CN108506962A - The second level burner of continuous burning device for gas turbine - Google Patents
The second level burner of continuous burning device for gas turbine Download PDFInfo
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- CN108506962A CN108506962A CN201810168642.0A CN201810168642A CN108506962A CN 108506962 A CN108506962 A CN 108506962A CN 201810168642 A CN201810168642 A CN 201810168642A CN 108506962 A CN108506962 A CN 108506962A
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- downstream
- upstream
- flame location
- combustion chamber
- flame
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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
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/042—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with fuel supply in stages
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2207/00—Ignition devices associated with burner
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
-
- 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
- F23R2900/03341—Sequential combustion chambers or burners
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
A kind of second level burner of continuous burning device for gas turbine, including：Incinerator (20)；The combustion chamber (21) that streamwise extends in incinerator (20) downstream, wherein, incinerator (20) and combustion chamber (21) form flow channel (15), and downstream flame location (33) and upstream flame location (34) are limited in combustion chamber (21)；And the downstream flameholder (35) at downstream flame location (33).
Description
Cross reference to related applications
The application asks to enjoy the priority of 2 months European Patent Application No.s 17158577.1 submitted for 28th in 2017, disclosure
Content is herein incorporated by reference.
Technical field
The present invention relates to a kind of second level burners of the continuous burning device for gas turbine, and one kind is for controlling
The method of the continuous burning device of gas turbine with first-stage burning device and second level burner.
Background technology
As is known, the control of pollutant emission is any kind of heat engine and the combustion gas in particular for power generator
Primary importance purpose in the design of turbine.In fact, the consciousness of environmental risk drives towards the increasingly strict requirement of formulation
Regulation.On the other hand, the management in modern electric market and continually changing demand do not allow for grasping under constant loading condition
Make device.Alternatively, meeting the demand fluctuation including increasing or declining suddenly and the needs of control mains frequency being contributed to want
Ask very flexible operation.However, making the reduction of pollutant emission very harsh by such flexible operating, because lance must be balanced
The requirement of shield.
For example, one in the problem to be solved discharge for being related to nitrogen oxides (NOx) and carbon monoxide (CO).It is practical
On, CO be emitted on it is fully loaded under be generally not problem, and need to pay attention to the generation tended to the increased NOx of temperature.Vice versa, portion
Lower temperature under point load helps to maintain that NOx emission is very low, but can anti-blocking complete oxidation, and be conducive to carbon monoxide
Formation.
In order to solve the problems, such as equipped with the gas turbine of two-stage combustion device this, solution be substantially based on control supply
It is proposed to the temperature of the air-flow of continuous burning device.It is well known, however, that solution it is unsatisfactory, and it is personal need it is further
Discharge is reduced, especially declines low NOx drainage and under part load reduction CO discharges fully loaded.
Invention content
The purpose of the present invention is to provide a kind of second level burners of the continuous burning device for gas turbine, and control
The method that fixture has the continuous burning device of the gas turbine of first-stage burning device and second level burner, allows to overcome or at least
Alleviate the limitation.
According to the present invention, a kind of second level burner of the continuous burning device for gas turbine is provided, including：
Incinerator；
The combustion chamber that streamwise extends in incinerator downstream, wherein incinerator and combustion chamber form flow channel, and downstream
Flame location and upstream flame location limit in the combustion chamber；And
Downstream flameholder at the flame location of downstream.
Downstream flameholder allows the control as follows of second level burner, that is, so that in some cases, flame anchoring
And stablize in downstream flame location, it can be set to as it is expected close to combustor exit.Specifically, flame can be negative in height
It carries and stablizes at the flame location of downstream under mode of operation (for example, being fully loaded with or for the present load higher than high load threshold).Knot
Fruit realizes the residence time after very low flame for the mixture burned in combustion chamber.Close to full load state, flame temperature
Degree is very high and allows the complete oxidation of carbon, therefore avoids or at least reduce the generation of CO.High flame temperature will be instead for NOx
It is unfavorable to discharge, but it is effectively compensated by the residence time after low flame.Therefore, high flame temperature can be in acceptable NOx
Reach in emission level.However, the only fraction of combustion chamber lining is exposed to temperature high in this way, to be conducive to the longevity of component
Life.Due to the stabilizer in downstream, downstream flame location can accurately be set, and will not significantly be changed.
On the other hand, the flame at the flame location of upstream under setting section load is controllably made in second level burner,
Particularly for being less than the present load of low-load threshold (it can be less than or equal to high load threshold).Flame temperature is in fractional load
Under it is relatively low, and leading to the problem of for NOx is generally not.Alternatively, the residence time is higher after flame, and the complete oxygen of carbon occurs
Change, therefore keeps CO discharges relatively low.
According to an aspect of the present invention, mistake of the cross section streamwise of flow channel between incinerator and combustion chamber
It crosses in region and gradually changes, and transitional region is configured to prevent from flowing through the gas of combustion chamber and be recycled at the flame location of upstream.
Stream recycling or reflux can be generated by the unexpected increase of the cross section of the flow channel of streamwise, and usually
For generating the stagnant areas in the inlet of combustion chamber in known burner, because stagnant areas is conducive to flame anchor
It is fixed.However, flame anchoring may be difficult to be discharged in the presence of recirculation flow, once so flame is anchored on upstream flame location
Locate, then the stabilization of the flame at the flame location of downstream can be obstructed or it is made to become harsh.Steady mistake from incinerator to combustion chamber
Crossing contributes to discharge flame from upstream flame location as it is expected instead.The stability of flame at the flame location of upstream can
Reached by the control of the inlet temperature of the mixture burned in a combustion chamber.
Downstream flameholder can by be adapted to ensure that the mixture at the flame location of downstream light any arrange
Apply, that is, by improve mixture reactivity, by provide local heat source or by be locally conducive to mixture stagnate come
Implement.
Therefore, according to an aspect of the present invention, downstream flameholder include it is following at least one：
Downstream electrode system, the ignition energy being operable in providing combustion chamber at the flame location of downstream；
Downstream igniter at the flame location of downstream；And
The cross section variation of the combustion chamber of streamwise at the flame location of downstream, cross section variation configuration is at causing to flow through burning
The gas of room recycles at the flame location of downstream.
Any combinations of the variation of downstream electrode system, downstream igniter and cross section can be utilized by expectation.
According to an aspect of the present invention, elongated fairing is extended to from incinerator in combustion chamber, and is configured to anti-fluid stopping
The gas for crossing combustion chamber recycles at the flame location of upstream.
Fairing helps to maintain the smooth transition in the flow channel between incinerator and combustion chamber.For example, fairing
The centerbody that incinerator can smoothly be linked carrys out anti-backflow.
According to an aspect of the present invention, downstream electrode system includes under one group on the fairing at the flame location of downstream
Electrode is swum, and the downstream voltage supply line to stretch in fairing.
According to an aspect of the present invention, downstream igniter includes one group of downstream combustion on the fairing at the flame location of downstream
Expect nozzle, and the downstream fuel supply line extended in fairing.
In addition to providing its typical air power function, fairing is also a housing for voltage and/or fuel supply line.Therefore,
Downstream flameholder can be obtained in the case where not actual influence passes through the air-flow of combustion chamber, and combustion chamber is not affected significantly.
According to an aspect of the present invention, the variation in the cross section of combustion chamber by fairing butt downstream and surround down
Trip flame location defines at least one of the circumferential step in the combustor liner of combustion chamber and limits.
According to an aspect of the present invention, the upstream flameholder optionally actuated is provided in upstream flame location
Place.
Firm flame stabilization at the flame location of upstream is reached by upstream flameholder.The fluctuation of gasinlet temperature
It is reflected on the burning time and flame location of mixture.Upstream flameholder allows the variation for compensating flame location, otherwise
This can influence burning in the case where being based purely on the control of inlet temperature.What upstream flameholder can be selectively actuated
The fact allows for being easy to discharge flame from upstream flame location, for example, when gas turbine loads and increases, and deposit and stablize in downstream
The advantages of flame at flame location.
For example, upstream flameholder can be implemented by improving the reactivity of mixture or by providing local heat source.
According to an aspect of the present invention, upstream flameholder include it is following at least one：
Upstream electrode system, the ignition energy being operable in providing combustion chamber at the flame location of upstream；And
Upstream igniter at the flame location of upstream.
The combination of upstream electrode system and upstream igniter can be utilized as it is expected.
According to an aspect of the present invention, at least one intermediate flameholder is provided in upstream flame location and downstream flame
At corresponding intermediate flame location between position.
Pollutant emission can be further decreased by it is expected to provide additional stable flame location along combustion chamber.
According to an aspect of the present invention, a kind of gas turbine including continuous incinerator is provided, continuous incinerator includes
First-stage burning device and second level burner defined as above.
According to an aspect of the present invention, gas turbine includes controller, is configured to corresponding to higher than the first load threshold
Current flame location is set at the flame location of downstream in first mode of operation of the load value of limit, and corresponding to less than not
Current flame location is set in more than in the second mode of operation of the load value of the second load threshold of the first load threshold
It swims at flame location.
According to an aspect of the present invention, controller is configured to control the heat for flowing to second level burner from first-stage burning device
The hot gas temperature of gas.
In addition to being generally conducive to burning, control hot gas temperature helps to stablize flame location.In some cases,
Hot gas temperature control can be sufficient to stablize at the flame location of upstream.
According to an aspect of the present invention, controller is configured to selectively to actuate downstream flame in the first mode of operation steady
Determine device.
According to an aspect of the present invention, controller is configured to selectively to actuate upstream flame in the second mode of operation steady
Determine device.
According to an aspect of the present invention, provide a kind of having first-stage burning device and second level burner for control
The method of the continuous burning device of gas turbine, second level burner include：
Incinerator；
The combustion chamber extended along the flow direction in incinerator downstream, wherein incinerator and combustion chamber form flow channel, and downstream
Flame location and upstream flame location limit in the combustion chamber；
This method is included in current flame location in the first mode of operation corresponding to the load value higher than the first load threshold
Stablize at the flame location of downstream, and corresponding to the load value less than the second load threshold no more than the first load threshold
Current flame location is stablized at the flame location of upstream in second mode of operation.
According to an aspect of the present invention, it includes that control flow to second level combustion from first-stage burning device to stablize current flame location
The hot gas temperature of the hot gas of burner.
Description of the drawings
The present invention is will now be described with reference to the attached figures, attached drawing shows the non-limiting embodiment of some present invention, attached
In figure：
Fig. 1 is the simplified block diagram of Gas Turbine Modules；
Fig. 2 is the longitudinal section of the continuous burning device across the second level burner including an embodiment according to the present invention；
Fig. 3 is across the longitudinal section of second level burner according to another embodiment of the present invention；
Fig. 4 is across the longitudinal section of second level burner according to another embodiment of the present invention；
Fig. 5 is across the longitudinal section of second level burner according to another embodiment of the present invention；
Fig. 6 is across the longitudinal section of second level burner according to another embodiment of the present invention；
Fig. 7 is across the longitudinal section of second level burner according to another embodiment of the present invention；And
Fig. 8 is across the longitudinal section of second level burner according to another embodiment of the present invention.
Specific implementation mode
Fig. 1 shows the simplification view of the Gas Turbine Modules generally indicated with number 1.Gas Turbine Modules 1 include
Compressor section 2, burner assembly 3 and turbine 5.Compressor 2 and turbine 3 extend along main shaft A.Compressor section
The air stream compressed in 2 is mixed with fuel, and is burned in burner assembly 3, may be added with diluent air.The mixture of burning
Then it is expanded to turbine 5, and is converted into mechanical energy.
It is configured to limit the controller 7 of the set point for gas turbine from 8 reception state signal of sensor, and passes through rush
Dynamic device 9 operates gas turbine to provide controlled power output.
Burner assembly 3 is two-stage continuous burning device, and includes multiple tubular burners 10 around main shaft A arrangements.
Each in one of them tubular burner 10 shown in figure 2 includes continuously arranging and limiting the of flow channel 15
Single-stage combustion device 12 and second level burner 13.
More specifically, first-stage burning device 12 includes incinerator 16 and combustion chamber 17.For delivering fuel to second
The fuel gun 18 of grade burner 13 extends axially through combustion chamber 17.
The second level burner 13 being shown in further detail in figure 3 is including incinerator 20, combustion chamber 21 and for being attached to this
In unshowned turbine 5 transition element 22.
Incinerator 20 is configured to the combustion for mixing the thermal current received from first-stage burning device 12 and being received via fuel gun 18
Material.Incinerator 20 includes the outer wall 24 extended along incinerator axis and centerbody 25.In incinerator 20, flow channel 15 is by wall
It 24 and is defined by centerbody 25.Fuel is ejected into via injector (not shown) in flow channel 15.
Combustion chamber 21 extends in 20 downstream streamwise of incinerator.In one embodiment, combustion chamber 21 includes outer lining
27, inside liner 28 and elongated fairing 30.Outer lining 27 wraps inside liner 28 at a certain distance from from inside liner, in order to will be cold
But channel 31 is limited between outer lining 27 and inside liner 28.Inside liner 28 defines flow channel 15 outside in combustion chamber 21,
And link the wall 24 of incinerator 20 in such a way, to limit the smooth transition of no step and possible sharp edge.
In one embodiment, the neighboring edge of the edge matching inside liner 27 of wall 24.
Fairing 30 is extended substantially in the axial direction from incinerator 20 into combustion chamber 21, until its outlet, and also with such one
Kind mode links the centerbody 25 of incinerator 20, to limit the smooth transition of no step and possible sharp edge.
Due on the one hand between inside liner 27 and wall 24 and on the other hand steady between fairing 30 and centerbody 25
Connection, therefore in the transitional region 32 between incinerator 20 and combustion chamber 21, the cross section streamwise of flow channel is gradual
Change.Therefore, transitional region is configured to prevent from flowing through the gas recycling of combustion chamber 21 and generates stagnant areas.
Downstream flame location 33 and upstream flame location 34 from being separated from each other are limited in combustion chamber 21.Implement one
In example, downstream flame location 33 is limited to the exit of combustion chamber 21, and upstream flame location 34 is limited to incinerator 20 and combustion
It burns in the transitional region 32 between room 21, for example, the inlet in combustion chamber 21.By this method, available whole in combustion chamber 21
A space can be used for minimizing the residence time after the flame under fully loaded and high temperature, and improve air and fuel mixing, therefore reduce
NOx emission, and the residence time after the flame under the fractional load and low temperature is maximized, therefore reduce CO discharges.On however,
Swim flame location smaller in the example of Fig. 2 and 3 compared with the distance between downstream flame location.
Downstream flameholder 35 and upstream flameholder 36 are separately positioned on downstream flame location 33 and upstream flame
At position 34.
In one embodiment, downstream flameholder 35 includes downstream electrode system, is operable in downstream flame position
The ignition energy provided at 33 in combustion chamber 21 is provided.Downstream electrode system includes on the fairing 30 at downstream flame location 33
One group of downstream electrode 37, and the downstream voltage supply line 38 that stretches in fairing 30 and fuel gun 18.Pass through downstream electrical
Pole 37, downstream flameholder 35 generates the spark across combustion chamber 21, and the mixture for flowing through combustion chamber 21 is caused to be ignited,
Regardless of the automatic burning time of state of temperature and mixture.In this regard, the automatic burning time of mixture can be growed even
Mixture is made to will not be in automatic combustion in combustion chamber 21, but downstream flameholder 35 under any circumstance can will
Flame stabilization is at downstream flame location 33.
Upstream flameholder 36 includes upstream electrode system, is operable to provide burning at upstream flame location 34
Ignition energy in room 21.Upstream electrode system includes one group of upstream electrode on the fairing 30 at upstream flame location 34
39 and upstream voltage supply line 40.In an embodiment (not shown), upstream electrode 39 can be in incinerator 20 and combustion chamber 21
Between interface be arranged on the centerbody 35 of incinerator 20.
Downstream flameholder 35 and upstream flameholder 36 are based on the load determined for Gas Turbine Modules 1 by controlling
Device 7 processed selectively actuates.When load is more than high load threshold, controller 7 actuates downstream flameholder 35, and deactivates
Flameholder 36 is swum, therefore current flame location is set at downstream flame location 33.Alternatively, when load is less than low
When loading threshold, controller 7 actuates upstream flameholder 36, and deactivates downstream flameholder 35.Therefore, current flame position
It installs and is scheduled at upstream flame location 34.Low-load threshold does not exceed high load threshold.
In an embodiment shown in Fig. 4, second level burner 113 includes incinerator 120 and combustion chamber 121.Burning
Room 121 includes the downstream flameholder 135 at downstream flame location 133, substantially as described with reference to Fig. 2 and 3, and
Upstream flameholder 136 at the upstream flame location 134 of the inlet of combustion chamber 121.Incinerator 120 and combustion chamber
121 are configured to prevent the recycling of the thermal current at upstream flame location 134.
Upstream flameholder 136 is limited by upstream igniter, and upstream igniter includes upstream fuel nozzle 139 and connection
To upstream fuel nozzle 139 and stretch across the upstream fuel supply line 140 of fuel gun 18.Upstream fuel nozzle 139 is circumferentially
Direction is evenly distributed on fairing (being indicated here by 130), and the form for the injection catheter that can be radially extended provides,
Conduit terminates at the intermediate radial distance between fairing 130 and the inside liner (being 128 here) of combustion chamber 121.As standby
Select embodiment (not shown), upstream fuel nozzle that can be provided in the side surface of fairing 130 with opening form.
Fig. 5 shows another embodiment of the present invention.In this case, second level burner 213 includes 220 He of incinerator
Combustion chamber 221.Combustion chamber 221 after and the downstream flameholder 235 that is included at downstream flame location 233, and burning
Upstream flameholder 236 at the upstream flame location 234 of the inlet of room 221.Incinerator 220 and combustion chamber 221 configure
At the recycling for preventing the thermal current at upstream flame location 234.
Downstream flameholder 235 is limited by downstream igniter, and downstream igniter has the stream at downstream flame location 233
One group of downstream fuel nozzle 241 in wire body (here by 230 indicate), and it is attached to downstream fuel nozzle 241 and in streamline
The downstream fuel supply line 242 to stretch in body 230.Downstream fuel nozzle 241 is evenly distributed in fairing 230 along circumferential direction
On, and the form for the injection catheter that can be radially extended provides, conduit terminates at the liner of fairing 230 and combustion chamber 221
In intermediate radial distance between (here by 228 indicate).Alternately, the form that downstream fuel nozzle can also be open carries
For in the side surface of fairing 230.
Equally, upstream flameholder 236 is limited, upstream igniter by upstream igniter (with reference to as described in Fig. 4)
Including upstream fuel nozzle 239, and it is attached to upstream fuel nozzle 239 and extends through the upstream fuel supply of fuel gun 18
Line 240.
Gas turbine is based on by controller 7 to the fuel supply of downstream flameholder 235 and upstream flameholder 236
1 present load determines.Specifically, controller actuates downstream flameholder when present load is more than high load threshold
235 and deactivate upstream flameholder 236；And actuate upstream flameholder 236 when present load is less than low-load threshold
And deactivate downstream flameholder 235.
In one embodiment shown in figure 6, second level burner 313 includes incinerator 320 and combustion chamber 321.Combustion
It includes outer lining 327, inside liner 328 and elongated fairing 330 to burn room 321.Substantially as described in reference Fig. 2 and 3, inside liner
328 define flow channel 315 outside in combustion chamber 321, and link the wall 324 of incinerator 320 in such a way, so as to
Limit the smooth transition of no step and possible sharp edge.
Fairing 330 is extended substantially in the axial direction from incinerator 320 into combustion chamber 321, until its outlet, and also in this way
A kind of mode links the centerbody 325 of incinerator 320, to limit the smooth transition of no step and possible sharp edge.
Downstream flame location 333 and upstream flame location 334 are limited in combustion chamber 321 with being separated from each other, and downstream
Flameholder 335 and upstream flameholder 336 are separately positioned at downstream flame location 333 and upstream flame location 334.
Downstream flameholder 335 includes the cross section of the combustion chamber 321 of the streamwise at downstream flame location 333
Variation.Cross section variation configuration is recycled at downstream flame location 333 at causing the gas for flowing through combustion chamber 321.In Fig. 6
Embodiment in, the variation of the cross section of combustion chamber 321 by fairing 330 butt downstream 330a, and by surrounding downstream
Flame location 333 defines the restrictions of the circumferential step 328a in the inside liner 327 of combustion chamber 321.However, in unshowned other realities
It applies in example, the variation of cross section can be only by the butt downstream of fairing, or is only limited by the circumferential step of inside liner.
Upstream flameholder 336 may include such as the upstream electrode system with reference to disclosed in Fig. 2 and 3.Alternately, upstream fire
Flame stabilizer may include upstream igniter.
Fig. 7 shows another embodiment, and wherein second level burner 413 includes incinerator 420 and combustion chamber 421.Downstream
Flame location 433 and upstream flame location 434 are limited in combustion chamber 421 with being separated from each other, and downstream flameholder 445
It is arranged at downstream flame location 433.Downstream flameholder 435 can be previously described type, it may for example comprise electrode system
The variation of the cross section of system, igniter or flow channel.In the example in figure 7, the streamline in combustion chamber 421 is arranged in electrode 437
On body 430, with the voltage supply line 438 in fairing 430.
As described with reference to figure 2 and 3, the transitional region 432 between incinerator 420 and combustion zone 421 is configured to prevent
The gas for flowing through combustion chamber recycles at upstream flame location 434.
Controller 7 is configured to control the inlet gas from first-stage burning device 12 to the hot gas of second level burner 413
Temperature, and the present load based on gas turbine 1 selectively actuates downstream flameholder 435 by expectation.In order to control into
The purpose of implication temperature, controller 7 for example may act on the power conveyed by first-stage burning device 12 and burn with by the second level
The power dividing for the power that device 413 conveys or power ratio, and/or mixed before acting on into second level burner 413 to next
From the diluent air stream of the hot gas of first-stage burning device 12.In the case, without the help of upstream flameholder, controller
Current flame location is set at upstream flame location 434 by the control of 7 temperature in use.In an embodiment (not shown), first block of data 50,
Controller can be by alternately or additionally in controlling gasinlet temperature come by current flame location using the stabilizer in combustion chamber
It is also set at the flame location of downstream.In the case, current flame location can be controlled by temperature, or by means of alternative
Upstream flameholder that ground actuates is set at the flame location of upstream.
In an embodiment as shown in fig. 8, second level burner 513 includes incinerator 520 and combustion chamber 521.Downstream
Flameholder 535 and upstream flameholder 536 are separately positioned on the downstream flame location 533 being defined in combustion chamber 521
At place and upstream flame location 534 on the fairing 530 of combustion chamber 521.In addition, one or more intermediate flame locations 550 limit
It is scheduled in the combustion chamber between upstream flame location 234 and downstream flame location 233, and corresponding intermediate flameholder 551
It is arranged at each intermediate flame location 550.Incinerator 520 and combustion chamber 521 are configured to prevent at upstream flame location 534
The recycling of thermal current.
Downstream flameholder 535 and upstream flameholder 536 may include electrode system, be respectively provided with one group of downstream
Electrode 537 and downstream voltage supply line 538 and one group of upstream electrode 539 and upstream voltage supply line 540.Each intermediate fire
Flame stabilizer 551 includes the corresponding set of target 552 at corresponding intermediate flame location 550, and in fairing 530
With the corresponding voltage supply line 553 to stretch in fuel gun 18.
Such as downstream flameholder 535, upstream flame location 536 is each by control in intermediate flameholder 551
Device 7 processed optionally actuates, to be set in current flame location based on the present load of gas turbine 1 as it is expected
At corresponding intermediate flame location 550.
It is finally apparent that the method for the second level burner and control continuous burning device can undergo change and variation, without
The scope of the present invention as defined in the appended claims can be detached from.
Claims (17)
1. a kind of second level burner of continuous burning device for gas turbine, including：
Incinerator (20;120;220;320;420;520)；
Streamwise is in the incinerator (20;120;220;320;420;520) combustion chamber (21 that downstream extends;121;
221;321;421;521), wherein the incinerator (20;120;220;320;420;And the combustion chamber (21 520);121;
221;321;421;521) flow channel (15), and downstream flame location (33 are formed;133;233;333;433;And upstream 533)
Flame location (34;134;234; 334;434;534) it is limited to the combustion chamber (21;121;221;321;421;521) in,
And
In the downstream flame location (33;133;233;333;433;533) the downstream flameholder (35 at place;135;235;
335;435;535)。
2. second level burner according to claim 1, wherein the cross section of the flow channel (15) is burnt described
Burner (20;120;220;320;420;520) with the combustion chamber (21;121;221;321;421;521) transition region between
Domain (32;432) it is gradually changed along the flow direction in and the transitional region (32;432) it is configured to prevent from flowing through described
Combustion chamber (21;121;221;321;421;521) gas is in the upstream flame location (34;134;234;334; 434;
534) place recycles.
3. the second level burner according to claim 1 or claim 2, which is characterized in that the downstream flame stabilization
Device (35;135;235;335;435;535) include it is following at least one：
Downstream electrode system (37,38;437,438;537,538) it, is operable in the downstream flame location (33;133;
233;333;433;533) place provides the combustion chamber (21;121;221;321; 421;521) ignition energy in；
In the downstream flame location (33;133;233;333;433;533) the downstream igniter (241,242) at place；And
In the downstream flame location (33;133;233;333;433;533) the place combustion chamber (21;121;221;321;
421;521) along the variation of the flow direction, the variation of the cross section (328a, 330a) matches for cross section (328a, 330a)
Being set to causes to flow through the combustion chamber (21;121;221;321;421;521) gas is in the downstream flame location (33;
133;233;333;433;533) place recycles.
4. second level burner according to claim 3, the second level burner includes elongated fairing (30;130;
230;330;430;530), from the incinerator (20;120;220;320;420;520) combustion chamber (21 is extended to;
121;221;321;421;521) it in, and is configured to prevent from flowing through the combustion chamber (21;121;221;321;421;521) gas
Body is in the upstream flame location (34;134;234;334;434;534) place recycles.
5. second level burner according to claim 4, wherein the downstream electrode system (37,38;437,438;
537,538) it is included in the downstream flame location (33;433;533) fairing (30 at place;430;530) one group on
Downstream electrode (37;437;537), and in the fairing (30;430;530) the downstream voltage supply line (38 that inside stretches;
437;538)。
6. according to the second level burner described in claim 4 or claim 5, wherein the downstream igniter (241,242)
One group of downstream fuel nozzle (241) being included on the fairing (230) at the downstream flame location (233), and
The downstream fuel supply line (242) to stretch on the inside of the fairing (230).
7. the second level burner according to any one of claim 4 to claim 6, wherein the combustion chamber (321)
Cross section (328a, 330a) variation by the fairing (330) butt downstream (330a) and around the downstream fire
Define at least one of the circumferential step (328a) in the combustor liner (328) of the combustion chamber (321) in flame position (233)
It limits.
8. second level burner according to any one of the preceding claims comprising in the upstream flame location (34;
134;234;334;434;534) the upstream flameholder (36 optionally triggered at place;136;236;336;536).
9. second level burner according to claim 8, wherein the upstream flameholder (36;136;236;
336;536) include it is following at least one：
Upstream electrode system (39,40;539,540) it, is operable in the upstream flame location (34;134;234;334;
434;534) place provides the combustion chamber (21;121;221;321;421;521) ignition energy in；And
In the upstream flame location (34;134;234;334;434;534) the upstream igniter (139,140 at place;239,
240)。
10. according to the second level burner described in claim 8 or claim 9 comprising in the upstream flame location
(34;134;234;334;434;534) with the downstream flame location (33;133;233;333;433;533) corresponding between
At least one intermediate flameholder (551) at intermediate flame location (551).
11. a kind of gas turbine including continuous incinerator, the continuous incinerator include first-stage burning device (12) and according to
The second level burner (13 of any one described in preceding claims;113;213;313;413;513).
12. gas turbine according to claim 11 comprising controller (7) is configured to corresponding to higher than first
It loads in the first mode of operation of the load value of threshold and current flame location is arranged in the downstream flame location (33;133;
233;333;433;533) place, and corresponding to the load value less than the second load threshold no more than the first load threshold
The current flame location is arranged in the upstream flame location (34 in second mode of operation;134;234;334;434;
534) place.
13. gas turbine according to claim 12, wherein the controller (7) is configured to control from the first order
Combustor flow to the hot gas of the second level burner hot gas temperature.
14. according to the gas turbine described in claim 12 or claim 13, wherein the controller (7) is configured in institute
It states and selectively actuates the downstream flameholder (35 in the first mode of operation;135;235;435;535).
15. according to the gas turbine being subordinated to described in the claim 14 of claim 8, wherein the controller (7) is configured to
The upstream flameholder (36 is selectively actuated in second mode of operation;136;236;336;536).
16. a kind of control has first-stage burning device (12) and second level burner (13;113;213;313;413;513) combustion
The method of the continuous burning device of gas-turbine, the second level burner include：
Incinerator (20;120;220;320;420;520)；
Streamwise is in the incinerator (20;120;220;320;420;520) combustion chamber (21 that downstream extends;121;
221;321;421;521), wherein the incinerator (20;120;220;320; 420;And the combustion chamber (21 520);121;
221;321;421;521) flow channel (15), and downstream flame location (33 are formed;133;233;333;433;And upstream 533)
Flame location (34;134;234;334;434;534) it is limited to the combustion chamber (21;121;221;321;421;521) in,
The method includes in the first mode of operation corresponding to the load value higher than the first load threshold by current flame position
It sets and stablizes in the downstream flame location (33;133;233;333;433;533) place, and corresponding to less than no more than described
The current flame location is stablized in institute in second mode of operation of the load value of the second load threshold of the first load threshold
State upstream flame location (34;134;234;334;434;534) place.
17. according to the method for claim 16, wherein it includes controlling from the first order to stablize the current flame location
Combustor flow to the hot gas of the second level burner hot gas temperature.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP17158577.1A EP3367001B1 (en) | 2017-02-28 | 2017-02-28 | Second-stage combustor for a sequential combustor of a gas turbine |
| EP17158577.1 | 2017-02-28 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108506962A true CN108506962A (en) | 2018-09-07 |
| CN108506962B CN108506962B (en) | 2021-09-24 |
Family
ID=58192218
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810168642.0A Active CN108506962B (en) | 2017-02-28 | 2018-02-28 | Second stage combustor for a sequential combustor of a gas turbine |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3367001B1 (en) |
| CN (1) | CN108506962B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4394253A1 (en) * | 2022-12-30 | 2024-07-03 | Ansaldo Energia Switzerland AG | Gas turbine engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2287312A (en) * | 1994-02-24 | 1995-09-13 | Toshiba Kk | Gas turbine combustion system |
| CN101539305A (en) * | 2003-09-05 | 2009-09-23 | 德拉文公司 | Pilot combustor for stabilizing combustion in gas turbine engines |
| CN104541104A (en) * | 2012-08-24 | 2015-04-22 | 阿尔斯通技术有限公司 | Sequential combustion with dilution gas mixer |
| EP3015772A1 (en) * | 2014-10-31 | 2016-05-04 | Alstom Technology Ltd | Combustor arrangement for a gas turbine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2771743A (en) * | 1951-08-10 | 1956-11-27 | Rolls Royce | Gas-turbine engine with reheat combustion equipment |
| US2974488A (en) * | 1956-11-27 | 1961-03-14 | Snecma | Combustion devices for continuous-flow internal combustion machines |
| FR1525092A (en) * | 1967-01-23 | 1968-05-17 | Snecma | Hot gas flow and cold air flow turbo-reactor |
| FR2595791B1 (en) * | 1986-03-14 | 1989-07-28 | Centre Nat Rech Scient | LOW EMISSION OF POLLUTANT GAS BURNER |
-
2017
- 2017-02-28 EP EP17158577.1A patent/EP3367001B1/en active Active
-
2018
- 2018-02-28 CN CN201810168642.0A patent/CN108506962B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2287312A (en) * | 1994-02-24 | 1995-09-13 | Toshiba Kk | Gas turbine combustion system |
| CN101539305A (en) * | 2003-09-05 | 2009-09-23 | 德拉文公司 | Pilot combustor for stabilizing combustion in gas turbine engines |
| CN104541104A (en) * | 2012-08-24 | 2015-04-22 | 阿尔斯通技术有限公司 | Sequential combustion with dilution gas mixer |
| EP3015772A1 (en) * | 2014-10-31 | 2016-05-04 | Alstom Technology Ltd | Combustor arrangement for a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108506962B (en) | 2021-09-24 |
| EP3367001A1 (en) | 2018-08-29 |
| EP3367001B1 (en) | 2020-12-23 |
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