CN104791847A - Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine - Google Patents
Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine Download PDFInfo
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- CN104791847A CN104791847A CN201510117660.2A CN201510117660A CN104791847A CN 104791847 A CN104791847 A CN 104791847A CN 201510117660 A CN201510117660 A CN 201510117660A CN 104791847 A CN104791847 A CN 104791847A
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Abstract
The invention discloses a low-rotational-flow multi-nozzle combustor structure applicable to a low-pollution combustion chamber of a gas turbine. A combustor is composed of six outer side low-rotational-flow nozzles and a center low-rotational-flow nozzle, the seven nozzles are of the same structure, and the six outer side low-rotational-flow nozzles are evenly arranged around the center nozzle at equal intervals in the circumferential direction. Gas fuel and air are premixed for combustion, and the flame temperature is reduced; a conical section flame stabilizing cover is installed at an outlet of each nozzle, and the stability of flames is improved. The combustor structure is stable in combustion, low in emission, small in combustion noise, reasonable in design, simple in structure and suitable for the low-pollution combustion chamber of the gas turbine.
Description
Technical field
The present invention relates to gas turbine technology field, specifically a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine.
Background technology
Gas-turbine combustion chamber extensively adopts swirl stabilized combustion technology.The recirculating zone quickening high-temperature combustion product that traditional high turbulent burner utilizes eddy flow to produce mixes with fresh reactant thing, thus stabilizes the flame.But it is long to there is the holdup time of pyroreaction thing in combustion chamber, causes the problem that NOx emission is higher.Low swirl flow combustion refers to and maintains flame stabilization burning with lower swirling number (swirling number is generally between 0.4 to 0.55), compared with high swirl flow combustion, there is not violent recirculating zone in low Swirling Flow, streamline is expanded at nozzle exit, cause air velocity to reduce, flame is just stabilized in the position that flame propagation velocity equals local air velocity.Through finding that patent WO2012141982A1 is described the low eddy flow single injector structure being applied to gas-turbine combustion chamber to the retrieval of prior art document, Chinese invention patent application numbers 201410073564.8, patent name: a kind of low swirl combustion chamber nozzle with Chinese invention patent application numbers 201410073523.9, proprietary term: the low swirl nozzle of a kind of gas-turbine combustion chamber has been set forth and has been applied to the low eddy flow single injector that gas turbine has different pre-mixed configuration.
But, in actual gas-turbine combustion chamber, usually nozzle annular close to each other or tubular multiinjector arrangement is adopted.Multiinjector structure both can increase thermic load and the load regulation rate of combustion chamber, and when can guarantee that again a nozzle stops working, it can rekindle by adjacent nozzle, maintained flame stabilization.In addition, multi-nozzle combustion system can reduce the wearing and tearing of combustion chamber, extends time between overhaul and reduces operating cost.Meanwhile, multi-nozzle combustion system has superior performance in suppression combustion noise and hot acoustical coupling vibration.
Summary of the invention
For the problems referred to above, the object of this invention is to provide the arrangement of the low eddy flow multi-injector burner of a kind of gas turbine premix, this multiinjector arrangement can suppress combustion noise and hot acoustical coupling vibration, improves stability and the load regulation rate of nozzle operation, and reduces pollutant emission.
For achieving the above object, the present invention takes following technical scheme:
A kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine, described multi-injector burner is made up of seven mutually isostructural low swirl nozzles, comprise the low swirl nozzle in outside and the low swirl nozzle in center, described six outer nozzle are equidistant, circumference is evenly arranged in the low swirl nozzle surrounding in center, described low swirl nozzle comprises low swirl nozzle outer wall, low swirl nozzle entrance and the outlet of low swirl nozzle, described low swirl nozzle entrance and the outlet of low swirl nozzle lay respectively at the two ends of described low swirl nozzle outer wall, described low swirl nozzle outer wall and low eddy flow cyclone constitute annular eddy flow runner and center flow channels, in described annular eddy flow runner, vane type axial swirler is installed, install in described cyclone center flow channels and open foraminate porous plate, the effect of porous plate is the flow regulated by center flow channels and annular eddy flow runner premix gas, in center flow channels, produce the turbulent flow of suitable intensity simultaneously, increase the spread speed of nozzle exit premixed flame, anti-anti-avulsion fire, described low eddy flow cyclone is arranged in the low swirl nozzle outer wall at h place, jet expansion upstream, in order to improve the stability of flame, described jet expansion one end is provided with cone section stable flame cover.
Preferably, the central axis of the low swirl nozzle of the low swirl nozzle in described outside and center is parallel to each other, and described outer nozzle is consistent with the rotation direction of the low swirl nozzle in center, and the rotation direction of described outer nozzle is identical.
Preferably, the low swirl nozzle in described outside is identical with center low swirl nozzle rotation direction.
Preferably, the spacing L of the low swirl nozzle of the low swirl nozzle in described center and outside is 1.5d-2.5d, and wherein d is low swirl nozzle diameter.
Preferably, the whirlpool caused in order to avoid the high-speed jet of nozzle exit gas is to the adverse effect of burning, and seven described low swirl nozzles stretch into combustion chamber one segment distance H, and described H is 0.5d-2d.
Preferably, the diameter d 1 of described multi-injector burner is 5d-8d.
Preferably, described axial swirler is made up of 6-10 sheet swirl vane.
Preferably, the blockage ratio of described porous plate is 35%-75%.
Preferably, described low eddy flow cyclone and the distance h of jet expansion are 1d-1.5d.
Preferably, the scope of the subtended angle α of described stable flame cover is 25 °-45 °, described stable flame cover length h
0scope be 0.4d-0.7d.
Compared with prior art, the present invention has the following advantages:
Owing to have employed multiinjector structure, compared to single injector burner under identical thermic load, reduce the air velocity by nozzle, the wearing and tearing of nozzle and combustion chamber can be reduced like this.By regulating the distance between nozzle, the interference effect that intercouples between Control Nozzle, reaches the object of restraint speckle and thermal acoustic oscillation.
In actual moving process, according to actual conditions, oepration at full load and operation at part load can be realized by opening and closing nozzle.Concrete operational mode is: oepration at full load (seven nozzles all work), four nozzles run (1,2a, 2c and 2f open or 1,2b, 2d and 2e open), single injector run (central nozzle 1 is opened) three kinds of operational modes.Like this when ensureing that nozzle air current speed is substantially constant, realize Load Regulation by selectively unlocking or shut-off nozzle.Improve the load regulation rate of nozzle, widen the working range of nozzle.
Due to the interaction of adjacent nozzle, there is time recirculating zone at the lip place of adjacent nozzle, a part of reactant reacts in secondary recirculating zone, and produce district of localized hyperthermia, this high-temperature region, as same lasting thermal source, improves the flameholding of nozzle flame.
Due to the poor premix state of nozzle operation, the equivalent proportion of work is near 0.6-0.8, and now flame temperature is lower, reduces the generation of thermal NO x.Swirl strength again due to jet expansion air-flow is lower, more weak in the recirculating zone, downstream of nozzle, or does not substantially form recirculating zone, shortens the holdup time of pyroreaction thing in combustion chamber, reduces the formation of NOx, reduces the discharge of burning pollutant.Meanwhile, multi-jetly the uniformity being beneficial to the Exit temperature distribution improving combustion chamber is furnished with.
Accompanying drawing explanation
Fig. 1 is the low turbulent burner structural representation of multiinjector in the embodiment of the present invention.
Fig. 2 is that in the embodiment of the present invention, the low turbulent burner of multiinjector arranges schematic diagram.
Fig. 3 is single low swirl nozzle structural representation in the embodiment of the present invention.
Fig. 4 is single low swirl nozzle sectional view in the embodiment of the present invention.
Fig. 5 is adjacent nozzle streamline distribution figure in multi-injector burner in the embodiment of the present invention.
Fig. 6 is multi-injector burner combustion chamber placement schematic diagram in the embodiment of the present invention, and (a) is the tubular combustion chamber placement of multiinjector, and (b) is that multiinjector can annular type combustor is arranged.
In figure: the low swirl nozzle in 1-center; 10-burner head tubular wall; Low swirl nozzle outside 2a/2b/2c/2d/2e/2f-; The low swirl nozzle entrance of 3-; The low swirl nozzle outer wall of 4-; The low swirl nozzle outlet of 5-; The low eddy flow cyclone of 60-; 62-axial swirler; 63-porous plate; 64-annular eddy flow runner; 65-cyclone center flow channels; 7-burner head end cap; 70-bores section stable flame cover; 8-suspension premixed flame; 90-recirculating zone; 91-adjacent nozzle outlet streamline.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
As Fig. 1, shown in Fig. 3 and Fig. 4, embodiments provide a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine, described multi-injector burner is made up of seven mutually isostructural low swirl nozzles, comprises the low swirl nozzle 2a in outside, 2b, 2c, 2d, 2e, the low swirl nozzle 1 of 2f and center, described six outer nozzle 2a, 2b, 2c, 2d, 2e, 2f is equidistant, circumference is evenly arranged in center low swirl nozzle 1 surrounding, and described low swirl nozzle comprises low swirl nozzle outer wall 4, low swirl nozzle entrance 3 and low swirl nozzle outlet 5, described low swirl nozzle entrance 3 and low swirl nozzle outlet 5 lay respectively at the two ends of described low swirl nozzle outer wall 4, annular eddy flow runner 64 and center flow channels 65 is provided with in described low swirl nozzle outer wall 4, in described annular eddy flow runner 64, vane type axial swirler 62 is installed, install by opening foraminate porous plate 63 in described cyclone center flow channels 65, the effect of porous plate 63 is the flow regulated by center flow channels 65 and annular eddy flow runner 64 premix gas, in center flow channels 65, produce the turbulent flow of suitable intensity simultaneously, increase the spread speed of nozzle exit premixed flame 8, anti-anti-avulsion fire, wherein, the blade number of axial swirler is 8, setting angle is 37 °, and the blockage ratio of porous plate is 30%.Swirling number is 0.55.In order to improve the stability of flame, cone section stable flame cover 70 is installed in the exit of each nozzle.In this embodiment, the subtended angle of stable flame cover 70 is α=45 °, and length is h
0=14mm.Described porous plate 63 one end is connected with low eddy flow cyclone 60, described low eddy flow cyclone 60 is arranged on h place, jet expansion 5 upstream, in order to improve the stability of flame, described jet expansion 5 one end is provided with cone section stable flame cover 70, and the spacing L of central nozzle and surrounding nozzle is 34mm.Multiple nozzle, to the adverse effect of burning, is stretched into combustion chamber one segment distance H=45mm by the whirlpool caused in order to avoid the high-speed jet of nozzle exit gas.The diameter d 1=280mm of multi-injector burner.
As shown in Figure 2, this multi-injector burner can adopt two kinds of different rotation direction combinations.A kind of is that the rotation direction of seven nozzles is all identical, as shown in Fig. 2 (a); Another arrangement is that nozzle 1,2a, 2c are consistent with the rotation direction of 2f, and nozzle 2b, 2d are identical with the rotation direction of 2e, but the rotation direction of these two groups of nozzles is contrary, as shown in Fig. 2 (b).
As shown in Figure 5, the one-jet specific works process of low eddy flow is, the premixed flow of gaseous fuel and air is by low turbulent burner, and a part of air-flow does not produce eddy flow by central passage, another part air-flow, through being equipped with the circular passage of swirl vane, produces high-speed rotational.Produce expanding streamline 91 at nozzle exit, air velocity reduces gradually, and premixed flame 8 is just stabilized in flame propagation velocity and equals on the position of local air velocity.Due to the interaction of the air-flow of adjacent nozzle, at the lip place of adjacent nozzle, there is time recirculating zone 90, part reactant reacts in secondary recirculating zone, produce district of localized hyperthermia, this high-temperature region, as same lasting thermal source, improves the combustion stability of nozzle flame.
Embodiment
Fig. 6 is multi-injector burner combustion chamber placement schematic diagram.As shown in the figure, in concrete layout, according to the structure of actual gas turbine, this multi-injector burner can be arranged to pipe-type chamber or can annular type combustor.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. one kind is applicable to the low eddy flow multi-injector burner structure of low-pollution burning chamber of gas turbine, it is characterized in that, described multi-injector burner is made up of seven mutually isostructural low swirl nozzles, comprise the low swirl nozzle (2a in outside, 2b, 2c, 2d, 2e, 2f) with the low swirl nozzle in center (1), described six outer nozzle (2a, 2b, 2c, 2d, 2e, 2f) equidistant, circumference is evenly arranged in center low swirl nozzle (1) surrounding, described low swirl nozzle comprises low swirl nozzle outer wall (4), low swirl nozzle entrance (3) and low swirl nozzle outlet (5), described low swirl nozzle entrance (3) and low swirl nozzle outlet (5) lay respectively at the two ends of described low swirl nozzle outer wall (4), described low swirl nozzle outer wall (4) and low eddy flow cyclone (60) constitute annular eddy flow runner (64) and center flow channels (65), in described annular eddy flow runner (64), vane type axial swirler (62) is installed, install in described cyclone center flow channels (65) and open foraminate porous plate (63), described low eddy flow cyclone (60) is arranged in the low swirl nozzle outer wall (4) at h place, jet expansion (5) upstream, described jet expansion (5) one end is provided with cone section stable flame cover (70).
2. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, the central axis in the low swirl nozzle in described outside (2a, 2b, 2c, 2d, 2e, 2f) and center low swirl nozzle (1) is parallel to each other, described outer nozzle (2a, 2c, 2f) is consistent with the rotation direction at the low swirl nozzle in center (1), and the rotation direction of described outer nozzle (2b, 2d, 2e) is identical.
3. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, the low swirl nozzle in described outside (2a, 2b, 2c, 2d, 2e, 2f) is identical with center low swirl nozzle (1) rotation direction.
4. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, the low swirl nozzle in described center (1) is 1.5d-2.5d with the spacing L in the low swirl nozzle in outside (2a, 2b, 2c, 2d, 2e, 2f), and wherein d is low swirl nozzle diameter.
5. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, seven described low swirl nozzles stretch into combustion chamber one segment distance H, and described H is 0.5d-2d.
6. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, the diameter d 1 of described multi-injector burner is 5d-8d.
7. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, described axial swirler (62) is made up of 6-10 sheet swirl vane.
8. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, the blockage ratio of described porous plate (63) is 35%-75%.
9. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, is characterized in that, described low eddy flow cyclone (60) is 1d-1.5d with the distance h of jet expansion (5).
10. a kind of low eddy flow multi-injector burner structure being applicable to low-pollution burning chamber of gas turbine according to claim 1, it is characterized in that, the scope of the subtended angle α of described stable flame cover (70) is 25 °-45 °, described stable flame cover (70) length h
0scope be 0.4d-0.7d.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510117660.2A CN104791847A (en) | 2015-03-17 | 2015-03-17 | Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine |
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| CN201510117660.2A CN104791847A (en) | 2015-03-17 | 2015-03-17 | Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143880A (en) * | 2017-05-16 | 2017-09-08 | 西北工业大学 | A kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine |
| CN107143881A (en) * | 2017-05-16 | 2017-09-08 | 西北工业大学 | A kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine |
| CN108613217A (en) * | 2018-03-29 | 2018-10-02 | 北京航天动力研究所 | A kind of partly-premixed injection device of distribution formula and combustion chamber |
| CN113776086A (en) * | 2021-10-08 | 2021-12-10 | 浙江浙能技术研究院有限公司 | Low-pollution combustion chamber nozzle structure and method |
| CN116147017A (en) * | 2022-11-02 | 2023-05-23 | 上海交通大学 | Lean premixed annular multi-nozzle combustor with strong and weak rotational flow matching function and gas turbine |
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| US7137258B2 (en) * | 2004-06-03 | 2006-11-21 | General Electric Company | Swirler configurations for combustor nozzles and related method |
| CN103822229A (en) * | 2014-02-28 | 2014-05-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low swirl nozzle for combustion chamber of gas turbine |
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2015
- 2015-03-17 CN CN201510117660.2A patent/CN104791847A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7137258B2 (en) * | 2004-06-03 | 2006-11-21 | General Electric Company | Swirler configurations for combustor nozzles and related method |
| CN103822229A (en) * | 2014-02-28 | 2014-05-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low swirl nozzle for combustion chamber of gas turbine |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107143880A (en) * | 2017-05-16 | 2017-09-08 | 西北工业大学 | A kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine |
| CN107143881A (en) * | 2017-05-16 | 2017-09-08 | 西北工业大学 | A kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine |
| CN107143880B (en) * | 2017-05-16 | 2020-02-14 | 西北工业大学 | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine |
| CN107143881B (en) * | 2017-05-16 | 2020-02-14 | 西北工业大学 | Multi-point direct injection head structure for low-pollution combustion chamber of gas turbine |
| CN108613217A (en) * | 2018-03-29 | 2018-10-02 | 北京航天动力研究所 | A kind of partly-premixed injection device of distribution formula and combustion chamber |
| CN113776086A (en) * | 2021-10-08 | 2021-12-10 | 浙江浙能技术研究院有限公司 | Low-pollution combustion chamber nozzle structure and method |
| CN113776086B (en) * | 2021-10-08 | 2023-01-31 | 浙江浙能技术研究院有限公司 | Low-pollution combustion chamber nozzle structure and method |
| CN116147017A (en) * | 2022-11-02 | 2023-05-23 | 上海交通大学 | Lean premixed annular multi-nozzle combustor with strong and weak rotational flow matching function and gas turbine |
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