METHOD FOR OPERATING GAS TURBINES

Abstract

According to the present invention, a gas turbine comprises: a first fuel injection nozzle capable of injecting a first fuel; and a second fuel injection nozzle capable of injecting a second fuel, located downstream of the first fuel injection nozzle. The first fuel and the second fuel contain hydrogen and a fuel other than hydrogen, respectively, and are combusted by a combustion chamber of the gas turbine.In a method for operating this gas turbine, when a total hydrogen co-combustion ratio corresponding to the total fuel supplied to the combustion chamber is increased to a preset target value for total hydrogen co-combustion ratio, a second hydrogen co-combustion ratio corresponding to the second fuel is controlled to increase, while a first hydrogen co-combustion ratio corresponding to the first fuel is limited to a first maximum hydrogen co-combustion ratio or less in a case where the total hydrogen co-combustion ratio is equal to or greater than a threshold value.

Description

Technical field

[0001] The present disclosure relates to a method for operating a gas turbine.

[0002] The present application claims the advantage of priority based on Japanese patent application No. 2023-128011, which was filed with the Japanese Patent Office on August 4, 2023, and the contents of which are incorporated herein by reference. State of the art

[0003] For example, in the case of a thermal power plant, improving electricity generation efficiency or actively using fuels such as hydrogen, which is different from fossil fuels, is being considered as a means of reducing the amount of carbon dioxide (CO2) emissions, which is a cause of global warming (see, for example, PTL 1). List of citations from patent literature

[0004] [PTL 1] Japanese unexamined patent application publication no. 2021-046949 Summary of the invention: Technical problem

[0005] To reduce carbon dioxide emissions, it is desirable to increase the hydrogen co-combustion ratio. However, since hydrogen has low ignition energy and a high combustion rate, increasing the hydrogen co-combustion ratio increases the likelihood of flame flashback or similar issues.

[0006] At least one embodiment of the present disclosure was made in view of the above circumstances, and one object of the present disclosure is to provide a method for operating a gas turbine which is capable of increasing a hydrogen co-combustion ratio while suppressing flame flashback or the like. Solution to the problem

[0007] To solve the problem described above, a method for operating a gas turbine according to at least one embodiment of the present disclosure is provided, comprising a combustion chamber containing a first fuel injection nozzle configured to inject a first fuel and located in a combustion chamber, and a second fuel injection nozzle configured to inject a second fuel and located downstream of the first fuel injection nozzle in the combustion chamber, wherein the combustion chamber is configured to use hydrogen and a fuel other than hydrogen as the first fuel and the second fuel, and wherein the method comprises: Increase if an overall hydrogen co-combustion ratio corresponding to an overall fuel supplied to the combustion chamber is increased to a preset target value for overall hydrogen co-combustion ratio, in a case where the overall hydrogen co-combustion ratio is equal to or greater than a threshold, a second hydrogen co-combustion ratio corresponding to the second fuel, while a first hydrogen co-combustion ratio corresponding to the first fuel is limited to being equal to or less than a first maximum hydrogen co-combustion ratio. Advantageous effects of the invention

[0008] According to at least one embodiment of the present disclosure, it is possible to provide a method for operating a gas turbine which is capable of increasing a hydrogen co-combustion ratio while suppressing flame flashback or the like. Brief description of the drawings Fig. Figure 1 is a schematic configuration view of a gas turbine according to one embodiment. Fig. Figure 2 is a schematic cross-sectional view of a combustion chamber of Fig. 1. Fig. Figure 3 is a schematic configuration diagram of a fuel supply device. Fig. 2. Fig. Figure 4 is a configuration diagram of a gas turbine control device according to one embodiment. Fig. Figure 5 is a diagram showing a control example of a first hydrogen co-combustion ratio and a second hydrogen co-combustion ratio, and a ratio of a hydrogen co-combustion ratio between the first hydrogen co-combustion ratio and the second hydrogen co-combustion ratio with respect to a total hydrogen co-combustion ratio by the gas turbine control device of Fig. 4 shows. Description of embodiments

[0009] Some embodiments of the present disclosure are described below with reference to the accompanying drawings. However, dimensions, materials, shapes, and relative arrangements of configurations described as embodiments or illustrated in the drawings are not intended to limit the scope of protection of the present disclosure and are merely examples used to describe the present disclosure.

[0010] First, a configuration of a gas turbine, which is an application goal of the method for operating a gas turbine according to at least one embodiment of the present disclosure, is described with reference to Fig. 1 described. Fig. Figure 1 is a schematic configuration diagram of a gas turbine 1 according to an embodiment.

[0011] The gas turbine 1 includes a compressor 2 for generating compressed air as an oxidizer, a combustion chamber 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be driven by the combustion gas. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6, and power generation is achieved through the rotational energy of the turbine 6.

[0012] The compressor 2 comprises a compressor housing 10, an air inlet port 12 provided on an inlet side of the compressor housing 10 for drawing in air, a rotor 8 designed to penetrate both the compressor housing 10 and a turbine housing 22 to be described later, and various blades arranged within the compressor housing 10. The various blades include an inlet guide blade 14 provided on one side of the air inlet port 12, several stator blades 16 attached to one side of the compressor housing 10, and several rotor blades 18 embedded in the rotor 8 arranged alternately with respect to the stator blades 16.

[0013] Compressor 2 may contain other components, such as a venting chamber (not shown). In compressor 2, the air drawn in through the air inlet port 12 passes through the multiple stator blades 16 and the multiple rotor blades 18 and is compressed to high-temperature, high-pressure compressed air. This high-temperature, high-pressure compressed air is then conveyed from compressor 2 to the combustion chamber 4 in a rear stage.

[0014] The combustion chamber 4 is arranged within a housing 20. Several combustion chambers 4 can be arranged in a ring around the rotor 8 within the housing 20. Fuel and compressed air generated by the compressor 2 are supplied to the combustion chamber 4, and the fuel is burned to produce combustion gas, which is a working fluid for the turbine 6. The combustion gas is then conveyed from the combustion chamber 4 to the turbine 6 in the downstream stage.

[0015] The turbine 6 comprises the turbine housing 22 and various blades arranged within the turbine housing 22. These blades include several stator blades 24, which are attached to one side of the turbine housing 22, and several rotor blades 26, which are embedded in the rotor 8 in an alternating arrangement with respect to the stator blades 24. The turbine 6 may also include other components, such as an exhaust guide vane. In the turbine 6, the rotor 8 is driven by causing the combustion gas to pass through the several stator blades 24 and the several rotor blades 26. This, in turn, drives the generator connected to the rotor 8.

[0016] An exhaust chamber 30 is connected downstream of the turbine housing 22 via an exhaust housing 28. After the turbine 6 has been driven, the combustion gas is discharged to the outside via the exhaust housing 28 and the exhaust chamber 30.

[0017] Fig. Figure 2 is a schematic cross-sectional view of combustion chamber 4. Fig. 1, and Fig. Figure 3 is a schematic configuration diagram of a fuel supply device 70 of Fig. 2. The combustion chamber 4 includes a combustion lining 46, which is provided in a combustion chamber housing 40, defined by the housing 20, a first fuel injection nozzle 50 for injecting a first fuel F1 into the combustion lining 46 and a second fuel injection nozzle 60 for injecting a second fuel F2 and which is located downstream of the first fuel injection nozzle 50.

[0018] The first fuel F1 and the second fuel F2 are each supplied by the fuel supply device 70 to the first fuel injection nozzle 50 and the second fuel injection nozzle 60, respectively. As in Fig. As shown in Figure 3, the fuel supply device 70 can use hydrogen FH as the fuel and natural gas FN, which is a fuel different from hydrogen, and can independently adjust hydrogen co-combustion ratios (a ratio of hydrogen FH to a total fuel) in the first fuel F1 and the second fuel F2.

[0019] The fuel supply device 70 includes a hydrogen supply source 72, which can supply hydrogen FH, and a natural gas supply source 74, which can supply natural gas FN. The hydrogen FH from the hydrogen supply source 72 can be supplied to each of the first fuel injector 50 and the second fuel injector 60 via a first hydrogen supply line 73, a second hydrogen supply line 75, and a third hydrogen supply line 76. A first control valve 80 for regulating the supply quantity of hydrogen FH to the first fuel injector 50 is provided in the second hydrogen supply line 75. A second control valve 81 for regulating the supply quantity of hydrogen FH to the second fuel injector 60 is provided in the third hydrogen supply line 76.The opening degree of the first control valve 80 and the opening degree of the second control valve 81 are controlled on the basis of a control signal from a gas turbine control device 100, so that a hydrogen co-combustion ratio (hereinafter optionally referred to as a "first hydrogen co-combustion ratio Cr1") of the first fuel F1 supplied to the first fuel injection nozzle 50 can be adjusted.

[0020] The natural gas FN from the natural gas supply source 74 can be supplied to each of the first fuel injection nozzle 50 and the second fuel injection nozzle 60 from a first natural gas supply line 77 via a second natural gas supply line 78 and a third natural gas supply line 79. A third control valve 82 for regulating the supply quantity of natural gas FN to the first fuel injection nozzle 50 is provided in the second natural gas supply line 78. A fourth control valve 83 for regulating the supply quantity of natural gas FN to the second fuel injection nozzle 60 is provided in the third natural gas supply line 79.The opening degree of the third control valve 82 and the opening degree of the fourth control valve 83 are controlled on the basis of the control signal from the gas turbine control device 100, so that a hydrogen co-combustion ratio (hereinafter optionally referred to as a "second hydrogen co-combustion ratio Cr2") of the second fuel F2 supplied to the second fuel injector 60 can be adjusted.

[0021] The first fuel F1, injected from the first fuel injector 50, and the second fuel F2, injected from the second fuel injector 60, are combusted by the compressor 2 at the combustion lining 46 by mixing with combustion air. The combustion gas produced by the combustion is fed to the turbine 6 via a transition piece 48, which is connected downstream of the combustion lining 46.

[0022] The following describes the gas turbine control device 100 for controlling the gas turbine 1 with the configuration described above. Fig. Figure 4 is a configuration diagram of the gas turbine control device 100 according to one embodiment.

[0023] The gas turbine control device 100 is a control unit that controls the gas turbine 1 and is configured, for example, with a central processing unit (CPU), random access memory (RAM), read-only memory (ROM), and a computer-readable storage medium or the like. A series of processing operations for realizing various functions is stored, for example, in a storage medium or the like in the form of a program, and the CPU reads this program into RAM or the like and performs processing for information processing and calculation, thereby realizing various functions.The program can be provided in a form pre-installed in ROM or on another storage medium, in a form provided in a state where it is stored on a computer-readable storage medium, or in a form delivered via wired or wireless communication means, or the like. The computer-readable storage medium is a magnetic disk, a magneto-optical disk, a CD-ROM, a DVD-ROM, a semiconductor memory, or the like.

[0024] As in Fig. As shown in Figure 4, the gas turbine control device 100 includes a setpoint adjustment unit 102 for total hydrogen co-combustion ratio, a first hydrogen co-combustion ratio control unit 104 and a second hydrogen co-combustion ratio control unit 106.

[0025] The setpoint adjustment unit 102 for total hydrogen co-combustion ratio is configured to set a setpoint (hereinafter referred to as a ‘setpoint Crt for total hydrogen co-combustion ratio’) with respect to a total hydrogen co-combustion ratio Cr (a ratio of hydrogen FH in a total quantity of the first fuel F1 supplied to the first fuel injector 50 and the second fuel F2 supplied to the second fuel injector 60).

[0026] The first hydrogen co-combustion ratio control unit 104 is configured to control a first hydrogen co-combustion ratio Cr1, corresponding to the first fuel F1. The first hydrogen co-combustion ratio Cr1 is a hydrogen co-combustion ratio in the first fuel F1 and is an indicator specifying the ratio of hydrogen FH to the total first fuel F1. Specifically, the first hydrogen co-combustion ratio control unit 104 controls the first hydrogen co-combustion ratio Cr1, as a ratio of hydrogen FH and natural gas FN in the first fuel F1, by adjusting the opening degrees of the first control valve 80 and the third control valve 82.

[0027] The second hydrogen co-combustion ratio control unit 106 is configured to control a second hydrogen co-combustion ratio Cr2, corresponding to the second fuel F2. The second hydrogen co-combustion ratio Cr2 is a hydrogen co-combustion ratio within the second fuel F2 and is an indicator specifying the ratio of hydrogen FH to the total second fuel F2. Specifically, the second hydrogen co-combustion ratio control unit 106 controls the second hydrogen co-combustion ratio Cr2 as a ratio of hydrogen FH and natural gas FN in the second fuel F2 by adjusting the opening degrees of the second control valve 81 and the fourth control valve 83.

[0028] The following describes a gas turbine control procedure performed by the gas turbine control device 100, which has the above configuration. Fig. Figure 5 is a diagram showing a control example of the first hydrogen co-combustion ratio Cr1 and the second hydrogen co-combustion ratio Cr2, and a ratio of a hydrogen co-combustion ratio Cr2 / Cr1 between the first hydrogen co-combustion ratio Cr1 and the second hydrogen co-combustion ratio Cr2 with respect to the total hydrogen co-combustion ratio Cr by the gas turbine control device 100. Fig. 4 shows.

[0029] In the present embodiment, a case in which the total hydrogen co-combustion ratio Cr, which is approximately zero in an initial state, is gradually increased by the gas turbine control device 100 so that the setpoint Crt for total hydrogen co-combustion ratio (> Crth) set by the setpoint adjustment unit 102 is reached is described as an example.

[0030] In a range where the total hydrogen co-combustion ratio Cr is from zero to less than a threshold value Crth, the first hydrogen co-combustion ratio control unit 104 and the second hydrogen co-combustion ratio control unit 106 control the total hydrogen co-combustion ratio Cr such that it is increased so that the first hydrogen co-combustion ratio Cr1 is equal to or less than the second hydrogen co-combustion ratio Cr2. That is, in this range, the total hydrogen co-combustion ratio Cr is controlled to increase from zero to the threshold value Crth, while the first hydrogen co-combustion ratio Cr1 is suppressed so that it is equal to or less than the second hydrogen co-combustion ratio Cr2.As a result, in an area where the total hydrogen co-combustion ratio Cr is relatively low, the first hydrogen co-combustion ratio Cr1 is suppressed so that it is equal to or less than the second hydrogen co-combustion ratio Cr2, thus more reliably reducing the probability of flame flashback or the like.

[0031] In this case, within a range where the total hydrogen co-combustion ratio Cr lies from zero to less than the threshold value Crth, an operating point can exist at which the first hydrogen co-combustion ratio Cr1 is equal to the second hydrogen co-combustion ratio Cr2. In the present embodiment, the first hydrogen co-combustion ratio Cr1 is specifically controlled such that it is equal to the second hydrogen co-combustion ratio Cr2 over the entire range of the total hydrogen co-combustion ratio Cr from zero to less than the threshold value Crth (that is, the ratio of the hydrogen co-combustion ratio Cr2 / Cr1 is approximately constant at "1").

[0032] On the other hand, in a range where the total hydrogen co-combustion ratio Cr is equal to or greater than the threshold Crth, the second hydrogen co-combustion ratio Cr2 is controlled to increase it, while the first hydrogen co-combustion ratio Cr1 is suppressed to be equal to or less than a first maximum hydrogen co-combustion ratio Cr1max. Consequently, in a case where the total hydrogen co-combustion ratio Cr is relatively high, the first hydrogen co-combustion ratio Cr1, corresponding to the first fuel F1 injected from the first fuel injector 50, located relatively upstream of a combustion chamber, is excessively large, thus effectively reducing the likelihood of flame flashback or similar phenomena.On the other hand, by increasing the second hydrogen co-combustion ratio Cr2, which corresponds to the second fuel F2 injected from the second fuel injector 60 located relatively downstream of the combustion chamber, the overall hydrogen co-combustion ratio Cr can be increased to the target value Crt for the overall hydrogen co-combustion ratio, which exceeds the threshold value Crth. In this way, it is possible to achieve hydrogen co-combustion operation with a high hydrogen co-combustion ratio while suppressing flame flashback or similar issues.

[0033] In the present embodiment, particularly in a range where the total hydrogen co-combustion ratio Cr is greater than the threshold Crth, the first hydrogen co-combustion ratio Cr1 is maintained constant at the first maximum hydrogen co-combustion ratio Cr1max, independent of the total hydrogen co-combustion ratio Cr. The first maximum hydrogen co-combustion ratio Cr1max is, for example, set to 40%. That is, in a range where the total hydrogen co-combustion ratio Cr exceeds the threshold Crth, the first hydrogen co-combustion ratio Cr1 can be increased to a maximum of 40% and cannot be increased further. Consequently, the first hydrogen co-combustion ratio Cr1 is excessively large, thus effectively reducing the probability of flame flashback or similar phenomena.

[0034] Furthermore, in a case where the total hydrogen co-combustion ratio Cr is equal to or greater than the threshold Crth, the second hydrogen co-combustion ratio Cr2 is limited to be equal to or less than a second maximum hydrogen co-combustion ratio Cr2max. In the present embodiment, the second maximum hydrogen co-combustion ratio Cr2max is, for example, 100%.In a range where the total hydrogen co-combustion ratio Cr is equal to or greater than the threshold Crth, the second hydrogen co-combustion ratio Cr2 can be increased in a range where the second hydrogen co-combustion ratio Cr2 is equal to or less than the second maximum hydrogen co-combustion ratio Cr2max, while the first hydrogen co-combustion ratio Cr1 is suppressed so that it is equal to or less than the first maximum hydrogen co-combustion ratio Cr1max, as described above, so that the total hydrogen co-combustion ratio Cr can be increased to a value greater than that in the prior art, while preventing flame flashback or the like.For example, in an area where the total hydrogen co-combustion ratio Cr is equal to or greater than the threshold Crth, the total hydrogen co-combustion ratio Cr can be increased to 70% by maintaining the first hydrogen co-combustion ratio Cr1 at 40% while increasing the second hydrogen co-combustion ratio Cr2 to 100%.

[0035] As described above, according to each of the embodiments described above, in a case where the total hydrogen co-combustion ratio Cr is increased to exceed the threshold Crth, the first hydrogen co-combustion ratio Cr1, corresponding to the first fuel F1 injected from the first fuel injector 50 located relatively upstream of the combustion chamber, is limited to be equal to or less than the first maximum hydrogen co-combustion ratio Cr1max in a case where the total hydrogen co-combustion ratio Cr is equal to or greater than the threshold Crth. As a result, the first hydrogen co-combustion ratio Cr1 is excessively large, thus effectively reducing the probability of flame flashback or similar phenomena.On the other hand, by increasing the second hydrogen co-combustion ratio Cr2, which corresponds to the second fuel F2 injected from the second fuel injector 60 located relatively downstream of the combustion chamber, the overall hydrogen co-combustion ratio Cr is increased to the target value Crt for the overall hydrogen co-combustion ratio, which exceeds the threshold value Crth. In this way, it is possible to achieve hydrogen co-combustion operation with a high hydrogen co-combustion ratio while suppressing flame flashback or similar issues.

[0036] Furthermore, it is possible to suitably replace the components in the embodiment described above with known components within the scope of protection, which does not deviate from the concept of the present disclosure, and the embodiments described above can be suitably combined with one another.

[0037] For example, the content disclosed in each of the embodiments is understood as follows. (1) A method for operating a gas turbine according to one aspect comprising a combustion chamber, which includes a first fuel injector configured to inject a first fuel into a combustion chamber, and a second fuel injector configured to inject a second fuel and located downstream of the first fuel injector in the combustion chamber, wherein the combustion chamber is configured to use hydrogen and a fuel other than hydrogen as the first fuel and the second fuel, and wherein the method comprises: Increase if an overall hydrogen co-combustion ratio corresponding to an overall fuel supplied to the combustion chamber is increased to a preset target value for overall hydrogen co-combustion ratio, in a case where the overall hydrogen co-combustion ratio is equal to or greater than a threshold, a second hydrogen co-combustion ratio corresponding to the second fuel, while a first hydrogen co-combustion ratio corresponding to the first fuel is limited to being equal to or less than a first maximum hydrogen co-combustion ratio.

[0038] According to aspect (1) described above, if the total hydrogen co-combustion ratio is increased to exceed the threshold, the first hydrogen co-combustion ratio corresponding to the first fuel injected from the first fuel injector located relatively upstream of the combustion chamber is limited to be equal to or less than the first maximum hydrogen co-combustion ratio if the total hydrogen co-combustion ratio is equal to or greater than the threshold. As a result, the hydrogen co-combustion ratio of the first fuel is excessively large, thus effectively reducing the likelihood of flame flashback or similar phenomena.On the other hand, by increasing the second hydrogen co-combustion ratio, which corresponds to the second fuel injected from the second fuel injector located relatively downstream of the combustion chamber, the overall hydrogen co-combustion ratio is increased to the target value for overall hydrogen co-combustion ratio, which exceeds the threshold. In this way, it is possible to achieve hydrogen co-combustion operation with a high hydrogen co-combustion ratio while suppressing flameback or similar issues.

[0039] (2) In another aspect, in accordance with aspect (1) described above

[0040] In a case where the total hydrogen co-combustion ratio is equal to or greater than the threshold, maintain the first hydrogen co-combustion ratio at the first maximum hydrogen co-combustion ratio.

[0041] According to aspect (2) described above, if the total hydrogen co-combustion ratio is increased to exceed the threshold, the first hydrogen co-combustion ratio is maintained constant at or below the first maximum hydrogen co-combustion ratio if the total hydrogen co-combustion ratio is equal to or greater than the threshold. As a result, the hydrogen co-combustion ratio of the first fuel is excessively high, thus effectively reducing the likelihood of flame flashback or similar phenomena.

[0042] (3) In another aspect, according to aspect (1) or (2) described above,

[0043] in a case where the total hydrogen co-combustion ratio is less than the threshold, the first hydrogen co-combustion ratio is equal to or less than the second hydrogen co-combustion ratio.

[0044] According to aspect (3) described above, in a case where the total hydrogen co-combustion ratio is increased so that it exceeds the threshold, the first hydrogen co-combustion ratio is adjusted so that, in a case where the total hydrogen co-combustion ratio is less than the threshold, it is equal to or less than the second hydrogen co-combustion ratio.

[0045] (4) Regarding another aspect, there is, in accordance with the aspect described above (3)

[0046] in a case where the total hydrogen co-combustion ratio is less than the threshold, a case where the first hydrogen co-combustion ratio is equal to the second hydrogen co-combustion ratio.

[0047] According to aspect (4) described above, in a case where the total hydrogen co-combustion ratio is increased to exceed the threshold, the first hydrogen co-combustion ratio and the second hydrogen co-combustion ratio are adjusted such that there is a point in time at which the first hydrogen co-combustion ratio is equal to the second hydrogen co-combustion ratio in a case where the total hydrogen co-combustion ratio is less than the threshold.

[0048] (5) In another aspect, according to one of the aspects described above (1) to (4) the first maximum hydrogen co-combustion ratio 40%.

[0049] According to aspect (5) described above, if the total hydrogen co-combustion ratio is increased to such an extent that it exceeds the threshold, the first maximum hydrogen co-combustion ratio, which is an upper limit of the first hydrogen co-combustion ratio, is set to 40%. As a result, the first hydrogen co-combustion ratio is excessively large, so that the probability of flame flashback or the like can be effectively reduced.

[0050] (6) For another aspect, in accordance with one of the aspects described above (1) to (5) If the total hydrogen co-combustion ratio, which corresponds to the total fuel supplied to the combustion chamber, is increased to the preset target value for total hydrogen co-combustion ratio, in a case where the total hydrogen co-combustion ratio is equal to or greater than the threshold, the second hydrogen co-combustion ratio is limited so that it is equal to or less than a second maximum hydrogen co-combustion ratio.

[0051] According to aspect (6) described above, in a case where the total hydrogen co-combustion ratio is increased to exceed the threshold, the second hydrogen co-combustion ratio is variably controlled in a range where the second hydrogen co-combustion ratio is limited to being equal to or less than the second maximum hydrogen co-combustion ratio, so that the total hydrogen co-combustion ratio can be adjusted to the setpoint for total hydrogen co-combustion ratio.

[0052] (7) In another aspect, according to the aspect described above (6) the second maximum hydrogen co-combustion ratio 100%.

[0053] According to aspect (7) described above, by setting the second maximum hydrogen co-combustion ratio, which is an upper limit of the second hydrogen co-combustion ratio, to 100%, a wide adjustment range of the overall hydrogen co-combustion ratio can be ensured by adjusting the second hydrogen co-combustion ratio. As a result, a high overall hydrogen co-combustion ratio can be achieved, while the first hydrogen co-combustion ratio is limited to being equal to or less than the first maximum hydrogen co-combustion ratio.

[0054] (8) In another aspect, according to one of the aspects described above (1) to (6) a maximum target value of 70% for the total hydrogen co-combustion ratio.

[0055] According to the aspect described above (8), increasing the overall hydrogen co-combustion ratio to 70% will enable the gas turbine to operate at a high hydrogen co-combustion ratio compared to the state of the art. Reference symbol list 1 gas turbine 2 compressor 4 Combustion chamber 6 Turbine 8 Rotor 10 compressor housings 12 Air intake connection 14 Inlet guide vane 16 Stator blades 18 rotor blades 20 cases 22 turbine housings 24 Stator blades 26 Rotor blade 28 outlet housings 30 Outlet chamber 40 combustion chamber housings 46 Combustion lining 48 Transition piece 50 first fuel injector 60 second fuel injector 70 Fuel supply device 72 Hydrogen supply source 73 first hydrogen supply line 74 Natural gas supply source 75 second hydrogen supply line 76 third hydrogen supply line 77 first natural gas supply line 78 second natural gas supply line 79 Third natural gas supply line 80 first control valve 81 second control valve 82 third control valve 83 fourth control valve 100 gas turbine control devices 102 Setpoint adjustment unit for total hydrogen co-combustion ratio 104 first hydrogen co-combustion ratio control unit 106 second hydrogen co-combustion ratio control unit QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] JP 2023-128011

[0002] JP 2021-046949

[0004]

Claims

[1] A method for operating a gas turbine comprising a combustion chamber containing a first fuel injector configured to inject a first fuel into the combustion chamber and a second fuel injector configured to inject a second fuel, located downstream of the first fuel injector in the combustion chamber, wherein the combustion chamber is configured to use hydrogen and a fuel other than hydrogen as the first fuel and the second fuel, and wherein the method comprises: Increase if an overall hydrogen co-combustion ratio corresponding to an overall fuel supplied to the combustion chamber is increased to a preset target value for overall hydrogen co-combustion ratio, in a case where the overall hydrogen co-combustion ratio is equal to or greater than a threshold, a second hydrogen co-combustion ratio corresponding to the second fuel, while a first hydrogen co-combustion ratio corresponding to the first fuel is limited to being equal to or less than a first maximum hydrogen co-combustion ratio. [2] Method for operating a gas turbine according to claim 1, wherein in a case where the total hydrogen co-combustion ratio is equal to or greater than the threshold, the first hydrogen co-combustion ratio is maintained at the first maximum hydrogen co-combustion ratio. [3] Method for operating a gas turbine according to claim 1 or 2, wherein in a case where the total hydrogen co-combustion ratio is less than the threshold, the first hydrogen co-combustion ratio is equal to or less than the second hydrogen co-combustion ratio. [4] Method for operating a gas turbine according to claim 3, wherein in a case where the total hydrogen co-combustion ratio is less than the threshold, there is a case where the first hydrogen co-combustion ratio is equal to the second hydrogen co-combustion ratio. [5] Method for operating a gas turbine according to claim 1 or 2, wherein the first maximum hydrogen co-combustion ratio is 40%. [6] A method for operating a gas turbine according to claim 1 or 2, wherein, when the total hydrogen co-combustion ratio corresponding to the total fuel supplied to the combustion chamber is increased to the preset target value for total hydrogen co-combustion ratio, in a case where the total hydrogen co-combustion ratio is equal to or greater than the threshold value, the second hydrogen co-combustion ratio is limited to be equal to or less than a second maximum hydrogen co-combustion ratio. [7] Method for operating a gas turbine according to claim 6, wherein the second maximum hydrogen co-combustion ratio is 100%. [8] Method for operating a gas turbine according to claim 1 or 2, wherein a maximum setpoint for total hydrogen co-combustion ratio is 70%.

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