WO2016104725A1 - バーナ、燃焼器、及びガスタービン - Google Patents
バーナ、燃焼器、及びガスタービン Download PDFInfo
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- WO2016104725A1 WO2016104725A1 PCT/JP2015/086273 JP2015086273W WO2016104725A1 WO 2016104725 A1 WO2016104725 A1 WO 2016104725A1 JP 2015086273 W JP2015086273 W JP 2015086273W WO 2016104725 A1 WO2016104725 A1 WO 2016104725A1
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- fuel
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- burner
- combustion
- cylinder
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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
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C1/00—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C99/00—Subject-matter not provided for in other groups of this subclass
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
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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
-
- 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
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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
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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
- F23R3/36—Supply of different fuels
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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 invention relates to a burner, a combustor, and a gas turbine.
- gas turbines use by-product hydrogen gas, which is generated as a secondary product from manufacturing processes such as petrochemical plants, in addition to natural gas, which is the main fuel of gas turbines, from the viewpoint of global warming prevention and effective use of resources. It is requested.
- Patent Document 1 a combustion cylinder that forms a combustion chamber inside, and a flow path of compressed air (referred to as combustion air) supplied from a compressor are formed around the combustion cylinder so as to cover the outside of the combustion cylinder.
- a plurality of second fuel nozzles (corresponding to a reheating burner) disposed through the peripheral wall of the combustion cylinder from the casing, and the second fuel (hydrogen-containing gas) from the peripheral wall of the combustion cylinder toward the combustion chamber ) Is injected inward in the radial direction, and the second fuel is diffused in the combustion product gas and burned.
- a lean premixed combustion method (Dry Low Emission combustion method) has attracted attention as a method for suppressing NOx emissions without using water or steam.
- a combustor (DLE) employing this combustion method has attracted attention.
- a gas turbine having a combustor is operating in a plant facility or the like.
- This refueling burner mixes combustion air introduced into the premixing channel from the upstream side with the first and second fuels in the premixing channel to generate a premixed gas, and the premixed gas is downstream.
- the first and second fuel injection holes for injecting the first and second fuels into the premixing chamber are to be injected and combusted from the side.
- the present invention premixes a hydrocarbon-based first fuel (for example, natural gas), a second fuel (for example, hydrogen gas), and combustion air in advance, and has a lean and uniform concentration distribution. It is an object of the present invention to provide a burner capable of injecting NO into the combustion chamber of the combustor and suppressing NOx emission, a combustor including the burner, and a gas turbine.
- a hydrocarbon-based first fuel for example, natural gas
- a second fuel for example, hydrogen gas
- the burner of the present invention mixes combustion air and fuel introduced from the upstream side into the premixing channel in the premixing channel to generate a premixed gas, and the premixed gas is introduced from the downstream side into the combustion chamber.
- a burner that injects and burns, and an outer cylinder in which the premixing channel is formed, and combustion air is supplied from the outer edge of the outer cylinder toward the center on the upstream side of the premixing channel A first air introduction section; a first fuel introduction section for introducing a first fuel into the premixing flow path; and a second fuel introduction for introducing a second fuel having a specific gravity smaller than that of the first fuel into the premixing flow path.
- the second fuel introduction part is formed to project into the premixing channel from the upstream end of the premixing channel toward the downstream side, and is introduced from the first air introduction unit A plurality of second fuel injection nozzles for injecting second fuel into the compressed air;
- the second fuel is injected from the second fuel injection nozzle to generate a primary mixture, and the first fuel is introduced from the first fuel introduction unit to the primary mixture to obtain a secondary mixture. Is generated.
- the second fuel is injected from each of the second fuel injection nozzles to the combustion air flowing from the outer edge of the outer cylinder toward the center on the upstream side of the premixing flow path, so that the primary mixture is generated. Generated.
- the second fuel is a low speed region of compressed air generated in the vicinity of the upstream end portion of the premixing channel from the second fuel injection nozzle protruding into the premixing channel from the upstream end portion of the premixing channel. It is injected into the flow of combustion air avoiding (viscous boundary layer).
- the second fuel has a low specific gravity and a low penetrating power, such as hydrogen gas
- a lean and uniform concentration mixture is generated.
- the first fuel is introduced from the first fuel introduction portion to the primary mixture to generate a secondary mixture (premixed gas).
- the specific gravity of the first fuel is larger than that of the second fuel
- the first fuel and the primary mixture are sufficiently agitated and mixed to be lean, and the secondary mixture has a more uniform concentration distribution than the primary mixture. Is generated.
- a lean premixed gas having a uniform concentration distribution is supplied to the combustion chamber, and the amount of NOx in the combustion exhaust gas can be suppressed.
- the first fuel introduction portion provided in the burner projects into the premixing channel concentrically with the outer cylinder from an upstream end of the premixing channel, and toward the outer edge of the outer cylinder. You may have the 1st fuel-injection nozzle which injects a fuel.
- the primary air-fuel mixture that flows from the outer edge of the outer cylinder to the center on the upstream side of the premixing channel flows along the outer periphery of the first fuel injection nozzle toward the downstream side of the premixing channel.
- the first fuel is injected from the first fuel injection nozzle to the primary mixture to generate a secondary mixture.
- the mixing of the first fuel and the primary mixture is promoted to generate a secondary mixture having a uniform concentration distribution.
- a lean premixed gas having a uniform concentration distribution is supplied to the combustion chamber, and NOx in the combustion exhaust gas can be suppressed.
- the burner includes a rectifying protrusion that protrudes into the premixing channel concentrically with the outer cylinder from an upstream end of the premixing channel, and the first fuel introduction unit included in the burner includes the You may have the some 1st fuel injection hole which is formed in the upstream edge part of the premix flow path, and is formed in the outer edge side rather than the said baffle projection part, and inclines in the outer edge side of an outer cylinder.
- the primary air-fuel mixture flows from the first fuel injection hole inclined toward the outer edge side of the outer cylinder with respect to the primary air-fuel mixture flowing upstream from the outer edge of the outer cylinder toward the center.
- a secondary air-fuel mixture is generated by the injection.
- the first fuel is injected in a direction intersecting with the flow of the primary mixture, the mixing of the primary mixture and the first fuel in the premix channel is promoted, and the concentration distribution is uniform 2 A secondary mixture is produced.
- a lean premixed gas with a uniform concentration distribution is supplied to the combustion chamber, and the generation of NOx can be suppressed.
- the secondary air-fuel mixture changes its direction along the flow straightening projection and flows downstream, and is injected into the combustion chamber without reducing the speed, backfire can be suppressed.
- the burner includes a rectifying protrusion that protrudes into the premixing channel concentrically with the outer cylinder from an upstream end of the premixing channel, and the first fuel introduction unit includes the first air introduction unit.
- a plurality of first fuel injection nozzles that inject the first fuel from the outer edge of the outer cylinder toward the center may be provided downstream of the portion.
- the primary air-fuel mixture that flows upstream from the outer edge of the outer cylinder toward the center on the upstream side of the premixing channel changes direction along the rectifying protrusion and flows toward the downstream side.
- the first fuel is injected from the first fuel injection hole toward the center of the outer cylinder with respect to the primary mixture, and a secondary mixture is generated.
- the mixing of the primary mixture and the first fuel in the premix channel is promoted, and the concentration distribution is uniform 2 A secondary mixture is produced.
- a lean premixed gas with a uniform concentration distribution is supplied to the combustion chamber, and the generation of NOx can be suppressed.
- the primary air-fuel mixture flows downstream without reducing the flow velocity along the rectifying protrusion, a decrease in the flow velocity during turning is suppressed. Therefore, since the premixed gas is injected into the combustion chamber while maintaining a sufficient flow rate, backfire can be suppressed.
- the burner may include a second air introduction part for introducing combustion air from the outer edge of the outer cylinder to the premixing flow path on the downstream side of the first air introduction part.
- the outer cylinder is composed of an upstream first cylindrical body and a downstream second cylindrical body, which are coaxially arranged, and the first cylindrical body and the second cylindrical body are The second air introduction part is partitioned by the first cylinder and the second cylinder, and from the upstream side to the downstream side. It may be an annular gap that gradually decreases in diameter.
- the inner diameter of the second cylinder may be substantially the same as the inner diameter of the first cylinder on the downstream side.
- a part of the combustion air is blown to the outer periphery of the first cylindrical body, and then introduced into the second air introduction section as secondary air.
- the secondary air is uniformly rectified by flowing from the upstream side to the downstream side through the second air introduction portion.
- the secondary air is fed into the premixing channel, so that the retention of the air-fuel mixture in the boundary layer can be more effectively suppressed.
- the secondary air can make a flow that guides the premixed gas staying in the boundary layer toward the center of the flow path by flowing through an annular gap that gradually decreases in diameter from the upstream side toward the downstream side.
- the first fuel may be natural gas or liquefied natural gas
- the second fuel may be hydrogen gas or hydrogen-containing gas
- the combustor of the present invention includes a combustion cylinder forming a combustion chamber for burning fuel, a premixed combustion type main burner disposed on the upstream side of the combustion cylinder, and a peripheral wall portion on the downstream side of the combustion cylinder
- a combustor of a gas turbine including a reheating burner disposed so as to pass through the reheating burner, wherein the reheating burner is any one of the burners described above.
- a combustor having a reheating burner capable of injecting a premixed gas having a uniform concentration distribution into the combustion chamber of the combustor and suppressing NOx emission.
- gas turbine of the present invention is characterized by including the above-described combustor.
- a first fuel for example, natural gas
- a second fuel for example, hydrogen gas
- combustion air are premixed, and a premixed gas having a uniform concentration distribution is supplied to the combustion chamber of the combustor.
- emission amount of NOx by injecting, the combustor which comprises the burner, and a gas turbine can be provided.
- FIG. 4 is a cross-sectional view of the premixing channel viewed from the AA direction in FIG. 3. It is the figure which showed the modification of 1st Embodiment. It is a longitudinal cross-sectional view of the reheating burner which concerns on 2nd Embodiment of this invention. It is a longitudinal cross-sectional view of the 1st example of the reheating burner which concerns on 3rd Embodiment of this invention.
- FIG. 1 A schematic configuration and functions of the gas turbine are shown in FIG.
- the compressor 2 sucks the atmosphere and generates compressed air 200.
- the compressed air 200 is combusted together with fuel in the combustor 3 to generate high-temperature and high-pressure combustion product gas (hereinafter referred to as “combustion exhaust gas 300”).
- the combustion exhaust gas 300 is supplied to the turbine 4 and used for rotating the rotor 5.
- the rotation of the rotor 5 is transmitted to the compressor 2 and used to generate compressed air 200 (hereinafter referred to as “combustion air 200”), while the rotation of the rotor 5 is transmitted to the generator 6 to generate power.
- combustion air 200 compressed air 200
- FIG. 2 shows the combustor 3.
- the combustor 3 includes a flow direction of compressed air 200 supplied from a compressor (see FIG. 1) (a direction from the top to the bottom in FIG. 1) and a flow direction of combustion exhaust gas 300 (see FIG. 1). Is a backflow can type combustor which is opposed to each other inside.
- the type of the combustor may be an annular type having a plurality of fuel injection valves on the circumference.
- the combustor 3 includes a combustion cylinder 34 and a casing 35 that are arranged concentrically on the central axis 302.
- a burner unit 30 is attached to the top of the combustion cylinder 34, and a combustion chamber 33 for burning fuel or the like injected from the burner unit 30 is formed inside the combustion cylinder 34.
- the combustion cylinder 34 is surrounded by a cylindrical casing 35, and an annular combustion air flow path 37 through which the combustion air 200 supplied from the compressor flows is formed between the combustion cylinder 34 and the casing 35. ing.
- the casing 35 and the combustion cylinder 34 support a plurality of reheating burners 36 on the downstream side of the burner unit 30.
- the burner unit 30 is disposed along the central axis 302 and premixed main burner 31 that injects a premixed gas generated by mixing fuel and combustion air 200 into the combustion chamber 33.
- a diffusion combustion type pilot burner 32 for directly injecting fuel into the combustion chamber 33.
- the main burner 31 is arranged concentrically around the pilot burner 32.
- the main burner 31 and the pilot burner 32 communicate with a first fuel supply source 305 (natural gas supply source) via a pipe 304.
- the main burner 31 has an outer cylinder 310 and an inner cylinder 312 that are arranged concentrically along the central axis 302.
- the inner cylinder 312 also serves as a combustion air injection cylinder 322b of a pilot burner 32 described later.
- An annular space between the outer cylinder 310 and the inner cylinder 312 is used as a premixing channel 314 for mixing fuel and combustion air.
- the premixing channel 314 has one end opened to the combustion chamber 33 and the other end opened to the combustion air channel 37 through the plurality of air intake ports 315 toward the radially outer side.
- a plurality of main fuel nozzles 316 for ejecting the first fuel are disposed outside the air intake port 315 in the radial direction.
- each main fuel nozzle 316 has a plurality of fuel injection holes (not shown) for injecting the first fuel toward the air intake 315 at a portion facing the air intake 315, and It is connected to the first fuel supply source 305 (natural gas supply source) via a pipe 304a including a flow rate adjustment valve, and is supplied from the first fuel supply source 305 by opening the flow rate adjustment valve during normal operation.
- first fuel supply source 305 natural gas supply source
- the fuel to be supplied together with the combustion air supplied from the combustion air flow path 37 is supplied from the air intake 315 to the premixing flow path 314 and mixed in the premixing flow path 314, and the premixed gas is mixed with the combustion chamber. 33 is injected.
- the air intake port 315 has a plurality of swirl blades (swirlers) 317 that impart a swirling force to the combustion air flowing into the premixing flow path 314 to promote premixing with the first fuel. Is provided.
- the pilot burner 32 includes a fuel injection cylinder 322a extending along the central axis 302 and a combustion air injection cylinder 322b concentrically mounted on the fuel injection cylinder 322a, and a fuel formed in the fuel injection cylinder 322a.
- An injection path (not shown) is connected to the first fuel supply source 305 (natural gas supply source) via a pipe 304b including a flow rate adjustment valve. Natural gas supplied from one fuel supply source is injected into the combustion chamber.
- An annular air flow path 324 is formed between the fuel injection cylinder 322a and the combustion air injection cylinder 322b, one end of which is connected to the combustion air flow path 37 and the other end is connected to the combustion chamber. The compressed air supplied from the compressor is injected into the combustion chamber.
- the reheating burner 36 is attached to the casing 35 and the combustion cylinder 34 along four axial centers 360 that are included in a plane orthogonal to the central axis 302 and are arranged at equal intervals in the circumferential direction.
- the reheating burner 36 is connected to a first fuel supply source (natural gas supply source) 305 and a second fuel supply source (hydrogen gas supply source) 307 via a pipe including a flow rate adjusting valve. And by opening the flow rate adjustment valve during high load operation, the combustion air taken in from the combustion air flow path 37 is mixed with the first fuel and the second fuel to generate a premixed gas, The premixed gas can be injected into the combustion chamber.
- the said 1st fuel shows the liquid containing 60 volume% or more of hydrocarbons, the gas which hydrogen gas is 10 volume% or less, or 60 volume% or more of hydrocarbons.
- the said 2nd fuel shows the gas containing 50 volume% or more of hydrogen.
- natural gas is illustrated as an example of the first fuel
- hydrogen gas is illustrated as an example of the second fuel.
- the operation of the combustor 3 having the above-described configuration will be described below with reference to FIG.
- the gas turbine (not shown) is started, the flow rate adjustment valve is opened, and the natural gas supplied from the main fuel supply source to the pilot burner 32 is injected into the combustion chamber 33.
- the combustion air injected from the annular air flow path 324 into the combustion chamber 33 is diffusely mixed in the combustion chamber 33 and ignited by an ignition source (not shown) to form a pilot flame by diffusion combustion.
- the premixed gas injected from the premixing flow path 314 of the main burner 31 is ignited by the pilot flame in the combustion chamber 33, and the primary combustion region S 1 upstream of the combustion chamber 33. Burn with. By burning the lean premixed gas, the combustion flame temperature in the combustion chamber 33 is lowered, and the amount of NOx in the combustion exhaust gas of the main burner is suppressed.
- a premixed gas of natural gas, hydrogen gas, and combustion air 200 generated in the additional burner 36 is introduced into the combustion chamber 33, In the secondary combustion region S2 downstream of the primary combustion region S1, it is mixed with the combustion exhaust gas of the main burner 31 and burned. By burning the lean premixed gas, the amount of NOx in the combustion exhaust gas is suppressed.
- FIG. 3 shows a reheating burner 36 according to the first embodiment of the present invention. 3 shows a cross section corresponding to FIG. 2, and FIG. 4 shows a cross section taken along line AA in FIG.
- the terms “upstream” and “downstream” are used with respect to the direction of fluid flow in the chasing burner 36.
- the reheating burner 36 has a plurality of configurations, for example, a head block arranged in order from the outside toward the inside on a radial axis 360 with respect to the central axis 302 of the combustor 3. 361, an outer cylinder 364 having a first cylinder part 362 and a second cylinder part 363.
- the head block 361 is fitted into a mounting hole 352 formed in the casing 35 and fixed, and the flange portion 365 of the first cylindrical portion 362 is fixed to the head block 361 via a plurality of connecting pieces 366.
- the second cylindrical portion 363 is fitted and fixed in a through hole 340 formed in the combustion cylinder 34.
- a premixing channel 367 for mixing the fuel and the combustion air 200 is formed as an internal space surrounded by the head block 361, the first cylinder 362, and the second cylinder part 363.
- the reheating burner 36 premixes the first fuel introduction portion 368 for introducing the natural gas supplied from the first fuel supply source into the premixing flow path 367 and the hydrogen gas supplied from the second fuel supply source.
- a second fuel introduction portion 369 that introduces the combustion air 200 is introduced into the premixing passage 367 from the combustion air passage 37 and the second fuel introduction portion 369 that is introduced into the passage 367.
- the first air introduction portion 370 is formed as a plurality of gap spaces (air intake ports) surrounded by the flange portion 365 of the first cylindrical portion 362, the head block 361, and a plurality of connection pieces 366 connecting them.
- a part of the compressed air 200 (combustion air 200) flowing through the combustion air flow path 37 from the first air introduction part 370 can be introduced into the premixing flow path 367.
- the combustion air 200 introduced into the premixing channel 367 flows from the outer edge (radially outer side) of the outer cylinder 364 toward the center (radially inner side).
- the connecting pieces 366 are arranged at equal intervals every 45 degrees on the circumference concentric with the outer cylinder 364, and are arranged at circumferential positions spaced from a second fuel injection nozzle 384 described later. Each air intake port is arranged at a circumferential position corresponding to the two fuel injection nozzles 384.
- the first fuel introduction portion 368 includes a first fuel supply path 380 extending from the upstream side to the downstream side along the axis 360 in the head block 361, and the axis 360 from the downstream side wall surface of the head block 361.
- a bottomed cylindrical first fuel injection nozzle 381 protruding into the premixing flow path 367 is provided.
- the upstream side of the first fuel supply path 380 communicates with the first fuel supply source via a pipe 306 including a flow rate adjustment valve, and the downstream side of the first fuel supply path 380 is the first fuel injection nozzle 381.
- the premix channel 367 communicates with a plurality of first fuel injection holes 382 formed through the peripheral wall in the radial direction. Further, the first fuel injection holes 382 are arranged at equal intervals in the circumferential direction and the axial direction. They are arranged every 90 degrees in the circumferential direction. With this configuration, the natural gas supplied from the first fuel supply source is injected into the premixing flow path 367 via the first fuel supply path 380 and the first fuel injection nozzle 381.
- the second fuel introduction portion 369 has a plurality of cylindrical shapes that protrude into the premixing passage 367 from the second fuel supply passage 383 extending from the upstream side to the downstream side in the head block 361 and the downstream side wall surface of the head block 361.
- the second fuel injection nozzle 384 is provided.
- the upstream side of the second fuel supply path 383 is connected to a second fuel supply source via a pipe 308 including a flow control valve.
- An annular flow path 385 that surrounds the first fuel supply path 380 and extends concentrically with the outer cylinder 364 is formed on the downstream side of the second fuel supply path 383.
- the downstream side of the annular flow path 385 communicates with the premixing flow path 367 via the internal space of each second fuel injection nozzle 384.
- the second fuel injection nozzles 384 are arranged at equal intervals every 45 degrees on the circumference concentric with the outer cylinder 364 and extend in parallel with the outer cylinder. With this configuration, the hydrogen gas supplied from the second fuel supply source is injected into the premixing flow path 367 via the second fuel supply path 383 and the second fuel injection nozzle 384.
- Combustion air 200 introduced from the first air introduction portion 370 into the premixing flow path 367 flows on the upstream side of the premixing flow path 367 from the outer edge of the outer cylinder 364 toward the center, and then the combustion air Hydrogen gas is injected from each second fuel injection nozzle 384 to 200, and a primary air-fuel mixture is generated.
- the hydrogen gas flows from the second fuel injection nozzles 384 projecting into the premixing channel 367 from the upstream end of the premixing channel 367 (the downstream side wall surface of the head block 361).
- the natural gas and the primary mixture are sufficiently agitated and mixed to produce a secondary mixture that is lean and has a more uniform concentration distribution than the primary mixture.
- the first fuel naturally gas
- the first fuel injection nozzle 381 since the first fuel (natural gas) is injected from the first fuel injection nozzle 381 in a direction crossing the flow direction of the primary mixture, the mixing of the first fuel and the primary mixture is promoted and the secondary fuel is promoted.
- the concentration distribution of the air-fuel mixture becomes uniform.
- a lean premixed gas 700 (secondary gas mixture) having a uniform concentration distribution is supplied to the secondary combustion region S2 downstream of the primary combustion region S1 of the combustion chamber 33, and is contained in the combustion exhaust gas. The amount of NOx can be suppressed.
- the reheating burner according to the first embodiment described above can be variously modified.
- hydrogen gas is injected from the second fuel injection hole 386 formed in the peripheral wall of the second fuel injection nozzle 384 in the direction opposite to the flow of the combustion air 200. It may be configured. According to such a configuration, the hydrogen gas injected from the second fuel injection hole 386 collides with the combustion air 200, thereby improving the hydrogen gas dispersion effect. As a result, mixing of hydrogen gas and combustion air 200 is promoted, and a more uniform primary air-fuel mixture can be generated.
- the number of the second fuel injection holes 386 may be one. However, as shown in FIG. 5, the effect of hydrogen gas dispersion can be further increased by making the number of the second fuel injection holes 386 plural. It can be expected to improve the mixing of hydrogen gas and combustion air.
- FIG. 6 shows a reheating burner 36 according to the second embodiment of the present invention.
- the basic structure of the tracking burner 36 according to the present embodiment is the same as that of the tracking burner 36 according to Embodiment 1 described with reference to FIG. Omitted.
- the reheating burner 36 according to the present embodiment is different from the reheating burner 36 according to the first embodiment described with reference to FIG. 3 in that it has an inverted conical shape extending coaxially with the outer cylinder 364 and into the premixing channel 367.
- the first fuel introduction portion 368 is configured such that the natural gas is injected from the point where the rectifying protrusion 390 is formed on the downstream side wall surface of the head block 361 and the plurality of first fuel injection holes 391 surrounding the rectifying protrusion 390. Two points.
- the upstream side of each first fuel injection hole 391 communicates with the first fuel supply passage 380, and the downstream side of the first fuel injection hole 391 communicates with the premixing passage 367.
- the first fuel injection holes 391 are arranged on the circumference concentric with the outer cylinder 364 and at equal intervals in the circumferential position corresponding to the second fuel injection nozzle 384 and the first air introduction portion 370. Each first fuel injection hole 391 is located closer to the center side of the outer cylinder 364 than the second fuel injection nozzle 384, and is inclined toward the outer edge side (radially outward) of the outer cylinder 364 from the upstream side toward the downstream side. ing.
- the operation of the chasing burner 36 having the above-described configuration will be described.
- the first fuel naturally gas
- the first fuel is injected from the plurality of first fuel injection holes 391, and a secondary gas mixture is generated.
- the first fuel is injected in a direction crossing the flow of the primary mixture, the mixing of the primary mixture and the first fuel in the premix channel 367 is promoted, and the uniform concentration of 2 A secondary gas mixture (premixed gas) is generated.
- a lean premixed gas 700 (secondary gas mixture) having a uniform concentration distribution is supplied to the secondary combustion region S2 downstream of the primary combustion region S1 of the combustion chamber 33, and is contained in the combustion exhaust gas. NOx can be suppressed.
- the secondary mixture flows downstream without reducing the flow velocity along the flow straightening projection 390 and is injected into the combustion chamber 33, so that backfire due to a decrease in the flow velocity of the secondary mixture can be suppressed.
- the reverse conical rectifying protrusion 390 is employed, but the shape of the rectifying protrusion 390 is not limited to the reverse conical shape. It only needs to have an outer peripheral shape capable of guiding the primary air-fuel mixture from the base end side to the terminal end side. That is, the cross-sectional area may be a shape that decreases from the base end side toward the terminal end side, and may be, for example, a partial spherical shape.
- reheating burner according to a third embodiment of the present invention.
- 7 to 10 show variations of the reheating burner 36 according to the third embodiment of the present invention.
- the structure of the reheating burner 36 of the present embodiment has a second air introduction part 393 for introducing the combustion air 200 into the premixing channel 367 on the downstream side of the first fuel introduction part 368. Except for this point, it is the same as the burn-up burner 36 according to the first embodiment described with reference to FIG.
- FIG. 7 shows a first example of a reheating burner according to the third embodiment of the present invention.
- the second air introduction part 393 of the first example is a gap formed between the first cylinder part 362 (first cylinder) and the second cylinder part 363 (second cylinder).
- the combustion air 200 flowing through the combustion air flow path 37 is divided into primary air 201 that flows in from the first air introduction part 370 and secondary air 202 that flows in from the second air introduction part 393. Distributed and introduced into the premix channel 367.
- the generation of a low speed region in the vicinity of the inner wall surface of the second cylindrical portion 363 is suppressed by the secondary air 202 that flows into the premixing channel 367 from the second air introduction portion 393. Thereby, the backfire which the combustion flame formed in the combustion chamber 33 transfers to the inner wall surface vicinity of the 2nd cylinder part 363 can be prevented.
- FIG. 8 shows a second example of the reheating burner according to the third embodiment of the present invention.
- the tracking burner 36 of the second example includes a second cylindrical portion 363A having a diameter larger than that of the first cylindrical portion 362, and an upstream end of the second cylindrical portion 363A and a downstream side of the first cylindrical portion 362.
- the side end portion is configured to overlap in the axial direction of the outer cylinder.
- the second air introduction portion 393 of the second example is an annular gap formed between the outer peripheral surface of the first cylindrical portion 362 and the inner peripheral surface of the second cylindrical portion 363A.
- the secondary air 202 introduced into the premixing flow path 367 from the second air introduction portion 393 is rectified by flowing through the annular gap from the upstream side to the downstream side, and the concentration of the secondary air mixture 700 is high. This is more effective than the first example because it flows in the vicinity of the inner wall surface of the cylindrical portion 363A.
- FIG. 9 shows a third example of the reheating burner according to the third embodiment of the present invention.
- the reheating burner 36 of the third example has a configuration for increasing the flow rate of the premixed gas 700 ejected to the combustion chamber 33 via the premixed flow path 367.
- the annular gap defined by the first cylinder part 362 and the second cylinder part 363 is gradually reduced in diameter toward the downstream side of the chasing burner 36.
- the inner peripheral surface 363B of the second air introduction portion 393 in the second cylindrical portion 363A is gradually reduced in diameter from the upstream side toward the downstream side.
- a tapered portion 394 having a gradually decreasing diameter from the upstream side toward the downstream side is formed on the outer peripheral surface of the downstream end portion of the first cylindrical portion 362 and facing the inner peripheral surface 363B.
- the inner diameter of the second cylindrical portion 363 may be substantially the same as the inner diameter of the first cylindrical portion 362 on the downstream side.
- the tracking burner 36 of the third example is the same as the tracking burner 36 of the second example shown in FIG. 8 except that it has the above-described configuration. The description is omitted.
- the reheating burner 36 of the third example having the above-described configuration has the following operational effects.
- a part of the compressed air 200 is blown to the outer periphery of the first cylindrical portion 362 and then introduced into the second air introduction portion 393 as the secondary air 202.
- the secondary air 202 is uniformly rectified by flowing through the second air introduction part 393 from the upstream side to the downstream side. Since the secondary air 202 is sent into the premixing flow path 367, the retention of the air-fuel mixture in the boundary layer can be more effectively suppressed.
- the secondary air 202 flows into the center of the flow path (second cylinder) through the premixed air 700 that stays in the boundary layer by flowing through an annular gap (tapered portion 394) that gradually decreases in diameter from the upstream side toward the downstream side. It is possible to create a flow that is guided toward the inner side in the radial direction of the portion 363A.
- the inner diameter of the second cylinder portion 363 is substantially the same as the inner diameter of the first cylinder portion 362 on the downstream side, the flow rate of the premixed gas 700 flowing through the premixing channel 367 is balanced. be able to.
- FIG. 10 shows a fourth example of the reheating burner according to the third embodiment of the present invention.
- the tracking burner 36 of the fourth example includes a second cylindrical portion 363A having a diameter larger than that of the first cylindrical portion 362, and an upstream end portion of the second cylindrical portion 363A is the flange of the first cylindrical portion 362.
- the structure is fixed to the portion 365.
- the 2nd air introduction part 393 of the 3rd example is a plurality of inflow ports formed in the peripheral wall part of the 2nd cylinder part 363A.
- the chasing burner 36 of the fourth example can also achieve the same effect as the second example.
- the ratio of the primary air 201 flowing in from the first air introduction part 370 and the secondary air 202 flowing in from the second air introduction part 393 is normally However, it is sufficient to increase the ratio of the primary air 201 if the reduction of NOx is considered, and to increase the ratio of the secondary air 202 if the prevention of flashback is considered. It has been confirmed in.
- FIG. 11 shows a reheating burner 36 according to a fourth embodiment of the present invention.
- the tracking burner 36 according to the present embodiment is different from the tracking burner 36 according to the first embodiment described in FIG. 3 in that the first cylindrical portion 362 is equally spaced in the circumferential direction.
- the first fuel introduction part 368 is configured so as to inject natural gas from the plurality of first fuel injection holes 395 arranged in the above, and the same rectifying projection part as in the second embodiment on the downstream side wall surface of the head block 361 390 is formed, and the second fuel supply path 383 is formed along the axis 360.
- the first fuel introduction portion 368 includes a cylindrical passage portion 396 formed on the upstream side of the head block 361 and a first annular passage portion 397 formed on the downstream side of the head block 361.
- a branch passage portion 398 formed downstream of the first annular passage 397 and extending from the downstream side of the head block 361 through the connecting piece 366 to the first tubular portion 362, and a first tubular portion 362
- the second annular passage portion 399 is formed in the flange portion 365 and the branch passages 398 join each other.
- the first annular passage portion 397 is disposed concentrically with the outer cylinder 364 so as to surround the second fuel supply passage 383.
- the branch passage portion 398 has two branch passages and is configured to pass through two connecting pieces 366 that face each other in the circumferential direction.
- the second annular passage portion 399 is disposed concentrically with the outer cylinder 364. As shown in the drawing, a plurality of first fuel injection holes 395 are formed at equal intervals in the circumferential direction on the inner surface of the first cylindrical portion 362. Each first fuel injection hole 395 extends radially outward and communicates with the second annular passage portion 399.
- the second fuel supply path 383 extends from the upstream side to the downstream side along the axis 360, and the upstream side is connected to the second fuel supply source via a 308 pipe having a flow control valve, and is downstream.
- the second fuel injection nozzle 384 is connected to the side via a header portion 385A.
- the reheating burner 36 according to the present embodiment employs a configuration in which the secondary air 202 described in the first to fourth examples of the reheating burner 36 according to the third embodiment is introduced into the premixing channel 367. It is also possible.
- the lean premixed gas 700 having a uniform concentration distribution is injected into the secondary combustion region S2 downstream of the primary combustion region S1 of the combustion chamber 33, and NOx in the combustion exhaust gas can be suppressed.
Abstract
Description
ガスタービンの概略構成と機能を図1に示す。このガスタービン1において、圧縮機2は大気を吸引して圧縮空気200を生成する。圧縮空気200は燃焼器3で燃料と共に燃焼され、高温高圧の燃焼生成ガス(以下、「燃焼排ガス300」と称する。)を生成する。燃焼排ガス300はタービン4に供給され、ロータ5の回転に利用される。ロータ5の回転は圧縮機2に伝達され、圧縮空気200(以下、「燃焼用空気200」と称する。)の生成に利用される一方、ロータ5の回転は例えば発電機6に伝達されて発電に利用される。
次に、本発明の第2実施形態に係る追焚きバーナについて説明する。図6は、本発明の第2実施形態に係る追焚きバーナ36を示す。なお、本実施の形態の追焚きバーナ36の基本構造は、図3で説明した実施の形態1に係る追焚きバーナ36と同じであるので、同一構成部分には同一符号を付して説明を省略する。
次に、本発明の第3実施形態に係る追焚きバーナについて説明する。図7~図10は、本発明の第3実施形態に係る追焚きバーナ36のバリエーションを示す。なお、本実施の形態の追焚きバーナ36の構造は、第1燃料導入部368よりも下流側において予混合流路367内に燃焼用空気200を導入するための第2空気導入部393を有する点を除いて図3で説明した実施の形態1に係る追焚きバーナ36と同じであるので、同一構成部分には同一符号を付して説明を省略する。
次に、本発明の第4実施形態に係る追焚きバーナについて説明する。図11は、本発明の第4実施形態に係る追焚きバーナ36を示す。なお、本実施の形態の追焚きバーナ36において、図3で説明した実施の形態1、及び図6で説明した実施の形態2に係る追焚きバーナ36と同一構成部分には同一符号を付して説明を省略する。
2 圧縮機
3 燃焼器
4 タービン
5 ロータ
6 発電機
31 メインバーナ
32 パイロットバーナ
33 燃焼室
34 燃焼筒
36 追焚きバーナ(燃料噴射装置)
37 燃焼用空気流路(空気流路)
200 圧縮空気(燃焼用空気)
300 燃焼排ガス
360 軸心
361 頭部ブロック
362 第1の筒部
363 第2の筒部
364 外筒
366 連結片
367 予混合流路
368 第1燃料導入部
369 第2燃料導入部
370 第1空気導入部
380 第1燃料供給路
381 第1燃料噴射ノズル
382 第1燃料噴射孔
383 第2燃料供給路
384 第2燃料噴射ノズル
390 整流突起部
393 第2空気導入部
700 予混合気
Claims (9)
- 上流側から予混合流路に導入した燃焼用空気と燃料を前記予混合流路内で混合して予混合気を生成し、前記予混合気を下流側から燃焼室に噴射して燃焼させるバーナであって、
内部に前記予混合流路が形成される外筒と、前記予混合流路の上流側において前記外筒の外縁から中心に向けて燃焼用空気を供給する第1空気導入部と、
第1燃料を前記予混合流路に導入する第1燃料導入部と、
前記第1燃料より比重が小さい第2燃料を前記予混合流路に導入する第2燃料導入部を備え、
前記第2燃料導入部は、前記予混合流路の上流側端部から下流側に向けて前記予混合流路内に突出して形成され、
前記第1空気導入部から導入された圧縮空気に第2燃料を噴射する複数の第2燃料噴射ノズルを有し、
前記燃焼用空気に対して前記第2燃料噴射ノズルから前記第2燃料が噴射されて1次混合気が生成され、
前記1次混合気に対して前記第1燃料導入部から前記第1燃料が導入されて2次混合気が生成されることを特徴とするバーナ。 - 前記第1燃料導入部は、前記予混合流路の上流側端部から前記外筒と同心状に前記予混合流路内に突出し、前記外筒の外縁に向けて前記第1燃料を噴射する第1燃料噴射ノズルを有する請求項1に記載のバーナ。
- 前記予混合流路の上流側端部から前記外筒と同心状に前記予混合流路内に突出する整流突起部を備え、
前記第1燃料導入部は、前記予混合流路の上流側端部であって前記整流突起部よりも外縁側に形成され、
前記予混合流路の外縁側に傾斜した方向に前記第1燃料を噴射する複数の第1燃料噴射孔を有する請求項1に記載のバーナ。 - 前記予混合流路の上流側端部から前記外筒と同心状に前記予混合流路内に突出する整流突起部を備え、
前記第1燃料導入部は、前記第1空気導入部よりも下流側において、前記外筒の外縁から中心に向けて第1燃料を噴射する複数の第1燃料噴射ノズルを備える請求項1に記載のバーナ。 - 前記外筒の外縁から前記予混合流路に空気を導入する第2空気導入部を前記第1空気導入部よりも下流側に備える請求項1から請求項4のいずれか1項に記載のバーナ。
- 前記外筒は、それぞれ同軸上に配置された上流側の第1の筒体、及び下流側の第2の筒体で構成され、
前記第1の筒体と前記第2の筒体は、前記軸の方向に一部オーバーラップして配置されており、
前記第2空気導入部は、前記第1の筒体と前記第2の筒体により区画されていると共に、上流側から下流側に向かって漸次縮径する環状の隙間である請求項5に記載のバーナ。 - 前記第1燃料は、天然ガス又は液化天然ガスであり、前記第2燃料は、水素ガス又は水素含有ガスである請求項1から請求項6のいずれか1項に記載のバーナ。
- 燃料を燃焼させる燃焼室を形成する燃焼筒と、前記燃焼筒の上流側に配置された予混合式のメインバーナと、
前記燃焼筒の下流側の周壁部を貫通して配置された追焚きバーナとを備えるガスタービンの燃焼器であって、
前記追焚きバーナは、請求項1から請求項7のいずれか1項に記載のバーナであることを特徴とするガスタービンの燃焼器。 - 請求項8に記載の燃焼器を備えることを特徴とするガスタービン。
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US15/539,314 US10837641B2 (en) | 2014-12-25 | 2015-12-25 | Burner, combustor, and gas turbine |
CN201580070785.2A CN107110506B (zh) | 2014-12-25 | 2015-12-25 | 烧嘴、燃烧器以及燃气轮机 |
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20210098795A (ko) * | 2020-02-03 | 2021-08-11 | 에이치에스디엔진 주식회사 | 버너장치 및 이를 포함하는 선박 |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016032436A1 (en) * | 2014-08-26 | 2016-03-03 | Siemens Energy, Inc. | Cooling system for fuel nozzles within combustor in a turbine engine |
US10234142B2 (en) * | 2016-04-15 | 2019-03-19 | Solar Turbines Incorporated | Fuel delivery methods in combustion engine using wide range of gaseous fuels |
US10386074B2 (en) * | 2016-12-09 | 2019-08-20 | Solar Turbines Incorporated | Injector head with a resonator for a gas turbine engine |
JP7298095B2 (ja) * | 2020-06-09 | 2023-06-27 | 株式会社三井E&S | ガスタービンの予混合管構造 |
CN112066371B (zh) * | 2020-09-02 | 2021-06-22 | 西安交通大学 | 一种基于值班火焰的氢气预混低氮燃烧器 |
US11692488B2 (en) | 2020-11-04 | 2023-07-04 | Delavan Inc. | Torch igniter cooling system |
US11608783B2 (en) | 2020-11-04 | 2023-03-21 | Delavan, Inc. | Surface igniter cooling system |
US11473505B2 (en) | 2020-11-04 | 2022-10-18 | Delavan Inc. | Torch igniter cooling system |
US11635027B2 (en) * | 2020-11-18 | 2023-04-25 | Collins Engine Nozzles, Inc. | Fuel systems for torch ignition devices |
US11421602B2 (en) | 2020-12-16 | 2022-08-23 | Delavan Inc. | Continuous ignition device exhaust manifold |
US11635210B2 (en) | 2020-12-17 | 2023-04-25 | Collins Engine Nozzles, Inc. | Conformal and flexible woven heat shields for gas turbine engine components |
US11754289B2 (en) | 2020-12-17 | 2023-09-12 | Delavan, Inc. | Axially oriented internally mounted continuous ignition device: removable nozzle |
US11486309B2 (en) | 2020-12-17 | 2022-11-01 | Delavan Inc. | Axially oriented internally mounted continuous ignition device: removable hot surface igniter |
US11680528B2 (en) | 2020-12-18 | 2023-06-20 | Delavan Inc. | Internally-mounted torch igniters with removable igniter heads |
US11209164B1 (en) | 2020-12-18 | 2021-12-28 | Delavan Inc. | Fuel injector systems for torch igniters |
US11846426B2 (en) | 2021-06-24 | 2023-12-19 | General Electric Company | Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel |
CN117795253A (zh) * | 2021-08-02 | 2024-03-29 | 西门子能源全球有限两合公司 | 燃气涡轮发动机中的燃烧室 |
CN113623653B (zh) * | 2021-08-12 | 2022-07-26 | 清华大学 | 气氛可调的轴切多级旋流掺氨燃烧器 |
US11578871B1 (en) | 2022-01-28 | 2023-02-14 | General Electric Company | Gas turbine engine combustor with primary and secondary fuel injectors |
US11885498B2 (en) | 2022-01-31 | 2024-01-30 | General Electric Company | Turbine engine with fuel system including a catalytic reformer |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008522123A (ja) * | 2004-11-30 | 2008-06-26 | アルストム テクノロジー リミテッド | 予混合バーナー内の水素を燃焼する方法及び装置 |
JP2008185247A (ja) * | 2007-01-29 | 2008-08-14 | Nippon Paint Co Ltd | 溶剤の燃焼処理装置 |
JP2011075174A (ja) * | 2009-09-30 | 2011-04-14 | Hitachi Ltd | 水素含有燃料対応燃焼器および、その低NOx運転方法 |
JP2013227885A (ja) * | 2012-04-24 | 2013-11-07 | Niigata Power Systems Co Ltd | ガスタービン燃焼器 |
JP2013231580A (ja) * | 2012-04-27 | 2013-11-14 | General Electric Co <Ge> | 燃焼器への燃料供給システム |
JP2013234769A (ja) * | 2012-05-07 | 2013-11-21 | Hitachi Ltd | ガスタービン燃焼器およびガスタービンの運転方法 |
WO2014092185A1 (ja) * | 2012-12-13 | 2014-06-19 | 川崎重工業株式会社 | マルチ燃料対応のガスタービン燃焼器 |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3712947B2 (ja) * | 2001-03-02 | 2005-11-02 | 川崎重工業株式会社 | ガスタービンエンジン用の液体燃料焚き低nox燃焼器 |
JP2005241178A (ja) * | 2004-02-27 | 2005-09-08 | Kawasaki Heavy Ind Ltd | ガスタービンの燃焼器 |
EP1645805A1 (de) * | 2004-10-11 | 2006-04-12 | Siemens Aktiengesellschaft | Brenner für fluidische Brennstoffe und Verfahren zum Betreiben eines derartigen Brenners |
US8511097B2 (en) * | 2005-03-18 | 2013-08-20 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine combustor and ignition method of igniting fuel mixture in the same |
JP4421620B2 (ja) * | 2007-02-15 | 2010-02-24 | 川崎重工業株式会社 | ガスタービンエンジンの燃焼器 |
JP4364911B2 (ja) * | 2007-02-15 | 2009-11-18 | 川崎重工業株式会社 | ガスタービンエンジンの燃焼器 |
US8613187B2 (en) | 2009-10-23 | 2013-12-24 | General Electric Company | Fuel flexible combustor systems and methods |
JP5636335B2 (ja) | 2011-05-27 | 2014-12-03 | 新潟原動機株式会社 | ガスタービン燃焼器 |
JP5772245B2 (ja) * | 2011-06-03 | 2015-09-02 | 川崎重工業株式会社 | 燃料噴射装置 |
US9400113B2 (en) | 2014-06-12 | 2016-07-26 | Kawasaki Jukogyo Kabushiki Kaisha | Multifuel gas turbine combustor |
-
2015
- 2015-12-25 WO PCT/JP2015/086273 patent/WO2016104725A1/ja active Application Filing
- 2015-12-25 CN CN201580070785.2A patent/CN107110506B/zh active Active
- 2015-12-25 DE DE112015005803.6T patent/DE112015005803B4/de active Active
- 2015-12-25 US US15/539,314 patent/US10837641B2/en active Active
- 2015-12-25 JP JP2016566526A patent/JP6637905B2/ja active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008522123A (ja) * | 2004-11-30 | 2008-06-26 | アルストム テクノロジー リミテッド | 予混合バーナー内の水素を燃焼する方法及び装置 |
JP2008185247A (ja) * | 2007-01-29 | 2008-08-14 | Nippon Paint Co Ltd | 溶剤の燃焼処理装置 |
JP2011075174A (ja) * | 2009-09-30 | 2011-04-14 | Hitachi Ltd | 水素含有燃料対応燃焼器および、その低NOx運転方法 |
JP2013227885A (ja) * | 2012-04-24 | 2013-11-07 | Niigata Power Systems Co Ltd | ガスタービン燃焼器 |
JP2013231580A (ja) * | 2012-04-27 | 2013-11-14 | General Electric Co <Ge> | 燃焼器への燃料供給システム |
JP2013234769A (ja) * | 2012-05-07 | 2013-11-21 | Hitachi Ltd | ガスタービン燃焼器およびガスタービンの運転方法 |
WO2014092185A1 (ja) * | 2012-12-13 | 2014-06-19 | 川崎重工業株式会社 | マルチ燃料対応のガスタービン燃焼器 |
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US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
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DE112015005803T5 (de) | 2017-09-14 |
CN107110506B (zh) | 2019-09-06 |
DE112015005803B4 (de) | 2022-08-25 |
JPWO2016104725A1 (ja) | 2017-12-07 |
US10837641B2 (en) | 2020-11-17 |
JP6637905B2 (ja) | 2020-01-29 |
US20170356656A1 (en) | 2017-12-14 |
CN107110506A (zh) | 2017-08-29 |
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