Control method for a gas turbine combustor and control device for a gas turbine combustor

Abstract

A control method of a gas turbine combustor according to at least one embodiment of the present disclosure is a control method of a gas turbine combustor that combusts hydrogen fuel and a fuel other than hydrogen fuel, the gas turbine combustor including an air hole plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes. The plurality of air holes includes a plurality of first air holes having a slanted passage extending in a direction inclined with respect to a center axis of the air hole plate in a region including at least an outlet end in a passage from an inlet end to the outlet end, and a plurality of second air holes extending in parallel with the center axis. The plurality of fuel nozzles includes a plurality of first fuel nozzles corresponding to the plurality of first air holes, and a plurality of second fuel nozzles corresponding to the plurality of second air holes. When only the hydrogen fuel is combusted, the plurality of first fuel nozzles are not supplied with the hydrogen fuel.

Description

Technical Field

[0001] This invention relates to a control method and a control device for a gas turbine burner.

[0002] This application claims priority based on Japanese Patent Application No. 2022-006878 filed with the Japan Patent Office on January 20, 2022, the contents of which are incorporated herein by reference. Background Technology

[0003] A gas turbine combustor is known in which an air orifice plate is disposed between a fuel nozzle and a combustion chamber, and fuel flow and air flow formed on the outer periphery of the fuel flow are ejected into the combustion chamber inside the air orifice plate (for example, see Patent Document 1).

[0004] Previous technical documents

[0005] Patent documents

[0006] Patent Document 1: Japanese Patent Application Publication No. 2018-150912 Summary of the Invention

[0007] The technical problem to be solved by the invention

[0008] For example, in a gas turbine combustor as described in Patent Document 1 above, if the air orifice extends in a direction inclined relative to the central axis of the air orifice plate, a region with relatively low flow velocity may be locally generated within or relatively close to the air orifice plate. For example, if hydrogen, which has a relatively fast combustion rate, is used as fuel, this region may become the starting point for backfire, and if backfire occurs, the flame may persist in this region. If the flame persists in this region, the combustor may be damaged.

[0009] In view of the above, the object of at least one embodiment of the present invention is to suppress damage to gas turbine combustors that burn hydrogen fuel and other fuels besides hydrogen fuel.

[0010] means for solving technical problems

[0011] (1) The control method for a gas turbine combustor according to at least one embodiment of the present invention is a control method for a gas turbine combustor that burns hydrogen fuel and other fuels besides hydrogen fuel, wherein the gas turbine combustor includes an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein,

[0012] The plurality of air holes include:

[0013] A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and

[0014] Multiple second air holes extend parallel to the central axis.

[0015] The plurality of fuel nozzles includes:

[0016] A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and

[0017] Multiple second fuel nozzles, each corresponding to one of the multiple second air holes,

[0018] When burning hydrogen fuel, the hydrogen fuel is not supplied to the plurality of first fuel nozzles.

[0019] (2) The control device for the gas turbine combustor according to at least one embodiment of the present invention is a control device for controlling combustion in a gas turbine combustor that burns hydrogen fuel and other fuels besides hydrogen fuel. The gas turbine combustor includes an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes respectively.

[0020] The plurality of air holes include:

[0021] A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and

[0022] Multiple second air holes extend parallel to the central axis.

[0023] The plurality of fuel nozzles includes:

[0024] A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and

[0025] Multiple second fuel nozzles, each corresponding to one of the multiple second air holes,

[0026] The control device for the gas turbine combustor includes:

[0027] A fuel flow regulating valve regulates the flow rate of fuel supplied to the plurality of first fuel nozzles; and

[0028] The fuel flow control unit controls the fuel flow regulating valve.

[0029] When burning hydrogen fuel, the fuel flow control unit controls the fuel flow regulating valve in such a way that hydrogen fuel is not supplied to the plurality of first fuel nozzles.

[0030] Invention Effects

[0031] According to at least one embodiment of the present invention, damage to gas turbine combustors that burn hydrogen fuel and other fuels besides hydrogen fuel can be suppressed. Attached Figure Description

[0032] Figure 1 This describes a schematic structure of a gas turbine having a gas turbine burner according to several embodiments.

[0033] Figure 2A This indicates that it is set in Figure 1 A schematic partial cross-sectional view of the structure near the burner in the combustor of a gas turbine according to one embodiment of the gas turbine shown.

[0034] Figure 2B This indicates that it is set in Figure 1 A schematic partial cross-sectional view of the structure near the burner in the combustor of a gas turbine, according to another embodiment of the gas turbine shown.

[0035] Figure 3A Observed from the downstream side of the axis Figure 2A A diagram of the air orifice plate of a burner according to one embodiment is shown.

[0036] Figure 3B Observed from the downstream side of the axis Figure 2B A diagram of the air orifice plate of a burner according to another embodiment shown.

[0037] Figure 4A This is a diagram showing an example of the first air hole in an air hole system.

[0038] Figure 4B This is a diagram showing another example of the first air hole in an air hole system.

[0039] Figure 5A It is used for Figure 2A and Figure 3A The diagram illustrates the control of the combustion injection ratio based on the hydrogen co-firing rate in a gas turbine combustor according to one embodiment.

[0040] Figure 5B It is used for Figure 2B and Figure 3B A diagram illustrating the control of the combustion injection ratio based on the hydrogen co-firing rate in a gas turbine combustor according to another embodiment is shown.

[0041] Figure 6A It means possessing Figure 2A and Figure 3AThe diagram illustrates the changes in fuel ratio and hydrogen co-firing rate of a gas turbine combustor in one embodiment, from the start of operation until the transition to dedicated hydrogen fuel combustion.

[0042] Figure 6B It means possessing Figure 2B and Figure 3B The diagram illustrates the changes in fuel ratio and hydrogen co-firing rate of a gas turbine from the start of operation until the transition to dedicated hydrogen fuel combustion, according to another embodiment shown. Detailed Implementation

[0043] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the constituent parts described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0044] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" that indicate relative or absolute configuration not only indicate such configuration in a strict sense, but also indicate a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0045] For example, expressions such as "same," "equal," and "homogeneous" that indicate that things are in an equal state not only indicate that they are the same in a strict sense, but also that there are differences in the degree to which they can achieve the same function.

[0046] For example, the description of shapes such as quadrilaterals or cylinders not only refers to quadrilaterals or cylinders in a strict geometric sense, but also includes shapes with concave or convex parts or chamfers within the range where the same effect can be obtained.

[0047] On the other hand, the expression "possessing," "having," "including," "containing," or "having" a constituent element is not an exclusive expression that excludes the existence of other constituent elements.

[0048] use Figure 1 Figure 2 illustrates several embodiments of the gas turbine burner according to the present invention.

[0049] Figure 1 This describes a schematic structure of a gas turbine equipped with a gas turbine burner according to several embodiments of the present invention.

[0050] Figure 1 The gas turbine 1 shown includes an air compressor 110, a gas turbine burner 100, and a turbine 180.

[0051] The gas turbine combustor 100 involved in several embodiments includes a combustor bushing (inner cylinder) 153, a bushing flow sleeve (outer cylinder) 154, a tailpipe 152, a tailpipe flow sleeve 150, a burner 200, a fuel system 300, and a control device 10 (see reference). Figure 2A , Figure 2B Additionally, in Figure 1 In the diagram, the burner 200 and fuel system 300 are simplified and illustrated, with a fuel manifold 230 and a fuel supply pipe 305, which will be described later. The burner 200 and fuel system 300 will be explained in more detail later.

[0052] exist Figure 1 In the gas turbine 1 shown, an air compressor 110 is driven by the turbine 180 to compress air (intake air) drawn in from the atmosphere via an intake section (not shown) to generate high-pressure air (combustion air) 120, which is then supplied to the gas turbine combustor 100. The gas turbine combustor 100 mixes and combusts the high-pressure air 120 supplied from the air compressor 110 with fuel supplied from the fuel system 300 to generate high-temperature combustion gas 170, which is then supplied to the turbine 180.

[0053] That is, in Figure 1 In the gas turbine 1 shown, combustion air, i.e. high-pressure air 120, injected from the air compressor 110 is introduced into the engine room 140 through the diffuser 130, and flows into the flow path formed in the gap between the tail tube 150 and the tail tube 152 disposed inside the tail tube 150, which is provided in the tail tube flow sleeve 150 of the gas turbine burner 100.

[0054] After the high-pressure air 120 flows into the flow path formed in the gap, it flows in the flow path between the burner bushing 153 formed in the gas turbine burner 100 and the bushing flow sleeve 154 disposed on the outer periphery of the burner bushing 153 and concentric with the burner bushing 153. After that, its flow is reversed and it mixes with the fuel introduced from the fuel system 300 and injected from the multiple fuel nozzles 210 that constitute the cluster nozzle. Then, it burns in the combustion chamber 160 inside the burner bushing 153 to form a flame 156 and produce high-temperature and high-pressure combustion gas 170.

[0055] Thus, the high-temperature and high-pressure combustion gas 170 generated in the gas turbine combustor 100 flows down the tailpipe 152 and is introduced into the turbine 180.

[0056] In the turbine 180 constituting the gas turbine 1, the work generated by the adiabatic expansion of the high-temperature and high-pressure combustion gas 170 introduced into the turbine 180 is converted into shaft rotational force, which drives the generator 190 connected to the turbine 180 through the turbine shaft and obtains output from the generator 190.

[0057] The air compressor 110 and generator 190 constituting the gas turbine 1 are connected to the turbine 180 via turbine shafts. However, the turbine shafts of the air compressor 110, turbine 180, and generator 190 may not be single-shaft structures but rather turbine shafts with dual or more shafts.

[0058] Furthermore, gas turbines, which are widely used in thermal power plants, typically have a structure in which multiple gas turbine burners are arranged radially relative to the turbine shaft.

[0059] Figure 2A This indicates that it is set in Figure 1 A schematic partial cross-sectional view of the structure near the burner 200 in the gas turbine combustor 100 according to one embodiment of the gas turbine 1 shown.

[0060] Figure 2B This indicates that it is set in Figure 1 A schematic partial cross-sectional view of the structure near the burner 200 in the gas turbine combustor 100 according to another embodiment of the gas turbine 1 shown.

[0061] Figure 3A Observed from the downstream side of the axis Figure 2A A diagram of the air orifice plate 25 of the burner 200 according to one embodiment is shown.

[0062] Figure 3B Observed from the downstream side of the axis Figure 2B A diagram of the air orifice plate 25 of the burner 200 according to another embodiment shown.

[0063] In the following description, the direction along the central axis AXc of the gas turbine combustor 100 is referred to as the axial direction of the gas turbine combustor 100, or simply the axial direction. Furthermore, along the axial direction, the direction in which the combustion gas 170 flows is referred to as the downstream side of the axial direction, or simply the downstream side, and the direction opposite to the direction in which the combustion gas 170 flows is referred to as the upstream side of the axial direction, or simply the upstream side.

[0064] Furthermore, in several embodiments of the gas turbine burner 100, the central axis AXc of the gas turbine burner 100 is, for example, the central axis of the burner bushing 153 having a cylindrical shape. In several embodiments of the gas turbine burner 100, the central axis AXc of the gas turbine burner 100 is arranged to coincide with the central axis AXp of the air orifice plate 25.

[0065] (Detailed information about gas turbine combustor 100)

[0066] The gas turbine combustor 100 involved in several embodiments is a gas turbine combustor capable of burning hydrogen fuel and other fuels besides hydrogen fuel. In the gas turbine combustor 100 involved in several embodiments, natural gas fuel is burned as another fuel. The gas turbine combustor 100 involved in several embodiments is capable of dedicated combustion of hydrogen fuel, dedicated combustion of natural gas fuel, and co-combustion of hydrogen fuel and natural gas fuel.

[0067] like Figure 2A and Figure 2B As shown, in several embodiments of the gas turbine combustor 100, the burner 200 is configured to be orthogonal to the central axis AXc (central axis of the burner bushing 153) of the gas turbine combustor 100, and is located at the axial upstream end of the burner bushing 153. In several embodiments of the gas turbine combustor 100, the burner 200 includes a fuel manifold 230, a plurality of fuel nozzles 210, and an air orifice plate 25.

[0068] The gas turbine combustor 100 involved in several embodiments is a type of combustor known as a cluster combustor. In the gas turbine combustor 100 involved in several embodiments, a plurality of air holes 250 are formed in an air orifice plate 25. Each of a plurality of fuel nozzles 210 is configured in a one-to-one correspondence with each of the plurality of air holes 250 formed in the air orifice plate 25 disposed near the axially downstream side of these fuel nozzles 210.

[0069] In addition, such as Figure 2A and Figure 2B As shown, the front end of each fuel nozzle 210 may or may not be inserted into each air hole 250.

[0070] like Figure 2A , Figure 2B , Figure 3A and Figure 3BAs shown, in the gas turbine combustor 100 of several embodiments, the burner 200 is a so-called multi-burner comprising a central burner 211 arranged coaxially with the combustor bushing 153 at the center and a plurality of (six in this embodiment) outer burners 212 arranged around the central burner 211. The central burner 211 and the outer burners 212 are each divided into a plurality of concentric annular rows (three in this embodiment). In the following description, the plurality of annular rows of the central burner 211 and the outer burners 212 are appropriately referred to as the first row, the second row, and the third row, respectively, from the inner peripheral side to the outer peripheral side.

[0071] (Central burner 211)

[0072] In several embodiments of the gas turbine combustor 100, a central burner 211 includes a fuel manifold 230, a plurality of fuel nozzles 210, and a plurality of air holes 250 formed on an air orifice plate 25. The central burner 211 is supported on the fuel manifold 230. The fuel nozzles 210 of the central burner 211 are arranged concentrically in the first to third rows of the central burner 211, and are arranged around the entire circumference of each row (in annular arrangement). The fuel nozzles 210 of the central burner 211 inject fuel supplied from the fuel system 300 toward the air holes 250 formed on the air orifice plate 25.

[0073] In the gas turbine combustor 100 of several embodiments, the fuel manifold 230 of the central burner 211 includes an inner peripheral fuel manifold 231 and an outer peripheral fuel manifold 232 disposed radially outside the inner peripheral fuel manifold 231.

[0074] In the gas turbine combustor 100 of several embodiments, the central burner 211 includes a plurality of fuel nozzles 210 connected to an inner peripheral fuel collection pipe 231 and an outer peripheral fuel nozzle 210o connected to an outer peripheral fuel collection pipe 232.

[0075] In the gas turbine combustor 100 of several embodiments, the inner peripheral fuel nozzle 210i of the central burner 211 corresponds to the fuel nozzle 210 of the first row, and the outer peripheral fuel nozzle 210o of the central burner 211 corresponds to the fuel nozzle 210 of the second and third rows.

[0076] In the gas turbine combustor 100 of several embodiments, the air orifice plate 25 includes a plurality of inner peripheral air holes 250i corresponding one-to-one with a plurality of inner peripheral fuel nozzles 210i of the central burner 211 and a plurality of outer peripheral air holes 250o corresponding one-to-one with a plurality of outer peripheral fuel nozzles 210o of the central burner 211.

[0077] In the gas turbine combustor 100 of several embodiments, the first column of the central burner 211 is composed of an inner peripheral fuel manifold 231, an inner peripheral fuel nozzle 210i and an inner peripheral air hole 250i, and the second and third columns are composed of an outer peripheral fuel manifold 232, an outer peripheral fuel nozzle 210o and an outer peripheral air hole 250o.

[0078] (Outer burner 212)

[0079] In several embodiments of the gas turbine combustor 100, the outer burner 212 includes a fuel manifold 230, a plurality of fuel nozzles 210, and a plurality of air holes 250 formed in the air orifice plate 25. The outer burner 212 is supported on the fuel manifold 230. The fuel nozzles 210 of the outer burner 212 are arranged concentrically in the first to third rows of the outer burner 212, and are arranged around the entire circumference of each row (in annular arrangement). The fuel nozzles 210 of the outer burner 212 inject fuel supplied from the fuel system 300 toward the air holes 250 formed in the air orifice plate 25.

[0080] In the gas turbine combustor 100 of several embodiments, the fuel manifold 230 of the outer burner 212 includes an inner peripheral fuel manifold 231 and an outer peripheral fuel manifold 232 arranged radially outside the inner peripheral fuel manifold 231.

[0081] In the gas turbine combustor 100 of several embodiments, the plurality of fuel nozzles 210 of the outer burner 212 include an inner peripheral fuel nozzle 210i connected to an inner peripheral fuel collection pipe 231 and an outer peripheral fuel nozzle 210o connected to an outer peripheral fuel collection pipe 232.

[0082] In the gas turbine combustor 100 of several embodiments, the inner peripheral fuel nozzle 210i of the outer burner 212 corresponds to the fuel nozzle 210 of the first row, and the outer peripheral fuel nozzle 210o of the outer burner 212 corresponds to the fuel nozzle 210 of the second and third rows.

[0083] In the gas turbine combustor 100 of several embodiments, the air orifice plate 25 includes a plurality of inner peripheral air holes 250i corresponding one-to-one with a plurality of inner peripheral fuel nozzles 210i of the outer burner 212 and a plurality of outer peripheral air holes 250o corresponding one-to-one with a plurality of outer peripheral fuel nozzles 210o of the outer burner 212.

[0084] In the gas turbine combustor 100 of several embodiments, the first column of the outer burner 212 is composed of an inner peripheral fuel manifold 231, an inner peripheral fuel nozzle 210i and an inner peripheral air hole 250i, and the second and third columns are composed of an outer peripheral fuel manifold 232, an outer peripheral fuel nozzle 210o and an outer peripheral air hole 250o.

[0085] Figure 4A This is a diagram showing an example of the first air hole 251 in the air hole 250.

[0086] Figure 4B This is a diagram showing another example of the first air hole 251 in the air hole 250.

[0087] like Figure 4A and Figure 4B As shown, in the gas turbine combustor 100 of several embodiments, the plurality of air holes 250 include: a plurality of first air holes 251 having an inclined channel 256 extending in a region of at least the outlet end 250b in a passage 255 from the inlet end 250a to the outlet end 250b in a direction inclined relative to the central axis AXp of the air hole plate 25; and a plurality of second air holes 252 extending parallel to the central axis AXp of the air hole plate 25.

[0088] In addition, such as Figure 4A As shown, the inclined channel 256 in the first air hole 251 may be only a part of the outlet end 250b side (axial downstream side) of the channel 255, and the channel 255 on the inlet end 250a side (axial upstream side) may extend parallel to the central axis AXp of the air hole plate 25.

[0089] And, as Figure 4B As shown, the inclined channel 256 in the first air hole 251 can extend from the inlet end 250a to the outlet end 250b.

[0090] In the gas turbine combustor 100 of several embodiments, the fuel nozzle 210 corresponding to the first air hole 251 is also referred to as the first fuel nozzle 21, and the fuel nozzle 210 corresponding to the second air hole 252 is also referred to as the second fuel nozzle 22.

[0091] (Regarding the air hole 250 of the burner 200 according to one embodiment)

[0092] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the inner circumferential air hole 250i corresponding to the fuel nozzle 210 of the first column of the central burner 211, i.e., the inner circumferential fuel nozzle 210i, is the first air hole 251.

[0093] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the inner peripheral air holes 250i of the central burner 211 constitute a first air hole group G1 in which a plurality of first air holes 251 are arranged adjacent to each other.

[0094] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the fuel nozzle 210 of the first column of the central burner 211, namely the inner peripheral fuel nozzle 210i, is the first fuel nozzle 21.

[0095] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the peripheral air hole 250o corresponding to the fuel nozzles 210 in the second and third columns of the central burner 211, i.e. the peripheral fuel nozzles 210o, is the second air hole 252.

[0096] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the peripheral air holes 250o of the central burner 211 constitute a group G2 of a plurality of second air holes 252 arranged adjacent to each other.

[0097] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the fuel nozzles 210 in the second and third rows of the central burner 211, i.e. the outer peripheral fuel nozzles 210o, are the second fuel nozzles 22.

[0098] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the inner peripheral air hole 250i corresponding to the fuel nozzles 210i in the first, second and third columns of the outer burner 212 (i.e., the inner peripheral fuel nozzles 210i) and the outer peripheral air hole 250o corresponding to the outer peripheral fuel nozzles 210o are the second air holes 252.

[0099] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the inner peripheral air hole 250i and the outer peripheral air hole 250o of the outer burner 212 constitute a second air hole group G2.

[0100] exist Figure 2A and Figure 3A In one embodiment of the burner 200 shown, all fuel nozzles 210 of the outer burner 212 are second fuel nozzles 22.

[0101] (Regarding the air hole 250 of the burner 200 involved in another embodiment)

[0102] exist Figure 2B and Figure 3BIn another embodiment of the burner 200 shown, the inner circumferential air hole 250i corresponding to the fuel nozzle 210 of the first column of the central burner 211, i.e., the inner circumferential fuel nozzle 210i, is the first air hole 251.

[0103] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the inner peripheral air holes 250i of the central burner 211 constitute the first air hole group G1.

[0104] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the fuel nozzle 210 of the first column of the central burner 211, namely the inner peripheral fuel nozzle 210i, is the first fuel nozzle 21.

[0105] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the peripheral air hole 250o corresponding to the fuel nozzles 210 in the second and third columns of the central burner 211, i.e. the peripheral fuel nozzles 210o, is the second air hole 252.

[0106] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the peripheral air holes 250o of the central burner 211 constitute the second air hole group G2.

[0107] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the fuel nozzles 210 in the second and third rows of the central burner 211, i.e. the outer peripheral fuel nozzles 210o, are the second fuel nozzles 22.

[0108] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the inner circumferential air hole 250i corresponding to the fuel nozzle 210 of the first column of the outer burner 212, i.e., the inner circumferential fuel nozzle 210i, is the first air hole 251.

[0109] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the inner peripheral air holes 250i of the outer burner 212 constitute the first air hole group G1.

[0110] exist Figure 2B and Figure 3BIn another embodiment of the burner 200 shown, the fuel nozzle 210 of the first column of the outer burner 212, i.e. the inner peripheral fuel nozzle 210i, is the first fuel nozzle 21.

[0111] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the peripheral air hole 250o corresponding to the fuel nozzles 210 in the second and third columns of the outer burner 212, i.e., the peripheral fuel nozzles 210o, is the second air hole 252.

[0112] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the outer peripheral air holes 250o of the outer burner 212 constitute the second air hole group G2.

[0113] exist Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the fuel nozzles 210 in the second and third rows of the outer burner 212, i.e., the outer peripheral fuel nozzles 210o, are the second fuel nozzles 22.

[0114] That is, in Figure 2A and Figure 3A In one embodiment of the burner 200 shown, the inner circumferential air hole 250i of the outer burner 212 is the second air hole 252, but... Figure 2B and Figure 3B In another embodiment of the burner 200 shown, the inner peripheral air hole 250i of the outer burner 212 is the first air hole 251. Figure 2A and Figure 3A The burner 200 and the embodiment shown herein are related to one of the embodiments. Figure 2B and Figure 3B The burner 200 involved in the other embodiment shown has the same structure except for the different types of the inner peripheral air holes 250i of the outer burner 212 and the different types of the inner peripheral fuel nozzles 210i of the outer burner 212.

[0115] (Fuel System 300)

[0116] In several embodiments of the gas turbine combustor 100, the fuel system 300 includes a hydrogen fuel pipeline 301 for hydrogen fuel and a natural gas fuel pipeline 302 for natural gas fuel. In several embodiments of the gas turbine combustor 100, the fuel system 300 includes a mixing device (mixer) 307 for generating a mixture of hydrogen and natural gas fuel and a fuel supply pipeline 305 for supplying the mixed fuel from the mixing device 307 or the hydrogen or natural gas fuel supplied via the mixing device 307 to each fuel manifold 230.

[0117] In the gas turbine combustor 100 of several embodiments, the fuel system 300 includes a plurality of fuel flow regulating valves 310, 320 for regulating the flow rate of fuel.

[0118] In the gas turbine combustor 100 of several embodiments, the fuel flow regulating valve 310 includes a hydrogen flow regulating valve 311 for regulating the flow rate of hydrogen fuel supplied to the mixing unit 307 via the hydrogen fuel line 301 and a natural gas flow regulating valve 312 for regulating the flow rate of natural gas fuel supplied to the mixing unit 307 via the natural gas fuel line 302.

[0119] In several embodiments of the gas turbine combustor 100, actuators (not shown) for changing the valve opening degree are respectively provided in the hydrogen flow regulating valve 311 and the natural gas flow regulating valve 312. In several embodiments of the gas turbine combustor 100, the control signals for driving these actuators are configured to be output from the fuel flow control unit 11 described later.

[0120] In the gas turbine combustor 100 of several embodiments, the fuel flow regulating valve 320 is a fuel flow regulating valve for regulating the flow rate of fuel supplied to each fuel manifold 230. The fuel flow regulating valve 320 includes: a first fuel flow regulating valve 321 for regulating the flow rate of fuel supplied to the inner peripheral fuel manifold 231 of the central burner 211; a second fuel flow regulating valve 322 for regulating the flow rate of fuel supplied to the outer peripheral fuel manifold 232 of the central burner 211; a third fuel flow regulating valve 323 for regulating the flow rate of fuel supplied to the inner peripheral fuel manifold 231 of the outer burner 212; and a fourth fuel flow regulating valve 324 for regulating the flow rate of fuel supplied to the outer peripheral fuel manifold 232 of the outer burner 212.

[0121] In several embodiments of the gas turbine combustor 100, actuators (not shown) for changing the valve opening degree are respectively provided in the first fuel flow regulating valve 321, the second fuel flow regulating valve 322, the third fuel flow regulating valve 323, and the fourth fuel flow regulating valve 324. In several embodiments of the gas turbine combustor 100, the control signals for driving these actuators are configured to be output from the fuel flow control unit 11 described later.

[0122] (Control device 10)

[0123] In the gas turbine combustor 100 of several embodiments, the control device 10 includes the aforementioned plurality of fuel flow regulating valves 310, 320 and a fuel flow control unit 11 that controls the aforementioned plurality of fuel flow regulating valves 310, 320.

[0124] The fuel flow control unit 11 includes a processor 12 that performs various arithmetic operations and a memory 13 that stores various data processed by the processor 12, either temporarily or non-temporarily. The processor 12 is implemented using a CPU, GPU, MPU, DSP, and other arithmetic devices or combinations thereof. The memory 13 is implemented using ROM, RAM, flash memory, or combinations thereof.

[0125] (Issues arising from the use of hydrogen fuel)

[0126] As in several embodiments of the gas turbine combustor 100, if the first air orifice 251 extends in a direction inclined relative to the central axis AXp of the air orifice plate 25, a region with relatively low flow velocity may be locally generated within or relatively close to the air orifice plate 25. For example, if hydrogen, which has a relatively fast combustion rate, is used as fuel, backfire may occur, and the flame may persist in the aforementioned region. If the flame persists in this region, the gas turbine combustor 100 may be damaged.

[0127] Therefore, in the gas turbine combustor 100 involved in several embodiments, damage to the gas turbine combustor 100 is suppressed as follows.

[0128] For example, in the gas turbine combustor 100 of several embodiments, when hydrogen fuel is burned exclusively, hydrogen fuel is not supplied to the first fuel nozzle 21.

[0129] When hydrogen fuel is burned exclusively, hydrogen fuel is not supplied to the first air hole 251 with the inclined channel 256, thus suppressing the continued residual of accidental flames and thereby preventing damage to the gas turbine combustor 100.

[0130] In the gas turbine combustor 100 of several embodiments, when viewed along the central axis AXp of the air orifice plate 25, the second air orifice group G2 can surround the first air orifice group G1.

[0131] The first air port 251 has an inclined passage 256, thus the premixed gas injected from the first air port group G1 forms a circulating flow with the combustion air, which facilitates flame retention. Furthermore, the flame of the premixed gas injected from the first air port group G1 can enhance the ignition and flame retention of the premixed gas injected from the second air port group G2. Therefore, the persistent residual flame can be suppressed, and the flame retention of the gas turbine combustor 100 can be improved.

[0132] In the gas turbine combustor 100 of several embodiments, the first air hole group G1 may be formed in the central region Rc, including the location where the central axis AXp of the air hole plate 25 passes through the air hole plate 25.

[0133] Therefore, a circulating flow is generated in the premixed gas in the downstream region of the central region Rc, which facilitates flame retention. Furthermore, the ignition and flame retention of the premixed gas injected from the second air hole group G2 can be enhanced by the flame of the premixed gas injected from the first air hole group G1. Thus, the persistent residual flame can be suppressed, and the flame retention of the gas turbine combustor 100 can be improved.

[0134] In another embodiment of the gas turbine combustor 100, such as Figure 3B As shown, the first air hole group G1 can be formed at multiple locations along the circumference of the air hole plate 25 at intervals.

[0135] Therefore, in the downstream region at multiple positions spaced apart circumferentially along the air orifice plate 25, a circulating flow is generated in the premixed gas, which facilitates flame retention. Furthermore, the ignition and flame retention of the premixed gas injected from the second air orifice group G2 can be enhanced by the flame of the premixed gas injected from the first air orifice group G1. Thus, the persistent residual flame can be suppressed, and the flame retention of the gas turbine combustor 100 can be improved.

[0136] In addition, Figure 2B and Figure 3B In another embodiment of the gas turbine combustor 100, the inner circumferential air hole 250i corresponding to the fuel nozzle 210 of the first column of the central burner 211, i.e., the inner circumferential fuel nozzle 210i, can be the second air hole 252.

[0137] (Regarding the ratio of natural gas fuel in premixed fuels used exclusively for burning natural gas)

[0138] In the gas turbine burner 100 of several embodiments, when burning natural gas fuel, natural gas fuel can be supplied to a plurality of first fuel nozzles 21 and a plurality of second fuel nozzles 22, such that the ratio of combustion air injected from the first air hole group G1 to natural gas fuel in the premixed fuel is greater than the ratio of natural gas fuel in the premixed fuel injected from the second air hole group G2.

[0139] This improves flame retention when burning natural gas.

[0140] (Regarding the hydrogen co-firing rate during co-firing)

[0141] In the gas turbine burner 100 of several embodiments, when hydrogen fuel and natural gas fuel are mixed, when the ratio of hydrogen fuel in the mixed fuel of hydrogen fuel and natural gas fuel, i.e., the hydrogen mixing rate, is less than a predetermined mixing rate, the mixed fuel is supplied to a plurality of first fuel nozzles 21 and a plurality of second fuel nozzles 22; when the hydrogen mixing rate exceeds the predetermined mixing rate, the mixed fuel is supplied to a plurality of second fuel nozzles 22 only.

[0142] The first air hole 251 corresponding to the first fuel nozzle 21 has an inclined channel 256, which tends to easily produce a persistent residual flame. Therefore, if the hydrogen co-combustion ratio in the hydrogen-natural gas fuel mixture is relatively high, it is easy to produce a persistent residual flame, but as the hydrogen co-combustion ratio decreases, it is difficult to produce a persistent residual flame.

[0143] Therefore, as described above, when the hydrogen co-firing ratio exceeds the prescribed co-firing ratio, mixed fuel is supplied only to the second fuel nozzle 22, and mixed fuel is not supplied to the first fuel nozzle 21, thereby suppressing the continued presence of unintended flames. This ensures the flame retention of the gas turbine combustor 100 and suppresses the continued presence of unintended flames.

[0144] Furthermore, in the fuel system 300, if the hydrogen co-firing ratio is different between the fuel supplied to the first fuel nozzle 21 and the fuel supplied to the second fuel nozzle 22, then when hydrogen fuel is co-fired with natural gas fuel, hydrogen fuel may not be supplied to the first fuel nozzle 21. In this case, natural gas fuel may be supplied only to the first fuel nozzle 21 in the fuel system 300.

[0145] This can further suppress the persistent residual flames caused by accidental combustion of hydrogen and natural gas fuels.

[0146] In the gas turbine burner 100 of several embodiments, when burning natural gas fuel, natural gas fuel can be supplied to the first fuel nozzle 21 and the second fuel nozzle 22.

[0147] The first air hole 251 corresponding to the first fuel nozzle 21 has an inclined channel 256, thus generating a circulating flow in the premixed gas of fuel and combustion air injected from the first air hole 251, which facilitates flame retention. Therefore, it is possible to improve flame retention when burning natural gas.

[0148] (Regarding the control of hydrogen co-firing ratio)

[0149] In the gas turbine combustor 100 of several embodiments, the hydrogen co-firing rate can be controlled as follows.

[0150] Figure 5A It is used for Figure 2A and Figure 3A The diagram illustrates the control of combustion injection ratios Q1, Q2, and Q3 based on the co-firing ratio in a gas turbine combustor 100 according to one embodiment.

[0151] Figure 5B It is used for Figure 2B and Figure 3B The diagram illustrates the control of combustion injection ratios Q1 and Q4 based on the co-firing ratio in a gas turbine combustor 100 according to another embodiment shown.

[0152] exist Figure 5A The diagram shows the ratios of combustion injection ratios Q1, Q2, and Q3 relative to the hydrogen co-firing rate (hereinafter also referred to as fuel ratios). Specifically, combustion injection ratio Q1 is the combustion injection ratio from the inner circumferential fuel nozzle 210i of the central burner 211, combustion injection ratio Q2 is the combustion injection ratio from the inner circumferential fuel nozzle 210i of the outer burner 212, and combustion injection ratio Q3 is the combustion injection ratio from the outer circumferential fuel nozzles 210o of both the central burner 211 and the outer burner 212.

[0153] exist Figure 5B The diagram shows the ratios (fuel ratios) of combustion injection ratios Q1 and Q4 relative to the hydrogen co-firing rate. Specifically, combustion injection ratio Q1 is the combustion injection ratio from the inner circumferential fuel nozzle 210i of the central burner 211, and combustion injection ratio Q4 is the combustion injection ratio from fuel nozzles 210 other than the inner circumferential fuel nozzle 210i of the central burner 211.

[0154] like Figure 5A As shown, in Figure 2A and Figure 3AIn the gas turbine combustor 100 of one embodiment shown, within a range where the hydrogen co-firing rate is zero or higher (i.e., when natural gas is burned exclusively) and a predetermined first co-firing rate a1 (%) is lower, the combustion injection ratio Q1 from the inner peripheral fuel nozzle 210i of the central burner 211 and the combustion injection ratio Q2 from the inner peripheral fuel nozzle 210i of the outer burner 212 gradually decrease as the hydrogen co-firing rate increases, while the combustion injection ratio Q3 from the outer peripheral fuel nozzle 210o of the central burner 211 and the outer burner 212 gradually increases.

[0155] exist Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, if the hydrogen mixing ratio is a first mixing ratio a1 (%) or higher, the combustion injection ratio Q2 of the inner circumferential fuel nozzle 210i from the outer burner 212 becomes a constant value.

[0156] exist Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, within a range where the hydrogen mixing rate is above a first mixing rate a1 (%) and below a predetermined second mixing rate a2 (%), the combustion injection ratio Q1 from the inner peripheral fuel nozzle 210i of the central burner 211 gradually decreases as the hydrogen mixing rate increases, while the combustion injection ratio Q3 from the outer peripheral fuel nozzles 210o of the central burner 211 and the outer burner 212 gradually increases.

[0157] exist Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, if the hydrogen mixing rate is a second mixing rate a2 (%) or higher, the combustion injection ratio Q1 of the inner peripheral fuel nozzle 210i from the central burner 211 becomes zero.

[0158] exist Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, if the hydrogen mixing rate is a second mixing rate a2 (%) or higher, the combustion injection ratio Q3 from the peripheral fuel nozzles 210o of the central burner 211 and the outer burner 212 becomes a constant value.

[0159] In addition, Figure 2A and Figure 3AIn one embodiment of the gas turbine combustor 100, if the mixing ratio exceeds a first mixing ratio a1 (%), the combustion injection ratio Q1 of the inner circumferential fuel nozzle 210i from the central burner 211 can be zero. That is, the combustion injection ratio Q1 of the inner circumferential fuel nozzle 210i from the central burner 211 can vary in a step-like manner with the first mixing ratio a1 (%) as the boundary.

[0160] Similarly, in Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, if the hydrogen co-firing ratio exceeds a first co-firing ratio a1 (%), then the combustion injection ratio Q3 from the peripheral fuel nozzles 210o of the central burner 211 and the outer burner 212 can be equal to... Figure 5A The values ​​shown are the same as those for the second mixing ratio a2 (%) and above. That is, the combustion injection ratio Q3 from the peripheral fuel nozzles 210o of the central burner 211 and the outer burner 212 can vary in a step-like manner with the first mixing ratio a1 (%) as the boundary.

[0161] In addition, Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, the rate of change of the combustion injection ratio Q1 varies with the first co-combustion ratio a1 (%) as the boundary, but it may also remain unchanged.

[0162] Similarly, in Figure 2A and Figure 3A In one embodiment of the gas turbine combustor 100, the rate of change of the combustion injection ratio Q3 changes with the first co-combustion ratio a1 (%) as the boundary, but it may also remain unchanged.

[0163] like Figure 5B As shown, in Figure 2B and Figure 3B In the gas turbine combustor 100 of the other embodiments shown, in the range where the hydrogen co-firing rate is above zero (i.e., when natural gas fuel is burned exclusively) and the second co-firing rate a2 (%) is below, as the hydrogen co-firing rate increases, the combustion injection ratio Q1 of the inner peripheral fuel nozzle 210i of the central burner 211 gradually decreases, while the combustion injection ratio Q4 of the fuel nozzles 210 other than the inner peripheral fuel nozzle 210i from the central burner 211 gradually increases.

[0164] exist Figure 2B and Figure 3BIn another embodiment of the gas turbine combustor 100, if the hydrogen mixing rate is a second mixing rate a2 (%) or higher, the combustion injection ratio Q1 of the inner peripheral fuel nozzle 210i from the central burner 211 becomes zero, and all fuel is injected from fuel nozzles 210 other than the inner peripheral fuel nozzle 210i of the central burner 211.

[0165] In addition, Figure 2B and Figure 3B In another embodiment of the gas turbine combustor 100, if the mixing ratio exceeds a first mixing ratio a1 (%), the combustion injection ratio Q1 of the inner circumferential fuel nozzle 210i from the central burner 211 can be zero. That is, the combustion injection ratio Q1 of the inner circumferential fuel nozzle 210i from the central burner 211 can vary in a step-like manner with the first mixing ratio a1 (%) as the boundary.

[0166] Similarly, in Figure 2B and Figure 3B In the gas turbine combustor 100 of the other embodiments shown, if the hydrogen co-firing ratio exceeds the first co-firing ratio a1 (%), the combustion injection ratio Q4 from the fuel nozzles 210 other than the inner circumferential fuel nozzles 210i of the central burner 211 can be equal to the ratio of the hydrogen co-firing ratio a1 (%). Figure 5B The values ​​shown are the same as those for the second mixing ratio a2 (%) and above. That is, the combustion injection ratio Q4 from the fuel nozzles 210 other than the inner peripheral fuel nozzles 210i of the central burner 211 can vary in a step-like manner with the first mixing ratio a1 (%) as the boundary.

[0167] In addition, Figure 2B and Figure 3B In another embodiment of the gas turbine combustor 100, the rate of change of the combustion injection ratio Q1 varies with the first co-combustion ratio a1 (%) as the boundary, but may also remain unchanged.

[0168] Similarly, in Figure 2B and Figure 3B In another embodiment of the gas turbine combustor 100, the rate of change of the combustion injection ratio Q4 changes with the first co-combustion ratio a1 (%) as the boundary, but may also remain unchanged.

[0169] (Example of how hydrogen co-firing ratio changes over time)

[0170] Figure 6A It means possessing Figure 2A and Figure 3A The graph shown illustrates the changes in fuel ratio and hydrogen co-firing rate of the gas turbine 1 in the gas turbine combustor 100 of one embodiment from the start of operation until the transition to dedicated hydrogen fuel combustion.

[0171] Figure 6B It means possessing Figure 2B and Figure 3B The graph shown is a curve of the change in fuel ratio and hydrogen co-firing rate of the gas turbine 1 of the gas turbine combustor 100 involved in another embodiment, from the start of operation to the transition to dedicated hydrogen fuel combustion.

[0172] like Figure 6A and Figure 6B As shown, in the gas turbine combustor 100 involved in several embodiments, the operation of the gas turbine 1 can be started by burning natural gas fuel exclusively (hydrogen co-firing rate 0%), and the hydrogen co-firing rate can be gradually increased over time to transition to burning hydrogen fuel exclusively (hydrogen co-firing rate 100%).

[0173] (Regarding the control of fuel flow regulating valves 310 and 320)

[0174] exist Figure 2A , Figure 2B , Figure 3A and Figure 3B In the gas turbine combustor 100 of the several embodiments shown, the fuel flow control unit 11 controls the fuel flow regulating valves 310 and 320 as follows.

[0175] (Control of hydrogen co-firing ratio)

[0176] exist Figure 2A , Figure 2B , Figure 3A and Figure 3B In the gas turbine combustor 100 of the several embodiments shown, for example, the processor 12 of the fuel flow control unit 11 calculates the opening degree of the hydrogen flow regulating valve 311 and the natural gas flow regulating valve 312 to generate fuel with a current co-combustion ratio determined, for example, by the operating conditions of the gas turbine 1. Furthermore, the processor 12 outputs control signals for driving actuators (not shown) of the hydrogen flow regulating valve 311 and the natural gas flow regulating valve 312, so that the opening degree of the hydrogen flow regulating valve 311 and the natural gas flow regulating valve 312 becomes the calculated opening degree.

[0177] In the hydrogen flow regulating valve 311 and the natural gas flow regulating valve 312, an actuator (not shown) adjusts the opening degree of the two valves by receiving the control signal. This, in turn, generates fuel with the desired co-firing ratio in the mixing unit 307.

[0178] (Control of fuel ratio)

[0179] exist Figure 2A , Figure 2B , Figure 3A and Figure 3BIn the gas turbine combustor 100 of the several embodiments shown, the processor 12 of the fuel flow control unit 11 calculates, for example, the opening degrees of the first fuel flow regulating valve 321, the second fuel flow regulating valve 322, the third fuel flow regulating valve 323, and the fourth fuel flow regulating valve 324, so that they correspond to the fuel ratio corresponding to the current co-combustion ratio determined by the operating conditions of the gas turbine 1. Furthermore, the processor 12 outputs control signals for driving actuators (not shown) of each fuel flow regulating valve 321, 322, 323, and 324, so that the opening degrees of each fuel flow regulating valve 321, 322, 323, and 324 become the calculated opening degrees.

[0180] In each of the fuel flow regulating valves 321, 322, 323, and 324, an actuator (not shown) adjusts the opening degree of each fuel flow regulating valve 321, 322, 323, and 324 by receiving the control signal. As a result, fuel is injected from each fuel nozzle 210 to achieve a fuel ratio corresponding to the current co-firing ratio.

[0181] The present invention is not limited to the above-described embodiments, but also includes modifications or appropriate combinations thereof to the above-described embodiments.

[0182] The contents described in the above embodiments can be understood as follows, for example.

[0183] (1) The control method of the gas turbine combustor 100 according to at least one embodiment of the present invention is a control method for burning hydrogen fuel and other fuels besides hydrogen fuel. The gas turbine combustor 100 includes an air orifice plate 25 having a plurality of air holes 250 and a plurality of fuel nozzles 210 corresponding to the plurality of air holes 250. The plurality of air holes 250 includes: a plurality of first air holes 251 having an inclined channel 256 extending in a direction inclined relative to the central axis AXp of the air orifice plate 25 in a region of a channel 255 from an inlet end 250a to an outlet end 250b; and a plurality of second air holes 252 extending parallel to the central axis AXp. The plurality of fuel nozzles 210 includes a plurality of first fuel nozzles 21 corresponding to the plurality of first air holes 251 and a plurality of second fuel nozzles 22 corresponding to the plurality of second air holes 252. When burning hydrogen fuel exclusively, hydrogen fuel is not supplied to the plurality of first fuel nozzles 21.

[0184] According to the method described in (1) above, when hydrogen fuel is burned exclusively, hydrogen fuel is not supplied to the first air hole 251 with the inclined channel 256, thus suppressing the continuous residual of accidental flames and thereby suppressing damage to the gas turbine combustor 100.

[0185] (2) In several embodiments, in the method described in (1) above, the air perforation plate 25 may have a first air perforation group G1 in which a plurality of first air perforations 251 are arranged adjacent to each other, and a second air perforation group G2 in which a plurality of second air perforations 252 are arranged adjacent to each other. When viewed along the central axis AXp described above, the second air perforation group G2 may surround the first air perforation group G1.

[0186] According to the method described in (2) above, the first air hole 251 has an inclined channel 256, thus generating a circulating flow in the premixed gas of fuel and combustion air injected from the first air hole group G1, which facilitates flame retention. Furthermore, the flame of the premixed gas injected from the first air hole group G1 can enhance the ignition and flame retention of the premixed gas injected from the second air hole group G2. Therefore, the persistent residual flame can be suppressed, and the flame retention of the gas turbine combustor 100 can be improved.

[0187] (3) In several embodiments, in the method described in (2) above, the first air hole group G1 may be formed in the central region Rc, including the position where the central axis AXp passes through the air hole plate 25.

[0188] According to the method described in (3) above, a circulating flow is generated in the premixed gas in the downstream region of the central region Rc, which facilitates flame retention. Furthermore, the ignition and flame retention of the premixed gas injected from the second air hole group G2 can be enhanced by the flame of the premixed gas injected from the first air hole group G1. As a result, the persistent residual flame can be suppressed, and the flame retention of the gas turbine combustor 100 can be improved.

[0189] (4) In several embodiments, in the method described in (2) or (3) above, the first air hole group G1 may be formed at multiple locations at intervals along the circumference of the air hole plate 25.

[0190] According to the method described in (4) above, a circulating flow is generated in the premixed gas in the downstream region of multiple locations spaced apart circumferentially along the air orifice plate 25, which facilitates flame retention. Furthermore, the ignition and flame retention of the premixed gas injected from the second air orifice group G2 can be enhanced by the flame of the premixed gas injected from the first air orifice group G1. As a result, the persistent residual flame can be suppressed, and the flame retention of the gas turbine combustor 100 can be improved.

[0191] (5) In several embodiments, in the method described in (3) or (4) above, when burning other fuels, other fuels may be supplied to a plurality of first fuel nozzles 21 and a plurality of second fuel nozzles 22 so that the ratio of other fuels in the premixed fuel of combustion air injected from the first air hole group G1 and other fuels is greater than the ratio of other fuels in the premixed fuel injected from the second air hole group G2.

[0192] According to the method described in (5) above, the flame retention is improved when burning other fuels.

[0193] (6) In several embodiments, in any of the methods (1) to (5) above, when hydrogen fuel is mixed with other fuels, when the ratio of hydrogen fuel in the mixed fuel of hydrogen fuel and other fuels, i.e. the hydrogen mixing rate, is less than a predetermined mixing rate, the mixed fuel is supplied to a plurality of first fuel nozzles 21 and a plurality of second fuel nozzles 22, and when the hydrogen mixing rate exceeds the predetermined mixing rate, the mixed fuel is supplied to a plurality of second fuel nozzles 22 only.

[0194] According to the method described in (6) above, even when a mixture of hydrogen fuel and other fuels is injected from multiple first fuel nozzles 21, the persistent residual flame can be suppressed. Thus, the flame retention of the gas turbine combustor 100 can be ensured, and the persistent residual flame can be suppressed.

[0195] (7) In several embodiments, in any of the methods (1) to (5) above, when hydrogen fuel is mixed with other fuels, hydrogen fuel may not be supplied to the plurality of first fuel nozzles 21.

[0196] According to the method described in (7) above, it is possible to suppress the persistent residual flame when hydrogen fuel is mixed with other fuels.

[0197] (8) In several embodiments, in any of the methods (1) to (7) above, when burning other fuels, other fuels may be supplied to a plurality of first fuel nozzles 21 and a plurality of second fuel nozzles 22.

[0198] According to the method described in (8) above, the flame retention can be improved when burning other fuels.

[0199] (9) The control device 10 of the gas turbine combustor 100 according to at least one embodiment of the present invention is a control device 10 for controlling combustion in a gas turbine combustor 100 for burning hydrogen fuel and other fuels besides hydrogen fuel. The gas turbine combustor 100 includes an air orifice plate 25 having a plurality of air holes 250 and a plurality of fuel nozzles 210 corresponding to the plurality of air holes 250. The plurality of air holes 250 includes: a plurality of first air holes 251 having an inclined channel 256 extending in a direction inclined relative to the central axis AXp of the air orifice plate 25 in a region of a passage 255 from an inlet end 250a to an outlet end 250b; and a plurality of second air holes 252 extending parallel to the central axis AXp. The plurality of fuel nozzles 210 includes: a plurality of first fuel nozzles 21 corresponding to the plurality of first air holes 251; and a plurality of second fuel nozzles 22 corresponding to the plurality of second air holes 252. A control device 10 for a gas turbine combustor 100 according to at least one embodiment of the present invention includes: fuel flow regulating valves 310 and 320 for regulating the flow rate of fuel supplied to a plurality of first fuel nozzles 21; and a fuel flow control unit 11 for controlling the fuel flow regulating valves 310 and 320. When burning hydrogen fuel exclusively, the fuel flow control unit 11 controls the fuel flow regulating valves 310 and 320 in such a way that hydrogen fuel is not supplied to the plurality of first fuel nozzles 21.

[0200] According to the structure described above (9), when hydrogen fuel is burned exclusively, hydrogen fuel is not supplied to the first air hole 251 with the inclined channel 256, thus suppressing the continuous residual of accidental flames and thereby suppressing damage to the gas turbine combustor 100.

[0201] Symbol Explanation

[0202] 10-Control device, 11-Fuel flow control unit, 21-First fuel nozzle, 22-Second fuel nozzle, 25-Air orifice plate, 100-Gas turbine burner, 210-Fuel nozzle, 250-Air orifice, 250a-Inlet end, 250b-Outlet end, 251-First air orifice, 252-Second air orifice, 255-Channel, 256-Inclined channel, 310-Fuel flow regulating valve, 320-Fuel flow regulating valve, G1-First air orifice group, G2-Second air orifice group, Rc-Central zone.

Claims

1. A control method for a gas turbine combustor, comprising a method for controlling the combustion of hydrogen fuel and other fuels besides hydrogen fuel, wherein the gas turbine combustor includes an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein... The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, The air perforated plate has: A first air hole group, wherein the plurality of first air holes are arranged adjacent to each other; and The second air hole group, wherein the plurality of second air holes are arranged adjacent to each other. When viewed along the central axis, the second group of air holes surrounds the first group of air holes. The first air hole group is formed in a central region including the location where the central axis passes through the air hole plate. When burning hydrogen fuel exclusively, hydrogen fuel is not supplied to the plurality of first fuel nozzles. When the other fuel is burned, the other fuel is supplied to the plurality of first fuel nozzles and the plurality of second fuel nozzles such that the proportion of the other fuel in the premixed fuel of the combustion air injected from the first air hole group is greater than the proportion of the other fuel in the premixed fuel injected from the second air hole group.

2. A control method for a gas turbine combustor, comprising a method for controlling the combustion of hydrogen fuel and other fuels besides hydrogen fuel, wherein the gas turbine combustor includes an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein... The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, When burning hydrogen fuel exclusively, hydrogen fuel is not supplied to the plurality of first fuel nozzles. When the hydrogen fuel is mixed with the other fuels, if the proportion of hydrogen fuel in the mixed fuel, i.e. the hydrogen mixing rate, is below a predetermined mixing rate, the mixed fuel is supplied to the plurality of first fuel nozzles and the plurality of second fuel nozzles; if the hydrogen mixing rate exceeds the predetermined mixing rate, the mixed fuel is supplied only to the plurality of second fuel nozzles.

3. A control method for a gas turbine combustor, comprising a method for controlling the combustion of hydrogen fuel and other fuels besides hydrogen fuel, wherein the gas turbine combustor includes an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein... The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, When burning hydrogen fuel exclusively, hydrogen fuel is not supplied to the plurality of first fuel nozzles. When the hydrogen fuel is mixed with the other fuels, the hydrogen fuel is not supplied to the plurality of first fuel nozzles.

4. A control method for a gas turbine combustor, comprising a method for controlling the combustion of hydrogen fuel and other fuels besides hydrogen fuel, wherein the gas turbine combustor includes an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein... The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, When burning hydrogen fuel exclusively, hydrogen fuel is not supplied to the plurality of first fuel nozzles. When burning other fuels, the other fuels are supplied to the plurality of first fuel nozzles and the plurality of second fuel nozzles.

5. The control method for a gas turbine combustor according to any one of claims 2 to 4, wherein, The air perforated plate has: A first air hole group, wherein the plurality of first air holes are arranged adjacent to each other; and The second air hole group, wherein the plurality of second air holes are arranged adjacent to each other. When viewed along the central axis, the second air hole group surrounds the first air hole group.

6. The control method for a gas turbine combustor according to claim 5, wherein, The first air hole group is formed in the central region including the location where the central axis passes through the air hole plate.

7. The control method for a gas turbine combustor according to claim 1, wherein, The first air hole group is formed at multiple locations along the circumference of the air hole plate at intervals.

8. A control device for a gas turbine combustor, which is a control device for controlling combustion in a gas turbine combustor that burns hydrogen fuel and other fuels besides hydrogen fuel, said gas turbine combustor comprising an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein, The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, The control device for the gas turbine combustor includes: A fuel flow regulating valve regulates the flow rate of fuel supplied to the plurality of first fuel nozzles; and The fuel flow control unit controls the fuel flow regulating valve. The air perforated plate has: A first air hole group, wherein the plurality of first air holes are arranged adjacent to each other; and The second air hole group, wherein the plurality of second air holes are arranged adjacent to each other. When viewed along the central axis, the second group of air holes surrounds the first group of air holes. The first air hole group is formed in a central region including the location where the central axis passes through the air hole plate. The fuel flow control unit controls the fuel flow regulating valve in the following manner: when burning hydrogen fuel exclusively, the hydrogen fuel is not supplied to the plurality of first fuel nozzles; when burning other fuels exclusively, the other fuels are supplied to the plurality of first fuel nozzles and the plurality of second fuel nozzles, so that the proportion of the other fuels in the premixed fuel of the combustion air injected from the first air orifice group is greater than the proportion of the other fuels in the premixed fuel injected from the second air orifice group.

9. A control device for a gas turbine combustor, which is a control device for controlling combustion in a gas turbine combustor that burns hydrogen fuel and other fuels besides hydrogen fuel, said gas turbine combustor comprising an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein, The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, The control device for the gas turbine combustor includes: A fuel flow regulating valve regulates the flow rate of fuel supplied to the plurality of first fuel nozzles; and The fuel flow control unit controls the fuel flow regulating valve. The fuel flow control unit controls the fuel flow regulating valve in the following manner: when burning hydrogen fuel exclusively, the hydrogen fuel is not supplied to the plurality of first fuel nozzles; when the hydrogen fuel is mixed with the other fuels, when the proportion of hydrogen fuel in the mixed fuel, i.e., the hydrogen mixing rate, is below a predetermined mixing rate, the mixed fuel is supplied to the plurality of first fuel nozzles and the plurality of second fuel nozzles; when the hydrogen mixing rate exceeds the predetermined mixing rate, the mixed fuel is supplied only to the plurality of second fuel nozzles.

10. A control device for a gas turbine combustor, which is a control device for controlling combustion in a gas turbine combustor that burns hydrogen fuel and other fuels besides hydrogen fuel, the gas turbine combustor comprising an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein, The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, The control device for the gas turbine combustor includes: A fuel flow regulating valve regulates the flow rate of fuel supplied to the plurality of first fuel nozzles; and The fuel flow control unit controls the fuel flow regulating valve. The fuel flow control unit controls the fuel flow regulating valve in the following manner: when burning hydrogen fuel exclusively, the hydrogen fuel is not supplied to the plurality of first fuel nozzles; when the hydrogen fuel is mixed with the other fuels, the hydrogen fuel is not supplied to the plurality of first fuel nozzles.

11. A control device for a gas turbine combustor, which is a control device for controlling combustion in a gas turbine combustor that burns hydrogen fuel and other fuels besides hydrogen fuel, said gas turbine combustor comprising an air orifice plate having a plurality of air holes and a plurality of fuel nozzles corresponding to the plurality of air holes, wherein, The plurality of air holes include: A plurality of first air holes have inclined channels extending in a direction inclined relative to the central axis of the air hole plate in a region including at least the outlet end of a passage from the inlet end to the outlet end; and Multiple second air holes extend parallel to the central axis. The plurality of fuel nozzles includes: A plurality of first fuel nozzles, each corresponding to a plurality of first air holes; and Multiple second fuel nozzles, each corresponding to one of the multiple second air holes, The control device for the gas turbine combustor includes: A fuel flow regulating valve regulates the flow rate of fuel supplied to the plurality of first fuel nozzles; and The fuel flow control unit controls the fuel flow regulating valve. The fuel flow control unit controls the fuel flow regulating valve in the following manner: when burning hydrogen fuel exclusively, hydrogen fuel is not supplied to the plurality of first fuel nozzles; when burning other fuels exclusively, the other fuels are supplied to the plurality of first fuel nozzles and the plurality of second fuel nozzles.

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