WO2018181002A1 - 燃焼装置及びガスタービン - Google Patents
燃焼装置及びガスタービン Download PDFInfo
- Publication number
- WO2018181002A1 WO2018181002A1 PCT/JP2018/011731 JP2018011731W WO2018181002A1 WO 2018181002 A1 WO2018181002 A1 WO 2018181002A1 JP 2018011731 W JP2018011731 W JP 2018011731W WO 2018181002 A1 WO2018181002 A1 WO 2018181002A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ammonia
- combustion
- cooling
- fuel
- combustor
- Prior art date
Links
Images
Classifications
-
- 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
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
- B01D53/34—Chemical or biological purification of waste gases
- B01D53/92—Chemical or biological purification of waste gases of engine exhaust gases
- B01D53/94—Chemical or biological purification of waste gases of engine exhaust gases by catalytic processes
- B01D53/9404—Removing only nitrogen compounds
- B01D53/9409—Nitrogen oxides
- B01D53/9431—Processes characterised by a specific device
-
- 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
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
-
- 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
- F02C7/16—Cooling of plants characterised by cooling medium
-
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23J—REMOVAL OR TREATMENT OF COMBUSTION PRODUCTS OR COMBUSTION RESIDUES; FLUES
- F23J7/00—Arrangement of devices for supplying chemicals to fire
-
- 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
-
- 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
- F23K5/002—Gaseous fuel
-
- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
Definitions
- the present disclosure relates to a combustion apparatus and a gas turbine.
- This application claims priority based on Japanese Patent Application No. 2017-060444 for which it applied to Japan on March 27, 2017, and uses the content here.
- Patent Document 1 discloses a combustion apparatus and a gas turbine for burning ammonia as fuel. That is, the combustion apparatus and the gas turbine obtain a combustion exhaust gas for driving the turbine by premixing ammonia (ammonia for fuel) with natural gas and supplying it to the combustor, and reduce nitrogen oxides (NOx). For this purpose, a reduction region in which nitrogen oxide (NOx) generated in the combustion region is reduced by reducing ammonia is formed on the downstream side in the combustor.
- ammonia ammonia for fuel
- NOx nitrogen oxides
- the combustion air used for combustion burns in the combustion chamber together with the ammonia for fuel, so that the side wall constituting the combustion chamber becomes high temperature. For this reason, the thermal degradation of the side wall is caused, and the life of the combustor may be shortened due to the thermal degradation.
- the present disclosure has been made in view of the above-described circumstances, and an object thereof is to suppress a temperature rise of a member constituting a combustor that burns fuel ammonia and extend the life of the combustor.
- a combustion apparatus includes a combustor that combusts fuel ammonia and combustion air in a combustion chamber, and the combustor converts the fuel ammonia into the combustor.
- a cooling ammonia supply unit is provided which is mixed with combustion air and supplied into the combustor.
- the combustor includes a side wall that forms the combustion chamber, and the cooling ammonia supply unit includes a combustion air supply source and the combustion air supply source in the combustion air flow path. It may be located between the side walls.
- the cooling ammonia supply unit may be provided at a position where the ammonia for fuel directly reaches the high temperature part of the side wall.
- the cooling ammonia supply unit includes a cooling nozzle that injects the fuel ammonia, and the cooling nozzle mixes the fuel ammonia with the combustion air. May be configured.
- the cooling ammonia supply unit includes a plurality of cooling nozzles that inject the fuel ammonia, and the plurality of cooling nozzles are flow paths for the combustion air.
- the fuel ammonia may be mixed with the combustion air.
- the ammonia for fuel injected from the cooling nozzle may be liquid ammonia.
- the gas turbine according to the second aspect of the present disclosure includes the combustion device according to the first aspect.
- the ammonia for fuel supplied from the cooling ammonia supply unit mixes with the combustion air and cools the member constituting the combustor and then flows into the combustor, so the temperature of the member constituting the combustor The rise can be suppressed and the life of the combustor can be extended.
- FIG. 1 is a block diagram illustrating an overall configuration of a combustion apparatus and a gas turbine according to an embodiment of the present disclosure. It is sectional drawing which shows the structure of the combustor in one Embodiment of this indication.
- the gas turbine A includes a compressor 1 (combustion air supply source), a turbine 2, a combustor 3, a reduction catalyst chamber 4, a tank 5, a pump 6, and a vaporizer 7. I have. Of these components, the combustor 3, the tank 5, the pump 6, and the carburetor 7 are included in the combustion apparatus C in the present embodiment.
- Such a gas turbine A is a drive source of the generator G, and generates rotational power by burning ammonia as a fuel.
- Compressor 1 generates compressed air by compressing air taken from outside air to a predetermined pressure.
- the compressor 1 of this embodiment is an axial flow type compressor.
- the compressor 1 supplies the compressed air to the combustor 3 mainly as combustion air.
- the combustor 3 burns gaseous ammonia separately supplied from the vaporizer 7 as fuel. That is, the combustor 3 generates combustion gas by burning gaseous ammonia using the combustion air as an oxidizing agent, and supplies the combustion gas to the turbine 2.
- the turbine 2 generates rotational power by using the combustion gas as a driving gas.
- the turbine 2 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 2 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 (N 2 ) by reduction treatment.
- the tank 5 has a predetermined volume and is a fuel tank that stores 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 can generate gaseous ammonia by vaporizing the liquid ammonia supplied from the pump 6.
- the vaporizer 7 supplies ammonia to the combustor 3 as fuel (ammonia for fuel).
- the vaporizer 7 can supply fuel ammonia as gaseous ammonia to a cooling ammonia supply unit 3g described later.
- the vaporizer 7 can supply fuel ammonia as gaseous ammonia to a main burner 3c described later.
- the vaporizer 7 supplies gaseous ammonia as a reducing agent (reducing ammonia) immediately before the reduction catalyst chamber 4 (that is, a position between the combustor 3 and the reduction catalyst chamber 4 in the flow path of the combustion exhaust gas). .
- the above-described reduction catalyst chamber 4 reduces nitrogen oxides (NOx) in cooperation with the reduction catalyst housed inside and the reducing ammonia.
- the vaporizer 7 can also supply liquid ammonia to the cooled ammonia supply unit 3g without vaporizing the liquid ammonia.
- the combustor 3 includes a casing 3a, a liner 3b, a main burner 3c, a compressed air introduction part 3e, an introduction flow path 3f (flow path), a cooling ammonia supply part 3g, and a scroll 3i.
- the main burner 3c includes a burner 3d1 and a rectifier 3d2.
- the vaporizer 7 mentioned above is connected to the burner 3d1 and the cooling ammonia supply part 3g.
- the combustor 3 of the present embodiment combusts ammonia for fuel and combustion air in a combustion chamber N described later.
- the casing 3a is a substantially cylindrical container that houses the liner 3b.
- a burner 3d1 and a rectifier 3d2 are attached to one end (one end in the central axis direction) of the casing 3a, and a scroll 3i is formed at the other end of the casing 3a.
- the liner 3b is provided inside the casing 3a, and is a cylindrical body that connects the main burner 3c and the scroll 3i and is provided substantially coaxially with the casing 3a.
- a gap is provided between the casing 3a and the liner 3b.
- the scroll 3i (or transition piece) connects the outlet of the liner 3b (the end opposite to the main burner 3c in the central axis direction) and the inlet of the turbine 2, and deflects the flow direction of the combustion gas flowing inside. It is.
- An internal space formed by the liner 3 b and the scroll 3 i is a combustion chamber N.
- the combustion chamber N is formed by the side wall H.
- the side wall H forms the liner 3b and the scroll 3i.
- the side wall H may constitute at least a part of the liner 3b or at least a part of the scroll 3i.
- the direction of the arrow shown in the combustion chamber N in FIG. 2 is the flow direction of the combustion gas in the combustion chamber N.
- Combustion air flows toward the main burner 3c in the gap between the casing 3a and the liner 3b.
- the liner 3b is convectively cooled (cooling by heat transfer) when combustion air (mixed gas) flows on the outer surface of the liner 3b.
- the liner 3b is configured so that air that has passed through a plurality of cooling holes (not shown) provided in the liner 3b flows on the inner surface of the liner 3b, thereby causing the inside of the combustion chamber N (on the inner surface of the liner 3b). It is also cooled by film cooling using a gas film formed in (1).
- the combustion chamber N has a cooling structure such as a plurality of effusion cooling holes (not shown) penetrating toward the inside of the combustion chamber N.
- the said cooling hole and effusion cooling hole are not an essential element for this indication, and do not need to be provided in the combustor 3 of this embodiment.
- the burner 3d1 is a nozzle that is provided on the central axis of the liner 3b at one end of the casing 3a and injects fuel into the combustion chamber N.
- the rectifier 3d2 is provided in an annular shape on the outer periphery of the burner 3d1, and supplies combustion air from one end of the combustion chamber N toward the inside.
- the compressed air introduction part 3e is provided on the wall surface of the casing 3a, and is connected to one end of the introduction flow path 3f (first end, the end on the downstream side in the flow direction of the combustion air).
- the other end (second end, upstream end in the flow direction of combustion air) of the introduction flow path 3 f is connected to the compressor 1.
- the compressor 1 and the casing 3a are connected via the introduction flow path 3f, and the introduction flow path 3f can supply the combustion air compressed by the compressor 1 into the casing 3a. is there.
- the cooling ammonia supply part 3g is provided at a position adjacent to the compressed air introduction part 3e, and is provided in the introduction flow path 3f. That is, the cooling ammonia supply unit 3g of the present embodiment is provided on the upstream side of the compressed air introduction unit 3e, and mixes the fuel ammonia with the combustion air and supplies it to the combustor 3.
- the cooling ammonia supply part 3g protrudes from the outside of the introduction flow path 3f toward the inside of the introduction flow path 3f, and includes a cooling nozzle 3h exposed inside the introduction flow path 3f. In the example shown in FIG.
- the cooling nozzle 3h mixes fuel ammonia with combustion air.
- a plurality of cooling ammonia supply units 3g may exist.
- the cooling nozzle 3h can inject the fuel ammonia supplied from the vaporizer 7 into the introduction flow path 3f.
- the cooling ammonia supply part 3g is located upstream (upstream part) from the side wall H in the flow direction of the combustion air. In other words, the cooling ammonia supply unit 3g is located between the compressor 1 (combustion air supply source) and the side wall H in the combustion air flow path.
- the cooling ammonia supply part 3g mixes the fuel ammonia with the combustion air flowing in the introduction flow path 3f, and forms the combustion chamber N with the mixed gas of the combustion air and the fuel ammonia mixed. It is possible to supply toward the side wall H (the liner 3b and the scroll 3i).
- the fuel ammonia supplied by the cooling ammonia supply unit 3g is mixed with the combustion air before being combusted by the combustor 3.
- liquid ammonia is supplied from the tank 5 to the vaporizer 7 when the pump 6 is operated, and gaseous ammonia is generated when the liquid ammonia is vaporized in the vaporizer 7.
- gaseous ammonia a part of the gaseous ammonia is supplied as combustion ammonia (ammonia for fuel) to the burner 3d1 and the cooling ammonia supply unit 3g, and the rest is supplied as reducing ammonia immediately before the reduction catalyst chamber 4.
- the combustion ammonia supplied to the burner 3d1 is injected along the central axis of the liner 3b from the burner 3d1 in the combustion chamber N, that is, inside the liner 3b and the scroll 3i.
- the combustion ammonia burns in the combustion chamber N, and in particular, the temperatures of the liner 3b and the scroll 3i, which are the side walls H constituting the combustion chamber N, rise.
- gaseous ammonia supplied to the cooling ammonia supply unit 3g is injected from the cooling nozzle 3h toward the inside of the introduction flow path 3f.
- the injected gaseous ammonia is mixed with the combustion air compressed by the compressor 1.
- the mixed gas of gaseous ammonia and combustion air mixed in the introduction flow path 3f is supplied from the compressed air introduction part 3e to the inside of the casing 3a (the gap between the casing 3a and the liner 3b) and introduced into the combustion chamber N.
- the side wall H of the combustion chamber N is cooled.
- the mixed gas is supplied into the combustion chamber N from the cooling holes provided in the liner 3b and the scroll 3i and the main burner 3c, and combusts.
- the mixed gas of combustion air and ammonia flows along the outer surface of the side wall H of the combustion chamber N toward the cooling holes provided in the main burner 3c, the liner 3b, and the scroll 3i.
- the side wall H of the combustion chamber N is cooled by these cooling actions. That is, not only using the fuel ammonia for combustion but also using a part of the fuel ammonia as cooling ammonia improves the cooling efficiency of the side wall H of the combustion chamber N, so the life of the side wall H of the combustion chamber N is improved. Can be lengthened.
- Ammonia is known to have a larger specific heat than air.
- the mixed gas of ammonia and combustion air has a characteristic that the temperature rise accompanying cooling is small. For this reason, the cooling efficiency of the side wall H of the combustion chamber N by the mixed gas of ammonia and combustion air is further improved.
- the temperature of gaseous ammonia is lower than the temperature of combustion air (compressed air) compressed by the compressor 1. For this reason, when gaseous ammonia is mixed with combustion air, the temperature of mixed gas will become lower than the temperature of combustion air. As a result, the cooling efficiency with respect to the side wall H of the combustion chamber N is improved by using the mixed gas as compared with the case where the side wall H of the combustion chamber N is cooled only by the combustion air.
- the temperature of combustion air is about 390 ° C., but the saturation temperature of ammonia gas is, for example, 100 ° C. or less at 20 atm. Therefore, it is possible to reliably improve the cooling efficiency of the sidewall H of the combustion chamber N by mixing ammonia with the combustion air.
- ammonia has the advantage that it is difficult to backfire, the combustor 3 can be operated safely.
- the present disclosure is not limited to this.
- the combustion apparatus according to the present disclosure is applicable to various apparatuses other than the gas turbine A, for example, a boiler and an incineration facility. In these boilers, incineration facilities, etc., when using a compressor that compresses combustion air, a configuration other than an axial flow compressor (such as a centrifugal compressor or a reciprocating compressor) may be used.
- a configuration other than an axial flow compressor such as a centrifugal compressor or a reciprocating compressor
- the liquid ammonia supplied from the cooling ammonia supply part 3g is mixed with the combustion air in the introduction flow path 3f, and the combustion air is further cooled by the heat of vaporization when the liquid ammonia evaporates. Therefore, the side wall H of the combustion chamber N constituting the combustor 3 can be more effectively cooled than when gaseous ammonia is mixed with the combustion air.
- the cooling ammonia supply part 3g may be provided at a position where ammonia reaches the high temperature part in the side wall H directly.
- the cooling ammonia supply unit 3g may be arranged so that ammonia (gas or liquid ammonia) supplied from the cooling ammonia supply unit 3g (cooling nozzle 3h) directly contacts the high temperature part of the side wall H.
- the high temperature part of the side wall H can be determined in advance by a combustion experiment using the combustor 3 or the like.
- a backfire detection thermometer may be provided near the introduction flow path 3f where the cooling ammonia supply unit 3g is provided.
- ammonia reducing ammonia
- a reducing agent other than ammonia reducing ammonia
- the cooling ammonia supply unit 3g has a shape protruding from the outside of the introduction channel 3f toward the inside of the introduction channel 3f, but the present disclosure is not limited thereto.
- a shape in which a plurality of cooling nozzles 3h are provided on the wall surface (inner surface) of the introduction flow path 3f may be employed.
- ammonia for fuel is used as the fuel supplied to the main burner 3c, but the present disclosure is not limited to this.
- a fuel other than ammonia (natural gas or the like) may be used as the fuel supplied to the main burner 3c.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Biomedical Technology (AREA)
- Health & Medical Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Analytical Chemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
Description
本願は、2017年3月27日に日本に出願された特願2017-060444号に基づき優先権を主張し、その内容をここに援用する。
本実施形態に係るガスタービンAは、図1に示すように圧縮機1(燃焼用空気供給源)、タービン2、燃焼器3、還元触媒チャンバ4、タンク5、ポンプ6、及び気化器7を備えている。また、これら複数の構成要素のうち、燃焼器3、タンク5、ポンプ6、及び気化器7は、本実施形態における燃焼装置Cに含まれている。このようなガスタービンAは、発電機Gの駆動源であり、燃料であるアンモニアを燃焼することにより回転動力を発生させる。
このタービン2は、図示するように圧縮機1及び発電機Gと軸結合しており、自らの回転動力によって圧縮機1及び発電機Gを回転駆動する。このようなタービン2は、動力回収した後の燃焼ガスを還元触媒チャンバ4に向けて排気する。還元触媒チャンバ4は、内部に還元触媒が充填されており、燃焼ガスに含まれる窒素酸化物(NOx)を還元処理することにより窒素(N2)に還元する。
特に、気化器7は、後述する冷却アンモニア供給部3gに対し、燃料用アンモニアを気体アンモニアとして供給することが可能である。また、気化器7は、後述する主バーナ3cに対し、燃料用アンモニアを気体アンモニアとして供給することが可能である。また、この気化器7は、気体アンモニアを還元剤(還元用アンモニア)として還元触媒チャンバ4の直前(すなわち燃焼排ガスの流動経路における燃焼器3と還元触媒チャンバ4との間の位置)に供給する。なお、上述した還元触媒チャンバ4は、内部に収容した還元触媒と還元用アンモニアとの協働によって窒素酸化物(NOx)を還元処理する。
なお、また、気化器7は、液体アンモニアを気化させずに、液体アンモニアを冷却アンモニア供給部3gに供給することもできる。
また、冷却アンモニア供給部3gが複数存在してもよい。冷却ノズル3hは、気化器7から供給される燃料用アンモニアを導入流路3f内に噴射することが可能である。冷却アンモニア供給部3gは、燃焼用空気の流動方向において、側壁Hよりも上流側(上流部)に位置する。換言すると、冷却アンモニア供給部3gは、燃焼用空気の流路において圧縮機1(燃焼用空気供給源)と側壁Hとの間に位置する。
燃焼用アンモニアは、燃焼室N内で燃焼し、特に、燃焼室Nを構成する側壁Hであるライナ3b及びスクロール3iの温度が上昇する。
アンモニアは、空気よりも比熱が大きいことが知られている。例えば、500℃における空気の比熱がCp=1.1kJ/(K・kg)であるのに対し、アンモニアの比熱はCp=3.0kJ/(K・kg)である。このため、燃焼用空気のみで燃焼室Nの側壁Hを冷却する場合よりも、アンモニアと燃焼用空気の混合気体は冷却に伴う温度上昇が小さいという特性を有する。このため、アンモニアと燃焼用空気の混合気体による燃焼室Nの側壁Hの冷却効率はより向上する。
(2)上記実施形態では、気体アンモニアを冷却アンモニア供給部3gに供給する場合について説明したが、液体アンモニアを冷却アンモニア供給部3gに供給してもよい。この場合、冷却アンモニア供給部3gから供給される液体アンモニアが導入流路3f内の燃焼用空気に混合され、液体アンモニアが蒸発する際の気化熱によって燃焼用空気がさらに冷却される。したがって、燃焼用空気に気体アンモニアを混合させる場合よりも、燃焼器3を構成する燃焼室Nの側壁Hをさらに効果的に冷却することができる。
(3)冷却アンモニア供給部3gは、側壁Hにおける高温部にアンモニアが直接到達する位置に設けられてもよい。例えば、冷却アンモニア供給部3g(冷却ノズル3h)から供給されたアンモニア(気体又は液体アンモニア)が直接に側壁Hの高温部に接触するように、冷却アンモニア供給部3gが配置されてもよい。なお、側壁Hの高温部は、燃焼器3を用いた燃焼実験等により予め決定することが可能である。
(4)逆火対策のため、冷却アンモニア供給部3gが設けられている導入流路3fの近くに逆火検知用温度計を設けてもよい。
(5)上記実施形態では、還元剤としてアンモニア(還元用アンモニア)を用いたが、本開示はこれに限定されない。アンモニア(還元用アンモニア)以外の還元剤を用いてもよい。
(6)上記実施形態では、冷却アンモニア供給部3gは、導入流路3fの外部から導入流路3fの内部に向けて突出した形状を有するが、本開示はこれに限定されない。導入流路3fの壁面(内面)に複数の冷却ノズル3hを設けた形状が採用されてもよい。
(7)上記実施形態では、主バーナ3cに供給される燃料として燃料用アンモニアを用いたが、本開示はこれに限定されない。主バーナ3cに供給される燃料としてアンモニア以外の燃料(天然ガス等)を用いてもよい。
C 燃焼装置
H 側壁
N 燃焼室
1 圧縮機(燃焼用空気供給源)
2 タービン
3 燃焼器
3a ケーシング
3b ライナ
3c 主バーナ
3d1 バーナ
3d2 整流器
3e 圧縮空気導入部
3f 導入流路
3g 冷却アンモニア供給部
3h 冷却ノズル
3i スクロール
4 還元触媒チャンバ
5 タンク
6 ポンプ
7 気化器
Claims (7)
- 燃料用アンモニアと燃焼用空気を燃焼室内で燃焼させる燃焼器を有する燃焼装置であって、
前記燃焼器は、前記燃料用アンモニアを前記燃焼用空気に混合して前記燃焼器内に供給する冷却アンモニア供給部を備える、燃焼装置。 - 前記燃焼器は、前記燃焼室を形成する側壁を備え、
前記冷却アンモニア供給部は、前記燃焼用空気の流路において燃焼用空気供給源と前記側壁との間に位置する、請求項1に記載の燃焼装置。 - 前記冷却アンモニア供給部は、前記側壁における高温部に前記燃料用アンモニアが直接到達する位置に設けられている、請求項2に記載の燃焼装置。
- 前記冷却アンモニア供給部は、前記燃料用アンモニアを噴射する冷却ノズルを備え、
前記冷却ノズルは、前記燃料用アンモニアを前記燃焼用空気に混合するように構成されている、請求項1から請求項3のいずれか一項に記載の燃焼装置。 - 前記冷却アンモニア供給部は、前記燃料用アンモニアを噴射する複数の冷却ノズルを備え、
前記複数の冷却ノズルは、前記燃焼用空気の流路に設けられ、前記燃料用アンモニアを前記燃焼用空気に混合するように構成されている、請求項1から請求項3のいずれか一項に記載の燃焼装置。 - 前記冷却ノズルから噴射される前記燃料用アンモニアは、液体アンモニアである、請求項4又は請求項5に記載の燃焼装置。
- 請求項1から請求項6のいずれか一項に記載の燃焼装置を備える、ガスタービン。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR1020197020357A KR20190096378A (ko) | 2017-03-27 | 2018-03-23 | 연소 장치 및 가스 터빈 |
EP18775182.1A EP3604765B1 (en) | 2017-03-27 | 2018-03-23 | Combustion device and gas turbine |
AU2018245202A AU2018245202B2 (en) | 2017-03-27 | 2018-03-23 | Combustion device and gas turbine |
CN201880020931.4A CN110506152B (zh) | 2017-03-27 | 2018-03-23 | 燃烧装置以及燃气轮机 |
US16/580,851 US20200018482A1 (en) | 2017-03-27 | 2019-09-24 | Combustion device and gas turbine engine system |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2017-060444 | 2017-03-27 | ||
JP2017060444A JP6772924B2 (ja) | 2017-03-27 | 2017-03-27 | 燃焼装置及びガスタービン |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US16/580,851 Continuation US20200018482A1 (en) | 2017-03-27 | 2019-09-24 | Combustion device and gas turbine engine system |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2018181002A1 true WO2018181002A1 (ja) | 2018-10-04 |
Family
ID=63676029
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2018/011731 WO2018181002A1 (ja) | 2017-03-27 | 2018-03-23 | 燃焼装置及びガスタービン |
Country Status (7)
Country | Link |
---|---|
US (1) | US20200018482A1 (ja) |
EP (1) | EP3604765B1 (ja) |
JP (1) | JP6772924B2 (ja) |
KR (1) | KR20190096378A (ja) |
CN (1) | CN110506152B (ja) |
AU (1) | AU2018245202B2 (ja) |
WO (1) | WO2018181002A1 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20230119019A (ko) | 2021-02-15 | 2023-08-14 | 미츠비시 파워 가부시키가이샤 | 연료 공급 방법, 연료 공급 설비, 이 연료 공급 설비를 구비한 연료 연소 설비, 및 가스 터빈 플랜트 |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11859535B2 (en) | 2021-03-09 | 2024-01-02 | Rtx Corporation | Fuel-cooled engine component(s) |
US11920524B2 (en) | 2021-04-15 | 2024-03-05 | Rtx Corporation | Multi-fuel, fuel injection system for a turbine engine |
EP4361094A1 (en) | 2022-10-24 | 2024-05-01 | Linde GmbH | Method and apparatus for processing ammonia |
EP4361096A1 (en) | 2022-10-24 | 2024-05-01 | Linde GmbH | Method and apparatus for processing ammonia |
EP4361095A1 (en) | 2022-10-24 | 2024-05-01 | Linde GmbH | Method and apparatus for providing heat |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000257808A (ja) * | 1999-03-11 | 2000-09-22 | Babcock Hitachi Kk | 圧力容器、加圧流動層ボイラ及びアンモニア注入装置 |
WO2010082359A1 (ja) * | 2009-01-14 | 2010-07-22 | トヨタ自動車株式会社 | エンジン |
JP2015031215A (ja) * | 2013-08-02 | 2015-02-16 | 一般財団法人電力中央研究所 | 再熱型アンモニアガスタービン |
JP2015094496A (ja) * | 2013-11-11 | 2015-05-18 | 株式会社Ihi | 燃焼装置、ガスタービン及び発電装置 |
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 |
JP2017060444A (ja) | 2015-09-25 | 2017-03-30 | 株式会社クボタ | 農作業機 |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3755811B2 (ja) * | 2001-02-06 | 2006-03-15 | 財団法人電力中央研究所 | 改質型ガス化ガス発電プラントおよびその運転方法 |
JP5524407B2 (ja) * | 2011-03-16 | 2014-06-18 | 三菱重工業株式会社 | ガスタービン燃焼器およびガスタービン |
JP2012255420A (ja) * | 2011-06-10 | 2012-12-27 | Nippon Shokubai Co Ltd | ガスタービンシステム |
JP6154988B2 (ja) * | 2012-01-05 | 2017-06-28 | 三菱日立パワーシステムズ株式会社 | 燃焼器 |
-
2017
- 2017-03-27 JP JP2017060444A patent/JP6772924B2/ja active Active
-
2018
- 2018-03-23 CN CN201880020931.4A patent/CN110506152B/zh active Active
- 2018-03-23 AU AU2018245202A patent/AU2018245202B2/en active Active
- 2018-03-23 WO PCT/JP2018/011731 patent/WO2018181002A1/ja unknown
- 2018-03-23 KR KR1020197020357A patent/KR20190096378A/ko active IP Right Grant
- 2018-03-23 EP EP18775182.1A patent/EP3604765B1/en active Active
-
2019
- 2019-09-24 US US16/580,851 patent/US20200018482A1/en not_active Abandoned
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000257808A (ja) * | 1999-03-11 | 2000-09-22 | Babcock Hitachi Kk | 圧力容器、加圧流動層ボイラ及びアンモニア注入装置 |
WO2010082359A1 (ja) * | 2009-01-14 | 2010-07-22 | トヨタ自動車株式会社 | エンジン |
JP2015031215A (ja) * | 2013-08-02 | 2015-02-16 | 一般財団法人電力中央研究所 | 再熱型アンモニアガスタービン |
JP2015094496A (ja) * | 2013-11-11 | 2015-05-18 | 株式会社Ihi | 燃焼装置、ガスタービン及び発電装置 |
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 |
JP2017060444A (ja) | 2015-09-25 | 2017-03-30 | 株式会社クボタ | 農作業機 |
Non-Patent Citations (1)
Title |
---|
See also references of EP3604765A4 |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20230119019A (ko) | 2021-02-15 | 2023-08-14 | 미츠비시 파워 가부시키가이샤 | 연료 공급 방법, 연료 공급 설비, 이 연료 공급 설비를 구비한 연료 연소 설비, 및 가스 터빈 플랜트 |
DE112022001079T5 (de) | 2021-02-15 | 2023-11-30 | Mitsubishi Heavy Industries, Ltd. | Brennstoffzufuhrverfahren, Brennstoffzufuhrsystem, mit Brennstoffzufuhrsystem versehenes Brennstoffverbrennungssystem und Gasturbinenanlage |
Also Published As
Publication number | Publication date |
---|---|
AU2018245202B2 (en) | 2021-06-03 |
EP3604765A4 (en) | 2020-12-16 |
AU2018245202A1 (en) | 2019-10-24 |
EP3604765A1 (en) | 2020-02-05 |
JP6772924B2 (ja) | 2020-10-21 |
US20200018482A1 (en) | 2020-01-16 |
JP2018162723A (ja) | 2018-10-18 |
KR20190096378A (ko) | 2019-08-19 |
CN110506152B (zh) | 2022-03-22 |
CN110506152A (zh) | 2019-11-26 |
EP3604765B1 (en) | 2024-06-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2018181002A1 (ja) | 燃焼装置及びガスタービン | |
JP6134544B2 (ja) | 作動流体を燃焼器に供給するシステム | |
JP6866570B2 (ja) | 燃焼装置及びガスタービン | |
US10330050B2 (en) | Fuel injection device for gas turbine | |
WO2018181063A1 (ja) | 燃焼装置及びガスタービン | |
JP6880561B2 (ja) | 燃焼装置及びガスタービン | |
WO2016056579A1 (ja) | 燃焼器及びガスタービンエンジン | |
KR101626692B1 (ko) | 연소기 | |
KR20190116522A (ko) | 가스 터빈 | |
US10443853B2 (en) | Fuel injection device for gas turbine | |
JP2005090951A (ja) | 燃焼器の音響を低減するための方法及び装置。 | |
WO2019188409A1 (ja) | 燃焼装置及びガスタービン | |
JP2016186387A (ja) | ガスタービン燃焼器およびガスタービン | |
KR101730446B1 (ko) | 농후연소와 희박연소 및 마일드 연소가 가능한 연소기 | |
JP2013228192A (ja) | 化学量論的燃焼のための燃焼器装置 | |
WO2019188012A1 (ja) | 燃焼装置及びガスタービン | |
KR101041466B1 (ko) | 다수 연료혼합장치가 구비된 가스터빈 저공해 연소기 | |
JP2020139691A (ja) | 燃焼器 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 18775182 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 20197020357 Country of ref document: KR Kind code of ref document: A |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
ENP | Entry into the national phase |
Ref document number: 2018245202 Country of ref document: AU Date of ref document: 20180323 Kind code of ref document: A |
|
ENP | Entry into the national phase |
Ref document number: 2018775182 Country of ref document: EP Effective date: 20191028 |