CN104685298A - Method of operating a multi-stage flamesheet combustor - Google Patents
Method of operating a multi-stage flamesheet combustor Download PDFInfo
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- CN104685298A CN104685298A CN201380051446.0A CN201380051446A CN104685298A CN 104685298 A CN104685298 A CN 104685298A CN 201380051446 A CN201380051446 A CN 201380051446A CN 104685298 A CN104685298 A CN 104685298A
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Classifications
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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
- 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
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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
- 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
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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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
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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
- 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
- F05D2270/09—Purpose of the control system to cope with emergencies
- F05D2270/091—Purpose of the control system to cope with emergencies in particular sudden load loss
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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
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/331—Mechanical loads
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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
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/335—Output power or torque
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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
- F23R2900/03343—Pilot burners operating in premixed mode
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The present invention discloses a novel way of controlling a gas turbine engine to reduce emissions levels when demand for power from the gas turbine engine is reduced. The operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide are kept within acceptable levels.
Description
Technical field
The present invention relate generally to a kind of for operating combustion system to reduce the method for the discharge in gas turbine combustor.More specifically, the improvement of the fuel staging for burner is provided.
Background technology
In order to reduce the discharge amount of pollution of the turbine from gas energy supply, government organs have promulgated and have required to reduce nitrogen oxide (NO
x) and many regulations of amount of carbon monoxide (CO).Lower burning and exhausting is attributable to more effective combustion process usually, specifically about position and the mixing effectiveness of fuel injector.
Early stage combustion system uses the nozzle of the diffusion types of combustion zone nearside, and wherein fuel mixes by spreading with the air outside fuel nozzle.Keep enough combustor stability and low combustion powered because fuel and air at high temperature stoichiometrically burn, therefore the nozzle of diffusion types produces maximum discharge.
The enhancing of combustion technology is to use premix, and wherein fuel and air mix to form homogeneous mixture before combustion, and it burns at the temperature of the flame lower than expanding type, and produces lower NO
xdischarge.Premix can occur, as long as it is in the upstream of combustion zone in fuel nozzle or outside it.Fig. 1 shows the example of the premix burner of prior art.Burner 8 has multiple fuel nozzle 18, and it all injects fuel in premix chamber 19, and wherein, fuel mixed with the compressed air 6 from bin 10 before entering combustion chamber 20.The fuel of premix allow fuel and air to be formed together with air before combustion evenly mixture, it will burn more completely, causes comparatively low emission.But in this configuration, fuel sprays in the relatively identical plane of burner, and by changing any possibility that mixing length prevents from improving.
Premix realizes by multiple combustion stage compared with the alternative means of low emission, the premix strengthened when this allow that load increases.Referring now to Fig. 2, show the example of the multistage burner of prior art.Burner 30 has the first combustion chamber 31 and the second combustion chamber 32 separated by Venturi tube 33, and Venturi tube 33 has narrower throat region 34.Fuel come across in the first combustion chamber or the second combustion chamber or two rooms although can be depending on load condition, but when the fuel sprayed by nozzle region 35 is to mix completely with compressed air in the first combustion chamber 31 before burning in the second combustion chamber 32, minimum emission level occurs.Therefore, this multistage burner with Venturi tube is more effective under higher load state.
Need gas-turbine unit that lower operation is set at multiple power.When gas-turbine unit connect drive generator, the required output of engine is measured according to the load capacity on generator or the power that must be produced by generator usually.Full load state is the point that maximum output is extracted from generator, and therefore needs peak power from engine to drive generator.This is the modal operating point of the continental rise gas turbine for generating electricity.But usual electric demand does not need the full capacity of generator, and operator expects that engine arranges lower operation in lower load, makes only to produce loading demand, thus fuel saving and reduction running cost.The combustion system of prior art, it is known that become unstable under lower load is arranged, especially under the load of 50%, also creates NO simultaneously
xwith the unacceptable level of CO discharge.This mainly due to most of combustion system high capacity is arranged under most valid function classification.The burning of potentially unstable and the combination of higher emissions prevent engine operators from arranging lower operation engine in lower load usually; force engine that lower operation is set higher; thus burn additional fuel or shutdown, and thus lose the valuable income that can be generated by fractional load demand.
The problem that engine is shut down is the additional cycles caused by engine hardware.Circulation is defined through the engine of normal operation range usually.Therefore, by making engine shut down, engine hardware accumulation additional cycles.Manufacturers of engines typically assesses hardware longevity according to hours run or equivalent operation cycle.Therefore, the additional cycles caused can shorten hardware longevity, and needs engine operators to spend premature repairs or replacement.Required is a kind of system; it can provide flame holding and low emission benefit under part-load condition and full load state; make engine can valid function under lower load condition; thus the spent fuel eliminated when not needing high capacity to operate, or cause the additional cycles in engine hardware when shutting down.
Summary of the invention
The invention discloses a kind of method of operating gas turbine engine, and more specifically, to improve the method for the mode operating gas turbine burner of the downward efficiency of engine.In an embodiment of the present invention, a kind of method of operating burner comprises the fuel supplying fuel to and guide nozzle, light bootstrap nozzle, and additional fuel is supplied to the level of guide adjustment injector.The method also disclose supply fuel to burner main fuel injector Part I, light this fuel to form main combustion flame, to supply fuel to the Part II of burner main fuel injector, and light this fuel to support main combustion flame.
In alternative of the present invention, provide a kind of Computerized method for the fuel in classification gas turbine combustor.This method provide a kind of mode by four different operation modes operations with the burner guiding nozzle, one group of guide adjustment injector and one group of main fuel injector.Additional flow in fuel is added into burner by each continuous mode of operation.
In yet another embodiment of the present invention, a kind of method that downward ability improving gas turbine combustor controls carbon monoxide generation is simultaneously disclosed.The method is adjusted to the Part I of the annular array of fuel injector and the flow in fuel of Part II, and be adjusted to the flow in fuel of one or more injector in the core section of gas turbine combustor, its SMIS section comprises and guides nozzle and guide one group of injector of nozzle for regulating.The adjustment of these fuel circuits is allowed and the overall minimizing of flow in fuel to support downward ability, is remained on operation in acceptable emission limit simultaneously.
In another embodiment of the present invention, a kind of method of operating burner comprises the level supplying fuel to and guide fuel nozzle and guide adjustment injector.By the ignited fuel that these loops are sprayed, and then additional fuel adds via the Part I of main fuel injector, and it lights to generate main combustion flame.Then, fuel is supplied to the Part II of main fuel injector, and this additional fuel is then lighted to support main combustion flame further.
In additional embodiment of the present invention, a kind of method of operating burner comprises and supplies fuel to guiding nozzle, and lights this fuel to form pilot flame.Additional fuel is added into burner by the Part I supplying fuel to main fuel injector.The ignited fuel added via the Part I of main ejector forms main combustion flame.Then, fuel is supplied to the Part II of main fuel injector, and lights to support main combustion flame further.
Attendant advantages of the present invention and feature will be partly articulated in the following description, and partly become apparent when those skilled in the art being consulted hereafter, or can from learning by doing of the present invention.Present general is concrete with reference to the accompanying drawings to describe the present invention.
Accompanying drawing explanation
The present invention is described in detail below with reference to accompanying drawing, in the figure:
Fig. 1 is the cross section of the gas turbine combustor of prior art.
Fig. 2 is the cross section of the alternative burner of prior art.
Fig. 3 is the cross section of gas turbine combustor according to an embodiment of the invention.
Fig. 4 is the end-view of the gas turbine combustor of Fig. 1 according to an embodiment of the invention.
Fig. 5 is the flow chart drawing the process controlling gas turbine combustor according to an embodiment of the invention.
Fig. 6 A is the cross sectional view of the gas turbine combustor operated in a first mode according to an embodiment of the invention.
Fig. 6 B is the cross sectional view of the gas turbine combustor operated in a second mode according to an embodiment of the invention.
Fig. 6 C is the cross sectional view of the gas turbine combustor operated in the 3rd pattern according to an embodiment of the invention.
Fig. 6 D is the cross sectional view of the gas turbine combustor operated in four-mode according to an embodiment of the invention.
Fig. 6 E is the cross sectional view of the gas turbine combustor operated in the adjustment version of the four-mode of Fig. 6 D according to an embodiment of the invention.
Fig. 7 A is the end-view of the gas turbine combustor operated in a first mode according to an embodiment of the invention.
Fig. 7 B is the end-view of the gas turbine combustor operated in a second mode according to an embodiment of the invention.
Fig. 7 C is the end-view of the gas turbine combustor operated in the 3rd pattern according to an embodiment of the invention.
Fig. 7 D is the end-view of the gas turbine combustor operated in four-mode according to an embodiment of the invention.
Fig. 8 is the flow chart of the process of the control gas turbine combustor drawn according to alternative of the present invention.
Fig. 9 is the flow chart of the process of the control gas turbine combustor drawn according to still another embodiment of the invention.
Detailed description of the invention
By referring to, the application is incorporated with U.S. Patent No. 6, and 935,116,6,986,254,7,137,256,7,237,384,7,308,793,7,513,115 and 7, the theme of 677,025.
The invention discloses and a kind ofly operate combustion system to improve the mode of the downward ability of gas-turbine unit.That is, The embodiment provides disclosed in for lower and therefore need to improve when exporting from engine less the means of the combustion stability in gas turbine combustor at the power demand carrying out self generator.
The present invention is discussed now with reference to Fig. 3-9.The embodiment of the gas turbine combustor of the method for operating can applying improvement of the present invention is depicted in Fig. 3.Combustion system 300 extends around longitudinal axis A-A, and comprises flow sleeve 302, for being guided by the outer surface of the compressed air of scheduled volume along combustion liner 304.Main fuel injector 306 is positioned at the radial outside of combustion liner 304, and is designed to provide a part for the outer surface of fuel supply entering the forward position combustion liner 304 in combustion liner 304 to mix with compressed air.The fuel sprayed by main fuel injector 306 mixes with compressed air, and advances in the inlet region along forward direction towards combustion liner 304, wherein, and fuel/air mixture then reverses direction and entering in combustion liner 304.For provide and keep combustion system pilot flame guiding fuel nozzle 308 substantially longitudinally A-A extend.Pilot flame is for lighting, supporting and keep multiple levels of the fuel injector of combustion system 300.
Combustion system 300 also comprises the premixed device 310 of radially classification.Premixed device 310 comprises the first fuel bin 314 having the longitudinal axis A-A around combustion system 300 and extend, and is positioned at the first fuel bin 314 radial outside and the second fuel bin 316 concentric with the first fuel bin 314.Radially the premixed device 310 of classification also comprises the radial direction had along multiple stators 320 of a direction orientation and to become a mandarin cyclone 318, and this direction is at least in part perpendicular to the longitudinal axis A-A of combustion system 300.
Guiding fuel nozzle 308 to be connected to fuel supply source (not shown), and providing fuel to combustion system 300 for supplying pilot flame 350, wherein, pilot flame 350 longitudinally A-A location substantially.Comprise fuel bin 314 and 316, radial direction becomes a mandarin cyclone 318 and the premixed device 310 of the radially classification of its multiple stator 320 provides fuel air mixture through stator 320, for regulating 352 to be supplied to pilot flame 350 via guide adjustment level or P additional fuel.
As described above, combustion system 300 also comprises main fuel injector 306.For the embodiments of the invention shown in Fig. 3, main fuel injector 306 is positioned at the radial outside of combustion liner 304, and scatters with the annular array around combustion liner 304.Main fuel injector 306 can comprise one or more part and level, they around the circumference of main fuel level equal or not etc. ground extend.As the example of described application of the present invention, main fuel injector divide into two levels, Part I and Part II.Part I extends about 120 degree, and Part II extends approximately remaining 240 degree of spans.As shown in Figure 4, the Part I of main fuel injector 306 generates main 1 flame 354, and the Part II of main fuel injector 306 generates main 2 flames 356.
With reference to Fig. 4, depict the rearview of the gas turbine combustor of forward-looking Fig. 3.Fig. 4 clearly demonstrates each radial direction in the flame location in combustion system 300 and circumferential position, wherein pilot flame 350 is in center, guide adjustment level 352 is positioned at the radial outside of pilot flame 350, and main 1 flame 354 and main 2 flames 356 are positioned at the radial outside of guide adjustment level 352.
As described above, gas-turbine unit combines multiple burner.Substantially, in order to the object discussed, gas-turbine unit can comprise low emission combustor, as disclosed herein those, and the cylinder circular structure around gas-turbine unit can be arranged to.The gas-turbine unit (such as, heavily loaded gas-turbine unit) of one type typically can be provided with but be not limited to 6 to 18 independently burners, and each in burner is combined with the component of above-outlined.Therefore, based on the type of gas-turbine unit, the some different fuel circuit for operating gas turbine engine can be there is.For embodiments of the invention, there are four fuel circuits used.But envision, special fuel loop and the controlling organization be associated can be revised to comprise less or additional fuel loop.
Discuss the physical layout of the combustion system 300 of the present invention's operation, describe the method for operating for this combustion system in detail now with reference to Fig. 5-9.Present invention uses four fuel-grade to come for regulating and operating flexibility.More specifically, with reference to Fig. 5, outline the method 500 of the operation combustion system 300 of Fig. 3, which use four different fuel levels to improve combustion stability, to allow to arrange lower operation in lower load.At first in step 502, fuel is supplied to the guiding fuel nozzle of gas turbine combustor.Then, in step 504, the ignited fuel of bootstrap fuel nozzle is carried out to form pilot flame.This is lighted and occurs by various ignition source, occurs as spark lighter or torch ignitor.When guiding fuel nozzle to locate along the longitudinal axis of burner substantially, the pilot flame of gained is also longitudinally located substantially.Supply fuel to and guide fuel nozzle and fire fuel to be recognized as the operator scheme 1 of combustion system to these steps forming pilot flame, and with operation in the opereating specification guiding the igniting of fuel nozzle or " stopping working " to start, and continue across " at full speed zero load " or " FSNL " state.As described above, FSNL is engine operation state, and wherein turbine and compressor operate under design maximum rotating speed, and its engine for 60Hz is about 3600 rpms, but zero load is applied by generator.The description that the pattern 1 of combustion system operates has been shown in Fig. 6 A and Fig. 7 A.
As understood by a person skilled in the art, flame comprises shear layer inherently.Generally speaking, shear layer or boundary layer are the flow region that wherein can there is remarkable velocity gradient.The shear layer of flame is the shared region between the outermost edge of flame and non-combustible environment or adjacent flame.
From one group of main fuel injector fuel light can due to the fuel/air mixture that controls the shear layer of pilot flame than ability and easier and reliably occur.More specifically, increase fuel supply by the outermost radial position place local in premix path, the fuel concentration in the shear layer of the pilot flame of gained increases.As a result, the shear layer of enrichment allows main ejector more easily and reliably lights, and does not need many energy, and this then causes comparatively low pulse level in the period of lighting of main fuel injector.
The additional benefits that can be enriched to the flow in fuel of shear layer is partly the ability keeping the stabilization process of lighting the fuel sprayed by main ejector.That is, in premix combustion systems, flow in fuel level remains poor as far as possible traditionally, to reduce discharge.By fuel being added into shear layer partly during select time section, the mixture of more fuel-rich material is formed, thus increases the fuel/air mixture ratio in shear layer district.The mixture of more fuel-rich material provides more favourable condition for generation of lighting a fire, and improves flame holding.Once light flame, then fuel enrichment level can be decreased to poorer mixture, and does not endanger the stability of flame.
In step 506, fuel continues to be supplied to guiding fuel nozzle, as in step 502, is also supplied to one group of guide adjustment level injector simultaneously.Guide adjustment level injector is arranged in radial direction and becomes a mandarin multiple stators 320 of cyclone 318, and it is positioned at the radial outside guiding fuel nozzle 308, and is sprayed to mix with ambient air stream from the fuel bin of end cap by fuel.This fuel air mixture then along pilot flame process, and for strengthening and supporting pilot flame, and the shear layer of enrichment pilot flame.The operation of fuel nozzle together with one group of guide adjustment level injector is guided to be recognized as the pattern 2 of the operation of combustion system.Pattern 2 can from quenching operations until the load of about 10%.The description that the pattern 2 of combustion system operates being shown in Fig. 6 B and Fig. 7 B, wherein having shown for surrounding pilot flame at pilot flame radial outside from the fuel/air mixture of guide adjustment level.
Next, in step 508, combustion system enters the mode 3 of operation, and wherein fuel is supplied to the Part I of main fuel injector, is also still supplied to simultaneously and guides fuel nozzle and one group of guide adjustment level injector.As described above, the main fuel injector 306 of combustion system is arranged to the annular array around combustion liner, and be divided into two parts, extend the Part I of about 120 degree around combustion liner 304, and extend the Part II of about 240 degree around combustion liner 304.In step 510, the ignited fuel sprayed by the Part I of main fuel injector in step 508 forms main combustion flame.The lighting due to the pilot flame of the formation by pattern 1 and 2 and occur of main combustion flame.But, in order to light this main combustion flame, combustion system rises to this point typically via fuel being added into guide adjustment level (at the end of pattern 2) to delay, wherein when being transferred to mode 3, the fuel added via guide adjustment level is then transferred to the Part I of main fuel injector.Which ensure that Dietary behavior 3 effectively and quietly shift.Fuel can be supplied to the Part I of main ejector with flame-out beginning and through the load condition of about 10%.The description of the mode 3 operation of combustion system has been shown in Fig. 6 C and Fig. 7 C, and the main combustion flame wherein formed in mode 3 is positioned at the radial outside of the fuel air mixture of the guide adjustment level from injector.
In step 512, combustion system operates in pattern 4, and wherein fuel is supplied to the Part I of the Part II of main fuel injector and main fuel injector, guides the guide adjustment level of fuel nozzle and injector.Therefore, in the pattern 4 of operation, fuel flows through all four loops of combustion system, and flow to now all main fuel injector.As a result, 360 degree of rings of fuel from main fuel injector be ejected into through air stream, and at the radial outside of combustion liner.In the step 514, the main combustion flame that the fuel sprayed by the Part II of main fuel injector is formed due to the fuel sprayed by the Part I from main fuel injector and lighting.This is that pattern 4 operates.Fuel can begin to pass the Part II of about 25% load condition injection through main fuel injector with flame-out.Fuel continues to flow through the load condition in these loops to about 100%, or it is also called basic load state.Operation in pattern 4 provides the wide and stable mode of operation of combustion system.The description that the pattern 4 of combustion system operates has been shown in Fig. 6 D and Fig. 7 D, and wherein main combustion flame is sprayed by the fuel in pattern 4 and strengthens, and around pilot flame circumferentially.
Once combustion system reaches basic load or 100% load condition, wherein fuel flows through all four loops, then likely be adjusted to one or more the flow in fuel in the loop of the core supplying fuel to burner, namely, the guiding fuel nozzle stream 360 regulated and/or the adjustment stream 362 to guide adjustment level, as is shown in figure 6e.When the lower load of needs, it is desirable for reducing fuel quantity.But traditionally, when flow in fuel level reduces, flame temperature is tending towards reducing, and the correspondence which results in CO discharge raises.Such as, refer back to Fig. 5, in step 516, can tune to the flow in fuel of core inlet zone, that is, guide fuel nozzle and/or guide adjustment level injector.But, by the flow in fuel of the Part I and Part II that are retained to main fuel injector, be adjusted to the flow in fuel of the guide adjustment level guiding fuel nozzle and/or injector simultaneously, as in Fig. 6 E paint, main combustion flame remains in whole ring, and is in the temperature hotter than pilot flame.Therefore, hotter main combustion flame will consume the CO generated by colder pilot flame.This adjustment of pattern 4 is drawn in Fig. 6 E, and occurs during the normal premixed operation of combustion system.
As skilled in the art will appreciate, when the power reduction needed for engine or lower timing, desirable is effectively reduce engine to export, and still keeps the operation of engine simultaneously.When engine needs less power, need less fuel in combustion.Therefore, in order to lower engine, flow in fuel also must reduce.But as described above, when flow in fuel level reduces, flame temperature is tending towards reducing, and this causes CO to discharge rising.Therefore required is burn this additional CO fully, to be remained in emissions adjustment by engine.A kind of mode of burning CO discharge is that the main combustion flame by Part I and the Part II by main fuel injector generates remains hot as far as possible.This careful adjustment by the flow in fuel to fuel injector realizes.More specifically, the flow in fuel to core district (guiding fuel nozzle and/or guide adjustment level injector) reduces, and slightly increases to the Part I of main injector and the flow in fuel of Part II.When reduce to the flow in fuel of boot section or at the end of, clean whole structure is the lower total fuel flow rate to burner, but higher than to guide and/or the fuel ratio of guide adjustment level guides into the main flame of support.
Although discuss supply flow in fuel and the step of lighting burner oil in order, it will be appreciated by those skilled in the art that flow in fuel must continue or the flame of gained will extinguish in order to keep the flame caused by the igniting of the fuel just sprayed.Therefore, required is that the step of fuel supply/injection occurs before ignited fuel or simultaneously.
In alternative of the present invention, combustion system 300 comprises for fuel being provided to two loops guiding fuel nozzle, one group of guide adjustment injector and extremely lead 1 and main 2 flames, defines four main fuel loops of main combustion flame as described above.But, determine that combustion noise and discharge improvement can use this hardware implementing, and at first fuel is not only guided to guiding fuel nozzle, but change into guiding fuel nozzle and one group of guide adjustment level injector to realize for fuel initial flame-out.
With reference to Fig. 8, in process 800, disclose the alternative procedure for operating gas turbine burner.In step 802, fuel is supplied to guiding fuel nozzle and one group of guide adjustment level injector of gas turbine combustor at first.Then, in step 804, lighted by the fuel guiding fuel nozzle and guide adjustment level injector to spray.Once flame is formed in boot section, then to guiding the level of fuel nozzle and guide adjustment injector to continue across the load condition of about 10% for fuel.Then, in step 806, fuel is supplied to the Part I of one group of main fuel injector.As described above, the Part I of one group of main fuel injector is made up of about 120 degree of curved section of fuel injector.Fuel continues to flow to guiding fuel nozzle and guide adjustment level, and fuel is supplied to the Part I of one group of main fuel injector simultaneously.In step 808, the ignited fuel sprayed by the Part I of one group of main fuel injector forms main combustion flame.The fuel sprayed by the Part I of main fuel injector early can begin to pass about 10% load condition as flame-out.Once form main combustion flame, then in step 810, fuel is then supplied to the Part II of one group of main fuel injector, continues the Part I of supply fuel to one group main burner simultaneously, guides fuel nozzle and guide adjustment level injector.Fuel can be supplied to the Part II of main fuel injector with flame-out beginning and about 25% load condition.Then, in step 812, the ignited fuel sprayed by the Part II of one group of main fuel injector is to strengthen main combustion flame.Another embodiment as described above, in step 814, the flow in fuel to guide adjustment level injector and guiding fuel nozzle is then adjustable to improve flame holding.
In yet another embodiment of the present invention, develop a kind of method of operating gas turbine burner, wherein as mentioned before, fuel is supplied to three loops, and is not supplied to the guide adjustment level of injector.Referring now to Fig. 9, the method 900 of operating gas turbine burner comprises the step 902 of the guiding fuel nozzle supplying fuel to gas turbine combustor.Then, in step 904, pilot flame is formed by the ignited fuel guiding fuel nozzle to spray.In step 906, fuel is supplied to the Part I of one group of main fuel injector, continues to guiding fuel nozzle supply fuel simultaneously.Fuel can be supplied to the Part I of main fuel injector with flame-out beginning and about 10% load condition.Then, in step 908, the ignited fuel from the Part I of main ejector forms main combustion flame.
In step 910, fuel is supplied to the Part II of one group of main fuel injector, is also supplied to the Part I of main fuel injector simultaneously and guides fuel nozzle.Fuel can at the Part II to be supplied to main ejector between flame-out beginning and about 25% load condition.In this type of embodiment of the present invention, the Part I of main ejector extends around about 120 degree with curved path, and the Part II of main ejector extends with the curved path of about 240 degree.In step 912, by the Part II of main ejector be supplied to burner ignited fuel and for strengthening main combustion flame.As described above, fuel continue to flow through these various loops until about 100% load.Depend on the mode of operation of engine, process can continue in step 914, is wherein adjustable to the flow in fuel guiding nozzle.As described above, this adjustment can comprise the amount being reduced to the flow in fuel guiding fuel nozzle, to support that engine is lowered, control CO discharges simultaneously.
As skilled in the art will recognize, the present invention can especially be presented as method, system or computer program.Therefore, embodiment can take the form of the embodiment of hardware embodiment, software implementation or integration software and hardware.In one embodiment, the present invention takes the form of Computerized method, e.g., computer program, it comprise be embodied in computer on one or more computer-readable medium can instruction.
Computer-readable medium comprises volatibility and non-volatile media, can remove and non-removable medium, and envisions the medium that can be read by database, switch and other network equipment various.As the means communicated with, network switching, router and associated components are conventional in nature.For example and do not limit, computer-readable medium comprises computer storage media and communication media.
Computer storage media or computer-readable medium are included in the medium for implementing in any method of storing information or technology.The example of storing information comprise computer can instruction, data structure, program module and other data representation.Computer storage media includes but not limited to RAM, ROM, EEPROM, flash memory or other memory technology, CD-ROM, digital versatile disks (DVD), holographic media or other disc storage, cassette, tape, disc storage and other magnetic storage device.These memory means can momentarily, temporarily or for good and all storage data.
Communication media typically store computer can instruction, comprise and regulate data structure in data-signal and program module.Term " regulate data-signal " refers to the signal of propagation, and it has one or more or the information that becomes in code signal in its feature group.Exemplary adjustments data-signal comprises carrier wave or other connecting gear.Propagation medium comprises any information delivery media.For example and not limit, communication media comprises wire medium, as cable network or direct wired connection, and wireless medium, as sound, infrared ray, radio, microwave, spread-spectrum and other wireless media technologies.More than combination is included in the scope of computer-readable medium.
Within the scope of the invention be, computerized method can be the independently software program in the hardware being stored in himself, its accessible site is in the operating system of gas-turbine unit, or can be software program, it is designed to be integrated in existing software, has managed the operating system of gas-turbine unit.
Although describe the present invention with the current content being recognized as preferred embodiment, will be appreciated that and the invention is not restricted to disclosed embodiment, and on the contrary, be intended to cover the various remodeling in the scope of following claim and equivalent arrangements.Describe the present invention about specific embodiment, this specific embodiment is intended to be all exemplary and nonrestrictive in all respects.The wearing and tearing that alternative enforcement and the required operation operation as the guard shield face of processing except carbide surface and carbide alloy causes will become apparent those skilled in the art, and not depart from its scope.
From above will it is seen that, the present invention is suitable for realizing all results mentioned above and object well, together with other advantage obvious and that system and method is intrinsic.Will be appreciated that some characteristic sum sub-portfolios is practical, and can when not using with reference to when further feature and sub-portfolio.This is envisioned by claim and within the scope of the claims.
Claims (31)
1. a method for operating gas turbine burner, comprising: the guiding fuel nozzle supplying fuel to described gas turbine combustor; Light the described fuel sprayed by described guiding fuel nozzle; Supply fuel to one group of guide adjustment level injector and described guiding fuel nozzle, described guide adjustment level injector is positioned at the radial outside of described guiding fuel nozzle; Supply fuel to the Part I of one group of main fuel injector, described guiding fuel nozzle and described guide adjustment level injector; Light the described fuel that sprayed by the Part I of described one group of main fuel injector to form main combustion flame; Supply fuel to the Part II of described one group of main fuel injector, the Part I of described one group of main ejector, described guiding fuel nozzle and described guide adjustment level injector; And light the described fuel that sprayed by the Part II of described one group of main fuel injector to strengthen described main combustion flame.
2. method according to claim 1, is characterized in that, described method also comprises the described fuel being adjusted to described guiding fuel nozzle and/or described guide adjustment level injector.
3. method according to claim 1, is characterized in that, at the flame-out of described gas turbine combustor with until at full speed during unloaded (FSNL) state, fuel is only supplied to described guiding fuel nozzle.
4. method according to claim 3, is characterized in that, fuel is supplied to described guide adjustment level injector from stopping working to about 10% load condition.
5. method according to claim 4, is characterized in that, fuel starts with flame-out the Part I being supplied to described main ejector to approximately described 10% load condition.
6. method according to claim 5, is characterized in that, fuel starts with flame-out the Part II being supplied to described main fuel injector to about 25% load condition.
7. method according to claim 1, it is characterized in that, the Part I of described one group of main fuel injector comprises the arc segment of the fuel injector crossing over about 120 degree, and the Part II of described one group of main fuel injector comprises the arc segment of the fuel injector crossing over about 240 degree.
8. the Computerized method implemented by processing unit for classification fuel in gas turbine combustor, wherein said gas turbine combustor has guiding fuel nozzle, for regulating one group of guide adjustment level injector of described guiding fuel nozzle, and one group of main fuel injector, described method comprises: operate described burner in the first mode that fuel is sprayed by described guiding fuel nozzle wherein; Fuel operates described burner by described guiding fuel nozzle and the second pattern for the described injector injection of described guide adjustment level wherein; Fuel operates described burner by described guiding fuel nozzle, the 3rd pattern of spraying for the Part I of the described injector of described guide adjustment level and described one group of main fuel injector wherein; And fuel operates described burner by described guiding fuel nozzle, the four-mode that sprays for the Part II of the described injector of described guide adjustment level, the Part I of described one group of main fuel injector and described one group of main fuel injector wherein.
9. method according to claim 8, is characterized in that, the Part I of described one group of main fuel injector extends the arcuate span across about 120 degree, and the Part II of described one group of main fuel injector extends the arcuate span across about 240 degree.
10. method according to claim 8, is characterized in that, pilot flame is provided to described gas turbine combustor by described first mode.
11. methods according to claim 10, is characterized in that, the fuel sprayed by described guide adjustment level provides additional fuel source for regulating and supporting described pilot flame.
12. methods according to claim 8, is characterized in that, the fuel sprayed by described 3rd pattern and described four-mode vertically updrift side sprays, and experience direction reversion before ignition.
13. methods according to claim 8, is characterized in that, extremely the flow in fuel of the injector of described guiding fuel nozzle and described guide adjustment level is adjustable after being to operate described burner in described four-mode.
14. 1 kinds of downward abilities improving gas turbine combustor control the method produced from the carbon monoxide of described gas turbine combustor simultaneously, comprise: be adjusted to the Part I of the annular array of main fuel injector and the flow in fuel of Part II, support main combustion flame; And
Be adjusted to the flow in fuel of one or more fuel injector in the core section of described gas turbine combustor.
15. methods according to claim 14, is characterized in that, the flow in fuel of the Part I and Part II that are adjusted to the annular array of main ejector comprises the described flow in fuel increasing to described Part I and described Part II.
16. methods according to claim 15, is characterized in that, the flow in fuel being adjusted to one or more fuel injector in core section comprises the described flow in fuel being reduced at least described guiding fuel nozzle.
17. methods according to claim 16, is characterized in that, when reducing to the total fuel flow of described engine, the flow in fuel to main fuel injector increases compared to the ratio of the described flow in fuel at least described guiding nozzle.
18. methods according to claim 14, is characterized in that, described Part I comprises the annular array of the main fuel injector extending about 120 degree, and described Part II comprises the annular array of the main fuel injector extending about 240 degree.
19. methods according to claim 14, it is characterized in that, the core section of described gas turbine combustor comprises the injector guiding fuel nozzle and guide adjustment level, and wherein the described guide adjustment level of fuel injector provides flow in fuel to support described pilot flame.
The method of 20. 1 kinds of operating gas turbine burners, comprising: the guiding fuel nozzle and the one group of guide adjustment level injector that supply fuel to described gas turbine combustor; Light the described fuel sprayed by described guiding fuel nozzle and described guide adjustment level injector; Supply fuel to the Part I of one group of main fuel injector, described guiding fuel nozzle and described guide adjustment level injector; Light the described fuel that sprayed by the Part I of described one group of main fuel injector to form main combustion flame; Supply fuel to the Part II of described one group of main fuel injector, the Part I of described one group of main ejector, described guiding fuel nozzle and described guide adjustment level injector; And light the described fuel that sprayed by the Part II of described one group of main fuel injector to strengthen described main combustion flame.
21. methods according to claim 20, is characterized in that, described method also comprise be adjusted to described guiding fuel nozzle and/or described guide adjustment level injector described fuel for improvement of the stability of described main combustion flame.
22. methods according to claim 20, is characterized in that, at the flame-out of described gas turbine combustor with until during about 10% load condition, fuel is only supplied to described guiding fuel nozzle and guide adjustment level injector.
23. methods according to claim 22, is characterized in that, fuel starts with flame-out the Part I being supplied to described main ejector to approximately described 10% load condition.
24. methods according to claim 23, is characterized in that, fuel starts with flame-out the Part II being supplied to described main fuel injector to about 25% load condition.
25. methods according to claim 20, it is characterized in that, the Part I of described one group of main fuel injector comprises the arc segment of the fuel injector crossing over about 120 degree, and the Part II of described one group of main fuel injector also comprises the arc segment of the fuel injector crossing over about 240 degree.
The method of 26. 1 kinds of operating gas turbine burners, comprising: the guiding fuel nozzle supplying fuel to described gas turbine combustor; Light the described fuel sprayed by described guiding fuel nozzle; Supply fuel to the Part I of one group of main fuel injector and described guiding fuel nozzle; Light the described fuel that sprayed by the Part I of described one group of main fuel injector to form main combustion flame; Supply fuel to the Part I of the Part II of described one group of main fuel injector, described one group of main ejector, and described guiding fuel nozzle; And light the described fuel that sprayed by the Part II of described one group of main fuel injector to strengthen described main combustion flame.
27. methods according to claim 26, is characterized in that, described method also comprises the described fuel being adjusted to described guiding fuel nozzle.
28. methods according to claim 26, is characterized in that, at the flame-out of described gas turbine combustor with until during about 10% load condition, fuel is only supplied to described guiding fuel nozzle and guide adjustment level injector.
29. methods according to claim 28, is characterized in that, fuel starts with flame-out the Part I being supplied to described main ejector to approximately described 10% load condition.
30. methods according to claim 29, is characterized in that, fuel starts with flame-out the Part II being supplied to described main fuel injector to about 25% load condition.
31. methods according to claim 26, it is characterized in that, the Part I of described one group of main fuel injector comprises the arc segment of the fuel injector crossing over about 120 degree, and the Part II of described one group of main fuel injector also comprises the arc segment of the fuel injector crossing over about 240 degree.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201261708323P | 2012-10-01 | 2012-10-01 | |
| US61/708323 | 2012-10-01 | ||
| US14/038,070 US20150184858A1 (en) | 2012-10-01 | 2013-09-26 | Method of operating a multi-stage flamesheet combustor |
| US14/038070 | 2013-09-26 | ||
| PCT/US2013/062693 WO2014055437A1 (en) | 2012-10-01 | 2013-09-30 | Method of operating a multi-stage flamesheet combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104685298A true CN104685298A (en) | 2015-06-03 |
| CN104685298B CN104685298B (en) | 2017-05-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380051446.0A Expired - Fee Related CN104685298B (en) | 2012-10-01 | 2013-09-30 | Method of operating a multi-stage flamesheet combustor |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US20150184858A1 (en) |
| EP (1) | EP2904327A1 (en) |
| JP (1) | JP2015531450A (en) |
| KR (1) | KR20150063507A (en) |
| CN (1) | CN104685298B (en) |
| CA (1) | CA2886765A1 (en) |
| MX (1) | MX2015003098A (en) |
| SA (1) | SA515360208B1 (en) |
| WO (1) | WO2014055437A1 (en) |
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Also Published As
| Publication number | Publication date |
|---|---|
| EP2904327A1 (en) | 2015-08-12 |
| JP2015531450A (en) | 2015-11-02 |
| MX2015003098A (en) | 2015-11-06 |
| US20150184858A1 (en) | 2015-07-02 |
| SA515360208B1 (en) | 2018-06-28 |
| KR20150063507A (en) | 2015-06-09 |
| CA2886765A1 (en) | 2014-04-10 |
| WO2014055437A1 (en) | 2014-04-10 |
| CN104685298B (en) | 2017-05-10 |
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