WO2019188484A1 - 燃料供給装置及びガスタービン - Google Patents
燃料供給装置及びガスタービン Download PDFInfo
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- WO2019188484A1 WO2019188484A1 PCT/JP2019/011130 JP2019011130W WO2019188484A1 WO 2019188484 A1 WO2019188484 A1 WO 2019188484A1 JP 2019011130 W JP2019011130 W JP 2019011130W WO 2019188484 A1 WO2019188484 A1 WO 2019188484A1
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- Prior art keywords
- valve
- supply pipe
- fuel
- ammonia
- gas
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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
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- 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
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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
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23K—FEEDING FUEL TO COMBUSTION APPARATUS
- F23K5/00—Feeding or distributing other fuel to combustion apparatus
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/08—Purpose of the control system to produce clean exhaust gases
- F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2241/00—Applications
- F23N2241/20—Gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Definitions
- the present disclosure relates to a fuel supply device and a gas turbine.
- This application claims priority based on Japanese Patent Application No. 2018-062165 filed in Japan on March 28, 2018, the contents of which are incorporated herein by reference.
- Patent Document 1 discloses a combustion apparatus and a gas turbine for burning ammonia as fuel. That is, this combustion apparatus and gas turbine premixes ammonia (ammonia for fuel) with natural gas and supplies it to the combustor, thereby obtaining combustion exhaust gas that drives the turbine and reducing nitrogen oxides (NOx). In order to achieve this, a reduction region is formed in which nitrogen oxides (NOx) generated in the combustion region are reduced using ammonia on the downstream side in the combustor.
- ammonia ammonia for fuel
- NOx nitrogen oxides
- the temperature and pressure in the supply pipe may be measured and a leak check may be performed.
- the gas fuel supply pipe needs to be heated and held during the leak check.
- a temperature distribution is generated in the supply pipe during heating, liquefaction of the gas fuel occurs due to a pressure change or a local temperature drop in the supply pipe, and a pressure drop occurs.
- Such a change in pressure accompanying the liquefaction of gas fuel inside the supply pipe or a change in temperature can be an adverse effect in a leak check.
- the temperature of the supply pipe is adjusted by a heater or the like in order to solve the above-described problems.
- it takes time to adjust the temperature of the supply pipe and the procedure becomes complicated.
- the present disclosure has been made in view of the above-described circumstances, and aims to suppress a pressure fluctuation during a leak check and simplify the leak check.
- a first supply pipe that supplies a first gaseous fuel to a combustor and the first supply pipe are provided.
- a first on-off valve, a second on-off valve provided in a portion of the first supply pipe closer to an outlet of the first supply pipe than the first on-off valve, and the first supply pipe A second supply pipe that supplies the second gas fuel having a liquefaction temperature lower than that of the gas fuel to the combustor, and a portion between the first on-off valve and the second on-off valve in the first supply pipe.
- the first on-off valve is closed, and the second on-off valve and the third on-off valve are opened.
- the first gas fuel remaining in the first supply pipe is replaced with the second gas fuel, and after the replacement, the first on-off valve and the
- the second on-off valve and the second on-off valve By controlling the second on-off valve to be in a closed state and the third on-off valve to be in an open state, the inside of the first supply pipe is pressurized with the second gas fuel, and the pressurization is performed.
- a control device for performing a leak check on the first supply pipe using the leak check measuring device by controlling the first to third on-off valves to be closed after Adopt a fuel supply device.
- the control device closes the first on-off valve and the third on-off valve before the replacement.
- a fuel supply device is adopted in which the inside of the first supply pipe is depressurized by controlling the second on-off valve to be in an open state.
- a gas vent whose one end is connected to a downstream side of the second on-off valve in the first supply pipe is provided.
- a gas supply pipe is further provided, and the gas vent pipe employs a fuel supply device that discharges the first gas fuel from the first supply pipe to the outside during the replacement or decompression.
- the first gas fuel and the second gas fuel in the combustor A fuel supply device that introduces the second gas fuel from the second supply pipe to the first supply pipe at the end of mixed combustion is employed.
- a fuel supply apparatus in which the first gas fuel is ammonia and the second gas fuel is natural gas is employed.
- a gas turbine including any one of the fuel supply devices of the first to sixth aspects is employed as a first aspect related to the gas turbine.
- the present disclosure by introducing the second gas fuel into the first supply pipe, it is possible to suppress the pressure fluctuation during the leak check and simplify the leak check.
- the gas turbine A includes a compressor 1, a combustor 2, a turbine 3, a reduction catalyst chamber 4, a tank 5, a pump 6, a vaporizer 7, a fuel supply unit 8,
- the illustrated control device is provided.
- the control device is composed of a CPU (Central Processing Unit), a RAM (Random Access Memory) and a ROM (Read Only Memory), a storage device such as an SSD (Solid State Drive) and a HDD (Hard Disc Drive), and the like.
- the combustor 2, the tank 5, the pump 6, the carburetor 7, and the fuel supply unit 8 constitute the combustion device C in the present embodiment.
- Such a gas turbine A is a drive source of the generator G, and generates rotational power by burning predetermined fuel.
- Compressor 1 generates compressed air by compressing air taken from outside air to a predetermined pressure.
- the compressor 1 supplies the compressed air to the combustor 2 mainly as combustion air.
- the combustor 2 generates combustion gas by burning fuel using the compressed air as an oxidant, and supplies the combustion gas to the turbine 3.
- the combustor 2 is supplied with gaseous ammonia (first gas fuel).
- the combustor 2 includes a casing 2a, a liner 2b, a rectifier 2c, a fuel supply pipe 2d (second supply pipe), a fuel nozzle 2e, an ammonia supply pipe 2f (first supply pipe). ), A plurality of ammonia injection nozzles 2g, a connecting pipe 2h, a gas vent pipe 2i, a temperature sensor 2j, and a pressure sensor 2k.
- the temperature sensor 2j and the pressure sensor 2k constitute a leak check measuring device. Further, as shown in FIG.
- the combustor 2 includes valves V1 to V5 controlled by the above-described control device.
- the valves V1 to V5 may be electrically connected to the control device.
- the natural gas in a gaseous state is used as the fuel (second gas fuel). Natural gas has a characteristic that its liquefaction temperature is lower than that of ammonia.
- the casing 2a is a substantially cylindrical container that houses the liner 2b.
- the casing 2a has a fuel nozzle 2e and a rectifier 2c attached to one end, and an exhaust port E formed on the other end.
- the liner 2b is a cylindrical body provided substantially coaxially with respect to the casing 2a, and the internal space of the liner 2b is a combustion chamber N.
- the direction of the central axis L of the liner 2b shown in FIG. 2 is the mainstream flow direction (mainstream direction) in the combustion chamber N.
- the liner 2b is supplied with cooling air along the inner peripheral surface of the liner 2b, and a cooling air layer is formed in the vicinity of the inner peripheral surface of the liner 2b.
- the fuel supply pipe 2d is a pipe connected to the fuel supply unit 8 and the fuel nozzle 2e.
- the fuel supply pipe 2d guides the fuel supplied from the fuel supply unit 8 to the fuel nozzle 2e.
- the fuel supply pipe 2d is provided with a first fuel valve V4 on the inlet side and a second fuel valve V5 on the outlet side.
- the fuel nozzle 2e is provided on the central axis L of the liner 2b at one end of the casing 2a, and is a fuel injection nozzle that injects fuel into the combustion chamber N.
- the rectifier 2c is provided in an annular shape on the outer periphery of the fuel nozzle 2e at one end of the casing 2a. The rectifier 2c supplies combustion air from one end of the combustion chamber N toward the exhaust port E, and at the center of the liner 2b. A swirl flow S of combustion air is formed around the axis L.
- the ammonia supply pipe 2f is a pipe connected to the vaporizer 7 and the ammonia injection nozzle 2g.
- the ammonia supply pipe 2f guides gaseous ammonia supplied from the vaporizer 7 to the ammonia injection nozzle 2g.
- the ammonia supply pipe 2f is provided with a first ammonia valve V1 (first on-off valve) on the inlet side and a second ammonia valve V2 (second on-off valve) on the outlet side.
- the first ammonia valve V1 may be provided near the inlet of the ammonia supply pipe 2f
- the second ammonia valve V2 may be provided near the inlet of the ammonia supply pipe 2f.
- the first ammonia valve V1 may be provided in the ammonia supply pipe 2f, and the second ammonia valve V2 may be provided closer to the outlet of the ammonia supply pipe 2f than the first ammonia valve V1. Further, the ammonia supply pipe 2f is connected to the gas vent pipe 2i at a site downstream of the second ammonia valve V2.
- the plurality of ammonia injection nozzles 2g are nozzles inserted into the liner 2b from the casing 2a, and are provided around the central axis L of the liner 2b, that is, around the flame K at every predetermined angle.
- the ammonia injection nozzle 2g is cylindrical.
- the downstream end of the ammonia injection nozzle 2g is inserted from the peripheral surface of the liner 2b, and is provided so as to be inclined radially inward of the liner 2b and upstream of the flame formation direction.
- the ammonia injection nozzle 2g is inserted into the liner 2b through an opening formed in the casing 2a and an opening formed in the peripheral surface of the liner 2b, and a rear end portion is fixed to the outside of the casing 2a. .
- These ammonia injection nozzles 2g are nozzles that inject gaseous ammonia toward the flame K from the inner surface of the liner 2b.
- the connecting pipe 2h is connected to a portion of the fuel supply pipe 2d between the first fuel valve V4 and the second fuel valve V5, and is connected to the first ammonia valve V1 and the second ammonia valve V2 of the ammonia supply pipe 2f. It is piping connected to the part between. Thereby, the connecting pipe 2h connects the fuel supply pipe 2d and the ammonia supply pipe 2f.
- the connecting pipe 2h is provided with a connecting pipe valve V3 (third on-off valve).
- the degassing pipe 2i is a pipe in which a catalyst (not shown) is provided, and is installed downstream of the second ammonia valve V2 in the ammonia supply pipe 2f.
- the degassing pipe 2i is provided for releasing gaseous ammonia or a gaseous mixture of gaseous ammonia and fuel into the atmosphere after being decomposed by the catalyst.
- the temperature sensor 2j and the pressure sensor 2k are provided downstream (position downstream) from the connection point between the ammonia supply pipe 2f and the connection pipe 2h, and are located upstream of the second ammonia valve V2. In the position. Moreover, the temperature sensor 2j and the pressure sensor 2k transmit the measured measurement data to the control device. The temperature sensor 2j and the pressure sensor 2k may be electrically connected to the control device.
- the flame K is a region having a relatively low oxygen concentration in the combustion chamber N, but the central portion Kc of the flame K is a region having the lowest oxygen concentration in the flame K.
- the plurality of ammonia injection nozzles 2 g inject gaseous ammonia toward the central portion Kc of the flame K in the mainstream direction, that is, the region having the lowest oxygen concentration.
- the center Kc of the flame K is not a single point but a region having a predetermined spread.
- the turbine 3 generates rotational power by using the combustion gas as a driving gas.
- the turbine 3 is axially coupled to the compressor 1 and the generator G as shown in the figure, and rotationally drives the compressor 1 and the generator G with its own rotational power.
- Such a turbine 3 exhausts the combustion gas after power recovery toward the reduction catalyst chamber 4.
- the reduction catalyst chamber 4 is filled with a reduction catalyst, and reduces nitrogen oxide (NOx) contained in the combustion gas to nitrogen (N2).
- the tank 5 is a fuel tank that stores a predetermined amount of liquid ammonia, and supplies the liquid ammonia to the pump 6.
- the pump 6 is a fuel pump that pressurizes liquid ammonia supplied from the tank 5 to a predetermined pressure and supplies it to the vaporizer 7.
- the vaporizer 7 generates gaseous ammonia by vaporizing the liquid ammonia supplied from the pump 6.
- the vaporizer 7 supplies gaseous ammonia as a reducing agent immediately before the combustor 2 and the reduction catalyst chamber 4.
- the above-described reduction catalyst chamber 4 reduces nitrogen oxides (NOx) by the cooperation of the reduction catalyst and the reducing agent accommodated therein.
- liquid ammonia is supplied from the tank 5 to the vaporizer 7 when the pump 6 operates, and gaseous ammonia is generated when the liquid ammonia is vaporized in the vaporizer 7.
- This gaseous ammonia is supplied immediately before each ammonia injection nozzle 2 g and the reduction catalyst chamber 4 of the combustor 2.
- the fuel is supplied from the fuel supply unit 8 to the combustor 2 and injected into the combustion chamber N from the fuel nozzle 2e.
- the compressed air is supplied to the rectifier 2c of the combustor 2 as combustion air.
- This combustion air is injected by the combustor 2 in the direction of the central axis L of the liner 2b as a swirling flow S that rotates around the central axis L of the liner 2b.
- the combustion air is initially injected from the rectifier 2d of the combustor 2 toward the central axis L of the liner 2b. At this time, the combustion air gradually spreads in the direction orthogonal to the central axis L due to centrifugal force caused by swirl, that is, toward the liner 2b (the inner peripheral surface of the liner 2b) located on the side of the central axis L. Gradually spread. Further, the fuel injected from the fuel nozzle 2e gradually spreads in the direction orthogonal to the central axis L as in the case of the combustion air by being drawn by such a flow of the combustion air. The fuel flowing in the combustion chamber N and the combustion air are mixed in this way, and a flame K is formed in the combustion chamber N.
- the first ammonia valve V1 and the second ammonia valve V2 are closed in the ammonia supply pipe 2f.
- gaseous ammonia remains in a portion between the first ammonia valve V1 and the second ammonia valve V2. That is, the control device controls the first ammonia valve V1, the second ammonia valve V2, and the connection pipe valve V3 so as to be in a closed state (procedure 1).
- the control device controls the first ammonia valve V1 and the connecting pipe valve V3 so as to be in a valve-closed state, and controls the second ammonia valve V2 so as to be in a valve-open state (procedure 2).
- the connecting pipe valve V3 is opened with the first fuel valve V4 of the fuel supply pipe 2d opened and the second fuel valve V5 closed. That is, the control device controls the first ammonia valve V1 so as to be in the closed state, and controls the second ammonia valve V2 and the connection pipe valve V3 so as to be in the open state (procedure 3). At this time, the control device controls the first fuel valve V4 and the connection pipe valve V3 so that the first fuel valve V4 is opened before the connection pipe valve V3 is opened.
- the fuel flows into the ammonia supply pipe 2f, the residual ammonia in the ammonia supply pipe 2f is pushed out and discharged, and the gaseous ammonia in the ammonia supply pipe 2f is replaced with the fuel.
- the second ammonia valve V2 is closed. That is, the control device controls the first ammonia valve V1 and the second ammonia valve V2 so as to be in the closed state, and controls the connection pipe valve V3 so as to be in the open state (procedure 4).
- the control device controls the first ammonia valve V1 and the second ammonia valve V2 so as to be in the closed state, and controls the connection pipe valve V3 so as to be in the open state (procedure 4).
- the connecting pipe valve V3 is closed with the first ammonia valve V1 and the second ammonia valve V2 closed. That is, the control device controls the first ammonia valve V1, the second ammonia valve V2, and the connection pipe valve V3 so as to be in a closed state (procedure 5). Thereby, the pressure and temperature data in the ammonia supply pipe 2f are acquired from the temperature sensor 2j and the pressure sensor 2k. And a leak check is implemented by measuring a temperature change and a pressure drop from the data acquired from the temperature sensor 2j and the pressure sensor 2k by a control device (not shown). After the leak check is completed, the second ammonia valve V2 is opened. Thereby, gaseous ammonia and fuel in the ammonia supply pipe 2f are rapidly released from the gas vent pipe 2i.
- the fuel is introduced into the ammonia supply pipe 2f through the connection pipe 2h, similarly to the leak check.
- the operation of the combustor 2 is stopped, almost no gaseous ammonia remains in the ammonia supply pipe 2f, so that gaseous ammonia is not liquefied in the ammonia supply pipe 2f.
- the fuel supplied at a pressure substantially equal to gaseous ammonia is introduced into the ammonia supply pipe 2f at the time of the leak check, so that the pressure in the ammonia supply pipe 2f is constant and the operation of the combustor 2 is performed. Liquefaction of gaseous ammonia remaining in the ammonia supply pipe 2f when stopped is prevented. Thereby, the change of the temperature and pressure in the ammonia supply pipe 2f can be prevented. Therefore, it is not necessary to adjust the temperature in the ammonia supply pipe 2f, and the leak check procedure is simplified.
- the gas released during the leak check is discharged to the outside through the degassing pipe 2i.
- the gas released during the leak check can be discharged to the outside after being appropriately processed without passing through the liner 2b. That is, the gas after the gas ammonia or the gas mixture of gaseous ammonia and fuel is decomposed by the catalyst can be released into the atmosphere by the gas vent pipe 2i without passing through the liner 2b.
- the inside of the ammonia supply pipe 2f is depressurized before the leak check. Therefore, it becomes easy to introduce fuel into the ammonia supply pipe 2f, and replacement of gaseous ammonia with fuel can be efficiently performed.
- the leak check is performed in the combustion device C of the gas turbine A, but the present disclosure is not limited to this, and may be a combustion device such as a jet engine or a boiler.
- natural gas is used as the second fuel.
- the present disclosure is not limited to this, and for example, hydrogen or the like can be used.
- the first fuel is not limited to ammonia, and may be a gas having a higher liquefaction temperature than the second fuel.
- gas vent pipe 2i is provided, but the present disclosure is not limited to this.
- the gaseous ammonia or the mixed gas of gaseous ammonia and fuel discharged from the ammonia supply pipe 2f during the leak check may be discharged to the liner 2b.
- the reduction catalyst chamber 4 may not be provided.
- the present disclosure by introducing the second gas fuel into the first supply pipe, it is possible to suppress the pressure fluctuation during the leak check and simplify the leak check.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
Description
(1)上記実施形態では、ガスタービンAの燃焼装置Cにおいてリークチェックを実施するものとしたが、本開示はこれに限定されず、例えばジェットエンジン等の燃焼装置や、ボイラとしてもよい。
2 燃焼器
2a ケーシング
2b ライナ
2c 整流器
2d 燃料供給管(第2の供給管)
2e 燃料ノズル
2f アンモニア供給管(第1の供給管)
2g アンモニア噴射ノズル
2h 接続管
2i ガス抜き管
2j 温度センサ
2k 圧力センサ
3 タービン
4 還元触媒チャンバ
5 タンク
6 ポンプ
7 気化器
8 燃料供給部
A ガスタービン
C 燃焼装置
E 排気口
G 発電機
K 火炎
Kc 中心部
V1 第1アンモニアバルブ(第1の開閉弁)
V2 第2アンモニアバルブ(第2の開閉弁)
V3 接続管バルブ(第3の開閉弁)
V4 第1燃料バルブ
V5 第2燃料バルブ
Claims (7)
- 第1のガス燃料を燃焼器に供給する第1の供給管と、
前記第1の供給管に設けられた第1の開閉弁と、
前記第1の供給管のうち前記第1の開閉弁よりも前記第1の供給管の出口に近い部分に設けられた第2の開閉弁と、
前記第1のガス燃料よりも液化温度が低い第2のガス燃料を前記燃焼器に供給する第2の供給管と、
前記第1の供給管における第1の開閉弁と第2の開閉弁との間の部位と、前記第2の供給管とを接続する接続管と、
前記接続管に設けられる第3の開閉弁と、
前記第1の供給管に備えられるリークチェック用計測装置とを備え、
前記第2のガス燃料を前記第1の供給管に導入することにより前記第1の供給管のリークチェックを行う燃料供給装置。 - 前記第1の開閉弁を閉弁状態とし、かつ前記第2の開閉弁及び前記第3の開閉弁を開弁状態とするように制御することにより、前記第1の供給管内に残留する前記第1のガス燃料を前記第2のガス燃料で置換し、
前記置換の後に、前記第1の開閉弁及び第2の開閉弁を閉弁状態とし、かつ前記第3の開閉弁を開弁状態とするように制御することにより、前記第1の供給管内を前記第2のガス燃料で加圧し、
前記加圧の後に、前記第1~第3の開閉弁を閉弁状態とするように制御することにより、前記リークチェック用計測装置を用いて前記第1の供給管のリークチェックを行う、制御装置をさらに備える請求項1に記載の燃料供給装置。 - 前記制御装置は、前記置換の前に前記第1の開閉弁及び前記第3の開閉弁を閉弁状態とし、かつ、第2の開閉弁を開弁状態とするように制御することにより、前記第1の供給管内が減圧される請求項2に記載の燃料供給装置。
- 前記第1の供給管のうち前記第2の開閉弁の下流側に一端が接続されるガス抜き管をさらに備え、
前記ガス抜き管は、前記置換時あるいは前記減圧時に前記第1のガス燃料を前記第1の供給管から外部に排出する請求項2または3に記載の燃料供給装置。 - 前記燃焼器における前記第1のガス燃料と前記第2のガス燃料との混焼の終了時に、前記第2の供給管から前記第1の供給管に前記第2のガス燃料を導入する請求項1~4のいずれか一項に記載の燃料供給装置。
- 前記第1のガス燃料はアンモニアであり、前記第2のガス燃料は天然ガスである請求項1~5のいずれか一項に記載の燃料供給装置。
- 請求項1から請求項6のいずれか一項に記載の燃料供給装置を備えるガスタービン。
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AU2019245081A AU2019245081A1 (en) | 2018-03-28 | 2019-03-18 | Fuel supply device and gas turbine |
EP19776206.5A EP3779149A1 (en) | 2018-03-28 | 2019-03-18 | Fuel supply device and gas turbine |
CN201980010167.7A CN111655992A (zh) | 2018-03-28 | 2019-03-18 | 燃料供给装置以及燃气轮机 |
KR1020207022060A KR20200100188A (ko) | 2018-03-28 | 2019-03-18 | 연료 공급 장치 및 가스 터빈 |
US16/940,580 US20200355372A1 (en) | 2018-03-28 | 2020-07-28 | Fuel supply device and gas turbine |
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