature of the F2 gas fuel 202 and a thermometer 603 for measuring the temperature of the F3 gas fuel 203, respectively, and a calorific value signal 401 of the gas fuel 200b measured by the calorimeter 600, and The temperature signals 402 to 404 of the F1 to F3 gas fuels 201 to 203 measured by the thermometers 601 to 603 are input to the control device 500.

  In a combustor having a multi-cluster burner and a plurality of fuel systems as in the present embodiment, the combustion part of the combustor 3 is divided into a plurality of parts by these burners and the fuel system, and the combustion part is divided according to the operating load. Increase or decrease. Specifically, at the time of start-up, one fuel system is used to burn the fuel with a part of the burner, and thereafter, as the fuel flow rate increases, the fuel system used is increased and the unignited burner is ignited sequentially. Thus, a method of increasing the combustion portion (combustion switching) is executed.

  The control device 500 takes in the above-described signals 400 to 404 and executes a calculation described later based on these signals to control the opening degrees of the flow rate control valve 66 and the F1 to F3 gas flow rate control valves 61a, 62, 63. As a result, the flow rates of the F1 to F3 gas fuels 201 to 203 and the starting oil fuel 210a are adjusted and controlled.

  Next, the control apparatus which comprises 2nd Embodiment of the gas turbine combustor and its operating method of this invention is demonstrated using FIG.7 and FIG.8. FIG. 7 is a block diagram showing the contents of a control device constituting the second embodiment of the gas turbine combustor and the operating method thereof according to the present invention, and FIG. 8 is the second diagram of the gas turbine combustor and the operating method thereof according to the present invention. It is a characteristic view which shows the fuel switching process of the control apparatus which comprises this embodiment. 7 and 8, the same reference numerals as those shown in FIGS. 1 to 6 are the same parts, and detailed description thereof is omitted.

  The control device 500 includes a gas turbine load signal 400 detected by the load detector 50, a calorific value signal 401 of the gas fuel 200b detected by the calorimeter 600, and a temperature signal 402 of the F1 gas fuel 201 detected by the thermometer 601. And an input unit that takes in the temperature signal 403 of the F2 gas fuel 202 detected by the thermometer 602 and the temperature signal 404 of the F3 gas fuel 203 detected by the thermometer 603, and an operation to be described later based on these signals An arithmetic unit that executes processing, and an output unit that outputs, for example, an opening command calculated by the arithmetic unit to the driving unit of the flow rate control valve 66 and the driving units of the F1 to F3 gas flow rate control valves 61a, 62, and 63. I have.

  In the calculation unit, as shown in FIG. 7, a fuel switching adjustment controller 501a, an F1 gas fuel adjustment valve controller 502a, an F2 gas fuel adjustment valve controller 503a, an F3 gas fuel adjustment valve controller 504a, And a starting fuel control valve controller 505a.

The fuel switching adjustment controller 501a includes a gas turbine load signal Mw ₀ (400), a calorific value signal Q ₀ (401) of the gas fuel 200b, a temperature signal T1 ₀ (402) of the F1 gas fuel 201, and an F2 gas fuel 202. Based on the temperature signal T2 ₀ (403) and the temperature signal T3 ₀ (404) of the F3 gas fuel 203, the time change of the flow rates of the F1 to F3 gas fuels 201 to 203 so as to ensure the combustion stability during fuel switching. The rate and the time change rate of the flow rate of the starting oil fuel 210a are calculated. Specifically, the reference value Qs of the calorific value in the gas fuel 200b and the reference value Ts of the temperature of the F1 to F3 gas fuels 201 to 203 are determined in advance, and the property (hydrogen-containing composition) of the gas fuel 200a is the reference value. is determined in advance the time rate of change of the fuel in the case where there in within a predetermined range, the heating value signal _{Q 0} of the temperature signal _T1 0 to T3 ₀ and gaseous fuel 200b of the detected F1~F3 gas fuel 201 to 203, these The rate of time change is changed according to the deviation from the reference value.

  Furthermore, the setting of the characteristics of the fuel switching process of the control device 500 will be described with reference to FIG. FIG. 8 shows temporal changes in the flow rates of the gas fuel 200a and the starting oil fuel 210a during the fuel switching period from the state (c) to the state (d) shown in FIG. Is the time. tc indicates the time of state (c), and td indicates the time of state (d). Here, (a) of the flow characteristic line of the starting oil fuel 210a is a reference characteristic line, and the rate of change over time when the above-described property (hydrogen-containing composition) of the gas fuel is within a predetermined range of the reference value. Is shown.

  As described above, in the present embodiment, the flow rate of the gas fuel 200a increases during fuel switching. As the flow rate of the gas fuel 200a increases, the number of fuel systems used increases and the unignited burner is ignited sequentially. Thus, a method of increasing the combustion portion (combustion switching) is also performed at the same time. Specifically, during the period from time tc to time tc1, only the central burner 32 is supplied with the F1 gas fuel 201 gradually increased at a predetermined time change rate. When the flow rate of the gas fuel 200a reaches the first combustion switching set fuel flow rate (time tc1), the outer peripheral burner 33 to which the F2 gas fuel 202 is supplied is ignited, and the flow rates of the gas fuel 200a are changed to the F1 gas fuel 201 and the F2 gas fuel. 202.

  Between the time tc1 and the time tc2, the F1 gas fuel 201 and the F2 gas fuel 202 are gradually increased at a predetermined rate of time change. When the flow rate of the gas fuel 200a reaches the second combustion switching setting fuel flow rate (time tc2), the outer peripheral burner 33 to which the F3 gas fuel 203 is supplied is ignited, and the flow rates of the gas fuel 200a are changed to the F1 gas fuel 201 and the F2 gas fuel. Distribute to 202 and F3 gas fuel. Between the time tc2 and the time td, the F1 gas fuel 201, the F2 gas fuel 202, and the F3 gas fuel 203 are gradually increased and supplied at a predetermined time change rate.

Calorific value _{Q 0} of fuel gas 200b is lower than the reference value Qs, or if the temperature _T1 0 to T3 ₀ from F1 gas fuel 201 F3 gas fuel 203 is lower than the reference value Ts, the combustion stability in the fuel switching In order to ensure, it is necessary to supply a large amount of heat for the low amount. Therefore, the increased amount of heat is supplemented by an increase in the flow rate of the starting oil fuel 210a. The fuel switching adjustment controller 501 increases the flow rate of the starting oil fuel 210a based on the calorific value signal Q ₀ (401) and the temperature signals T1 _{0 to} T3 ₀ (402 to 404). ) Is calculated.

On the other hand, higher than the reference value Qs calorific value _{Q 0} of fuel gas 200b, or if the temperature _T1 0 to T3 ₀ from F1 gas fuel 201 F3 gas fuel 203 is higher than the reference value Ts, combustion stability in the fuel switching In order to ensure the property, it is necessary to reduce the amount of heat by the high amount. Therefore, the amount of heat reduction is dealt with by the flow rate reduction of the starting oil fuel 210a. The fuel switching adjustment controller 501 reduces the flow rate of the starting oil fuel 210a based on the calorific value signal Q ₀ (401) and the temperature signals T1 _{0 to} T3 ₀ (402 to 404). ) Is calculated.

  Returning to FIG. 7, the flow rate change rate signals of the respective fuels calculated in this way are the F1 gas fuel control valve controller 502a, the F2 gas fuel control valve controller 503a, and the F3 gas fuel control valve controller 504a. It is output to the starting fuel control valve controller 505a.

  The F1 gas fuel control valve controller 502a issues an opening command of the F1 gas flow control valve 61a so that the flow rate of the F1 gas fuel 201 changes based on the fuel flow time change rate calculated by the fuel switching adjustment controller 501a. calculate. This opening degree command is converted into a current signal, for example, and is output to the drive unit of the F1 gas flow rate adjustment valve 61a.

  The F2 gas fuel control valve controller 503a gives an opening degree command for the F2 gas flow control valve 62 so that the flow rate of the F2 gas fuel 202 changes based on the fuel flow time change rate calculated by the fuel switching adjustment controller 501a. calculate. This opening degree command is converted into, for example, a current signal and output to the drive unit of the F2 gas flow rate adjustment valve 62.

  The F3 gas fuel control valve controller 504a issues an opening degree command for the F3 gas flow control valve 63 so that the flow rate of the F3 gas fuel 203 changes based on the fuel flow time change rate calculated by the fuel switching adjustment controller 501a. calculate. This opening degree command is converted into a current signal, for example, and output to the drive unit of the F3 gas flow rate adjustment valve 63.

  The startup fuel control valve controller 505a calculates the opening command of the flow rate control valve 66 so that the flow rate of the startup oil fuel 210a changes based on the fuel flow time change rate calculated by the fuel switching adjustment controller 501. To do. This opening degree command is converted into, for example, a current signal and output to the drive unit of the flow rate adjustment valve 66.

According to the present embodiment, in the gas turbine combustor provided with a so-called multi-cluster burner, when the fuel is switched from the starting oil fuel 210a to the gas fuel 200a that is the hydrogen-containing fuel, the calorific value Q _{0 of the} gas fuel 200b. And the temperature T1 _{0 to} T3 ₀ of the F1 to F3 gas fuels 201 to 203 are detected, the amount of heat of the F1 to F3 gas fuels 201 to 203 is calculated, and the time change rate is set. Even if the composition of the hydrogen-containing fuel in the gas fuel 200a changes, combustion stability can be ensured and the fuel can be switched stably.

  According to the second embodiment of the gas turbine combustor and the method of operating the same described above, the hydrogen content of the gas fuel 200a is changed during the switching from the starting oil fuel 210a to the gas fuel 200a that is the hydrogen-containing fuel. Even if the composition of the fuel changes, the combustion stability can be ensured and the fuel can be switched stably.

DESCRIPTION OF SYMBOLS 1 Gas turbine plant 2 Air compressor 3 Combustor 4 Turbine 5 Combustion chamber 6 Generator 8 Burner 10 Outer cylinder 12 Main chamber liner 13 Combustor end cover 20 Air hole plate 21 Air hole 22 Fuel nozzle 23 Fuel distributor 32 Central burner 33 Peripheral burner 40 Oil nozzle 50 Load detector 51 First row air hole 52 Second row air hole 53 Third row air hole 60 Fuel shut-off valve 61 Gas flow control valve 61a F1 gas flow control valve 62 F2 gas flow control valve 63 F3 gas flow rate control valve 66 Flow rate control valve 101 Air 102 Compressed air 103 Cooling air 110 Combustion gas 111 Exhaust gas 200a Gas fuel 210a Starting oil fuel 301 Air hole plate combustion chamber side surface 400 Gas turbine load measurement value signal 401 Fuel heat generation Quantity measurement value signal 402 Fuel temperature measurement signal 500 Controller 501 Fuel switching Adjustment controller 502 gas fuel adjustment valve controller 503 start fuel adjustment valve controller 501a fuel switching adjustment controller 502a F1 gas fuel adjustment valve controller 503a F2 gas fuel adjustment valve controller 504a F3 gas fuel adjustment valve controller 505a Fuel control valve controller 600 for starting Calorimeter 601 Thermometer

Claims (6)

In the gas turbine combustor that switches the fuel from the starting fuel to the gas fuel during the starting process of the gas turbine,
A plurality of fuel nozzles for injecting the gaseous fuel into a downstream combustion chamber, a plurality of air holes installed between the plurality of fuel nozzles and the combustion chamber, and leading compressed air to the combustion chamber A burner provided with a plurality of concentric air hole plates coaxially with the fuel nozzle;
An activation fuel nozzle that is provided at the axial center of the burner and injects the activation fuel;
A gas supply pipe for supplying the gas fuel to the burner;
A starting fuel supply pipe for supplying the starting fuel to the starting fuel nozzle;
A gas fuel flow control valve that is provided in the gas supply pipe and adjusts a supply flow rate of the gas fuel;
A starting fuel flow rate adjusting valve that is provided in the starting fuel supply pipe and adjusts a supply flow rate of the starting fuel;
A temperature detector provided in the gas supply pipe for measuring the temperature of the gas fuel;
A calorimeter provided in the gas supply pipe for measuring the calorific value of the gas fuel;
Taking in the temperature and calorific value of the gas fuel measured by the temperature detector and the calorimeter, the rate of change over time in the flow rate of the gas fuel when switching from the starting fuel to the gas fuel in the starting process And a control device that calculates each flow rate command signal and outputs each flow rate command signal to the gas fuel flow rate control valve and the starter fuel flow rate control valve. A gas turbine combustor characterized by comprising: In the gas turbine combustor that switches the fuel from the starting fuel to the gas fuel during the starting process of the gas turbine,
A plurality of fuel nozzles for injecting the gaseous fuel into a downstream combustion chamber, a plurality of air holes installed between the plurality of fuel nozzles and the combustion chamber, and leading compressed air to the combustion chamber A central burner disposed at the axial center of the gas turbine combustor, comprising a fuel nozzle and a plurality of concentrically arranged air hole plates coaxially;
A plurality of fuel nozzles for injecting the gaseous fuel into a downstream combustion chamber, a plurality of air holes installed between the plurality of fuel nozzles and the combustion chamber, and leading compressed air to the combustion chamber A plurality of concentrically arranged air hole plates coaxial with the fuel nozzle, and a plurality of outer peripheral burners disposed on the outer peripheral portion of the central burner;
An activation fuel nozzle that is provided at the center of the central burner and injects the activation fuel;
A plurality of gas supply pipes each supplying the gas fuel to the plurality of outer peripheral burners and the central burner;
A starting fuel supply pipe for supplying the starting fuel to the starting fuel nozzle;
A plurality of gas fuel flow control valves that are provided in the plurality of gas supply pipes and respectively adjust the supply flow rate of the gas fuel;
A starting fuel flow rate adjusting valve that is provided in the starting fuel supply pipe and adjusts a supply flow rate of the starting fuel;
A plurality of temperature detectors provided in the plurality of gas supply pipes, each for measuring the temperature of the gas fuel;
A calorimeter provided at a supply source of the plurality of gas supply pipes and measuring a calorific value of the gas fuel of the supply source;
The temperature and the calorific value of the gas fuel measured by the plurality of temperature detectors and the calorimeter are taken in, and when the fuel is switched from the starting fuel to the gas fuel in the starting process, the flow time of the gas fuel The rate of change and the time rate of change of the starting fuel flow rate are calculated, each flow rate command signal is calculated, and each flow rate command signal is output to the plurality of gas fuel flow rate control valves and the startup fuel flow rate control valve A gas turbine combustor comprising a control device. The gas turbine combustor according to claim 1 or 2,
The control device previously sets a reference value for the temperature of the gas fuel and a reference value for the calorific value, and the temperature and calorific value of the gas fuel measured by the reference value, the temperature detector, and the calorimeter. The time change rate of the flow rate of the gas fuel and the time change of the startup fuel flow rate are changed according to the deviation from the above. The gas turbine combustor according to claim 1 or 2,
The control device sets a reference value for the temperature of the gas fuel and a reference value for the calorific value in advance, and the temperature of the gas fuel measured by the temperature detector and the calorimeter with respect to these reference values. When the calorific value is low, the gas turbine combustor is changed to a time change rate at which the starting fuel flow rate increases. The gas turbine combustor according to claim 1 or 2,
The control device sets a reference value for the temperature of the gas fuel and a reference value for the calorific value in advance, and the temperature of the gas fuel measured by the temperature detector and the calorimeter with respect to these reference values. When the calorific value is high, the gas turbine combustor is changed to a time change rate at which the starting fuel flow rate decreases. A plurality of fuel nozzles for injecting the gaseous fuel into a downstream combustion chamber, a plurality of air holes installed between the plurality of fuel nozzles and the combustion chamber, and leading compressed air to the combustion chamber A burner provided with a plurality of concentric air hole plates coaxially with the fuel nozzle;
An activation fuel nozzle that is provided at the axial center of the burner and injects the activation fuel;
A gas supply pipe for supplying the gas fuel to the burner;
A starting fuel supply pipe for supplying the starting fuel to the starting fuel nozzle;
A gas fuel flow control valve that is provided in the gas supply pipe and adjusts a supply flow rate of the gas fuel;
A starting fuel flow rate adjusting valve that is provided in the starting fuel supply pipe and adjusts a supply flow rate of the starting fuel;
A temperature detector provided in the gas supply pipe for measuring the temperature of the gas fuel;
A gas turbine combustor operating method provided in the gas supply pipe, comprising a calorimeter for measuring the calorific value of the gas fuel, and switching the fuel from the starting fuel to the gas fuel in the starting process,
Capturing the temperature and calorific value of the gas fuel measured by the temperature detector and the calorimeter, determining the start of fuel switching from the starting fuel to the gas fuel in the starting process, and Calculating a flow rate change rate and a time change rate of the starting fuel flow rate to calculate each flow rate command signal; and each flow rate command signal to the gas fuel flow rate control valve and the startup fuel flow rate control valve. And a step of outputting the gas turbine combustor.

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