CN103703317B - Fuel-cooled burner - Google Patents
Fuel-cooled burner Download PDFInfo
- Publication number
- CN103703317B CN103703317B CN201180072312.8A CN201180072312A CN103703317B CN 103703317 B CN103703317 B CN 103703317B CN 201180072312 A CN201180072312 A CN 201180072312A CN 103703317 B CN103703317 B CN 103703317B
- Authority
- CN
- China
- Prior art keywords
- fuel
- fuel circuit
- stream
- path
- burner
- 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.)
- Expired - Fee Related
Links
- 239000000446 fuel Substances 0.000 claims abstract description 167
- 238000010438 heat treatment Methods 0.000 claims abstract description 11
- 238000001816 cooling Methods 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 6
- 239000003085 diluting agent Substances 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 238000002156 mixing Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 12
- 239000000203 mixture Substances 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000000567 combustion gas Substances 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 3
- 239000002826 coolant Substances 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23K—FEEDING FUEL TO COMBUSTION APPARATUS
- F23K5/00—Feeding or distributing other fuel to combustion apparatus
- F23K5/02—Liquid fuel
- F23K5/14—Details thereof
- F23K5/20—Preheating 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
- F23R3/005—Combined with pressure or heat exchangers
-
- 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
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
-
- 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
- F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
This application provides a kind of burner being used together with gas-turbine unit and fuel stream.This burner can include burning surface and fuel passage, and this fuel passage makes the fuel stream heat treatment burning surface by this fuel passage in being positioned at burning surface.
Description
Technical field
The application relates generally to gas-turbine unit, and relates more specifically to the gas turbine combustor cooled down at least in part with fuel stream.
Background technology
In general, gas turbine engine combustion fuel air mixture is to form high-temperature combustion gas stream.High-temperature combustion gas flows through and is transported to turbine by hot gas path.Turbine will be converted into mechanical energy from the heat energy of high-temperature combustion gas stream, in order to revolving wormgear axle.Gas-turbine unit can be used in various application, e.g., for providing power to pump or electromotor etc..Other type of gas-turbine unit can be used to construct.
The operating efficiency of gas-turbine unit generally increases when the temperature of burning gases stream increases.But, higher gas stream temperature can produce higher levels of nitrogen oxides (" NOX"), this is affected by the United States Federal's Hezhou control, and by the control of similar type abroad.Therefore, within the scope of effective temperature, operate gas turbine and also ensure NO simultaneouslyXAnd the output of other type of emission be maintained at require below horizontal between there is balance.
Fuel air mixture can burn in the burner.Burner generally cools down via cooling air stream.But, for active combustion, this cooling air stream may be not involved in fuel-air mixed process.Therefore, in the case of gas turbine parameter rises, the deficiency of the amount of air needed for the operation of fuel-lean air mixture can be there is.Additionally, the temperature risen also can cause NOXEmission rises to unacceptable level.
Accordingly, there exist the burner for improving and the expectation of burner cooling means.This type of burner and cooling means will allow for gas turbine parameter and the performance increased, simultaneously by NOXEmission is limited in requiring level.
Summary of the invention
Therefore, this application provides a kind of burner being used together with gas-turbine unit and fuel stream.This burner can include burning surface and fuel passage, and this fuel passage is positioned in burning surface so that by the fuel stream heat treatment burning surface of this fuel passage.
Present invention also provides a kind of with fuel stream with the method for air flow operation burner.The method can comprise the following steps that provides fuel stream and air stream to fuel circuit, fuel stream is made to flow through the path extended along fuel circuit, with fuel stream heat treatment fuel circuit, fuel combination stream and air stream after the cooling step, and at the fired downstream fuel stream of fuel circuit and air stream.
Present invention also provides a kind of burner being used together with gas-turbine unit and fuel stream.Burner can include the burning surface of the fuel circuit of some, some, one or more during wherein fuel circuit includes burning surface, and the fuel passage of some, wherein one or more in fuel passage be positioned in burning surface one or more in.By the fuel stream of fuel passage cool down in burning surface one or more.
When combining some accompanying drawings and claims consider, for those skilled in the art, these and other feature and the improvement of the application will be understood when inspecting described in detail below.
Accompanying drawing explanation
Fig. 1 is such as the explanatory view of the gas-turbine unit can being used together with burner described herein.
Fig. 2 is the explanatory view of nested burner.
Fig. 3 is can the side cross-sectional view of burner as described in this article.
Fig. 4 is can the side cross-sectional view of the alternative of burner as described in this article.
Parts List
10 gas-turbine units
20 compressors
30 burners
40 turbines
50 loads
The burner of 100 nestings
110 first fuel circuits
120 central nozzles
130 first fuel circuit cyclones
140 fuel streams
150 air streams
160 recirculation regions
170 second fuel circuits
180 first fuel circuit housings
190 second fuel circuit housings
200 second fuel circuit cyclones
210 second fuel circuit shear layers
220 the 3rd fuel circuits
230 the 3rd fuel circuit housings
240 the 3rd fuel circuit cyclones
250 the 3rd fuel circuit shear layers
300 burners
310 central nozzle fuel paths
320 first fuel circuit housing paths
330 second fuel circuit housing paths
340 flanks
350 burning surfaces
360 burners
370 liquid fuel streams
380 diluent flows.
Detailed description of the invention
Referring now to accompanying drawing, in the accompanying drawings, similar numeral refers to similar element in some views all the time, and Fig. 1 shows the explanatory view of gas-turbine unit 10.As described above, gas-turbine unit 10 can include that compressor 20 is to compress the air stream come in.Compressor 20 transmits the air of compression and flows to burner 30.Burner 30 mixes the air stream of compression and the fuel stream of compression and lights this mixture.Although illustrate only single burner 30, but gas-turbine unit 10 can including any number of burner 30.The burning gases of heat are sent to turbine 40 then.The combustion gases drive turbine 40 of heat is to produce mechanical power.The mechanical power produced by turbine 40 drives compressor 20 and external loading 50, e.g., electromotor etc..
Gas-turbine unit 10 can use natural gas, various types of synthesis gas, and other type of fuel.Gas-turbine unit 10 can be the 9FBA heavy duty gas turbine engine provided by the General Electric Co. Limited of New York SIKA Nai Ta.Gas-turbine unit 10 can have other structure, and can use other type of component.Other type of gas-turbine unit be may be used herein.Multiple gas-turbine units 10, other type of turbine, and other type of dynamic force generation device can be used together in this article.
Fig. 2 shows the explanatory view of the burner 100 of nesting.Nested burner 100 provides axially staged fuel injection.Therefore, nested burner 100 includes the first fuel circuit 110.Central nozzle 120 can include central nozzle fuel path 310(Fig. 3).First fuel circuit 110 can include central nozzle fuel path 310(Fig. 3).First fuel circuit cyclone 130 is around central nozzle 120.Fuel stream 140 not only can be through central nozzle 120 but also can be through the first fuel circuit cyclone 130.Similarly, air stream 150 can be through the first fuel circuit cyclone 130.Fuel stream 140 and air stream 150 are in the mixed downstream of central nozzle 120 and light.Shear layer or recirculation regions 160 can be formed via mixed flow 140,150 in central nozzle 120 downstream.May used herein other structure.
The second fuel circuit 170 can be formed around the first fuel circuit 110.Second fuel circuit 170 can be formed between the first fuel circuit housing 180 and the second fuel circuit housing 190.The second fuel circuit cyclone 200 can have been positioned betwixt.As it has been described above, fuel stream 140 and air stream 150 can mix for at this through the second fuel circuit cyclone 200.Second fuel circuit shear layer 210 can produce via mixed flow 140,150 in the second fuel circuit cyclone 200 downstream.Other can be used herein to construct.
3rd fuel circuit 220 can be around the second fuel circuit 170.3rd fuel circuit 220 can be formed between the second fuel circuit housing 190 and the 3rd fuel circuit housing 230.The 3rd fuel circuit cyclone 240 can have been positioned betwixt.Fuel stream 140 can mix in this place with air stream 150.3rd fuel circuit shear layer 250 also can be formed at the 3rd fuel circuit cyclone 240 downstream via the stream 140,150 of mixing.Other can be used herein to construct.Nested burner 100 can have any number of fuel circuit in this article.
Under high-temperature operation, all of three fuel circuits 110,170,220 can be in operation.During medium load operates, the first fuel circuit 110 and the second fuel circuit 170 can be work, and the 3rd fuel circuit 220 and pass through the air stream 150 at this and can substantially be not involved in combustion process.During low-load operates, the only first fuel circuit 110 can be in operation.Second fuel circuit 170 and the 3rd fuel circuit 220 and can be substantially not involved in combustion process by the air stream 150 at this.
Fig. 3 shows can the part of burner 300 as described in this article.Burner 300 can the most substantially use fuel circuit 110,170,220.Central nozzle fuel path 310 can extend along the length of central nozzle 120 and terminate around the first fuel circuit cyclone 130.First fuel circuit housing 180 may also include the first fuel circuit housing path 320 extended through at this.First fuel circuit housing path 320 also can extend along the length of the first fuel circuit housing 180 and terminate around the first fuel circuit cyclone 130.Second fuel circuit housing 190 can include the second fuel circuit housing path 330.Second fuel circuit housing path 330 also can extend along the length of the second fuel circuit housing 190 and terminate around the second fuel circuit cyclone 200.Other can be used herein to construct.
Therefore, fuel circuit housing path 310,320,330 can provide the heat treatment around central fuel nozzle the 120, first fuel circuit housing 180 and the second fuel circuit housing 190.Specifically, fuel circuit housing path 310,320,330 provides impinging cooling.Fuel circuit housing path 310,320,330 also can include flank 340 wherein to promote that more turbulent flow flows through at this.Assume can use for cooling purposes fuel stream 140, then fuel circuit housing path 310,320,330 only cools the surface of the burner 300 burning wherein occur, the i.e. burning surface 350 of some.The region or the surface that have neither part nor lot in burning can continue to be cooled down by air stream 150.Thus, coolant stream is always proportional to the wall area of thermal region and flame temperature.
Fig. 4 shows can another embodiment of burner 360 as described in this article.Burner 360, can be substantially consistent with said burner 300 in addition to can using liquid fuel stream 370 and diluent flow 380.Liquid fuel stream 370 can flow through central nozzle the 120, second fuel circuit housing path 330 and the second fuel circuit cyclone 200.Diluent flow 360 can be through central nozzle fuel path 310 and the first fuel circuit housing path 320.May used herein other structure and other type of fuel.
Therefore, the use for the fuel circuit housing path 310,320,330 of heat treatment provides the cooling performance of increase, allows to use air stream 150 to prepare for fuel-lean air mixture simultaneously.Thus, the NO that gas turbine parameter can increase and not haveXEmission or the appreciable growth of wall temperature.Therefore, almost all of air stream can be used for lean air fuel mixture and prepares.May also provide fuel-air ratio and the conforming more preferable control of emission when closed.Acoustic characteristic and power can by the flame stabilization structures axially staged, multiple of heat release and before combustion heating fuel alleviate to increase fueling injection pressure ratio.May also provide fuel tolerance, because less ignitable fuel can be guided by stronger flame of centre.The fuel of more lower energy content can provide more fuel coolant stream.
It should be clear that foregoing teachings only relates to some embodiment of the application, and in the case of the substantially spirit or scope without departing from the present invention such as limited by claims and its equivalent, can many variations and modifications may be made by those skilled in the art.
Claims (8)
1. the burner being used together with gas-turbine unit and fuel stream, including:
First fuel circuit (110)；
Central nozzle (120)；
Second fuel circuit (170), it is formed around the first fuel circuit (110), and the second fuel circuit (170) is formed between the first fuel circuit housing (180) and the second fuel circuit housing (190)；
3rd fuel circuit (220), it is formed around the second fuel circuit (170), and the 3rd fuel circuit (220) is formed between the second fuel circuit housing (190) and the 3rd fuel circuit housing (230)；
Wherein, central nozzle (120) includes central nozzle fuel path (310), first fuel circuit housing (180) includes that the first fuel circuit housing path (320), the second fuel circuit housing (190) include the second fuel circuit housing path (330)；
Central nozzle fuel path (310), the first fuel circuit housing path (320) and the second fuel circuit housing path (330) provide central nozzle (120), the first fuel circuit housing (180) and the second fuel circuit housing (190) heat treatment around.
Burner the most according to claim 1, it is characterised in that central nozzle fuel path (310), the first fuel circuit housing path (320) and the second fuel circuit housing path (330) provide impinging cooling.
Burner the most according to claim 1, it is characterised in that described first, second, and third fuel circuit includes cyclone therein, for mixing described fuel stream and air stream.
Burner the most according to claim 1, it is characterised in that central nozzle fuel path (310), the first fuel circuit housing path (320) and the second fuel circuit housing path (330) include flank therein.
Burner the most according to claim 1, it is characterised in that described fuel stream includes liquid fuel stream and diluent flow.
6. with fuel stream and air flow operation according to the method for the burner according to any one of claim 1-5, including:
One or more offers described fuel stream in first, second, and third fuel circuit and described air stream；
Described fuel stream is made to flow through central nozzle fuel path (310), the first fuel circuit housing path (320) and the second fuel circuit housing path (330)；
With first, second, and third fuel circuit described in described fuel stream heat treatment；
Described fuel stream and described air stream is mixed after described heat treatment step；And
At fuel stream described in the fired downstream of described first, second, and third fuel circuit and described air stream.
Method the most according to claim 6, it is characterised in that the only one or more offers described air stream in described first, second, and third fuel circuit.
Method the most according to claim 6, it is characterised in that the step of first, second, and third fuel circuit described in heat treatment includes heating described fuel stream further.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/RU2011/000514 WO2013009211A1 (en) | 2011-07-14 | 2011-07-14 | Fuel cooled combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103703317A CN103703317A (en) | 2014-04-02 |
| CN103703317B true CN103703317B (en) | 2016-09-14 |
Family
ID=45688949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201180072312.8A Expired - Fee Related CN103703317B (en) | 2011-07-14 | 2011-07-14 | Fuel-cooled burner |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP2732212A1 (en) |
| CN (1) | CN103703317B (en) |
| WO (1) | WO2013009211A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104165379A (en) * | 2014-09-01 | 2014-11-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustor head structure with cooling device |
| US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
| US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
| DE102021110614A1 (en) | 2021-04-26 | 2022-10-27 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber assembly for an engine with at least one heat exchange channel for fuel to be injected |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4399652A (en) * | 1981-03-30 | 1983-08-23 | Curtiss-Wright Corporation | Low BTU gas combustor |
| EP0725253A2 (en) * | 1995-02-01 | 1996-08-07 | Mitsubishi Jukogyo Kabushiki Kaisha | Gas turbine combustor |
| US6201029B1 (en) * | 1996-02-13 | 2001-03-13 | Marathon Oil Company | Staged combustion of a low heating value fuel gas for driving a gas turbine |
| CN101253366A (en) * | 2005-08-27 | 2008-08-27 | 西门子公司 | Devices for adjusting the composition of gaseous fuels |
| EP2161500A1 (en) * | 2008-09-04 | 2010-03-10 | Siemens Aktiengesellschaft | Combustor system and method of reducing combustion instability and/or emissions of a combustor system |
-
2011
- 2011-07-14 WO PCT/RU2011/000514 patent/WO2013009211A1/en active Application Filing
- 2011-07-14 EP EP11819132.9A patent/EP2732212A1/en not_active Withdrawn
- 2011-07-14 CN CN201180072312.8A patent/CN103703317B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4399652A (en) * | 1981-03-30 | 1983-08-23 | Curtiss-Wright Corporation | Low BTU gas combustor |
| EP0725253A2 (en) * | 1995-02-01 | 1996-08-07 | Mitsubishi Jukogyo Kabushiki Kaisha | Gas turbine combustor |
| US6201029B1 (en) * | 1996-02-13 | 2001-03-13 | Marathon Oil Company | Staged combustion of a low heating value fuel gas for driving a gas turbine |
| CN101253366A (en) * | 2005-08-27 | 2008-08-27 | 西门子公司 | Devices for adjusting the composition of gaseous fuels |
| EP2161500A1 (en) * | 2008-09-04 | 2010-03-10 | Siemens Aktiengesellschaft | Combustor system and method of reducing combustion instability and/or emissions of a combustor system |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2013009211A1 (en) | 2013-01-17 |
| CN103703317A (en) | 2014-04-02 |
| EP2732212A1 (en) | 2014-05-21 |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160914 Termination date: 20170714 |
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| CF01 | Termination of patent right due to non-payment of annual fee |