CN103703317A - Fuel cooled combustor - Google Patents
Fuel cooled combustor Download PDFInfo
- Publication number
- CN103703317A CN103703317A CN201180072312.8A CN201180072312A CN103703317A CN 103703317 A CN103703317 A CN 103703317A CN 201180072312 A CN201180072312 A CN 201180072312A CN 103703317 A CN103703317 A CN 103703317A
- Authority
- CN
- China
- Prior art keywords
- fuel
- fuel circuit
- flow
- burner
- circuit
- 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.)
- Granted
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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
- F23R3/34—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
- 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
Abstract
The present application provides a combustor for use with a gas turbine engine and a flow of fuel. The combustor may include a combustion surface and a fuel pathway positioned within the combustion surface such that the flow of fuel through the fuel pathway heat treats the combustion surface.
Description
Technical field
The application relates generally to gas-turbine unit, and relates more specifically at least in part with the cooling gas turbine combustor of fuel flow.
Background technology
In general, gas-turbine unit combustion fuel air mixture is to form high-temperature combustion gas stream.High-temperature combustion gas is flowed through by hot gas delivery pathways to turbine.Turbine becomes mechanical energy by the thermal power transfer from high-temperature combustion gas stream, so that revolving wormgear axle.Gas-turbine unit can be used in various application, as, for providing power to pump or generator etc.Can use the gas-turbine unit structure of other type.
The operating efficiency of gas-turbine unit increases conventionally when the temperature of burning gases stream increases.Yet higher gas flow temperature can produce higher levels of nitrogen oxide (" NO
x"), this is to be subject to the United States Federal's Hezhou control, and is subject to the control of similar type abroad.Therefore, in effective temperature range, operating gas turbine also guarantees NO simultaneously
xand the output of the emission of other type remains on and requires between below horizontal to have balance.
Fuel air mixture can burn in burner.Burner comes cooling via cooling-air stream substantially.Yet for active combustion, this cooling-air stream may not participate in fuel-air mixed process.Therefore,, in the situation that gas turbine parameter rises, can there is the deficiency of the amount of the required air of the operation of poor fuel air mixture.In addition, the temperature of rising also can cause NO
xemission rises to unacceptable level.
Therefore, exist for the burner improving and the expectation of burner cools method.This type of burner and cooling means are by allowing gas turbine parameter and the performance of increase, simultaneously by NO
xemission is limited in and requires in level.
Summary of the invention
Therefore, the application provides a kind of burner using together with fuel flow with gas-turbine unit.This burner can comprise burning surface and fuel passage, and this fuel passage is positioned in burning surface, makes the fuel flow heat treatment burning surface by this fuel passage.
The application also provides a kind of method with fuel flow and air stream operating burner.The method can comprise the following steps: to fuel circuit, provide fuel flow and air stream, the path that makes fuel flow flow through and extend along fuel circuit, with fuel flow heat treatment fuel circuit, fuel combination stream and air stream after cooling step, and at the downstream of fuel circuit burn fuel flow and air stream.
The application also provides a kind of burner using together with fuel flow with gas-turbine unit.Burner can comprise the fuel circuit of some, the burning surface of some, wherein fuel circuit comprises one or more in burning surface, and the fuel passage of some, wherein one or more in fuel passage are positioned in one or more in burning surface.One or more by the fuel flow cooling combustion surface of fuel passage.
When in conjunction with some accompanying drawings and claims consideration, concerning those skilled in the art, while describing in detail, the application's these and other feature and improvement will be known below inspection.
Accompanying drawing explanation
Fig. 1 is the explanatory view of the gas-turbine unit as used together with burner described herein.
Fig. 2 is the explanatory view of nested burner.
Fig. 3 is the side cross-sectional view of burner as described in this article.
Fig. 4 is 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
100 nested burners
110 first fuel circuits
120 central nozzles
130 first fuel circuit cyclones
140 fuel flows
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.
The specific embodiment
Now, referring to accompanying drawing, in the accompanying drawings, similar numeral refers to all the time similar element in some views, and Fig. 1 shows the explanatory view of gas-turbine unit 10.As described above, gas-turbine unit 10 can comprise the air stream that compressor 20 is come in compression.The air that compressor 20 transmits compression flows to burner 30.Burner 30 mixes the air stream of compression and the fuel flow of compression and lights this mixture.Although only show single burner 30, gas-turbine unit 10 can comprise the burner 30 of any number.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 drive compression machine 20 and the external loading 50 that by turbine 40, are produced, as, generator etc.
Gas-turbine unit 10 can use natural gas, various types of synthesis gas, and the fuel of other type.The 9FBA heavy duty gas turbine engine that gas-turbine unit 10 can provide for the General Electric Co. Limited by New York Si Kanaita.Gas-turbine unit 10 can have other structure, and can use the member of other type.Also can use the gas-turbine unit of other type herein.The turbine of a plurality of gas-turbine units 10, other type, and the power of other type generation equipment can be used in this article together.
Fig. 2 shows the explanatory view of nested burner 100.Nested burner 100 provides axially staged fuel to spray.Therefore, nested burner 100 comprises the first fuel circuit 110.The first fuel circuit 110 comprise by the first fuel circuit cyclone 130 around central nozzle 120.Fuel flow 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 flow 140 and air stream 150 are in the mixed downstream of central nozzle 120 and light.In central nozzle 120 downstreams, can form shear layer or recirculation regions 160 via mixed flow 140,150.Can use other structure herein.
Around the first fuel circuit 110, can form the second fuel circuit 170.The second fuel circuit 170 can be formed between the first fuel circuit housing 180 and the second fuel circuit housing 190.Can be positioned with betwixt the second fuel circuit cyclone 200.As mentioned above, fuel flow 140 and air stream 150 can be through the second fuel circuit cyclone 200 for mixing with this place.The second fuel circuit shear layer 210 can produce via mixed flow 140,150 in the second fuel circuit cyclone 200 downstreams.Can use other structure herein.
The 3rd fuel circuit 220 can be around the second fuel circuit 170.The 3rd fuel circuit 220 can be formed between the second fuel circuit housing 190 and the 3rd fuel circuit housing 230.Can be positioned with betwixt the 3rd fuel circuit cyclone 240.Fuel flow 140 can mix at this place with air stream 150.The 3rd fuel circuit shear layer 250 also can be formed on the 3rd fuel circuit cyclone 240 downstreams via the stream 140,150 mixing.Can use other structure herein.Nested burner 100 can have the fuel circuit of any number in this article.
Under high-temperature operation, all three fuel circuits 110,170,220 can be in operation.In medium load operating period, the first fuel circuit 170 and the second fuel circuit 170 can be and work, and the 3rd fuel circuit 220 and the air stream 150 by this place can not participate in combustion process substantially.During low load operation, only the first fuel circuit 110 can be in operation.The second fuel circuit 170 and the 3rd fuel circuit 220 and the air stream 150 by this place can not participate in combustion process substantially.
Fig. 3 shows a part for burner 300 as described in this article.Burner 300 can use fuel circuit 110,170,220 as mentioned above substantially.In this example, central nozzle 120 can comprise central nozzle fuel path 310.Central nozzle fuel path 310 can extend and around finish at the first fuel circuit cyclone 130 along the length of central nozzle 310.The first fuel circuit housing 180 also can comprise the first fuel circuit housing path 320 that extends through this place.The first fuel circuit housing path 320 also can be extended and around finish at the first fuel circuit cyclone 130 along the length of the first fuel circuit housing 180.The second fuel circuit housing 190 can comprise the second fuel circuit housing path 330.The second fuel circuit housing path 330 also extensible the second fuel circuit housing 190 length and at the second fuel circuit cyclone 200, around finish.Can use other structure herein.
Therefore, fuel circuit housing path 310,320,330 can provide center fuel nozzle 120, the first loop housing 180 and second servo loop housing 190 heat treatment around.Particularly, it is cooling that fuel circuit housing path 310,320,330 provides impact.Fuel path 310,320, also can comprise flank 340 in 330 therein to promote more turbulent flow this place that flows through.Suppose can use fuel flow 140 for cooling object, fuel circuit housing path 310,320,330 is only cooling wherein there is the surface of the burner 300 of burning, the i.e. burning surface 350 of some.The region or the surface that have neither part nor lot in burning can be continued by air stream 150 cooling.Thereby coolant flow is always proportional with wall area and the flame temperature of thermal region.
Fig. 4 shows another embodiment of burner 360 as described in this article.Burner 360, can be substantially consistent with said burner 300 except using liquid fuel stream 370 and diluent flow 380.Liquid fuel stream 370 can flow through central nozzle 120, the second fuel circuit housing path 330 and the 3rd fuel circuit cyclone 240.Diluent flow 360 can pass through central nozzle fuel path 310 and the first fuel circuit housing path 320.Can use the fuel of other structure and other type herein.
Therefore, for the use in heat treated fuel circuit housing path 310,320,330, provide the cooling performance of increase, allowed to use air stream 150 to prepare for poor fuel air mixture simultaneously.Thereby gas turbine parameter can increase and the NO that do not have
xthe appreciable growth of emission or wall temperature.Therefore, nearly all air stream can be used for poor air fuel mixture preparation.Fuel-air ratio and the conforming better control of emission when closing also can be provided.Acoustic characteristic and power can by axially staged, a plurality of flame stabilization structures of heat release and before burning heating fuel to increase fueling injection pressure, recently alleviate.Also can provide fuel tolerance, because can be by stronger flame of centre guiding ignitable fuel still less.More the fuel of lower energy content can provide more fuel coolant flow.
Should be understood that, aforementioned content only relates to some embodiment of the application, and in the situation that do not depart from cardinal principle main idea of the present invention and the scope as limited by claims and its equivalent, can make many variations and modification by those skilled in the art.
Claims (20)
1. the burner using together with fuel flow with gas-turbine unit, comprising:
Burning surface; And
Be positioned at the fuel passage in described burning surface;
Wherein, through burning surface described in the described fuel flow heat treatment of described fuel passage.
2. burner according to claim 1, is characterized in that, by the cooling described burning surface of described fuel flow of described fuel passage.
3. burner according to claim 1, is characterized in that, described burner also comprises fuel circuit, and wherein, and described fuel circuit comprises described burning surface on described fuel circuit and the described fuel passage in described fuel circuit.
4. burner according to claim 3, is characterized in that, described burner also comprises a plurality of fuel circuits, a plurality of burning surface and a plurality of fuel passage.
5. burner according to claim 3, is characterized in that, described fuel circuit comprises central nozzle, and wherein, described fuel passage comprises the central nozzle fuel path through this place.
6. burner according to claim 3, is characterized in that, described fuel circuit comprises the first fuel circuit housing, and wherein, described fuel passage comprises the first fuel circuit housing path through this place.
7. burner according to claim 3, is characterized in that, described fuel circuit comprises the second fuel circuit housing, and wherein, described fuel passage comprises the second fuel circuit housing path through this place.
8. burner according to claim 3, is characterized in that, described fuel circuit comprises cyclone wherein, for mixing described fuel flow and air stream.
9. burner according to claim 1, is characterized in that, described fuel passage comprises flank wherein.
10. burner according to claim 1, is characterized in that, described fuel flow comprises liquid fuel stream and diluent flow.
11. 1 kinds of methods with fuel flow and air stream operating burner, comprising:
To fuel circuit, provide described fuel flow and described air stream;
The path that makes described fuel flow flow through and extend along described fuel circuit;
With fuel circuit described in described fuel flow heat treatment;
After described heat treatment step, mix described fuel flow and described air stream; And
Described fuel flow and described air stream burn in the downstream of described fuel circuit.
12. methods according to claim 11, is characterized in that, described method also comprises a plurality of fuel circuits, and only also comprise to one or more in described a plurality of fuel circuits described air stream is provided.
13. methods according to claim 11, is characterized in that, the step of fuel circuit comprises the described fuel flow of further heating described in heat treatment.
14. methods according to claim 11, is characterized in that, described in heat treatment the step of fuel circuit comprise impact cooling.
15. methods according to claim 11, is characterized in that, the step of fuel circuit comprises one or more burning surfaces of cooling described fuel circuit described in heat treatment.
16. 1 kinds of burners that use together with fuel flow with gas-turbine unit, comprising:
A plurality of fuel circuits;
A plurality of burning surfaces, wherein, described a plurality of fuel circuits comprise one or more in described a plurality of burning surface; And
A plurality of fuel passage, wherein, one or more in described a plurality of fuel passage are positioned in one or more in described a plurality of burning surface;
Wherein, one or more through in the cooling described a plurality of burning surfaces of described fuel flow of described a plurality of fuel passage.
17. burners according to claim 16, is characterized in that, described a plurality of fuel circuits comprise central nozzle, and wherein, described a plurality of fuel passage comprise the central nozzle fuel path through this place.
18. burners according to claim 17, is characterized in that, described a plurality of fuel circuits comprise the first fuel circuit housing, and wherein, described a plurality of fuel passage comprise the first fuel circuit housing path through this place.
19. burners according to claim 18, is characterized in that, described a plurality of fuel circuits comprise the second fuel circuit housing, and wherein, described a plurality of fuel passage comprise the second fuel circuit housing path through this place.
20. burners according to claim 16, is characterized in that, the one or more flanks that comprise wherein in described a plurality of fuel passage.
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 true CN103703317A (en) | 2014-04-02 |
| CN103703317B 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) |
Cited By (1)
| 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 |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
| US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
| 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 | An apparatus for modifying the content of a gaseous fuel |
| 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 EP EP11819132.9A patent/EP2732212A1/en not_active Withdrawn
- 2011-07-14 CN CN201180072312.8A patent/CN103703317B/en not_active Expired - Fee Related
- 2011-07-14 WO PCT/RU2011/000514 patent/WO2013009211A1/en active Application Filing
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 | An apparatus for modifying the content of a gaseous fuel |
| 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 |
Cited By (1)
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103703317B (en) | 2016-09-14 |
| EP2732212A1 (en) | 2014-05-21 |
| WO2013009211A1 (en) | 2013-01-17 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| 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 |