WO2022209562A1 - ガスタービンシステム - Google Patents
ガスタービンシステム Download PDFInfo
- Publication number
- WO2022209562A1 WO2022209562A1 PCT/JP2022/009179 JP2022009179W WO2022209562A1 WO 2022209562 A1 WO2022209562 A1 WO 2022209562A1 JP 2022009179 W JP2022009179 W JP 2022009179W WO 2022209562 A1 WO2022209562 A1 WO 2022209562A1
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- WIPO (PCT)
- Prior art keywords
- ammonia
- turbine system
- gas turbine
- combustor
- flow path
- Prior art date
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- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims abstract description 399
- 229910021529 ammonia Inorganic materials 0.000 claims abstract description 197
- 238000000354 decomposition reaction Methods 0.000 claims abstract description 105
- 239000003054 catalyst Substances 0.000 claims abstract description 85
- 238000002485 combustion reaction Methods 0.000 claims abstract description 47
- 238000001816 cooling Methods 0.000 claims description 13
- 239000007789 gas Substances 0.000 description 247
- 239000000446 fuel Substances 0.000 description 21
- 230000004048 modification Effects 0.000 description 15
- 238000012986 modification Methods 0.000 description 15
- 238000010586 diagram Methods 0.000 description 10
- 238000000034 method Methods 0.000 description 10
- 230000008569 process Effects 0.000 description 9
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 4
- 230000004913 activation Effects 0.000 description 4
- 238000000605 extraction Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 239000001257 hydrogen Substances 0.000 description 4
- 229910052739 hydrogen Inorganic materials 0.000 description 4
- 239000006200 vaporizer Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000005856 abnormality Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000498 cooling water Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/24—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being liquid at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
Definitions
- a gas turbine system that obtains power by burning fuel in a combustor is used.
- a gas turbine system for example, as disclosed in Patent Document 1, there is a system that uses ammonia as a fuel. Emission of carbon dioxide is suppressed by using ammonia as a fuel.
- Ammonia has the property (that is, flame retardancy) that it is difficult to burn compared to other fuels. Therefore, combustors in which ammonia is used as fuel may fail to ignite. Also, even if ignition is successful, there is a risk that some fuel will be discharged without being burned.
- An object of the present disclosure is to provide a gas turbine system capable of improving combustibility in a combustor in which ammonia is used as fuel.
- the gas turbine system of the present disclosure includes an ammonia tank, a combustor connected to the ammonia tank and having a combustion chamber, an intake flow path connected to the combustor, and an intake flow path provided in the intake flow path.
- a cracked gas reservoir connected to the combustor; a bleed flow path connected to the compressor; an ammonia decomposition catalyst disposed in a space communicating with the flow path and connected to the ammonia tank and the decomposition gas storage device.
- a cooling device may be provided in the channel connecting the ammonia decomposition catalyst and the decomposition gas storage device.
- the cooling device is a heat exchanger provided in a flow path connecting the ammonia decomposition catalyst and the cracked gas storage device, and the flow path connecting the ammonia tank and the ammonia decomposition catalyst may pass through the heat exchanger. .
- a flow path connecting the ammonia tank and the ammonia decomposition catalyst is provided with a first flow rate control valve, and the first flow rate is controlled so that ammonia is supplied from the ammonia tank to the ammonia decomposition catalyst during operation of the gas turbine system.
- a control device for controlling the control valve may be provided.
- a second flow control valve is provided in the flow path connecting the cracked gas storage device and the combustor, and a third flow control valve is provided in the flow path connecting the ammonia tank and the combustor.
- the second flow control valve and the second flow control valve are arranged so that the supply of ammonia from the ammonia tank to the combustor starts after the supply of cracked gas from the cracked gas storage to the combustor starts.
- 3 flow control valves may be controlled.
- FIG. 1 is a schematic diagram showing the configuration of a gas turbine system according to an embodiment of the present disclosure.
- FIG. 2 is a flowchart showing an example of the flow of processing performed by the control device according to the embodiment of the present disclosure.
- FIG. 3 is a schematic diagram showing the configuration of a gas turbine system according to a first modification.
- FIG. 4 is a schematic diagram showing the configuration of a gas turbine system according to a second modification.
- FIG. 5 is a schematic diagram showing the configuration of a gas turbine system according to a third modification.
- FIG. 6 is a schematic diagram showing the configuration of a gas turbine system according to a fourth modification.
- FIG. 1 is a schematic diagram showing the configuration of a gas turbine system 1 according to this embodiment.
- the gas turbine system 1 includes a supercharger 11, a generator 12, a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, and a decomposition gas storage device 17. , a first flow control valve 21 , a second flow control valve 22 , a third flow control valve 23 , an air bleed valve 24 and a control device 31 .
- the gas turbine system 1 includes a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, a decomposition gas storage device 17, a first flow control valve 21, a second flow control valve 22, A third flow control valve 23 and a controller 31 are included in the combustion device 10 .
- the supercharger 11 has a compressor 11a and a turbine 11b. Compressor 11a and turbine 11b rotate as a unit. Compressor 11a and turbine 11b are connected by a shaft.
- the compressor 11 a is provided in an intake passage 41 connected to the combustor 13 . Air supplied to the combustor 13 flows through the intake passage 41 . An intake port (not shown) through which air is taken in from the outside is provided at the upstream end of the intake passage 41 . Air taken in from the intake port passes through the compressor 11 a and is sent to the combustor 13 . The compressor 11a compresses air and discharges it downstream.
- the turbine 11 b is provided in an exhaust flow path 42 connected to the combustor 13 . Exhaust gas discharged from the combustor 13 flows through the exhaust flow path 42 . An exhaust port (not shown) through which the exhaust gas is discharged to the outside is provided at the downstream end of the exhaust passage 42 . Exhaust gas discharged from the combustor 13 passes through the turbine 11b and is sent to the exhaust port. The turbine 11b generates rotational power by being rotated by the exhaust gas.
- a bleed flow path 43 is connected to the compressor 11a. A part of the air compressed by the compressor 11 a is extracted and flows through the extraction flow path 43 .
- An air bleed valve 24 is provided in the air bleed passage 43 .
- the bleed valve 24 adjusts the flow rate of air (that is, bleed air) flowing through the bleed flow path 43 .
- the degree of opening of the bleed valve 24 is controlled based on, for example, the required load. However, the bleed valve 24 may not be provided in the bleed flow path 43 .
- the bleed air that has flowed through the bleed flow path 43 is discharged to the outside, for example, from a discharge port (not shown).
- a discharge port not shown.
- the extracted air that has flowed through the extracted air flow path 43 is cooled by heat exchange with the ammonia decomposition catalyst 16, as will be described later, it is not used to cool the exhaust gas flowing into the turbine 11b or the turbine 11b itself. good too.
- the generator 12 is connected to the turbocharger 11.
- the generator 12 generates power using the rotational power generated by the supercharger 11 .
- ammonia is used as fuel for combustion.
- fuel other than ammonia for example, cracked gas as fuel for ignition described later
- the gas turbine system 1 is started (that is, when the combustion device 10 is started).
- the combustor 13 has a combustion chamber 13a and an ignition device 13b. Air compressed by a compressor 11a is supplied from an intake passage 41 to the combustion chamber 13a. Fuel is supplied to the combustion chamber 13a. For example, liquid ammonia is supplied (specifically, sprayed) from the ammonia tank 14 to the combustion chamber 13a as fuel. A mixture containing fuel and air is produced in the combustion chamber 13a.
- the ignition device 13b ignites the air-fuel mixture in the combustion chamber 13a. For example, the ignition device 13b is provided inside the combustion chamber 13a. Exhaust gas generated by combustion in the combustion chamber 13 a is discharged to the exhaust passage 42 .
- Liquid ammonia is stored in the ammonia tank 14 .
- Ammonia tank 14 is connected to combustor 13 and ammonia decomposition catalyst 16, respectively. Thereby, ammonia can be supplied from the ammonia tank 14 to each of the combustor 13 and the ammonia decomposition catalyst 16 .
- a channel 44 is connected to the ammonia tank 14 .
- a channel 45 and a channel 46 are connected to the downstream end of the channel 44 .
- Flow path 45 is connected to combustor 13 . That is, the ammonia tank 14 is connected to the combustor 13 via the flow paths 44 and 45 .
- Liquid ammonia is supplied from the ammonia tank 14 to the combustor 13 (specifically, the combustion chamber 13 a ) through the flow paths 44 and 45 .
- the flow path 46 is connected with the ammonia decomposition catalyst 16 . That is, the ammonia tank 14 is connected to the ammonia decomposition catalyst 16 via the flow paths 44 and 46 .
- Liquid ammonia is supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 through the flow paths 44 and 46 .
- a pump 15 is provided in the channel 44 .
- the pump 15 sends ammonia supplied from the ammonia tank 14 to the downstream side. Ammonia delivered by pump 15 passes through channel 44 and is sent to channels 45 and 46 .
- a third flow control valve 23 is provided in the flow path 45 .
- the third flow control valve 23 controls (that is, adjusts) the flow rate of ammonia flowing through the flow path 45 . That is, the third flow control valve 23 adjusts the amount of ammonia supplied from the ammonia tank 14 to the combustor 13 . The amount of ammonia supplied from the ammonia tank 14 to the combustor 13 is adjusted by adjusting the opening degree of the third flow control valve 23 .
- a first flow control valve 21 is provided in the flow path 46 .
- the first flow control valve 21 controls (that is, adjusts) the flow rate of ammonia flowing through the flow path 46 . That is, the first flow control valve 21 adjusts the amount of ammonia supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 . The amount of ammonia supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 is adjusted by adjusting the opening degree of the first flow control valve 21 .
- the ammonia decomposition catalyst 16 is a catalyst that decomposes ammonia to generate decomposition gas.
- Ammonia decomposition catalyst 16 decomposes ammonia into hydrogen and nitrogen. That is, the cracked gas contains hydrogen and nitrogen. In addition to hydrogen and nitrogen, the cracked gas may contain ammonia that has not been cracked.
- Decomposition of ammonia by the ammonia decomposition catalyst 16 is actively performed when the temperature of the ammonia decomposition catalyst 16 is equal to or higher than a reference temperature (for example, about 400° C. to 500° C.). That is, when the temperature of the ammonia decomposition catalyst 16 becomes equal to or higher than the reference temperature, the ammonia decomposition catalyst 16 actively decomposes ammonia.
- a reference temperature for example, about 400° C. to 500° C.
- the ammonia decomposition catalyst 16 is arranged in the bleed flow path 43 . Specifically, heat exchange is possible between the ammonia decomposition catalyst 16 and the bleed air in the bleed passage 43 while the internal space of the ammonia decomposition catalyst 16 and the bleed passage 43 are not in communication. Since the bleed air flowing through the bleed air passage 43 is air compressed by the compressor 11a, it is at a high temperature (for example, 400° C. or higher). Therefore, during operation of the gas turbine system 1 (that is, during operation of the combustion device 10), the temperature of the ammonia decomposition catalyst 16 is such that ammonia is actively decomposed (that is, the temperature is equal to or higher than the reference temperature). is heated by the bleed air flowing through the bleed air passage 43.
- a high temperature for example, 400° C. or higher
- the ammonia decomposition catalyst 16 is provided with a temperature sensor 16a.
- a temperature sensor 16 a detects the temperature of the ammonia decomposition catalyst 16 .
- the cracked gas storage device 17 stores cracked gas.
- the cracked gas storage device 17 is connected to the ammonia cracking catalyst 16 via a channel 47 .
- Cracked gas generated by decomposition by the ammonia decomposition catalyst 16 is sent to the cracked gas storage device 17 via the flow path 47 .
- the flow path 47 may be provided with a check valve, a cutoff valve, or the like for preventing reverse flow of the cracked gas from the cracked gas storage device 17 to the ammonia decomposition catalyst 16 .
- the cracked gas reservoir 17 is provided with a pressure sensor 17a.
- a pressure sensor 17 a detects the pressure in the cracked gas reservoir 17 .
- the cracked gas storage device 17 is connected to the combustor 13 via a flow path 48. Cracked gas is supplied from the cracked gas storage device 17 to the combustor 13 (specifically, the combustion chamber 13a) through the flow path 48 .
- a second flow control valve 22 is provided in the flow path 48 .
- the second flow control valve 22 controls (that is, adjusts) the flow rate of the cracked gas flowing through the flow path 48 . That is, the second flow control valve 22 adjusts the amount of cracked gas supplied from the cracked gas reservoir 17 to the combustor 13 . By adjusting the degree of opening of the second flow control valve 22, the amount of cracked gas supplied from the cracked gas reservoir 17 to the combustor 13 is adjusted.
- the control device 31 includes a central processing unit (CPU), a ROM storing programs and the like, a RAM as a work area, and the like, and controls the gas turbine system 1 as a whole.
- the control device 31 controls the ignition device 13b, the pump 15, the first flow control valve 21, the second flow control valve 22 and the third flow control valve 23. Further, the control device 31 acquires detection results from the temperature sensor 16a and the pressure sensor 17a.
- FIG. 2 is a flowchart showing an example of the flow of processing performed by the control device 31.
- FIG. The processing flow shown in FIG. 2 is executed, for example, when the user performs an input operation to start up the gas turbine system 1 .
- An input operation by the user is accepted by the control device 31, for example.
- the control device 31 determines whether or not the activation condition is satisfied.
- the activation condition is a condition for permitting activation of the gas turbine system 1 .
- the startup condition is that there is no abnormality in each device of the gas turbine system 1 (for example, there is no abnormal value in the output value output from each device, or there is no fluid leakage in each flow path). etc.).
- step S101/YES If it is determined that the activation condition is satisfied (step S101/YES), proceed to step S102. On the other hand, if it is determined that the startup condition is not satisfied (step S101/NO), the process proceeds to step S111, and the gas turbine system 1 is stopped as described later.
- step S101 the control device 31 causes the ignition device 13b to ignite in step S102.
- step S ⁇ b>103 the control device 31 starts supplying cracked gas from the cracked gas storage device 17 to the combustor 13 .
- the control device 31 controls the second flow rate control valve 22 so that the supply of cracked gas from the cracked gas storage device 17 to the combustor 13 is started. That is, the control device 31 opens the closed second flow control valve 22 .
- cracked gas is generated by the ammonia decomposition catalyst 16 during operation of the gas turbine system 1 , and the generated cracked gas is stored in the cracked gas storage device 17 . Therefore, at the start of the processing flow shown in FIG. 2, the cracked gas is stored in advance in the cracked gas reservoir 17 . However, when the gas turbine system 1 is started for the first time, the cracked gas is stored in advance in the cracked gas storage device 17 by another method.
- step S104 the control device 31 determines whether or not the ignition has succeeded. If it is determined that the ignition has succeeded (step S104/YES), the process proceeds to step S105. On the other hand, if it is determined that the ignition has not succeeded (step S104/NO), the process proceeds to step S111, and the gas turbine system 1 is stopped as described later.
- step S105 the control device 31 increases the supply amount of the cracked gas. Specifically, the control device 31 controls the second flow rate control valve 22 so that the amount of cracked gas supplied from the cracked gas storage device 17 to the combustor 13 increases. That is, the control device 31 increases the opening degree of the second flow control valve 22 . For example, the control device 31 increases the amount of cracked gas supplied from the cracked gas reservoir 17 to the combustor 13 so as to change in a preset transition.
- the control device 31 determines whether or not the supply amount of cracked gas has reached the reference supply amount.
- the reference supply amount is the amount at which the combustibility in the combustor 13 is maintained at a predetermined level or higher even when the supply of ammonia to the combustor 13 is started (that is, the amount of ammonia that does not burn partially). is set to the value of
- step S106/YES When it is determined that the supply amount of the cracked gas has reached the reference supply amount (step S106/YES), the control device 31 determines that even if the supply of ammonia to the combustor 13 is started, the combustibility in the combustor 13 does not reach the predetermined level. is maintained at or above the level of , and the process proceeds to step S107. On the other hand, when it is determined that the supply amount of the cracked gas has not reached the reference supply amount (step S106/NO), the control device 31 starts supplying ammonia to the combustor 13, and the combustibility in the combustor 13 increases. It is determined that the value falls below the predetermined level, and the process returns to step S105.
- the control device 31 permits the supply of ammonia from the ammonia tank 14 to the combustor 13 in step S107. That is, the control device 31 starts supplying ammonia from the ammonia tank 14 to the combustor 13 when the required output of the gas turbine system 1 is greater than or equal to the reference output. In this case, the control device 31 drives the pump 15 and controls the third flow control valve 23 so that the supply of ammonia from the ammonia tank 14 to the combustor 13 is started. That is, the control device 31 opens the closed third flow control valve 23 . Thereby, combustion using ammonia as fuel is started. In addition, when the required output of the gas turbine system 1 is smaller than the reference output, the supply of ammonia from the ammonia tank 14 to the combustor 13 becomes unnecessary.
- cracked gas is supplied to the combustor 13, and combustion using ammonia as fuel is started in a state where combustibility is maintained at a predetermined level or higher. That is, the cracked gas is used as fuel for supporting combustion (ie, fuel for supporting combustion). This suppresses the occurrence of a situation in which some ammonia does not burn. Note that after starting the supply of ammonia to the combustor 13 , the control device 31 may continue or stop the supply of cracked gas to the combustor 13 .
- the cracked gas generation condition is a condition for permitting generation of cracked gas by the ammonia decomposition catalyst 16 (that is, decomposition of ammonia).
- the cracked gas generation condition is that the temperature of the ammonia decomposition catalyst 16 is equal to or higher than the reference temperature (that is, the temperature at which the ammonia decomposition catalyst 16 actively decomposes ammonia).
- step S108/YES If it is determined that the cracked gas generation condition is satisfied (step S108/YES), the process proceeds to step S109. On the other hand, if it is determined that the decomposition gas generation condition is not satisfied (step S108/NO), the process proceeds to step S110 without executing step S109.
- the control device 31 supplies ammonia from the ammonia tank 14 to the ammonia decomposition catalyst 16 in step S109. Specifically, the control device 31 controls the first flow control valve 21 so that ammonia is supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 . That is, the control device 31 opens the closed first flow control valve 21 . As a result, ammonia is decomposed in the ammonia decomposition catalyst 16 to generate cracked gas. The generated cracked gas is sent to the cracked gas reservoir 17, and the pressure inside the cracked gas reservoir 17 rises.
- step S109 the control device 31 controls the amount of ammonia supplied to the ammonia decomposition catalyst 16 by the first flow control valve 21 so that the pressure in the decomposition gas storage device 17 becomes the reference pressure.
- control of the amount of ammonia supplied to the ammonia decomposition catalyst 16 (specifically, control of the opening degree of the first flow control valve 21) is specifically realized by feedback control.
- the reference pressure is the required amount of cracked gas to be used until the supply of ammonia to the combustor 13 is started (hereinafter simply referred to as the required amount) of cracked gas stored in the cracked gas storage device 17 . It is an index for judging whether or not there is For example, when the pressure in the cracked gas reservoir 17 is lower than the reference pressure, it corresponds to the case where the cracked gas reservoir 17 does not store the necessary amount of cracked gas.
- step S110 the control device 31 determines whether or not the stop condition is satisfied.
- the stop condition is a condition for permitting stoppage of the gas turbine system 1 .
- the stop condition is that there is no demand for power generation and the pressure in the cracked gas reservoir 17 is equal to or higher than the reference pressure.
- step S110/YES If it is determined that the stop condition is satisfied (step S110/YES), the process proceeds to step S111. On the other hand, if it is determined that the stop condition is not satisfied (step S110/NO), the process returns to step S108.
- step S111 the control device 31 stops the gas turbine system 1, and the processing flow shown in FIG. 2 ends. Specifically, the control device 31 stops the supply of ammonia to the combustor 13, the supply of cracked gas to the combustor 13, and the supply of ammonia to the ammonia decomposition catalyst 16, so that the gas turbine system 1 to stop
- control device 31 supplies ammonia from the ammonia tank 14 to the ammonia decomposition catalyst 16 without stopping the gas turbine system 1 when the pressure in the decomposition gas storage device 17 is lower than the reference pressure. continue. Thereby, the gas turbine system 1 can be stopped after the pressure in the cracked gas storage device 17 recovers to the reference pressure or higher.
- the ammonia decomposition catalyst 16 is arranged in the extraction flow path 43 .
- the ammonia decomposition catalyst 16 is heated by the bleed air flowing through the bleed air flow path 43 to a temperature at which ammonia is actively decomposed (that is, a temperature equal to or higher than the reference temperature).
- a temperature at which ammonia is actively decomposed that is, a temperature equal to or higher than the reference temperature.
- the ammonia decomposition catalyst 16 is connected to the combustor 13 via the decomposition gas storage device 17 .
- the cracked gas can be stored in the cracked gas storage device 17 by causing the ammonia cracking catalyst 16 to break down the ammonia to generate the cracked gas.
- the combustibility in the combustor 13 can be improved.
- control device 31 operates the first flow control valve 21 so that ammonia is supplied from the ammonia tank 14 to the ammonia decomposition catalyst 16 during operation of the gas turbine system 1 (that is, during operation of the combustion device 10). Control.
- the cracked gas is generated by the ammonia decomposition catalyst 16 and stored in the cracked gas storage device 17 .
- the control device 31 starts supplying the cracked gas from the cracked gas storage device 17 to the combustor 13, and the The second flow control valve 22 and the third flow control valve 23 are controlled so as to start supplying ammonia to the combustor 13 .
- the cracked gas is used as fuel for ignition, so that failure of ignition in the combustor 13 is suppressed and reliability of ignition is appropriately improved.
- FIG. 3 is a schematic diagram showing the configuration of a gas turbine system 1A according to a first modified example.
- a heat exchanger 51 is provided in a flow path 47 and a heat exchanger 51 is provided in a flow path 46, unlike the gas turbine system 1 described above. 51 is different.
- the gas turbine system 1A includes a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, a decomposition gas storage device 17, a first flow control valve 21, a first A second flow control valve 22, a third flow control valve 23, a controller 31, and a heat exchanger 51 are included in the combustion device 10A.
- the flow path 47 connects the ammonia decomposition catalyst 16 and the decomposition gas storage device 17 as described above.
- a heat exchanger 51 is provided in such a flow path 47 .
- the flow path 46 connects the ammonia tank 14 and the ammonia decomposition catalyst 16 as described above. Such a flow path 46 passes through the heat exchanger 51 .
- the heat exchanger 51 heat is exchanged between the cracked gas flowing through the flow path 47 and the ammonia flowing through the flow path 46.
- the temperature of the cracked gas flowing through the flow path 47 is higher than the temperature of the ammonia flowing through the flow path 46 . Therefore, in the heat exchanger 51 , heat is transferred from the cracked gas flowing through the flow path 47 to the ammonia flowing through the flow path 46 . Therefore, the cracked gas flowing through the flow path 47 is cooled.
- the heat exchanger 51 corresponds to a cooling device that cools the cracked gas flowing through the flow path 47 .
- the temperature of the cracked gas sent to the cracked gas storage device 17 is high (for example, about 400°C). However, the temperature of the cracked gas in the cracked gas storage device 17 drops between the time the gas turbine system 1 is stopped and the next time it is started. The greater the drop in the temperature of the cracked gas in the cracked gas reservoir 17, the more the pressure in the cracked gas reservoir 17 drops.
- the flow path 47 connecting the ammonia decomposition catalyst 16 and the decomposition gas storage device 17 is provided with a cooling device (specifically, the heat exchanger 51).
- a cooling device specifically, the heat exchanger 51.
- the temperature of the cracked gas sent to the cracked gas reservoir 17 can be lowered. Therefore, the amount of decrease in the temperature of the cracked gas in the cracked gas storage device 17 can be reduced during the period from when the gas turbine system 1 is stopped until the next start-up, thereby suppressing a decrease in pressure in the cracked gas storage device 17. can.
- the pressure in the cracked gas reservoir 17 can be made higher than the pressure in the combustion chamber 13 a , so that the cracked gas can be properly supplied from the cracked gas reservoir 17 to the combustor 13 .
- the heat exchanger 51 through which the flow path 46 passes is provided in the flow path 47 as a cooling device.
- the cooling device provided in flow path 47 is not limited to heat exchanger 51 .
- a device for cooling the cracked gas flowing through the flow path 47 with cooling water or air may be provided in the flow path 47 as a cooling device.
- FIG. 4 is a schematic diagram showing the configuration of a gas turbine system 1B according to a second modified example.
- a heat exchanger 52 and a heat exchanger 53 are provided in the exhaust flow path 42, unlike the gas turbine system 1 described above. The difference is that path 49 passes through heat exchanger 52 and heat exchanger 53 .
- the gas turbine system 1B includes a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, a decomposition gas storage device 17, a first flow control valve 21, a second A second flow control valve 22, a third flow control valve 23, and a control device 31 are included in the combustion device 10B.
- the flow path 49 is shown in a simplified manner in FIG. 4, the flow path 49 is a closed circuit. In other words, the water circulates inside the flow path 49 .
- Flow path 49 is provided with a turbine, not shown, and is powered by the turbine using a flow of water (specifically, steam).
- the flow path 49, the heat exchanger 52, the heat exchanger 53, and the turbine are included in a system different from the gas turbine system 1B.
- the heat exchanger 52 is provided downstream of the heat exchanger 53 in the exhaust passage 42 .
- the heat exchanger 52 is provided upstream of the heat exchanger 53 in the flow path 49 .
- the liquid water flowing through the flow path 49 is heated by the exhaust gas flowing through the exhaust flow path 42 .
- the heated liquid water is heated again by the exhaust gas flowing through the exhaust passage 42 in the heat exchanger 53 and vaporized into gas (that is, water vapor).
- a turbine (not shown) is rotated by the steam to generate rotational power.
- the gas turbine system 1B shares a part with another system.
- the configuration and application of another system partially shared with the gas turbine system 1B are not limited to the above example. Even in such a case, the same effects as those of the gas turbine system 1 described above can be obtained.
- FIG. 5 is a schematic diagram showing the configuration of a gas turbine system 1C according to a third modified example. As shown in FIG. 5, in the gas turbine system 1C according to the third modification, the extraction flow path 43 is not provided and the installation position of the ammonia decomposition catalyst 16 is different from that of the gas turbine system 1 described above.
- the gas turbine system 1C includes a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, a decomposition gas storage device 17, a first flow control valve 21, a second A second flow control valve 22, a third flow control valve 23, and a control device 31 are included in the combustion device 10C.
- the ammonia decomposition catalyst 16 is arranged between the compressor 11a and the combustor 13 in the intake passage 41. Specifically, heat exchange is possible between the ammonia decomposition catalyst 16 and the air in the intake passage 41 while the internal space of the ammonia decomposition catalyst 16 and the intake passage 41 are not in communication.
- the air flowing downstream from the compressor 11a in the air intake passage 41 is the air compressed by the compressor 11a, and thus has a high temperature (for example, 400° C. or higher).
- the temperature of the ammonia decomposition catalyst 16 is such that ammonia is actively decomposed (that is, the temperature is equal to or higher than the reference temperature). is heated by the air flowing through the intake passage 41.
- the ammonia decomposition catalyst 16 is arranged between the compressor 11a and the combustor 13 in the intake passage 41, unlike the gas turbine system 1 described above. Even in such a case, heating of the ammonia decomposition catalyst 16 is realized by effectively utilizing the heat of the air compressed by the compressor 11a, as in the gas turbine system 1 described above. Therefore, the same effects as those of the gas turbine system 1 described above can be obtained.
- the air supplied from the compressor 11a to the combustor 13 is used to cool the members forming the combustion chamber 13a of the combustor 13 (specifically, the liner 13d in FIG. 6, which will be described later).
- the combustion device 10C of the gas turbine system 1C heat exchange is performed between the air supplied from the compressor 11a to the combustor 13 and the ammonia decomposition catalyst 16, thereby decreasing the temperature of the air. Therefore, the temperature of the air reaching the member forming the combustion chamber 13a of the combustor 13 is also lowered. Therefore, the member forming the combustion chamber 13a of the combustor 13 can be effectively cooled.
- FIG. 6 is a schematic diagram showing the configuration of a gas turbine system 1D according to a fourth modification. As shown in FIG. 6, in the gas turbine system 1D according to the fourth modification, the installation position of the ammonia decomposition catalyst 16 is different from that of the gas turbine system 1 described above.
- FIG. 6 shows only the combustor 13 and its peripheral components in the gas turbine system 1D.
- the components of the gas turbine system 1D are the same as those of the gas turbine system 1 described above, except that the installation position of the ammonia decomposition catalyst 16 is different.
- the gas turbine system 1D includes a combustor 13, an ammonia tank 14, a pump 15, an ammonia decomposition catalyst 16, a decomposition gas storage device 17, a first flow control valve 21, a first A second flow control valve 22, a third flow control valve 23, and a control device 31 are included in the combustion device 10D.
- the ammonia decomposition catalyst 16 is arranged in the space S that communicates the combustion chamber 13a and the intake passage 41 in the combustor 13. Specifically, heat exchange between the ammonia decomposition catalyst 16 and the air in the space S is possible in a state in which the internal space of the ammonia decomposition catalyst 16 and the space S are not communicated with each other.
- the combustor 13 has a casing 13c, a liner 13d, and a burner 13e in addition to the combustion chamber 13a and the ignition device 13b described above.
- the casing 13c has a substantially cylindrical shape.
- a liner 13d is provided inside the casing 13c.
- the liner 13d has a substantially cylindrical shape.
- the liner 13d is arranged coaxially with the casing 13c.
- a combustion chamber 13a is formed inside the liner 13d. That is, the internal space of the liner 13d corresponds to the combustion chamber 13a.
- An exhaust passage 42 is connected to the combustion chamber 13a.
- An ignition device 13b is provided on the inner peripheral portion of the liner 13d.
- An opening is formed at the end of the liner 13d (left end in FIG. 6).
- a burner 13e is inserted through an opening at the end of the liner 13d.
- a channel 45 and a channel 48 are connected to the burner 13e.
- Ammonia is sent to the burner 13e through the flow path 45. As shown in FIG.
- the cracked gas is sent to the burner 13e through the flow path 48. As shown in FIG.
- the burner 13e faces the combustion chamber 13a. Ammonia and cracked gas are injected into the combustion chamber 13a from the burner 13e.
- a space S is formed between the inner surface of the casing 13c and the outer surface of the liner 13d.
- An intake passage 41 is connected to the space S. Air is sent to the space S from the compressor 11 a through an intake passage 41 .
- the space S communicates with the opening at the end of the liner 13d. As indicated by the dashed-dotted line arrow in FIG. 6, the air sent to the space S passes through the space S and then is sent to the combustion chamber 13a through the opening at the end of the liner 13d.
- the air circulating in the space S is compressed by the compressor 11a, so it is at a high temperature (for example, 400°C or higher). Therefore, during operation of the gas turbine system 1D (that is, during operation of the combustion device 10D), the temperature of the ammonia decomposition catalyst 16 is such that ammonia is actively decomposed (that is, the temperature is equal to or higher than the reference temperature). is heated by the air flowing through the space S.
- the ammonia decomposition catalyst 16 is arranged in the space S that communicates the combustion chamber 13a and the intake passage 41 in the combustor 13, unlike the gas turbine system 1 described above. Even in such a case, heating of the ammonia decomposition catalyst 16 is realized by effectively utilizing the heat of the air compressed by the compressor 11a, as in the gas turbine system 1 described above. Therefore, the same effects as those of the gas turbine system 1 described above can be obtained.
- the rotational power generated by the supercharger 11 is used as energy for driving the generator 12. example.
- the rotational power generated by the turbocharger 11 is used for other purposes (for example, moving objects such as ships). for the purpose of driving etc.).
- liquid ammonia is supplied to the combustor 13 and the ammonia decomposition catalyst 16 in the gas turbine system 1, the gas turbine system 1A, the gas turbine system 1B, the gas turbine system 1C, and the gas turbine system 1D
- gaseous ammonia may be supplied to the combustor 13 and the ammonia decomposition catalyst 16 in the gas turbine system 1, the gas turbine system 1A, the gas turbine system 1B, the gas turbine system 1C, and the gas turbine system 1D.
- a vaporizer may be provided downstream of the pump 15 , and the ammonia may be vaporized by the vaporizer and then supplied to the combustor 13 or the ammonia decomposition catalyst 16 .
- an accumulator may be provided downstream of the vaporizer.
- a vaporizer and an accumulator may be provided in flow path 44 and may be provided in flow path 45 and flow path 46, respectively.
- a cooling device specifically, the heat exchanger 51
- a heat exchanger 51 may be additionally provided in the flow path 47 for the gas turbine system 1B, the gas turbine system 1C, and the gas turbine system 1D.
- gas turbine system 1B in which a system including the flow path 49, the heat exchanger 52 and the heat exchanger 53 is additionally provided with respect to the gas turbine system 1 has been described.
- a system including flow path 49, heat exchanger 52 and heat exchanger 53 may be additionally provided for gas turbine system 1A, gas turbine system 1C and gas turbine system 1D.
- Gas turbine system 1A Gas turbine system 1B: Gas turbine system 1C: Gas turbine system 1D: Gas turbine system 11a: Compressor 13: Combustor 13a: Combustion chamber 14: Ammonia tank 16: Ammonia decomposition catalyst 17: Decomposed gas Reservoir 21: 1st flow control valve 22: 2nd flow control valve 23: 3rd flow control valve 31: Control device 41: Intake flow path 43: Extraction flow path 44: Flow path 45: Flow path 46: Flow path 47 : Channel 48: Channel 49: Channel 51: Heat exchanger (cooling device) S: Space
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- Engineering & Computer Science (AREA)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
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Abstract
Description
Claims (5)
- アンモニアタンクと、
前記アンモニアタンクと接続され、燃焼室を有する燃焼器と、
前記燃焼器と接続される吸気流路と、
前記吸気流路に設けられる圧縮機と、
前記燃焼器と接続される分解ガス貯蔵器と、
前記圧縮機と接続される抽気流路、前記吸気流路のうち前記圧縮機と前記燃焼器との間、または、前記燃焼器において前記燃焼室と前記吸気流路とを連通する空間に配置され、前記アンモニアタンクおよび前記分解ガス貯蔵器と接続されるアンモニア分解触媒と、
を備える、
ガスタービンシステム。 - 前記アンモニア分解触媒と前記分解ガス貯蔵器とを接続する流路には、冷却装置が設けられる、
請求項1に記載のガスタービンシステム。 - 前記冷却装置は、前記アンモニア分解触媒と前記分解ガス貯蔵器とを接続する流路に設けられる熱交換器であり、
前記アンモニアタンクと前記アンモニア分解触媒とを接続する流路は、前記熱交換器を通過する、
請求項2に記載のガスタービンシステム。 - 前記アンモニアタンクと前記アンモニア分解触媒とを接続する流路には、第1流量制御弁が設けられ、
前記ガスタービンシステムの運転中に、前記アンモニアタンクから前記アンモニア分解触媒へアンモニアが供給されるように、前記第1流量制御弁を制御する制御装置を備える、
請求項1から3のいずれか一項に記載のガスタービンシステム。 - 前記分解ガス貯蔵器と前記燃焼器とを接続する流路には、第2流量制御弁が設けられ、
前記アンモニアタンクと前記燃焼器とを接続する流路には、第3流量制御弁が設けられ、
前記制御装置は、前記ガスタービンシステムの起動時に、前記分解ガス貯蔵器から前記燃焼器への分解ガスの供給が開始した後に、前記アンモニアタンクから前記燃焼器への前記アンモニアの供給が開始するように、前記第2流量制御弁および前記第3流量制御弁を制御する、
請求項4に記載のガスタービンシステム。
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KR1020237031169A KR20230144627A (ko) | 2021-03-30 | 2022-03-03 | 가스 터빈 시스템 |
EP22779787.5A EP4317665A1 (en) | 2021-03-30 | 2022-03-03 | Gas turbine system |
CN202280019415.6A CN116964308A (zh) | 2021-03-30 | 2022-03-03 | 燃气轮机系统 |
AU2022252441A AU2022252441A1 (en) | 2021-03-30 | 2022-03-03 | Gas turbine system |
JP2023510712A JPWO2022209562A1 (ja) | 2021-03-30 | 2022-03-03 | |
US18/474,785 US20240011435A1 (en) | 2021-03-30 | 2023-09-26 | Gas turbine system |
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EP (1) | EP4317665A1 (ja) |
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Publication number | Priority date | Publication date | Assignee | Title |
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CN117536741A (zh) * | 2023-10-19 | 2024-02-09 | 佛山仙湖实验室 | 氨内燃机燃料整备系统及使用方法 |
WO2024095638A1 (ja) * | 2022-10-31 | 2024-05-10 | 株式会社Ihi | ガスタービンシステム |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH10110630A (ja) * | 1996-10-08 | 1998-04-28 | Toshiba Corp | ガスタービン燃焼器の燃料プラント |
JP2006077698A (ja) * | 2004-09-10 | 2006-03-23 | Kawasaki Heavy Ind Ltd | ガス改質設備 |
JP2010270594A (ja) * | 2009-05-19 | 2010-12-02 | Hitachi Ltd | 重質油改質燃料焚きガスタービンシステム |
JP2012255420A (ja) * | 2011-06-10 | 2012-12-27 | Nippon Shokubai Co Ltd | ガスタービンシステム |
JP2016191507A (ja) | 2015-03-31 | 2016-11-10 | 株式会社Ihi | 燃焼装置、ガスタービン及び発電装置 |
JP2017180266A (ja) * | 2016-03-30 | 2017-10-05 | 株式会社Ihi | 燃焼装置及びガスタービン |
JP2021057441A (ja) | 2019-09-30 | 2021-04-08 | 株式会社デンソー | 半導体装置 |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3313103A (en) * | 1965-08-25 | 1967-04-11 | Gen Motors Corp | Gas turbine combustion process |
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- 2022-03-03 EP EP22779787.5A patent/EP4317665A1/en active Pending
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- 2022-03-03 CN CN202280019415.6A patent/CN116964308A/zh active Pending
- 2022-03-03 KR KR1020237031169A patent/KR20230144627A/ko unknown
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2023
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Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH10110630A (ja) * | 1996-10-08 | 1998-04-28 | Toshiba Corp | ガスタービン燃焼器の燃料プラント |
JP2006077698A (ja) * | 2004-09-10 | 2006-03-23 | Kawasaki Heavy Ind Ltd | ガス改質設備 |
JP2010270594A (ja) * | 2009-05-19 | 2010-12-02 | Hitachi Ltd | 重質油改質燃料焚きガスタービンシステム |
JP2012255420A (ja) * | 2011-06-10 | 2012-12-27 | Nippon Shokubai Co Ltd | ガスタービンシステム |
JP2016191507A (ja) | 2015-03-31 | 2016-11-10 | 株式会社Ihi | 燃焼装置、ガスタービン及び発電装置 |
JP2017180266A (ja) * | 2016-03-30 | 2017-10-05 | 株式会社Ihi | 燃焼装置及びガスタービン |
JP2021057441A (ja) | 2019-09-30 | 2021-04-08 | 株式会社デンソー | 半導体装置 |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2024095638A1 (ja) * | 2022-10-31 | 2024-05-10 | 株式会社Ihi | ガスタービンシステム |
CN117536741A (zh) * | 2023-10-19 | 2024-02-09 | 佛山仙湖实验室 | 氨内燃机燃料整备系统及使用方法 |
CN117536741B (zh) * | 2023-10-19 | 2024-04-19 | 佛山仙湖实验室 | 氨内燃机燃料整备系统及使用方法 |
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JPWO2022209562A1 (ja) | 2022-10-06 |
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CN116964308A (zh) | 2023-10-27 |
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KR20230144627A (ko) | 2023-10-16 |
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