CN104685298B - Method of operating a multi-stage flamesheet combustor - Google Patents
Method of operating a multi-stage flamesheet combustor Download PDFInfo
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- CN104685298B CN104685298B CN201380051446.0A CN201380051446A CN104685298B CN 104685298 B CN104685298 B CN 104685298B CN 201380051446 A CN201380051446 A CN 201380051446A CN 104685298 B CN104685298 B CN 104685298B
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- 238000000034 method Methods 0.000 title claims abstract description 48
- 239000000446 fuel Substances 0.000 claims abstract description 289
- 238000002485 combustion reaction Methods 0.000 claims description 69
- 238000002347 injection Methods 0.000 claims description 17
- 239000007924 injection Substances 0.000 claims description 17
- 239000007921 spray Substances 0.000 claims description 8
- 238000012545 processing Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims 4
- 238000010977 unit operation Methods 0.000 claims 4
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 abstract description 11
- 229910002091 carbon monoxide Inorganic materials 0.000 abstract description 11
- 239000007789 gas Substances 0.000 description 32
- 239000000203 mixture Substances 0.000 description 11
- 230000033228 biological regulation Effects 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 238000003860 storage Methods 0.000 description 6
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000002156 mixing Methods 0.000 description 4
- 241001672694 Citrus reticulata Species 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 3
- 238000004891 communication Methods 0.000 description 3
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- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000004590 computer program Methods 0.000 description 2
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- 238000004364 calculation method Methods 0.000 description 1
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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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
Landscapes
- 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 method of controlling a gas turbine engine to reduce emissions levels when demand for power from the gas turbine engine is reduced. The method provides a series of operating modes for a gas turbine combustor (300) 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 relates generally to a kind of discharge in operating combustion system to reduce gas turbine combustor
Method.More specifically, there is provided for the improvement of the fuel staging of burner.
Background technology
In order to reduce the discharge amount of pollution of the turbine from gas energy supply, government organs have promulgated that requirement reduces nitrogen oxides
(NOx) and carbon monoxide (CO) amount many regulations.Relatively low burning and exhausting is generally attributable to more effective combustion process,
Position and mixing effectiveness particularly with regard to fuel injector.
The combustion system of early stage using the diffusion types of combustion zone nearside nozzle, the wherein sky outside fuel and fuel nozzle
Gas is by spreading mixing.Stoichiometrically burned at high temperature due to fuel and air keep enough combustor stability and
It is low combustion powered, therefore the nozzle of diffusion types produces maximum discharge.
The enhancing of combustion technology is that, using premix, wherein fuel and air mixes to form uniform mixing before combustion
Thing, it is burned at a temperature of the flame less than expanding type, and produces relatively low NOxDischarge.Premix can be in fuel nozzle
Interior or its outer generation, as long as it is in the upstream of combustion zone.Fig. 1 shows the example of the premix burner of prior art.Burner 8
With multiple fuel nozzles 18, it is injected fuel in premix chamber 19, wherein, fuel before into combustion chamber 20 with come
Mix from the compressed air 6 of bin 10.The fuel and air of premix allows before combustion together fuel and air to form more equal
Even mixture, it will more completely burn, cause compared with low emission.However, in this configuration, fuel is in the relatively the same of burner
Plane in spray, and by changing mixing length preventing improved any possibility.
Premix can be realized by multiple combustion stages compared with the alternative means of low emission, this allow that enhanced during load increase
Premix.Referring now to Fig. 2, the example of the multistage burner of prior art is shown.Burner 30 have separated by Venturi tube 33
The first combustion chamber 31 and the second combustion chamber 32, Venturi tube 33 have narrower throat region 34.Although fuel may depend on load
State is come across in the first combustion chamber or the second combustion chamber or two rooms, but is second in the fuel sprayed by nozzle region 35
When being thoroughly mixed with compressed air in the first combustion chamber 31 before burning in combustion chamber 32, minimum emission level occurs.Therefore,
The multistage burner with Venturi tube is more effective under higher load state.
Gas-turbine unit is needed to operate under multiple power setting.Generating is driven in gas-turbine unit connection
In the case of machine, the required output of engine comes generally according to the load capacity on generator or the power that must be produced by generator
Measurement.Full load state is the point that maximum output is extracted from generator, and therefore needs the peak power from engine
Drive generator.This is the modal operating point of the continental rise gas turbine for generating electricity.However, generally electricity demand need not be sent out
The full capacity of motor, and operator expects that engine is operated in the case where arranging compared with low-load so that loading demand is only produced, so as to
Save fuel and reduce running cost.The combustion system of prior art it is known that become unstable in the case where arranging compared with low-load,
Especially under 50% load, while also creating NOxWith the unacceptable level of CO discharges.This is mainly due to most
Number combustion system is for the most effective operation classification under high capacity setting.The burning of potentially unstable and the combination of higher emissions are logical
Often prevent engine operators from running engine in the case where arranging compared with low-load, force engine compared with high setting run, so as to
Additional fuel or shutdown are burned, and so as to lose the valuable income that can be generated by fractional load demand.
The problem that engine is shut down is set to be the additional cycles caused by engine hardware.Circulation is typically defined to through normal
The engine of opereating specification.Therefore, shut down by making engine, engine hardware accumulation additional cycles.Manufacturers of engines allusion quotation
Hardware longevity is assessed according to the operation circulation of hours run or equivalent type.Therefore, the additional cycles for causing can shorten hardware
Life-span, and need engine operators' cost to come premature repairs or replacement.A kind of system is desirable for, it can be in fractional load
Flame holding and low emission benefit are provided under state and full load state so that engine can be under relatively low load condition effectively
Operation, so as to eliminate the spent fuel when not needing high capacity to operate, or additional following of causing in engine hardware when shutting down
Ring.
The content of the invention
The invention discloses a kind of method of operation gas-turbine unit, and more specifically, to improve engine
Lower the method that the mode of efficiency operates gas turbine combustor.In an embodiment of the present invention, a kind of side of operation burner
Method includes supplying fuel to guiding nozzle, lights the fuel for carrying out bootstrap nozzle, and additional fuel is supplied to guiding tune
The level of section injector.The method also discloses and supplies fuel to the Part I of burner main fuel injector, lights the combustion
Expect to form main burning flame, supply fuel to the Part II of burner main fuel injector, and light the fuel
Support main burning flame.
The present invention alternative in, there is provided it is a kind of for being classified gas turbine combustor in fuel calculating
Machine method.This method provide a kind of operation by four different operation modes and there is guiding nozzle, one group of guide adjustment spray
The mode of the burner of emitter and one group of main fuel injector.Each continuous mode of operation adds additional The fuel stream to combustion
Burner.
In yet another embodiment of the present invention, a kind of same time control of downward ability of improvement gas turbine combustor is disclosed
The method that carbon monoxide processed is produced.The method adjusts the combustion of the Part I to the annular array of fuel injector and Part II
Stream, and the The fuel stream of the one or more injectors adjusted into the core section of gas turbine combustor, its SMIS area
Section includes guiding nozzle and one group of injector for adjusting guiding nozzle.The total of The fuel stream is allowed in the regulation of these fuel circuits
Body is reduced, to support downward ability, while operation is maintained in acceptable emission limit.
In another embodiment of the present invention, a kind of method of operation burner includes supplying fuel to guiding fuel
Both levels of nozzle and guide adjustment injector.The ignited fuel sprayed by these loops, and then additional fuel via
The Part I addition of main fuel injector, it lights to generate main burning flame.Then, fuel is supplied to main fuel injector
Part II, and the additional fuel then lighted further to support main burning flame.
In the additional embodiment of the present invention, a kind of method of operation burner includes supplying fuel to guiding nozzle,
And the fuel is lighted forming pilot flame.Additional fuel by supply fuel to the Part I of main fuel injector come
Add to burner.The ignited fuel added via the Part I of main ejector is forming main burning flame.Then, fuel is supplied
To the Part II of main fuel injector, and should light further to support main burning flame.
The attendant advantages and feature of the present invention will be partly articulated in the following description, and will be in those skilled in the art
Member partly becomes apparent when consulting hereafter, or can be from the learning by doing of the present invention.To come referring in particular to accompanying drawing now
The description present invention.
Description of the drawings
The present invention is described in detail below with reference to accompanying drawing, in the figure：
Fig. 1 is the section of the gas turbine combustor of prior art.
Fig. 2 is the section of the alternative burner of prior art.
Fig. 3 is the section of the gas turbine combustor according to embodiments of the invention.
Fig. 4 is the end-view of the gas turbine combustor of the Fig. 1 according to embodiments of the invention.
Fig. 5 is the flow chart for drawing the process for controlling gas turbine combustor according to an embodiment of the invention.
Fig. 6 A are the section view of the gas turbine combustor for operating in the first mode according to embodiments of the invention.
Fig. 6 B are the section view of the gas turbine combustor for operating in a second mode according to embodiments of the invention.
Fig. 6 C are the section view of the gas turbine combustor operated in the 3rd pattern according to embodiments of the invention.
Fig. 6 D are the section view of the gas turbine combustor operated in fourth mode according to embodiments of the invention.
Fig. 6 E are the gas turbine for adjusting operation in version of the fourth mode in Fig. 6 D according to embodiments of the invention
The section view of burner.
Fig. 7 A are the end-view of the gas turbine combustor for operating in the first mode according to embodiments of the invention.
Fig. 7 B are the end-view of the gas turbine combustor for operating in a second mode according to embodiments of the invention.
Fig. 7 C are the end-view of the gas turbine combustor operated in the 3rd pattern according to embodiments of the invention.
Fig. 7 D are the end-view of the gas turbine combustor operated in fourth mode according to embodiments of the invention.
Fig. 8 is the flow chart of the process of the control gas turbine combustor for drawing alternative of the invention.
Fig. 9 is the flow chart of the process for drawing control gas turbine combustor according to still another embodiment of the invention.
Specific embodiment
By referring to, the application is incorporated with United States Patent (USP) No. 6,935,116,6,986,254,7,137,256,7,237,
384th, 7,308,793,7,513,115 and 7,677,025 theme.
The invention discloses a kind of operate combustion system to improve the mode of the downward ability of gas-turbine unit.
That is, it is disclosed The embodiment provides for relatively low in the power demand that carrys out self generator and therefore need to come spontaneous
The means of the combustion stability in gas turbine combustor are improved during the less output of motivation.
The present invention is discussed now with reference to Fig. 3-9.Depicting in Fig. 3 can apply improved method of operating of the invention
The embodiment of gas turbine combustor.Combustion system 300 extends around longitudinal axis A-A, and including flow sleeve 302, is used for
Outer surface of the compressed air of scheduled volume along combustion liner 304 is guided.Main fuel injector 306 is positioned at combustion liner 304
Radial outside, and be designed to provide fuel supply come in the appearance into the forward position combustion liner 304 in combustion liner 304
The part in face mixes with compressed air.The fuel sprayed by main fuel injector 306 mixes with compressed air, and along forward
Direction towards combustion liner 304 inlet region advance, wherein, fuel/air mixture then reverses direction and enter burning lining
In set 304.For the guiding fuel nozzle 308 of pilot flame that provides and keep combustion system, generally longitudinally A-A prolongs
Stretch.Pilot flame is used for multiple levels of the fuel injector for lighting, support and keeping combustion system 300.
Combustion system 300 also includes the premixed device 310 being radially classified.Premixed device 310 includes having around combustion system
The first fuel plenum 314 that 300 longitudinal axis A-A extends, and it is positioned at the radial outside of the first fuel plenum 314 and with first
The second concentric fuel plenum 316 of fuel plenum 314.The premixed device 310 being radially classified also includes having to be determined in one direction
To the radial direction of multiple stators 320 become a mandarin cyclone 318, the direction is at least partially perpendicularly to the longitudinal axis of combustion system 300
A-A。
Guide fuel nozzle 308 to be connected to fuel supply source (not shown), and provide fuel is used for combustion system 300
Supply pilot flame 350, wherein, generally longitudinally A-A is positioned pilot flame 350.Including fuel plenum 314 and 316, footpath
The fuel through stator 320 is provided to the premixed device 310 being radially classified of become a mandarin cyclone 318 and its multiple stator 320
Air mixture, supplies to pilot flame 350 for additional fuel to be adjusted into 352 via guide adjustment level or P.
As described above, combustion system 300 also includes main fuel injector 306.For the reality of the invention shown in Fig. 3
Example is applied, main fuel injector 306 is located at the radial outside of combustion liner 304, and with around the annular array of combustion liner 304
Spread.Main fuel injector 306 may include one or more parts and level, and they are equal or not around the circumference of main fuel level
Etc. ground extend.Used as the example of the application of the present invention, main fuel injector divide into two levels, Part I and second
Point.Part I extends about 120 degree, and Part II extends about remaining 240 degree of spans.As shown in Figure 4, main fuel
The Part I of 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, the rearview of the gas turbine combustor of forward-looking Fig. 3 is depicted.Fig. 4 clearly demonstrates burning
Each radially and circumferentially position in flame location in system 300, wherein pilot flame 350 is in center, guide adjustment
Level 352 is located at the radial outside of pilot flame 350, and main 1 flame 354 and main 2 flame 356 are located at guide adjustment level 352
Radial outside.
As described above, gas-turbine unit combines multiple burners.Generally, for the purpose discussed, combustion gas
Turbogenerator may include low emission combustor, as disclosed herein those, and may be disposed to start around gas turbine
The cylinder circular structure of machine.A type of gas-turbine unit (for example, heavily loaded gas-turbine unit) typically can be provided with
But 6 to 18 independent burners are not limited to, each in burner is combined with the component of above-outlined.Therefore, based on combustion gas
The type of turbogenerator, can exist for operating some different fuel circuit of gas-turbine unit.For the present invention
Embodiment, there are four fuel circuits for using.It is, however, contemplated that go out, special fuel loop and associated control machine
Structure can be changed to include less or additional fuel loop.
The physical layout of the combustion system 300 of present invention operation is discussed, has been described in detail now with reference to Fig. 5-9
For the method for operating of the combustion system.Present invention uses four fuel-grades are come for regulation and operating flexibility.More specifically
For, with reference to Fig. 5, the method 500 of the operation combustion system 300 of Fig. 3 is outlined, which use four different fuel levels to carry
High combustion stability, to allow to operate in the case where arranging compared with low-load.Initially in step 502, fuel is supplied to gas turbine
The guiding fuel nozzle of burner.Then, in step 504, the ignited fuel for carrying out bootstrap fuel nozzle is fiery to form guiding
Flame.This is lighted can occur by various ignition source, such as spark lighter or torch ignitor and occur.When guiding, fuel nozzle is big
When longitudinal axis on body along burner is positioned, the pilot flame of gained is also generally longitudinally positioned.Supply fuel to and draw
Lead fuel nozzle and these steps for lighting fuel to form pilot flame are recognized as the operator scheme 1 of combustion system, and
With guide fuel nozzle igniting or " flame-out " beginnings opereating specification in operation, and continue across " full speed zero load " or "
FSNL " states.As described above, FSNL is engine operation state, wherein turbine and compressor under design maximum rotating speed
Operation, its engine for 60Hz is about 3600 rpms, but zero load is applied by generator.In both Fig. 6 A and Fig. 7 A
Show the description of the operation of pattern 1 of combustion system.
As understood by a person skilled in the art, flame inherently includes shear layer.In general, shear layer or boundary layer are
Wherein there may be the flow region of notable velocity gradient.The shear layer of flame is the outermost edge and non-flammable environment or adjacent of flame
Shared region between flame.
Lighting for fuel from one group of main fuel injector can be due to the fuel/air mixture of the shear layer of control pilot flame
The ability of ratio and be easier and reliably occur.More specifically, by local at the outermost radial position in premix path
Increase fuel supply, the fuel concentration increase in the shear layer of the pilot flame of gained.As a result, the shear layer of enrichment allows main jet
Emitter is easier and reliably lights, without many energy, this then cause during the lighting of main fuel injector compared with
Low pulse level.
It is to keep lighting being sprayed by main ejector that can partly be enriched with to the additional benefits of the The fuel stream of shear layer
The ability of the stabilization process of fuel.That is, in premix combustion systems, fuel flow horizontal traditionally remain it is as lean as possible, so as to
Reduce discharge.By partly adding fuel to shear layer during selection time section, the mixture of more fuel-rich is formed, from
And increase the fuel/air rate in shear layer area.The mixture of more fuel-rich provides more favourable condition to send out for igniting
It is raw, and improve flame holding.Once lighting flame, then fuel enrichment level can be decreased to leaner mixture, and not
The stability of harm flame.
In step 506, fuel continues to supply to guiding fuel nozzle, such as in step 502, while also supplying to one group
Guide adjustment level injector.Guide adjustment level injector is located in multiple stators 320 of the cyclone 318 that radially becomes a mandarin, and it is located at
The radial outside of guiding fuel nozzle 308, and fuel is mixed from the fuel plenum injection of end cap with the air stream of surrounding.
The fuel air mixture is then passed through along pilot flame, and for strengthening and supporting pilot flame, and enrichment guiding fire
The shear layer of flame.The operation together of guiding fuel nozzle and one group of guide adjustment level injector is recognized as the operation of combustion system
Pattern 2.Pattern 2 can be from load of the quenching operations up to about 10%.The pattern of combustion system is shown in both Fig. 6 B and Fig. 7 B
The description of 2 operations, wherein the fuel/air mixture from guide adjustment level is shown as in pilot flame radial outside and surrounds
Pilot flame.
Next, in step 508, combustion system enters the pattern 3 of operation, and wherein fuel is supplied to main fuel injector
Part I, while also still supplying to guiding fuel nozzle and one group of guide adjustment level injector.As described above, burning system
The main fuel injector 306 of system is arranged to the annular array around combustion liner, and is divided into two parts, around combustion liner
304 extend about 120 degree of Part I, and extend about 240 degree of Part II around combustion liner 304.In step
In 510, the ignited fuel for being sprayed by the Part I of main fuel injector in step 508 is forming main burning flame.Main combustion
Lighting for flame of making a fire occurs due to the pilot flame of the formation by pattern 1 and 2.However, in order to light the main burning flame,
Combustion system is delayed typically via fuel is added to guide adjustment level (at the end of pattern 2) and rises to the point, wherein turning
During the pattern 3 of moving to, the fuel added via guide adjustment level is then transferred to the Part I of main fuel injector.Which ensure that
Effective and quiet transfer of Dietary behavior 3.Fuel can be started with stopping working and the load condition through about 10% is supplied to master
The Part I of injector.The description of the operation of pattern 3 of combustion system is shown in both Fig. 6 C and Fig. 7 C, wherein in pattern 3
The main burning flame of formation is located at the radial outside of the fuel air mixture of the guide adjustment level from injector.
In step 512, combustion system is operated in pattern 4, and wherein fuel is supplied to second of main fuel injector
Point and main fuel injector Part I, guiding fuel nozzle and injector guide adjustment level.Therefore, in the mould of operation
In formula 4, fuel flows through all four loop of combustion system, and flow to all main fuel injectors now.As a result, fuel
360 degree of rings from main fuel injector be ejected into through air stream, and in the radial outside of combustion liner.In the step 514,
By main fuel injector Part II spray fuel due to by from main fuel injector Part I injection fuel shape
Into main burning flame and light.This is that pattern 4 is operated.Fuel can begin to pass the injection of about 25% load condition with flame-out
Through the Part II of main fuel injector.Fuel continues to flow through the load condition in these loops to about 100%, or it also claims
For basic load state.Wide and stable mode of operation of the operation in pattern 4 there is provided combustion system.Both Fig. 6 D and Fig. 7 D
In show combustion system pattern 4 operation description, wherein main burning flame by pattern 4 fuel injection strengthen, and
Around pilot flame circumferentially.
Once combustion system reaches basic load or 100% load condition, wherein fuel flows through all four loop, then has
The one or more The fuel stream into the loop of the core for supplying fuel to burner may be adjusted, i.e. the guiding of regulation
Fuel nozzle stream 360 and/or the regulation stream 362 to guide adjustment level, as is shown in figure 6e.When needing compared with low-load, reduce
Fuel quantity is desirable.However, traditionally, when fuel flow horizontal is reduced, flame temperature tends to reducing, and which results in CO
The correspondence rising of discharge.For example, Fig. 5 is referred back to, in step 516, the The fuel stream of core inlet zone is can tune to, i.e. guiding
Fuel nozzle and/or guide adjustment level injector.However, by keeping to the Part I and Part II of main fuel injector
Both The fuel streams, while the The fuel stream of the guide adjustment level adjusted to guiding fuel nozzle and/or injector, such as institute in Fig. 6 E
Paint, main burning flame is maintained in whole ring, and in the temperature hotter than pilot flame.Therefore, hotter main burning fire
Flame will consume the CO generated by colder pilot flame.The regulation of pattern 4 is drawn in Fig. 6 E, and in combustion system just
Often occur during premixed operation.
As skilled in the art will appreciate, it is desirable when the power reduction needed for engine or lower timing
It is to efficiently reduce engine output, while still keeping the operation of engine.When engine needs less power, burned
Less fuel is needed in journey.Therefore, in order to lower engine, The fuel stream also must be reduced.However, as described above, fuel is worked as
When flow horizontal reduces, flame temperature tends to reducing, and this causes CO discharges to raise.Therefore it is desirable for fully burning this and adds
CO, so that engine is maintained in emissions adjustment.A kind of mode for burning CO discharges is by by the of main fuel injector
The main burning flame that a part and Part II are generated remains as hot as possible.This can be by the The fuel stream to fuel injector
It is careful to adjust to realize.More specifically, the The fuel stream to core area (guiding fuel nozzle and/or guide adjustment level injector) subtracts
Few, the The fuel stream of Part I and Part II to main injector slightly increases.When to boot section The fuel stream reduce or
At the end of, net whole structure be to the relatively low total fuel flow rate of burner, but higher than guiding and/or guide adjustment level fuel ratio
Rate guides into the main flame of support.
Although the step of discussing supply The fuel stream in order and light spray fuel, it will be appreciated by those skilled in the art that
, for the flame for keeping the igniting by the fuel for just having sprayed to cause, The fuel stream must continue to or the flame of gained will extinguish.
It is therefore desirable to the step of fuel is supplied/sprayed occurs before or while ignited fuel.
The present invention alternative in, combustion system 300 include for provide fuel into guiding fuel nozzle, one
Group guide adjustment injector and two loops to 2 flames of master 1 and master, define four of main burning flame as described above
Primary fuel circuit.However, determine that combustion noise and discharge improvement can be realized using this hardware, and initially fuel only do not guided to
Guiding fuel nozzle, but be changed to realize initially putting out for fuel to both guiding fuel nozzle and one group of guide adjustment level injector
Fire.
With reference to Fig. 8, the alternative procedure for operating gas turbine combustor is disclosed in process 800.In step 802,
Fuel is initially supplied to the guiding fuel nozzle and one group of guide adjustment level injector of gas turbine combustor.Then, in step
In 804, the fuel sprayed by guiding fuel nozzle and guide adjustment level injector is ignited.Once flame is formed in boot section
In, then about 10% load condition is continued across for fuel to the level of guiding fuel nozzle and guide adjustment injector.Then,
In step 806, fuel is supplied to the Part I of one group of main fuel injector.As described above, one group of main fuel injector
Part I be made up of about 120 degree of curved sections of fuel injector.Fuel continues to flow to guiding fuel nozzle and guiding
Governing stage, while fuel is supplied to the Part I of one group of main fuel injector.In step 808, sprayed by one group of main fuel
The ignited fuel of the Part I injection of device is forming main burning flame.The fuel sprayed by the Part I of main fuel injector
Early as flame-out can begin to pass about 10% load condition.Once forming main burning flame, then in step 810, fuel connects
The Part II supplied to one group of main fuel injector, while continuing to supply the Part I of fuel to one group of main burner, drawing
Lead fuel nozzle and guide adjustment level injector.Fuel can start to be supplied to main fuel with about 25% load condition with flame-out
The Part II of injector.Then, in step 812, the ignited fuel for being sprayed by the Part II of one group of main fuel injector
To strengthen main burning flame.Another embodiment as described above, in step 814, to guide adjustment level injector
Then it is adjustable so as to improve flame holding with the The fuel stream of guiding fuel nozzle.
In yet another embodiment of the present invention, a kind of method of operation gas turbine combustor is developed, wherein such as front
Literary described, fuel is supplied to three loops, and is not supplied to the guide adjustment level of injector.Referring now to Fig. 9, combustion gas is operated
The method 900 of turbine burner includes the step of supplying fuel to the guiding fuel nozzle of gas turbine combustor 902.Connect
, in step 904, the ignited fuel sprayed by guiding fuel nozzle is forming pilot flame.In step 906, fuel is supplied
The Part I of Ying Zhiyi group main fuel injectors, while continuing to guiding fuel nozzle supply fuel.Fuel can be with flame-out
Start and about 10% load condition is supplied to the Part I of main fuel injector.Then, in step 908, from main injection
The ignited fuel of the Part I of device is forming main burning flame.
In step 910, fuel is supplied to the Part II of one group of main fuel injector, while also supplying to main fuel spray
The Part I and guiding fuel nozzle of emitter.Fuel can start to be supplied to master and about 25% load condition between with flame-out
The Part II of injector.In such embodiment of the present invention, the Part I of main ejector around about 120 degree with
Curved path extends, and the Part II of main ejector is extended with about 240 degree of curved path.In step 912, by main jet
The Part II of emitter supplies the ignited fuel to burner and for strengthening main burning flame.As described above, fuel after
It is continuous to flow through the load that these various loops are up to about 100%.Depending on the mode of operation of engine, process can be in step
Continue in 914, wherein being adjustable to the The fuel stream of guiding nozzle.As described above, the regulation may include to reduce to guiding fuel
The amount of the The fuel stream of nozzle, to support that engine is lowered, while controlling CO discharges.
As skilled in the art will recognize, the present invention can especially be presented as method, system or computer program
Product.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 includes being embodied in one
Or the available instruction of the computer on more computer-readable mediums.
Computer-readable medium includes both volatibility and non-volatile media, can remove and non-removable medium, and
And envision can by database, switch and various other network equipments read medium.As the means for communicating with, network
Switch, router and associated components are in nature conventional.For example and do not limit, computer-readable medium includes meter
Calculation machine storage medium and communication media.
Computer storage media or computer-readable medium are real in being included in for storing up stored any method or technique
The medium applied.Store up stored example to represent including the available instruction of computer, data structure, program module and other data.
Computer storage media includes but is not limited to RAM, ROM, EEPROM, flash memory or other memory technologies, CD-ROM, number
According to versatile disc (DVD), holographic media or other disc storages, cassette, tape, disc storage and other magnetic storage devices.
These memory means can momentarily, either temporarily or permanently store data.
Communication media typically stores the available instruction of computer, including adjusts the data structure and program in data-signal
Module.Term " adjust data-signal " refers to the signal of propagation, and it has one or more in its feature group or is changed into compiling
Information in code signal.Exemplary adjustments data-signal includes carrier wave or other connecting gears.Propagation medium includes any information
Pumped (conveying) medium.Do not limit, communication media includes wire medium, such as cable network or direct wired connection, and
Wireless medium, such as sound, infrared ray, radio, microwave, spread-spectrum and other wireless media technologies.Combination of the above is included in
In the range of computer-readable medium.
Within the scope of the invention, computerized method can be stored in it is independent soft in the hardware of its own
Part program, it can be integrated in the operating system of gas-turbine unit, or can be software program, and it is designed to be integrated into now
In some software, the operating system of gas-turbine unit has been managed.
Although describing the present invention with the content for being currently recognized as preferred embodiment, it is to be understood that the present invention is not limited
In disclosed embodiment, and on the contrary, it is intended to cover the various remodeling and equivalent arrangements in the range of following claims.Close
The present invention is described in specific embodiment, the specific embodiment is intended to all be in all respects exemplary and nonrestrictive.It is standby
Choosing is implemented and the required abrasion for operating the operation in shield face and hard alloy of the such as processing in addition to carbide surface to cause
To become apparent for those skilled in the art, and without departing from its scope.
Will be seen that from above, the present invention is well adapted to realize all results mentioned above and purpose, together with bright
The intrinsic further advantage of aobvious and system and method.It will be appreciated that some features and sub-portfolio are practical, and can not join
Use in the case of according to further feature and sub-portfolio.This is envisioned and within the scope of the claims by claim.
Claims (11)
1. the method that one kind operates gas turbine combustor (300), including：
Supply fuel to the guiding fuel nozzle (308) of the gas turbine combustor (300)；
Light by the fuel of guiding fuel nozzle (308) injection；
Supply fuel to the Part I of one group of main fuel injector (306)；
Light by the fuel of the Part I injection of one group of main fuel injector (306) to form main burning flame (354)；
Supply fuel to the Part II of one group of main fuel injector (306)；And
Light by the fuel of the Part II injection of one group of main fuel injector (306) to strengthen the main burning flame
(354,356)。
2. method according to claim 1, it is characterised in that methods described also include supplying fuel to be positioned at it is described
One group of guide adjustment level injector of the radial outside of guiding fuel nozzle (308), and in the gas turbine combustor
(300) flame-out and until at full speed during unloaded (FSNL) state, fuel be supplied only to into guiding fuel nozzle (308) and used
In lighting, one group of guide adjustment level injector is supplied fuel to for lighting, with flame-out from stopping working to 10% load condition
The Part I for starting to supply fuel to one group of main fuel injector (306) to 10% load condition is used to light, and/
Or be used for the Part II for starting to supply fuel to one group of main fuel injector (306) to 25% load condition that stops working
Light.
3. method according to claim 1, it is characterised in that methods described also includes that supplying fuel to one group of guiding adjusts
Assistant warden injector, and supply is adjusted to guiding fuel nozzle (308) and/or one group of guide adjustment level injector
Fuel.
4. method according to claim 1, it is characterised in that the Part I of one group of main fuel injector (306)
Including the arc segment across 120 degree of fuel injector, and the Part II bag of one group of main fuel injector (306)
Include the arc segment across 240 degree of fuel injector.
5. a kind of in the method implemented by processing unit of the middle classification fuel of gas turbine combustor (300), wherein described
Gas turbine combustor (300) is with guiding fuel nozzle (308), for adjusting the guiding fuel nozzle one group of (308)
Guide adjustment level injector, and one group of main fuel injector (306), methods described includes：
Wherein fuel is by described in the first mode of guiding fuel nozzle (308) injection by the processing unit operation
Gas turbine combustor (300)；
Wherein fuel is by guiding fuel nozzle (308) and the second mode of one group of guide adjustment level injector injection
In by gas turbine combustor (300) described in the processing unit operation；
Wherein fuel is by guiding fuel nozzle (308), one group of guide adjustment level injector and one group of main combustion
By gas turbine combustor described in the processing unit operation in 3rd pattern of the Part I injection of material ejector (306)
(300)；
And wherein fuel guides fuel nozzle (308), one group of guide adjustment level injector, one group of master by described
The fourth mode of the Part II injection of the Part I of fuel injector (306) and one group of main fuel injector (306)
In by gas turbine combustor (300) described in the processing unit operation.
6. method according to claim 5, it is characterised in that the Part I of one group of main fuel injector (306)
120 degree of arcuate span is extended across, and the Part II of one group of main fuel injector (306) is extended across 240 degree
Arcuate span.
7. method according to claim 5, it is characterised in that the first mode provides pilot flame (350) to institute
Gas turbine combustor (300) is stated, and/or additional combustion is provided by the fuel that one group of guide adjustment level injector sprays
Material source is used to adjusting and supporting the pilot flame (350).
8. method according to claim 5, it is characterised in that the combustion sprayed by the 3rd pattern and the fourth mode
Material updrift side injection vertically, and direction reversion is experienced before ignition, and/or supply to the guiding fuel spray
The fuel of mouth (308) and one group of guide adjustment level injector is that the gas turbine combustion is operated in the fourth mode
It is adjustable after device (300).
9. the method that one kind operates gas turbine combustor (300), including：
The guiding fuel nozzle (308) and one group of guide adjustment level for supplying fuel to the gas turbine combustor (300) sprays
Emitter；
Light by the fuel of guiding fuel nozzle (308) and one group of guide adjustment level injector injection；
Supply fuel to the Part I of one group of main fuel injector (306)；
Light by the fuel of the Part I injection of one group of main fuel injector (306) to form main burning flame (354)；
Supply fuel to the Part II of one group of main fuel injector (306)；And
Light the fuel sprayed by the Part II of one group of main fuel injector (306) fiery to strengthen the main burning
Flame (354,356).
10. method according to claim 9, it is characterised in that methods described also includes adjusting supply to the guiding combustion
The fuel of material nozzle (308) and/or one group of guide adjustment level injector is used to improve the main burning flame (354,356)
Stability.
11. methods according to claim 9, it is characterised in that in the flame-out and straight of the gas turbine combustor (300)
To 10% load condition during, fuel is supplied only to guiding fuel nozzle (308) and one group of guide adjustment level injection
Device, fuel starts to 10% load condition to supply to the Part I of the main fuel injector (306) with flame-out, and/
Or the Part II that fuel starts to 25% load condition to supply to the main fuel injector (306) to stop working.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201261708323P | 2012-10-01 | 2012-10-01 | |
| US61/708323 | 2012-10-01 | ||
| US14/038070 | 2013-09-26 | ||
| US14/038,070 US20150184858A1 (en) | 2012-10-01 | 2013-09-26 | Method of operating a multi-stage flamesheet combustor |
| 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 CN104685298A (en) | 2015-06-03 |
| CN104685298B true CN104685298B (en) | 2017-05-10 |
Family
ID=49305226
Family Applications (1)
| 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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| US9897317B2 (en) | 2012-10-01 | 2018-02-20 | Ansaldo Energia Ip Uk Limited | Thermally free liner retention mechanism |
| US10060630B2 (en) | 2012-10-01 | 2018-08-28 | Ansaldo Energia Ip Uk Limited | Flamesheet combustor contoured liner |
| US9347669B2 (en) | 2012-10-01 | 2016-05-24 | Alstom Technology Ltd. | Variable length combustor dome extension for improved operability |
| US10378456B2 (en) | 2012-10-01 | 2019-08-13 | Ansaldo Energia Switzerland AG | Method of operating a multi-stage flamesheet combustor |
| US11384939B2 (en) * | 2014-04-21 | 2022-07-12 | Southwest Research Institute | Air-fuel micromix injector having multibank ports for adaptive cooling of high temperature combustor |
| CN104315541B (en) * | 2014-09-26 | 2019-01-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion chamber grade nozzle on duty and the method for using the nozzle |
| US10718525B2 (en) | 2015-06-30 | 2020-07-21 | Ansaldo Energia Ip Uk Limited | Fuel injection locations based on combustor flow path |
| WO2017002076A1 (en) * | 2015-06-30 | 2017-01-05 | Ansaldo Energia Ip Uk Limited | Gas turbine control system |
| US20170058784A1 (en) * | 2015-08-27 | 2017-03-02 | General Electric Company | System and method for maintaining emissions compliance while operating a gas turbine at turndown condition |
| EP3455556B1 (en) * | 2016-05-12 | 2020-03-18 | Siemens Aktiengesellschaft | A method of selective combustor control for reduced emissions |
| US10739003B2 (en) * | 2016-10-03 | 2020-08-11 | United Technologies Corporation | Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine |
| US10436124B2 (en) * | 2017-02-06 | 2019-10-08 | Nicolas Demougeot | Signal processing for auto-tuning a gas turbine engine |
| US10739007B2 (en) * | 2018-05-09 | 2020-08-11 | Power Systems Mfg., Llc | Flamesheet diffusion cartridge |
| 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 |
| US11795879B2 (en) * | 2021-12-20 | 2023-10-24 | General Electric Company | Combustor with an igniter provided within at least one of a fuel injector or a compressed air passage |
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Also Published As
| Publication number | Publication date |
|---|---|
| CA2886765A1 (en) | 2014-04-10 |
| EP2904327A1 (en) | 2015-08-12 |
| SA515360208B1 (en) | 2018-06-28 |
| WO2014055437A1 (en) | 2014-04-10 |
| MX2015003098A (en) | 2015-11-06 |
| KR20150063507A (en) | 2015-06-09 |
| CN104685298A (en) | 2015-06-03 |
| JP2015531450A (en) | 2015-11-02 |
| US20150184858A1 (en) | 2015-07-02 |
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