CN100368667C - Attenuated and diffused combustion nozzle of combustion turbine - Google Patents
Attenuated and diffused combustion nozzle of combustion turbine Download PDFInfo
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- CN100368667C CN100368667C CNB2006100116662A CN200610011666A CN100368667C CN 100368667 C CN100368667 C CN 100368667C CN B2006100116662 A CNB2006100116662 A CN B2006100116662A CN 200610011666 A CN200610011666 A CN 200610011666A CN 100368667 C CN100368667 C CN 100368667C
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Abstract
A dilution-expansion burning nozzle of gas turbine is prepared as setting three conical nozzles to be concentric-jacketed mode in sequence, fixing nozzle at external layer on end cover, jacketing nozzle at middle layer in nozzle at external layer in coaxial mode and jacketing nozzle at internal layer in nozzle at middle layer in coaxial mode.
Description
Technical field
The present invention relates to gas turbine and other gas phase combustion system fields thereof, be a kind of long-pending, thereby reach efficient, stable and oligosaprobic a kind of attenuated and diffused combustion nozzle of combustion turbine in the outlet geometric cross section that run duration is regulated the air of burner and fuel according to different dilution modes, different thinner and different amount of dilution.
Background technique
Gas turbine technology is a main direction of using energy source, coal is the main energy in the energy resource structure of China, so the circulation of integrated gasification combined cycle plants (IGCC) and integral coal gasification humid air turbine (IGHAT) is the energy utilization patterns that are fit to China.The firing chamber is a critical component in the gas turbine cycle, and it is related to the efficient and the pollutant emission of system.Therefore require the firing chamber can adapt to the burning of synthetic gas and different amount of dilution, and will reach stable, efficient and low pollutant emission burning, cost is low, long service life.
The dilution, diffusion and combustion technology is applicable to some advanced gas turbine cycle (HAT circulation and ISTG circulation etc.) on the one hand, because its system itself has determined that its combustion manner must be a dilution, diffusion and combustion.The dilution, diffusion and combustion technology can improve humid air turbine (HAT) circulation and steam injection turbine (ISTG) circuit system effectiveness and than merit, can reduce NO greatly simultaneously
xDischarging.Burn for the synthetic gas in the integrated gasification combined cycle plants (IGCC) because the variation of its component is bigger on the other hand, must adopt diffusive combustion, in order to reduce NO
xDischarging must be adopted the dilute combustion technology.Dilution, diffusion and combustion can be divided into fuel dilution and air dilution.Thinner can be water, water vapor and nitrogen etc.The scope of dilution is also very wide, the 1%-40% that thinner can duty tolerance.
Existing dilute combustion technology is by injecting water, water vapor or nitrogen in the general gas turbine combustion chamber, thereby reaches the purpose that reduces pollutant emission by means of reducing flame temperature.It can not regulate the situation of burning according to different dilution situations, and therefore under different dilution situations, the stability of burning, efficient and pollutant can not reach optimum value, even can not smooth combustion under some operating mode.Therefore be necessary to do further work, component and dilution component dynamic organization flow field according to synthetic gas make that whole firing chamber can be stablized, efficient, oligosaprobic burning under different operating modes.
Summary of the invention
The object of the present invention is to provide a kind of attenuated and diffused combustion nozzle of combustion turbine, the present invention under different operating modes (synthesis gas components, dilution component, amount of dilution), can stablize, efficiently, the dilution, diffusion and combustion technology of combustion with reduced pollutants.Its innovative point is can be according to synthesis gas components, and dilution component and amount of dilution are dynamically adjusted the outlet geometric area of burner, thus adjust the flow field make burner noz(zle) under different operating modes, can stablize, efficiently, lowly impurely burn.Also can adopt the present invention in the gas fired boiler in addition.
For achieving the above object, attenuated and diffused combustion nozzle of combustion turbine provided by the invention comprises three concentric successively sheathed tapered nozzles, wherein:
Outermost nozzle is fixed on the end cap; One side of this end cap and on be fixed with little end cap;
The mesosphere nozzle is set in the outermost nozzle coaxially, and the tapering of its tapering and outermost nozzle forms air passageways; The mesosphere nozzle bottom is fixed on the connecting rod by the fuel influx pipe, and this connecting rod is the gaseous fuel pipeline, and it has outside thread, matches with the internal thread that is embedded in the adjustment cover that small end covers;
The innermost layer nozzle is set in the nozzle of mesosphere coaxially, and the tapering of its tapering and mesosphere nozzle forms fuel channel; The innermost layer nozzle is fixed in one and is provided with on the externally threaded connecting rod, and this connecting rod is the liquid fuel pipeline, and it has outside thread, matches with the internal thread that is embedded in the adjustment cover that small end covers;
Rotate two respectively and adjust cover, drive mesosphere nozzle and innermost layer nozzle and move axially, adjust the discharge area of air passageways and fuel channel.
Described attenuated and diffused combustion nozzle of combustion turbine wherein is equipped with air swirler between outermost nozzle and the second layer nozzle.
Described attenuated and diffused combustion nozzle of combustion turbine wherein is equipped with the fuel swirl device between mesosphere nozzle and the innermost layer nozzle.
Described attenuated and diffused combustion nozzle of combustion turbine, wherein air swirler and fuel swirl device are vane swirler or tangential admission cyclone separator.
Described attenuated and diffused combustion nozzle of combustion turbine is wherein adjusted cover and is manual or driven by motor.
Described attenuated and diffused combustion nozzle of combustion turbine, wherein liquid fuel is diesel oil, heavy oil or methyl alcohol.
Put it briefly, attenuated and diffused combustion nozzle of combustion turbine provided by the invention, comprise fixedly tapered structure and two tapered structure movably, wherein be positioned at the stationary conduit of ragged edge and the air passageways that the intermediate movable tapered structure has formed a ring-like variable outlet, and be positioned at the fuel gas passage that innermost removable tapered structure and intermediate movable tapered structure have also constituted a ring-like variable discharge area, in the intermediate movable structure liquid fuel nozzle is arranged.Two removable frames link to each other with female thread structure on the end cap by two externally threaded pipes respectively, just can regulate the axial distance of two removable tapered structures by the inner thread piece on the rotary end cover, thereby change the discharge area of air and fuel, adjust its outlet velocity, reach under the different combustion condition stable, efficient, oligosaprobic burning.
When burner noz(zle) of the present invention moves, regulate two removable cone structures under non-dilution operating mode, make its discharge area that guarantees air and fuel a less position, this moment, flame holding was under design conditions.When air is diluted, because the air quantity after the dilution increases, make outlet velocity increase, make operating mode off-design operating mode, at this moment the internal thread controlling mechanism that covers of adjustable side makes two removable tapered structures move backward vertically, makes the discharge area of air increase, thereby the air outlet slit speed with under the non-dilution operating mode that makes air outlet slit speed become is identical, makes that flame can smooth combustion under different air dilution operating modes.When fuel dilution, similar in appearance to air dilution, regulate movable mechanism and make the discharge area of passage of fuel increase, make fuel outlet speed keep roughly constant, thereby guarantee the flow field condition of smooth combustion.
In addition, the present invention also is applicable to the synthetic gas burning of different component in the gas turbine, when synthesis gas components changes, two internal thread controlling mechanisms that cover by the adjustable side change the distance of the discharge area suggestion fuel outlet of fuel channel apart from air outlet slit, thereby realize stable, efficiently, oligosaprobic burning different component synthetic gas.
Description of drawings
Fig. 1 is an extreme adjusted position schematic representation of the present invention
Fig. 2 is another extreme adjusted position schematic representation of the present invention
Embodiment
Accompanying drawing is a specific embodiment schematic representation of the present invention.Wherein accompanying drawing 1 and accompanying drawing 2 are respectively two extreme adjusted positions of the present invention.With reference to accompanying drawing 1 as can be known, burner noz(zle) of the present invention mainly comprise three coaxial sheathed and tapered structure nozzles 1,2 and 3, its mesosphere nozzle 2 and innermost layer nozzle 3 can move axially structure.Outermost nozzle is fixed on the end cap 6 by fixed structure 7 (as support etc.).Middle interlayer nozzle 2 coaxial being set in the outermost nozzle 1, the spout place of two nozzles 1,2 forms air passageways 14.Mesosphere nozzle 2 is fixed on the connecting rod 10 by fuel influx pipe 8, and this connecting rod 10 is the fuel gas passage of hollow, and it has outside thread, and gaseous fuel can enter into fuel influx pipe 8 by connecting rod 10.Be inlaid with two rotating adjustment covers 12,13 on the small end lid 9 side by side, this adjustments cover 12,13 has female thread structure, wherein connecting rod 10 with adjust cover 12 by threads engaged (adjustment overlap 13 match with connecting rod 11 described later).Rotate and adjust cover 12, mesosphere nozzle 2 can be realized moving axially, thereby changes the sectional area of air passageways 14, promptly changes the throughput (as shown in Figure 2) of air fuel.Also be provided with air swirler 4 between the above-mentioned two-layer nozzle, be fixed on the outermost nozzle 1, this air swirler can be vane swirler or tangential admission cyclone separator etc.
Similar to outermost nozzle 1 with mesosphere nozzle 2, innermost layer nozzle 3 coaxial being set in the mesosphere nozzle 2, the spout place of these two nozzles 2,3 forms fuel channel 15.This innermost layer nozzle 3 is connected one and is with on the externally threaded connecting rod 11, and this connecting rod 11 is the fuel channel of hollow, feeds liquid fuel, diesel oil, heavy oil, methyl alcohol etc.Connecting rod 11 matches with the internal thread that small end covers the adjustment cover 13 on 9, and adjust cover 13 by rotation and can realize that innermost layer nozzle 3 moves axially, thus the sectional area (as shown in Figure 2) of change fuel channel 15.Be provided with fuel swirl device 5 between mesosphere nozzle 2 and the innermost layer nozzle 3, this fuel swirl device 5 is fixed on the mesosphere nozzle 2, and this air swirler can be vane swirler or tangential admission cyclone separator etc.
Adjusting cover 12 and 13 can be manual control, also can connect step motor control.
When air is diluted, because the increase of diluted air quantity makes the outlet velocity of air increase, flame off-design operating mode, and can not well burn.The present invention is according to different thinners and amount of dilution, described thinner comprises water, water vapor, nitrogen and carbon dioxide etc., regulate and adjust cover 12 and 13, make mesosphere nozzle 2 and innermost layer nozzle 3 move backward, make the discharge area of air passageways 14 increase like this, though the air quantity after diluted increases, outlet velocity remains unchanged.After general air is diluted, for the efficiency of turbine that guarantees gas turbine is constant, need to increase fuel quantity, at this moment also corresponding the adjusting adjusted cover 13 and made the discharge area of fuel channel 15 also increase and the fuel quantity that adapts to increase.So just can be under different operating modes, flame can be stablized, and is efficient, oligosaprobic burning.
Similar, when fuel is diluted, fuel quantity is owing to thinner and need the increase fuel quantity to guarantee that the efficiency of turbine of gas turbine increases, therefore for smooth combustion, regulating adjustment cover 13 makes innermost layer nozzle 3 move backward, thereby increase the discharge area of fuel channel 15, and keep the outlet velocity of fuel constant.So just can guarantee under different fuel dilution situations, keep the stable of flame, efficient, oligosaprobic burning.
When fuel is synthetic gas, because in the gas turbine operation process, the component of synthetic gas might change, and in different applications, the component of synthetic gas changes, if can not realize Field adjustment, can not realize smooth combustion.When the change of component of synthetic gas fuel, thereby the present invention by discharge area that regulate to adjust cover 12 and 13 and change fuel channels 15 and air passageways 14 with and relative position, thereby guarantee, the synthetic gas fuel of different component can be realized stable on this nozzle, efficiently, oligosaprobic burning.
Claims (6)
1. an attenuated and diffused combustion nozzle of combustion turbine comprises three concentric successively sheathed tapered nozzles, and wherein the innermost layer nozzle is set in the nozzle of mesosphere coaxially, and the tapering of its tapering and mesosphere nozzle forms fuel channel; The innermost layer nozzle is fixed in one and is provided with on the externally threaded connecting rod, and this connecting rod is the liquid fuel pipeline, and it has outside thread, matches with the internal thread that is embedded in the adjustment cover that small end covers;
Rotate two respectively and adjust cover, drive mesosphere nozzle and innermost layer nozzle and move axially, adjust the discharge area of air passageways and fuel channel;
It is characterized in that: outermost nozzle is fixed on the end cap; One side of this end cap and on be fixed with little end cap;
The mesosphere nozzle is set in the outermost nozzle coaxially, and the tapering of its tapering and outermost nozzle forms air passageways; The mesosphere nozzle bottom is fixed on the connecting rod by the fuel influx pipe, and this connecting rod is the gaseous fuel pipeline, and it has outside thread, matches with the internal thread that is embedded in the adjustment cover that small end covers.
2. attenuated and diffused combustion nozzle of combustion turbine as claimed in claim 1 is characterized in that, wherein is equipped with air swirler between outermost nozzle and the second layer nozzle.
3. attenuated and diffused combustion nozzle of combustion turbine as claimed in claim 1 is characterized in that, wherein is equipped with the fuel swirl device between mesosphere nozzle and the innermost layer nozzle.
4. as claim 2 or 3 described attenuated and diffused combustion nozzle of combustion turbine, it is characterized in that wherein air swirler and fuel swirl device are vane swirler or tangential admission cyclone separator.
5. attenuated and diffused combustion nozzle of combustion turbine as claimed in claim 1 is characterized in that, wherein adjusts cover and is manual or driven by motor.
6. attenuated and diffused combustion nozzle of combustion turbine as claimed in claim 1 is characterized in that, wherein liquid fuel is diesel oil, heavy oil or methyl alcohol.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100116662A CN100368667C (en) | 2006-04-13 | 2006-04-13 | Attenuated and diffused combustion nozzle of combustion turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100116662A CN100368667C (en) | 2006-04-13 | 2006-04-13 | Attenuated and diffused combustion nozzle of combustion turbine |
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| Publication Number | Publication Date |
|---|---|
| CN1959087A CN1959087A (en) | 2007-05-09 |
| CN100368667C true CN100368667C (en) | 2008-02-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2006100116662A Active CN100368667C (en) | 2006-04-13 | 2006-04-13 | Attenuated and diffused combustion nozzle of combustion turbine |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102937300B (en) * | 2012-11-28 | 2014-09-17 | 哈尔滨汽轮机厂有限责任公司 | Diluting-agent graded injection system for gas turbine |
| CN105642198B (en) * | 2016-03-18 | 2018-03-30 | 神华集团有限责任公司 | A kind of fixed bed multiphase atomizer |
| CN107442311B (en) * | 2017-08-02 | 2023-01-31 | 农业部南京农业机械化研究所 | Embedded gas-assisted spray head |
| CN111043625B (en) * | 2019-12-31 | 2024-06-04 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of miniature gas turbine and miniature gas turbine |
| CN111043626B (en) * | 2019-12-31 | 2024-06-04 | 新奥能源动力科技（上海）有限公司 | Nozzle, combustion chamber and gas turbine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4762977A (en) * | 1987-04-15 | 1988-08-09 | Browning James A | Double arc prevention for a transferred-arc flame spray system |
| DE3930569A1 (en) * | 1989-09-13 | 1991-03-21 | Siegfried W Schilling | Oil or gas burner mixing system - has coaxial air guide tube round nozzle stem of length twice hydraulic dia |
| CN1101113A (en) * | 1993-09-28 | 1995-04-05 | 德士古发展公司 | Partial oxidation prcess and burner with porous tip |
| EP0864812A2 (en) * | 1997-03-12 | 1998-09-16 | A. Schwarz + Co. | Mixing device for gas and oil burner |
| JPH11257664A (en) * | 1997-12-30 | 1999-09-21 | United Technol Corp <Utc> | Fuel injection nozzle/guide assembly for gas turbine engine |
| CN2463690Y (en) * | 2001-01-21 | 2001-12-05 | 董沐琴 | Atomized fuel and gas burner |
| CN1526927A (en) * | 2003-01-31 | 2004-09-08 | 通用电气公司 | Cooled flushing fuel injector |
-
2006
- 2006-04-13 CN CNB2006100116662A patent/CN100368667C/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4762977A (en) * | 1987-04-15 | 1988-08-09 | Browning James A | Double arc prevention for a transferred-arc flame spray system |
| DE3930569A1 (en) * | 1989-09-13 | 1991-03-21 | Siegfried W Schilling | Oil or gas burner mixing system - has coaxial air guide tube round nozzle stem of length twice hydraulic dia |
| CN1101113A (en) * | 1993-09-28 | 1995-04-05 | 德士古发展公司 | Partial oxidation prcess and burner with porous tip |
| EP0864812A2 (en) * | 1997-03-12 | 1998-09-16 | A. Schwarz + Co. | Mixing device for gas and oil burner |
| JPH11257664A (en) * | 1997-12-30 | 1999-09-21 | United Technol Corp <Utc> | Fuel injection nozzle/guide assembly for gas turbine engine |
| CN2463690Y (en) * | 2001-01-21 | 2001-12-05 | 董沐琴 | Atomized fuel and gas burner |
| CN1526927A (en) * | 2003-01-31 | 2004-09-08 | 通用电气公司 | Cooled flushing fuel injector |
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| Publication number | Publication date |
|---|---|
| CN1959087A (en) | 2007-05-09 |
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