CN105102894B - Burner assembly, the combustion chamber including the burner assembly and the method for supplying fuel to the burner assembly - Google Patents
Burner assembly, the combustion chamber including the burner assembly and the method for supplying fuel to the burner assembly Download PDFInfo
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- CN105102894B CN105102894B CN201380065883.8A CN201380065883A CN105102894B CN 105102894 B CN105102894 B CN 105102894B CN 201380065883 A CN201380065883 A CN 201380065883A CN 105102894 B CN105102894 B CN 105102894B
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- Prior art keywords
- auxiliary
- burner
- fuel flow
- convection current
- current time
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00013—Reducing thermo-acoustic vibrations by active means
Abstract
A kind of burner assembly of combustion chamber for gas turbine unit, it is provided with：It is configurable to generate the main burner of the primary combustion zone with the main convection current time；Being configured as at least generation has the secondary burner in secondary combustion region of secondary convection current time；It is different from the main convection current time that the secondary burner is configured to the secondary convection current time.
Description
Technical field
The present invention relates to burner assembly, the combustion chamber including the burner assembly and supply fuel to the burning
The method of device assembly.Especially, the present invention relates to be used for the combustion chamber of the gas pipeline of energy production unit.
Background technology
Known combustion device assembly generally includes the high-temp combustion portion of main low-temperature burning portion and secondary, and its stabilization is by master
Want the flame that portion is generated.
It is unstable due to being constantly present thermoacoustic in combustion system, so needing the operating stably of secondary section.Thermoacoustic is unstable
Surely it is the phenomenon characterized by the presence of thermoacoustic flame oscillation, its generation pressure wave.The such pressure propagated in a combustion chamber
Reeb, reflects on the wall of combustion chamber and reaction is on flame.These thermal acoustic oscillations can increase unstability until damaging
The wall of bad combustion chamber, or they can weaken.
Thus, when by burning process excite thermal acoustic oscillation and they increased with amplitude when, there is unstable sternness
Condition.
" the A Mechanism of Combustion Instability according to the article by Tim lieuwen et al.
The in Lean Premixed Gas Turbine Combustors (combustion instabilities in poor pre-mixing gas combustion turbine combustion room
The mechanism of property) ", Transaction of ASME (ASME can report), Vol (volume) .123,2001 is defined
, when heat release fluctuation with pressure oscillation with phase when, there is combustion instability.Therefore, shaken by pressure oscillation and thermoacoustic
Time delay T management unstability between swinging.
Time delay T is interfered significantly on by " convection current time " τ, it is each the fuel supply line in burner assembly
It is distinctive.Especially, time delay T and convection current time τ is constrained by lower relation of plane：
T/Tperiod=f (τ, the length of flame, kinematics chemical reaction)
Wherein
T is time delay；And
Tperiod is the time corresponding with the vibration completely fluctuated in combustion chamber.Wherein by fluctuation be desired for heat fluctuation and
Both pressure oscillations, it has identical cycle but different phases.
The accurate evaluation of T can be performed by experimental study or by large eddy simulation (LES) computational methods.
In the combustion system with " poor premix (lean premix) " technology, wherein implement premixed flame, by by
The space that convection current time τ is defined as being traveling between fuel injection point and flame pedestal by the time that mixing is implemented, according to following
Relation：
τ=Linj/Uavg
Wherein：
Linj is the distance between fuel injection point and flame pedestal；
Uavg is the average speed in the mixing in the Linj for stretching.
Due to combustion temperatures, secondary section is responsible for most of disposals of pollutants.According to ignition temperature, actual pollutant is pointed to
The dynamics of the chemical reaction of formation is represented depending on the temperature for not being High Linear, and the index of pollutant increases.
Correspondingly, supply on restriction is limited to the quality of fuel of secondary section with preventing from exceeding the law related to disposal of pollutants
System., also comprising the subsequent limitation of the fuel flow rate for being fed to main portion, the action that it needs to stablize secondary section is with can for this
Generation is burnt astatically.
In a word, because the method for controlling the rough burning device for reducing discharge or vice versa, limits known type
Burner assembly performance.
Only in a given situation (wherein, the complexity of usual combustion system is dramatically increased), can exceed known
Burner assembly in stabilization limitation.
Disclosure of the invention
It is an object of the invention to enable high-performance combustor component stabilization burning to occur and can accord with the same time
Close the legal restriction related to disposal of pollutants.
Especially, it is an object of the invention to enable particularly flexible burner assembly to increase range of capacity, at it
Middle unit can be run while discharge is maintained at below legal restriction.
According to purpose so, the present invention relates to the burner of the combustion chamber of gas turbine unit according to claim 1
Component.
Other purpose of the invention is high-performance combustion chamber is generated stabilization burning and can be met and pollution
Discharge related legal restriction.
According to purpose so, the present invention relates to combustion chamber as claimed in claim 12.
Finally, other purpose of the invention is to provide a kind of method for supplying fuel to burner assembly, the burning
Device assembly can aid in the burning of generation stabilization and can meet the legal restriction related to disposal of pollutants.
According to such purpose, the method the present invention relates to supply fuel to fuel assembly as claimed in claim 13.
The brief description of accompanying drawing
Diagram other feature of the invention according to the description below its non-limiting example, referring to the drawings and excellent
Point will become apparent, wherein：
Fig. 1 is the diagrammatic view for including the gas turbine unit 1 of the combustion chamber according to embodiment；
Fig. 2 is burner of the invention, with the viewgraph of cross-section for clear removed part.
For preferred embodiment of the present invention
Label 1 in Fig. 1 is indicated with the gas pipeline 2, compressor 3, combustion chamber 4 extended along axle A, for that will fire
Material is fed to the component 6 of combustion chamber 4 and the powerplant module of generator 7, the machinery that the generator will be supplied by gas pipeline 2
Power-supply change-over is electric power.
Combustion chamber 4 includes multiple seated connections (seat) 8, and each uses suitable for burned device assembly 9 and (preferably represents
In fig. 2).Seated connection 8 is arranged along the circular path of the periphery edge close to combustion chamber 4.What is be described herein and show is non-
In limitative examples, combustion chamber 4 is annular type and there is 24 seated connections 8 and burner assembly 9.
Reference picture 2, each burner assembly 9 extends and including main burner 10 and secondary burner 11 along axle B.
Secondary burner 11 extends substantially along axle B, and main burner 10 is in the secondary burner 11 parallel with axle B
Surrounding extends.
Main burner 10 is configured to supply air-fuel mixture and defines primary combustion zone 12 and (shown with chain-dotted line
Show in figure to meaning property).
Air and fuel are supplied along the supply direction D1 of the inside for pointing to combustion chamber 4.
Especially, main burner 10 includes air supply ring duct 13 and fuel supply ring duct 14.
Air supply ring duct 13 receives air and with the reduction radial direction height in direction D1 is supplied from compressor 3
Spend to generate the conduit of substantial truncated cone.
Fuel supply ring duct 14 extends parallel to axle B and ends in multiple nozzles 15, and it region be directly facing air confession
Answer ring duct 13.
Air supply ring duct 13 is provided in end 16 extend parallel to axle B, with cylindrical outer element 18.
Along supply ring duct 13 (the preferably downstream of nozzle 15) arrangement cyclone 17, it is configured as lifting vortex
Generation promoting the mixing between air and fuel.Especially, cyclone 17 is suitable to flow through its mixture around axle B rotations
Turn in order to stabilize the flame for being generated and the flame for allowing the more preferable inside for controlling and being located at combustion chamber 4.
Cyclone (swirler) 17 includes multiple blades (not shown in the accompanying drawings), and it is fastened at and defines air supply ring
The wall of shape conduit 13.
What is extended close to the end 16 of air supply ring duct 13 and cylindrical outer element 18 is primary combustion zone
12, air supply ring duct 13 is risen in the burning of wherein air-fuel mixture.
Primary combustion zone 12 has main convection current time τp.According to above-mentioned definition, main convection current time τpIt is to be implemented by fuel
, the time being traveling in the distance between nozzle 15 and primary combustion zone 12.
Main convection current time τpDepending on the solid of main burner 10, launch the position of nozzle 15 depending on fuel and take
Certainly in it is determined that the hydrodynamics and kinematic conditions of the position of primary combustion zone 12.
Although the low production for disposal of pollutants is had a responsibility for (due to low combustion temperature), primary combustion zone 12 is characterized as
Low combustion stability.Lean combustion stability is included therein all primary combustion zones 12 of localization heat release.
Ring duct 14 (see Fig. 1) is supplied with main fuel flow velocity QP supply fuel, is advantageously led to as shown in following details
The control device 19 for crossing component 6 is adjusted to it for supplying fuel (Fig. 1).Secondary burner 11 is configured to supply partly-premixed
The air-fuel mixture of conjunction and define one or more secondary combustion regions 20 and (be shown schematically in dotted line
Figure in).
Ignition temperature in secondary combustion region 20 exists more than the ignition temperature and feature in primary combustion zone 12
In low temperature changeability.
Preferably secondary burner 11 is configured to secondary combustion region 20 and overlaps primary combustion zone 12 at least in part.
Preferably, secondary combustion region 20 is contained in primary combustion zone 12 substantially unitaryly.
Secondary combustion region 20 has secondary convection current time τs.According to above-mentioned definition, secondary convection current time τsIt is by combustion
It is that material is implemented, be traveling in the distance between the nozzle of fuel for supplying secondary burner 11 and secondary combustion region 20
Time.
Secondary convection current time τsDepending on the solid of secondary burner 11, secondary burner is transmitted into depending on by fuel
The position of 11 nozzle and the hydrodynamics and kinematic conditions of the position depending on determination primary combustion zone 20.
Secondary burner 11 is configured to supply with different from main convection current time τpSecondary convection current time τsSecondary combustion
Burn region 20.
The thermoacoustic ripple that is generated by main burner 10 and the thermoacoustic ripple that is generated by secondary burner 11 independently phase
Mutually propagate.
The appropriately configured of secondary burner 11 allows to change convection current time τsWill pass through what secondary burner 11 was generated
Thermoacoustic ripple does not cause constructive interference, and it can cause increased unstability and accordingly result in the damage of combustion chamber 4.
Preferably, configuration secondary burner 11 is so as in the thermoacoustic ripple generated by main burner 10 and by secondary burner
There is destruction interference between the 11 thermoacoustic ripples for being generated.Substantially, the thermoacoustic ripple generated by secondary burner 11 is prevented
With the thermoacoustic ripple generated by main burner 10 is with phase and causes mutually intervention long to be important.If secondary convection current time τs
With main convection current time τpIt is different then meet situation so.So as to whole time delay T lack prolonging for region with individually main
The slow time is different and can be by changing secondary convection current time τsMode it is modulated.
In the non-limiting example for being described herein as and showing, secondary burner 11 includes the first auxiliary burner 24 and the
Two auxiliary burners 25, both of which is capable of the diffusion combustion of generating portion premixing.
Especially, the first auxiliary burner 24 is pre- in each the first auxiliary combustion region 27 (being represented by dashed line) generating portion
The diffusion combustion of mixing, while the second auxiliary burner 25 is in each the second auxiliary combustion region 28 (being represented by dashed line) generating unit
Divide the diffusion combustion of premixing.
First auxiliary combustion region 27 and the second auxiliary combustion region 28 help to define secondary combustion region 20.As above
State, preferably the first auxiliary combustion region 27 and the second auxiliary combustion region 28 are fully contained in primary combustion zone 12.
First auxiliary combustion region 27 had for the first auxiliary convection current time τs1And extended to from cylindrical outer element 18
Apart from d1, while the second auxiliary combustion region 28 had for the second auxiliary convection current time τs2And extend from cylindrical outer element 18
To apart from d2.
Preferably, it is more than apart from d1 apart from d2.
According to as defined above, the first auxiliary convection current time τs1It is the fuel by being fed to the first auxiliary burner 24
The time in the first auxiliary combustion region 27 is reached, while the second auxiliary convection current time τs2It is by being fed to the second auxiliary burner
25 fuel reaches the time in the second auxiliary combustion region 28.
Preferably, the second auxiliary convection current time τs2With the first auxiliary convection current time τs1Difference about 1-2ms, while first
Auxiliary convection current time τs1With main convection current time τpDifference about 2-3ms.
The purpose for stabilization is experimentally found, by the first auxiliary burner 24 and by the second auxiliary combustion
Effect caused by device 25 is supplement and is characterised by the different efficiency based on loading condition.Preferably the first auxiliary combustion
Device 24 is designed to the stabilization primary combustion zone 12 under full load service condition, while the second auxiliary burner 25 is designed to
Low-load stabilization primary combustion zone 12.
The research of the distribution of the temperature on flame 16 represents that the second auxiliary burner 25 can also promote by main burning
The operating stably caused by the first auxiliary burner 24 in region 12.This determination elevated temperature in primary combustion zone 12
Uniformity.
The first embodiment of the first auxiliary burner 24 and the first embodiment of the second auxiliary burner 25 are described below.
Such embodiment is described by way of non-limiting example.In fact, in the presence of suitable for respectively in the first auxiliary
The first auxiliary burner of the diffusion combustion of generating portion premixing and the in combustion zone and in the second auxiliary combustion region
The other embodiment of two auxiliary burners.First auxiliary combustion region and the second auxiliary combustion region are at least partially contained within master
In combustion zone.First auxiliary convection current time τs1With the second auxiliary convection current time τs2With main convection current time τpIt is different.
Especially, the first auxiliary burner 24 be provided be fed directly to the air supply circular passage 30 of combustion chamber 4 with
And fuel supply circular passage 31, wherein fuel supply circular passage extends parallel to and flows into and circular passage with axle B
The end of the close circular passage 30 of 30 external margin 33.
Cyclone 34 is arranged in the external margin 33 of circular passage 30 and the edge of circular passage 31, it is configured to make a living
Into being vortexed and promote the mixing risen in respectively between circular passage 30 and the air and fuel of circular passage 31.Especially,
Cyclone 34 is suitable to flow through its mixture and is rotated with the generated flame of stabilization around axle B and allow preferably control to be located at
Flame inside combustion chamber 4.
As that will see in detailed below, under the control of the control device 19 of component 6, with the first auxiliary fuel flow velocity
QA1 supplies ring duct 31 to provide fuel (Fig. 1).
Second auxiliary burner 25 is provided with burning supply circular passage 35, and the air that it flows directly into main burner 10 is supplied
Answer ring duct 13.
Especially, circular passage 35 is provided with multiple nozzles 35, and it is along the inwall of air supply ring duct 13 by cloth
Put at the position being included between the spray site of nozzle 15 and cylindrical outer element 18.
Preferably, in the arranged downstream nozzle 36 of cyclone 17.
The position influence second of nozzle 36 aids in convection current time τs2.Especially, set up with design procedure and experimental procedure
The position of nozzle 36.
Calculating instrument is used in design procedure, it is it can be considered that pneumatic, acoustics and chemistry kinematic conditions.With
CFD (computational fluid dynamics) simulation program generally assesses hydrodynamics influence.
Experimental procedure is related to perform the scene for being designed to optimize and select the scheme formed by design procedure above
Adjustment and a series of tests.
In the non-limiting example for being described herein as and representing, with to cyclone 17 and substantive to cylindrical outer element 18
On be arranged equally spaced nozzle 36.
In the non-limiting example for being described herein as and representing, nozzle 36 has border circular areas and equably along main burning
The air supply ring duct 13 of device 10 is distributed.Variant (not shown) is provided with the transmission for being configured as preventing sound to be distributed
The implementation of appropriate arrowband and the nozzle 36 with increased diameter.Preferably, inserted between nozzle 36 and circular passage 35
Arrowband is adjusting the second auxiliary convection current time τs2。
Supply the second auxiliary fuel flow velocity QA2 to provide to circular passage 35 under the control of the control device 19 of component 6
Fuel (Fig. 1).
Control device 19 is configured as regulation main fuel flow velocity QP, the auxiliary combustions of the first auxiliary fuel flow velocity QA1 and second
Stream speed QA2.Especially, control device 19 adjusts fuel flow rate to follow the second auxiliary fuel flow velocity QA2 and total fuel flow
Fast QTOT to fixed-ratio.
Total fuel flow speed QTOT is defined as the summation of main fuel flow velocity QP and secondary fuel flow velocity QS.While secondary fuel
Flow velocity QS is defined as the summation of the first auxiliary fuel flow velocity QA1 and the second auxiliary fuel flow velocity QA2.
Especially, the regulation of control device 19 fuel flow rate is auxiliary second to follow to be based on the capacity that unit 1 is discharged
Help between fuel flow rate QA2 and total fuel flow speed QTOT to fixed-ratio.
In fact, control device 19 is configured to supply equal to overall flow rate QTOT about when unit operation is in low-load
40% the second auxiliary flow velocity QA2, while when unit 1 operates in intermediate loads, it is configured to supply relative to being fed to
The flow velocity of low-load and reduce second auxiliary flow velocity QA2 (it is generally equal to about the 10% of overall flow rate QTOT).
In fact, be disposal of pollutants in low-load subject matter, especially CO.The generation of second auxiliary burner 25 can draw
Play the second auxiliary combustion region 28 burnt completely of uniform temperature distribution and fuel in primary combustion zone 12.In fact,
Imperfect combustion is the main cause that CO discharges occur.
So as to reduce the minimum environmental loads of technology relative to the value that can be obtained in known unit and need not be absorbed in
The undesirable increase of CO discharges.
In intermediate loads, the temperature in combustion chamber 4 is high and allows the complete oxidation of CO.In addition, in intermediate loads
Heat-acoustic instability is not high.In this configuration, the optimization of the second auxiliary burner 25 pairs burning is without helping and therefore significantly
Reduce the second auxiliary fuel flow velocity QA2.
Increase by the second auxiliary fuel flow velocity QA2 again until it reaches the 20% of overall flow rate QTOT in nominal load.It is actual
On, under normal loading conditions, heat-sound oscillation in a combustion chamber increases.The increase of the second auxiliary fuel flow velocity QA2 and second auxiliary
Help convection current time τs2Modulation allow to want controlled such vibration.
One variant (not shown) provides to combine main burner and secondary combustion in burner assembly to be configured
To generate non-flaming combustion treatment in primary combustion zone 12 between device.Non-flaming combustion treatment is desired for when air-combustion
The burning treatment that oxidation processes occur when material mixture is higher than flammable limitation and more than autoignition temperature.Can be by preheated-combustion-supporting
Air and recycle the mode of burnt gas and obtain these conditions.Obtained for preheating sky by flue gas recycled
The condition of gas.In fact, so as to heat is sent into reactant from product and combustion adjuvant is diluted with fuel and combustion products.Can
With by recycling being managed by the particular fluid dynamic behavior of burner, beyond combustion chamber and within combustion chamber
To set up the recycling of flue gas." without flame " definition comes to be had during it there is combustion reaction relative to the extension of combustion volume
The thickness of reduction and in the absence of defined flame front.
Advantageously, in the case where disposal of pollutants is equal, burner assembly of the invention 9 can be relative to existing skill
The burner assembly of art ensures the increased combustion stability of institute.
This permission changes relative to heat release is quickly obtained with those acquired in the burner assembly as prior art.
So as to burner assembly of the invention 9 can be rapidly reached by the volume change needed for unit 1.
Especially, the increased stability of burning mainly due to configuration secondary burner 11 so that secondary convection current time τsWith
Main convection current time τpThe fact that different.In fact, reducing the thermoacoustic of main burner 10 by the reaction of secondary burner 11
Vibration.
In addition, secondary burner 11 includes the first auxiliary burner 25 and the second auxiliary burner 28 (by respective combustion
The fact that material supply connection is to its independently supplying), the homogeneous distribution of the generation different convection current times related from multiple fuel sources.
Relative to burning acquired in the burner assembly that only convection current time associates with main burner wherein, convection current time
Homogeneous distribution generate more stable burning.In fact, the homogeneous distribution of convection current time allow time delay to be adjusted with
Just the instable influence of thermoacoustic is offset.
In addition, configuration secondary burner 11 is completely contained in the thing within primary combustion zone 12 so as to secondary combustion region 20
Cause ignition temperature to change in fact to reduce (there is significant advantage with regard to disposal of pollutants aspect), and all combustion zones is efficient steady
It is fixed.
According to the present invention, stablizing effect is designated as modulating the convection current time at least in part, while the reduction of discharge is referred to
Send to improve the Temperature Distribution in combustion zone.
Flameholding is generally assigned to control burner by known combustion device assembly.However, control burner includes having
The presence of the combustion zone of high-temperature and corresponding ground contamination.
Finally, based on the capacity discharged by unit 1, the regulation by the fuel flow rate performed by control device 19 is true
Guarantor follow between the second auxiliary flow velocity QA2 and total burning flow velocity QTOT to fixed-ratio.So as in all operation bars of unit 1
The stabilization of burning is ensure that under part.
Finally, without departing from the scope of the appended claims, it is clear that can be to burner group described herein
Part, to combustion chamber and to making various modifications and variations for supplying the method for the burner assembly.
Claims (17)
1. a kind of burner assembly (9), for the combustion chamber (4) of gas turbine unit (1), the burner assembly (9) includes：
Main burner (10), was configurable to generate with the main convection current time (τp) primary combustion zone (12)；With
Secondary burner (11), being configured as at least generation has the secondary convection current time (τs) secondary combustion region (20)；
The secondary burner (11) is configured to the secondary convection current time (τs) with the main convection current time (τp) different；
The wherein main convection current time (τp) and the secondary convection current time (τs) cause thermoacoustic ripple and secondary burner in main burner (10)
(11) the destruction interference between thermoacoustic ripple.
2. burner assembly according to claim 1, wherein the secondary convection current time (τs) it is less than the main convection current time (τp)。
3. burner assembly according to claim 1, wherein secondary combustion region (20) are at least partially contained within main combustion
In burning region (12).
4. burner assembly according to claim 1, wherein secondary combustion region (20) are completely contained in primary combustion zone
(12) in.
5. burner assembly according to claim 1, wherein main burner (10) extends around secondary burner (11)
And supply ring duct (14) including air supply ring duct (13) and fuel.
6. burner assembly according to claim 5, wherein secondary burner include the first auxiliary burner (24) and the
Two auxiliary burners (25), the first auxiliary burner (24) was configurable to generate with the first auxiliary convection current time (τs1) first
Auxiliary combustion region (27), the second auxiliary burner (25) was configurable to generate with the second auxiliary convection current time (τs2) second
Auxiliary combustion region (28)；First auxiliary convection current time (τs1) and the second auxiliary convection current time (τs2) with the main convection current time (τp) no
Together.
7. burner assembly according to claim 6, wherein the first auxiliary convection current time (τs1) and second auxiliary convection current when
Between (τs2) it is less than the main convection current time (τp)。
8. burner assembly according to claim 7, wherein the first auxiliary convection current time (τs1) less than the second auxiliary convection current
Time (τs2)。
9. burner assembly according to claim 6, wherein the second auxiliary burner (25) is logical including fuel supply annular
Road (35), its air supply ring duct (13) for flowing directly into main burner (10).
10. burner assembly according to claim 9, wherein fuel supply circular passage (35) are provided with multiple nozzles
(36) fuel injection point and main burning that, it is disposed in main burner (10) along the inwall of air supply ring duct (13)
At position between the external margin (18) of device (10).
A kind of 11. combustion chambers, including at least one burner assembly (9) as claimed in claim 1.
A kind of 12. combustions for supplying fuel to the gas turbine unit (1) as described in any one of preceding claims
The method for burning the burner assembly (9) of room (4)；The described method comprises the following steps：
Main fuel flow velocity (QP) is fed to main burner (10)；
Secondary fuel flow velocity (QS) is fed to secondary burner (11)；
Secondary fuel flow velocity (QS) is adjusted based on the load of unit (1).
13. methods according to claim 12, wherein secondary burner (11) are including being configurable to generate the combustion of the first auxiliary
The first auxiliary burner (24) for burning region (27) and the second auxiliary combustion for being configurable to generate the second auxiliary combustion region (28)
Burner (25)；The described method comprises the following steps：
The first auxiliary fuel flow velocity (QA1) is supplied to the first auxiliary burner (24)；
The second auxiliary fuel flow velocity (QA2) is supplied to the second auxiliary burner (25)；
The second auxiliary fuel flow velocity (QA2) is adjusted based on the load of unit (1).
14. methods according to claim 13, wherein adjusting the second auxiliary fuel flow velocity based on the load of unit (1)
(QA2) the step of, includes reducing the second auxiliary fuel flow velocity (QA2) when the load of unit (1) increases.
15. methods according to claim 13, wherein the step of adjusting the second auxiliary fuel flow velocity (QA2) is included when load
During less than first threshold, second auxiliary fuel flow velocity (QA2) of the supply equal to the 40% of total fuel flow speed (QTOT), total fuel
Flow velocity (QTOT) is the summation of main fuel flow rate (QP) and secondary fuel flow velocity (QS).
16. methods according to claim 13, wherein the step of adjusting the second auxiliary fuel flow velocity (QA2) is included when load
When between first threshold and Second Threshold, second auxiliary fuel flow velocity of the supply equal to the 20% of total fuel flow speed (QTOT)
(QA2), total fuel flow speed (QTOT) is the summation of main fuel flow rate (QP) and secondary fuel flow velocity (QS).
17. methods according to claim 13, wherein adjust the second auxiliary fuel flow velocity (QA2) including when load is more than the
During two threshold values, second auxiliary fuel flow velocity (QA2) of the supply equal to the 10% of total fuel flow speed (QTOT), total fuel flow speed
(QTOT) it is main fuel flow rate (QP) and the summation of secondary fuel flow velocity (QS).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT002154A ITMI20122154A1 (en) | 2012-12-17 | 2012-12-17 | BURNER UNIT, COMBUSTION CHAMBER INCLUDING THE BURNER UNIT AND METHOD FOR POWERING THE BURNER GROUP |
| ITMI2012A002154 | 2012-12-17 | ||
| PCT/IB2013/061052 WO2014097153A1 (en) | 2012-12-17 | 2013-12-17 | Burner assembly, combustion chamber comprising said burner assembly and method for supplying fuel to said burner assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105102894A CN105102894A (en) | 2015-11-25 |
| CN105102894B true CN105102894B (en) | 2017-07-11 |
Family
ID=47720641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380065883.8A Active CN105102894B (en) | 2012-12-17 | 2013-12-17 | Burner assembly, the combustion chamber including the burner assembly and the method for supplying fuel to the burner assembly |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP2932158B1 (en) |
| KR (1) | KR20150103039A (en) |
| CN (1) | CN105102894B (en) |
| IT (1) | ITMI20122154A1 (en) |
| WO (1) | WO2014097153A1 (en) |
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|---|---|---|---|---|
| US5193346A (en) * | 1986-11-25 | 1993-03-16 | General Electric Company | Premixed secondary fuel nozzle with integral swirler |
| CN1357706A (en) * | 2000-11-13 | 2002-07-10 | 阿尔斯托姆电力有限公司 | Combustor with stepped fuel spray and its running process |
| EP1662202A1 (en) * | 2004-11-30 | 2006-05-31 | Siemens Aktiengesellschaft | Burner for a gas turbine and method to operate such a burner |
| CN101981379A (en) * | 2008-04-01 | 2011-02-23 | 西门子公司 | Size scaling of a burner |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2001272682A1 (en) * | 2000-06-15 | 2001-12-24 | Alstom Power N.V. | Method for operating a burner and burner with stepped premix gas injection |
| DE10164099A1 (en) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Burner with staged fuel injection |
-
2012
- 2012-12-17 IT IT002154A patent/ITMI20122154A1/en unknown
-
2013
- 2013-12-17 KR KR1020157017921A patent/KR20150103039A/en not_active Application Discontinuation
- 2013-12-17 EP EP13831864.7A patent/EP2932158B1/en active Active
- 2013-12-17 WO PCT/IB2013/061052 patent/WO2014097153A1/en active Application Filing
- 2013-12-17 CN CN201380065883.8A patent/CN105102894B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5193346A (en) * | 1986-11-25 | 1993-03-16 | General Electric Company | Premixed secondary fuel nozzle with integral swirler |
| CN1357706A (en) * | 2000-11-13 | 2002-07-10 | 阿尔斯托姆电力有限公司 | Combustor with stepped fuel spray and its running process |
| EP1662202A1 (en) * | 2004-11-30 | 2006-05-31 | Siemens Aktiengesellschaft | Burner for a gas turbine and method to operate such a burner |
| CN101981379A (en) * | 2008-04-01 | 2011-02-23 | 西门子公司 | Size scaling of a burner |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20150103039A (en) | 2015-09-09 |
| EP2932158B1 (en) | 2022-02-02 |
| WO2014097153A1 (en) | 2014-06-26 |
| ITMI20122154A1 (en) | 2014-06-18 |
| WO2014097153A8 (en) | 2015-02-26 |
| CN105102894A (en) | 2015-11-25 |
| EP2932158A1 (en) | 2015-10-21 |
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