CN104110699A - Premixing nozzle of gas turbine combustion chamber - Google Patents
Premixing nozzle of gas turbine combustion chamber Download PDFInfo
- Publication number
- CN104110699A CN104110699A CN201410325716.9A CN201410325716A CN104110699A CN 104110699 A CN104110699 A CN 104110699A CN 201410325716 A CN201410325716 A CN 201410325716A CN 104110699 A CN104110699 A CN 104110699A
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- Prior art keywords
- combustion chamber
- gradual shrinkage
- gas
- centerbody
- turbine combustion
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 28
- 239000000446 fuel Substances 0.000 claims abstract description 60
- 238000002156 mixing Methods 0.000 claims description 52
- 230000008676 import Effects 0.000 claims description 11
- 239000000203 mixture Substances 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 2
- 230000002035 prolonged effect Effects 0.000 abstract 1
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 15
- 239000007789 gas Substances 0.000 description 11
- 230000000694 effects Effects 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 6
- 239000007800 oxidant agent Substances 0.000 description 6
- 238000005496 tempering Methods 0.000 description 5
- 230000001590 oxidative effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 206010020843 Hyperthermia Diseases 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000036031 hyperthermia Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Abstract
The invention discloses a premixing nozzle of a gas turbine combustion chamber and relates to a nozzle structure with axial rotational flow. According to the technical scheme, a gradually-shrinking type annular pipe is arranged between a gradually-shrinking type center body and an axial cyclone, an annular channel is formed between the gradually-shrinking type annular pipe and the gradually-shrinking type center body, an inner-layer air inlet is formed in the front end of the annular channel, and a guide vane is arranged in the annular channel. The guide vane is provided with an inner-layer fuel outlet and an inner-layer fuel channel, and the inner-layer fuel channel is communicated with a center gas fuel inlet and an outer-layer fuel channel. According to premixing nozzle, due to the feature that backfire is prone to occurring in a low-speed area, a layer of irrotational-flow or weak rotational-flow circulation channel is added on the outer side of the gradually-shrinking type center body and on the inner side of the axial cyclone. The low-speed area, caused by the rotating centrifugal force of the cyclone, of the center portion is effectively eliminated, and therefore the backfire problem of premixing combustion can be prevented, the service life of the premixing nozzle can be prolonged, and the use and maintaining cost of the gas turbine combustion chamber can be reduced.
Description
Technical field
The present invention relates to use the gas-turbine combustion chamber structure of gaseous fuel premixed combustion, particularly a kind of nozzle arrangements with axial rotational flow.
Background technology
Because the requirement of environmental protection is more and more stricter, in gas turbine burner in recent years, the mode with premixed combustion reduces the discharge of nitrogen oxide (NOx) more and more.Premixed combustion combustion chamber adopts eddy flow hybrid technology to realize fuel to mix with the good of oxidant more, thereby reaches the needs of low NOx combustion.
Thereby this eddy flow hybrid technology applies certain tangential momentum by multiple blade constructions being set in nozzle mixing section upstream to air-flow, consequent turbulent perturbation makes fuel and oxidant to realize quick and uniform mixed effect at downstream space.It has been generally acknowledged that, swirl strength is larger, more can realize even mixing.But the introducing of tangential momentum, can produce in the region of mixing section near axis the lower region of axial velocity, and along with the increase of swirl strength, this low regime also can expand rapidly, even produces and refluxes.Owing to having started to mix at mixing section fuel and oxidant, the high-temperature gas that backflow is brought into probably makes the mixture burns of fuel-oxidant, even makes flame stabilization in the low regime of mixing section, and then causes burning of nozzle.Therefore,, for adopting the combustion chamber of eddy flow hybrid technology, need to adopt particular design means to avoid the generation of this phenomenon.
Prior art conventionally adopts the nozzle vane design of lower swirl strength and adjusts fuel nozzle mode, reaches the object of eliminating flame in mixing section and exist possibility.In design, spray by the fuel that adopts major diameter high pressure ratio in early days, make fuel away from center low speed district; Improve design, by adopting blade surface to spray, adjusting the position of spray-hole, realizing fuel poorer at mixing section center, be difficult to form active combustion.Thereby these two kinds of methods are all by the fuel concentration in low regime being reduced to the following possibility that reduces tempering of combustion limits, but all do not have from eliminating in essence low regime.In the time of upstream or the variation of downstream airflow condition, well-designed fuel and the distribution of oxidant in blender is originally easy to be upset, and still has larger tempering risk.In addition, the fuel concentration of reduction low regime is not effectively utilized the blending space in mixing section.
In patent ZL02802306.4, proposed to be provided with the space that gas passes through between the inner peripheral surface of swirler blades wheel hub and nozzle shaft, the method can reduce the scope of low regime.But because wheel hub has just increased the passage of gas communication in the altitude range of swirl vane, and its passage providing is straight channel, the effect of the minimizing low regime that it can reach is very limited, and the problem of tempering still exists.
Summary of the invention
The object of the invention is for shortcomings and deficiencies of the prior art, a kind of pre-mixing nozzle structure of gas-turbine combustion chamber is proposed, be intended to eliminate the possibility that nozzle mixing section Nei Di flow velocity district exists, thereby suppress the generation of tempering, extend the life-span of pre-mixing nozzle, reduce the operation and maintenance cost of gas-turbine combustion chamber.
Technical scheme of the present invention is as follows: a kind of pre-mixing nozzle of gas-turbine combustion chamber, and this pre-mixing nozzle contains axial swirler, gradual shrinkage centerbody and mixing section, be provided with outer air import at the front end of described axial swirler, on the swirl vane of axial swirler, be provided with outer fuel outlet and outer fuel channel, be provided with center gas fuel inlet at gradual shrinkage centerbody front end, it is characterized in that: between gradual shrinkage centerbody and axial swirler, be provided with the gradual shrinkage ring pipe coaxially arranged with gradual shrinkage centerbody, this gradual shrinkage ring pipe is by ring pipe direct tube section, ring pipe converging transition and ring pipe outlet straight section composition, between gradual shrinkage ring pipe and gradual shrinkage centerbody, circularize passage, the front end of circular passage is provided with inner air import, and be furnished with guide vane in the straight section of circular passage, guide vane is provided with internal layer fuel outlet and internal layer fuel channel, internal layer fuel channel is connected with center gas fuel inlet and outer fuel channel.
In technique scheme, the eddy flow angle of described guide vane is preferably 0～10 °.
Technical characterictic of the present invention is also: the length that described gradual shrinkage ring pipe extends vertically exceedes the length of gradual shrinkage centerbody, and is less than or equal to the length of mixing tube, and the length exceeding is at least 0.2 times of gradual shrinkage centerbody diameter.
Another technology of the present invention is characterized in that: the excursion of the circulation area of described circular passage is 0～10%.The circulation area of circular passage is 5%～50% of mixing section circulation area.
Another technology of the present invention is characterized in that: on the inwall of the mixing section in gradual shrinkage centerbody downstream, be furnished with flow spoiler; Described flow spoiler is convex structure; Described convex structure is preferably continuous annulus convex structure or discrete convex structure.
The present invention compared with prior art, have the following advantages and high-lighting effect: for the nozzle arrangements of individual layer eddy flow hybrid channel that adopts gradual shrinkage centerbody, fuel-oxidant mixtures body under the effect of centrifugal force of rotation towards nozzle flows outside, thereby cause generation low regime, nozzle center region.Thereby easily causing tempering, the existence of low regime may cause burning of pre-mixing nozzle.Pre-mixing nozzle of the present invention, by the circular passage at gradual shrinkage centerbody outside, axial swirler inner side introducing acylic motion or low eddy flow, makes because the low regime that outside eddy flow produces reduces; By controlling the circulation area of circular passage, effectively control the distribution of gas flow rate, thereby further reduce low regime further.Show by the three-dimensional pneumatic analysis to this pre-mixing nozzle, by the eddy flow angle of reasonable control guide vane and the circulation area of circular passage, can substantially eliminate the low regime in centerbody downstream, effectively pre-anti-backfire.On the other hand, owing to having reduced the low regime in nozzle, therefore can utilize more fully the blending space of nozzle interior.After introducing flow spoiler, the mixed performance of nozzle is further promoted.Because fuel and air were just fully mixed before entering burner inner liner, thereby in the time of burning, suppress the existence of localized hyperthermia, can effectively suppress like this discharge of NOx.
Brief description of the drawings
Fig. 1 is the structural principle schematic diagram of the pre-mixing nozzle of a kind of gas-turbine combustion chamber provided by the invention.
Fig. 2 is axial swirler perspective view.
Fig. 3 expresses on the inwall of mixing section and is furnished with flow spoiler.
In figure: 1-axial swirler; The import of 11-outer air; 12-swirl vane; The outer fuel channel of 121-; The outer fuel outlet of 122-; 13-cyclone outer wall; 2-gradual shrinkage centerbody; 21-fuel inlet; 3-mixing section; 4-gradual shrinkage ring pipe; 5-circular passage; The import of 51-inner air; 6-guide vane; 61-internal layer fuel outlet; 62-internal layer fuel channel; 7-flow spoiler; The outer fuel channel of 121-; The outer fuel outlet of 122-.
Detailed description of the invention
Below in conjunction with accompanying drawing, to principle of the present invention, structure and detailed description of the invention are described further.
Fig. 1, Fig. 2 are the structural principle schematic diagram of the pre-mixing nozzle of a kind of gas-turbine combustion chamber provided by the invention.This nozzle comprises axial swirler 1, gradual shrinkage centerbody 2, mixing section 3, wherein, on axial swirler 1, be provided with outer air import 11, swirl vane 12 and cyclone outer wall 13, on swirl vane 12, be provided with outer fuel outlet 122 and outer fuel channel 121, on gradual shrinkage centerbody 2, be provided with center gas fuel inlet 21, in gradual shrinkage centerbody 2 outsides, axial swirler 1 inner side is provided with the gradual shrinkage ring pipe 4 coaxially arranged with gradual shrinkage centerbody 2, the outer wall of the inwall of gradual shrinkage ring pipe and gradual shrinkage centerbody 2 forms circular passage 5, the front end of circular passage 5 forms inner air import 51, and in the straight section of circular passage 5, be furnished with guide vane 6, guide vane 6 is provided with internal layer fuel outlet 61 and internal layer fuel channel 62, internal layer fuel channel 62 is connected with center gas fuel inlet 21 and outer fuel channel 121.
For using the premixing nozzle structure of axial swirler, the centerbody structure that is absolutely necessary, its is on the one hand for axial swirler provides center support, thereby provides on the other hand gaseous fuel import to ensure the supply of fuel.The gradual shrinkage centerbody 2 that the present invention adopts has larger help for the low regime of reducing tail district, but due to impact and the turning effort of axial swirler 1 to air-flow of gradual shrinkage centerbody 2 tails, if do not taken measures, the central area of mixing section 3 still has larger low regime.Along with reducing of axial swirler 1 eddy flow angle, the low regime in mixing section 3 has certain reducing.But along with reducing of eddy flow angle, the mixed performance of fuel and air can decline.Based on above analysis, the present invention proposes nozzle passage radial grading, introduce circular passage 5, carry out flowing of body tail district of control centre by controlling the circulation area of circular passage 5.Because the circulation area of circular passage 5 is less, the circulation area of general circular passage is 5%～50% of mixing section circulation area, the axial velocity that can ensure gas in whole passage due to less circulation road is higher, thereby can eliminate the low regime in gradual shrinkage centerbody 2 tail districts.In order to ensure that the gas in circular passage 5 has higher speed all the time in the tail district of gradual shrinkage centerbody 2, the length that gradual shrinkage ring pipe 4 extends vertically should exceed the length of gradual shrinkage centerbody 2, and being less than or equal to the length of mixing tube, the length exceeding is at least 0.2 times of gradual shrinkage centerbody diameter.In addition, the eddy flow angle of guide vane 6 is set to 0～10 °, because can cause the Speed Reduction of the central segment of mixing section 3 in the time that eddy flow angle is excessive, thereby reduces the effect of less low regime.Fined away and also can, in minor betterment mobile performance, reduce the low regime of end in gradual shrinkage ring pipe 4 ends.
In such scheme, in order to reduce flow resistance, the circulation area variable quantity of circular passage 5 should be controlled at 0～10%.
Owing to having reduced the low regime in nozzle, therefore can utilize more fully the blending space of nozzle interior.Except the fuel from outer fuel outlet 121 mixes with from the rotational flow air of outer air import 11, also mix circular passage 5 is interior with air from inner air import 51 from the fuel of internal layer fuel outlet 61.In the situation that reaching same mixed effect, thereby can having less volume, this pre-mixing nozzle is conducive to save cost.
By adjusting the area of outer fuel outlet 121 and internal layer fuel outlet 61, can control the distribution of gaseous fuel in mixing section, this will be conducive to produce the benefit of the aspect such as operability, discharge in given combustion chamber.Because fuel and air had just reached good mixed effect before entering burner inner liner, thereby in the time of burning, suppress the existence of localized hyperthermia, can effectively suppress like this discharge of NOx.
Referring to Fig. 3, the present invention is furnished with flow spoiler 7 on the inwall of the mixing section 3 in the downstream of gradual shrinkage centerbody 2, and its effect is to improve near the mobile performance of mixing section 3 internal faces, strengthens the mixing intensity of fuel and air.Flow spoiler 7 entirety are convex structure, and this convex structure can be continuous annulus convex structure, can be also discrete convex structures.
Claims (8)
1. a pre-mixing nozzle for gas-turbine combustion chamber, this pre-mixing nozzle contains axial swirler (1), gradual shrinkage centerbody (2 and mixing section (3); be provided with outer air import (11) at the front end of described axial swirler (1), on the swirl vane (12) of axial swirler, be provided with outer fuel outlet (122) and outer fuel channel (121), be provided with center gas fuel inlet (21) at gradual shrinkage centerbody (2) front end, it is characterized in that: between gradual shrinkage centerbody (2) and axial swirler (1), be provided with the gradual shrinkage ring pipe (4) coaxially arranged with gradual shrinkage centerbody (2), this gradual shrinkage ring pipe (4) is by ring pipe direct tube section, ring pipe converging transition and ring pipe outlet straight section composition, between gradual shrinkage ring pipe and gradual shrinkage centerbody (2), circularize passage (5), the front end of circular passage (5) is provided with inner air import (51), and in the straight section of circular passage (5), be furnished with guide vane (6), guide vane (6) is provided with internal layer fuel outlet (61) and internal layer fuel channel (62), internal layer fuel channel (62) is connected with center gas fuel inlet (21) and outer fuel channel (121).
2. the pre-mixing nozzle of a kind of gas-turbine combustion chamber as claimed in claim 1, is characterized in that: the eddy flow angle of described guide vane (6) is 0～10 °.
3. a kind of pre-mixing nozzle of gas-turbine combustion chamber as claimed in claim 1 or 2, it is characterized in that: the length that described gradual shrinkage ring pipe (4) extends vertically exceedes the length of gradual shrinkage centerbody (2), and being less than or equal to the length of mixing tube (3), the length exceeding is at least 0.2 times of gradual shrinkage centerbody (2) diameter.
4. the pre-mixing nozzle of a kind of gas-turbine combustion chamber as claimed in claim 1, is characterized in that: the excursion of the circulation area of described circular passage (5) is 0～10%.
5. the pre-mixing nozzle of a kind of gas-turbine combustion chamber as claimed in claim 1, is characterized in that: the circulation area of circular passage (5) is 5%～50% of mixing section (3) circulation area.
6. the pre-mixing nozzle of a kind of gas-turbine combustion chamber as claimed in claim 1, is characterized in that: on the inwall of the mixing section (3) in the downstream of gradual shrinkage centerbody (2), be furnished with flow spoiler (7).
7. the pre-mixing nozzle of a kind of gas-turbine combustion chamber as claimed in claim 6, is characterized in that: described flow spoiler (7) is convex structure.
8. the pre-mixing nozzle of a kind of gas-turbine combustion chamber as claimed in claim 7, is characterized in that: described convex structure is continuous annulus convex structure or discrete convex structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410325716.9A CN104110699B (en) | 2014-07-09 | 2014-07-09 | A kind of pre-mixing nozzle of gas-turbine combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410325716.9A CN104110699B (en) | 2014-07-09 | 2014-07-09 | A kind of pre-mixing nozzle of gas-turbine combustion chamber |
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| Publication Number | Publication Date |
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| CN104110699A true CN104110699A (en) | 2014-10-22 |
| CN104110699B CN104110699B (en) | 2017-09-15 |
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| CN104373963A (en) * | 2014-10-28 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Inner body slotting type swirl nozzle for combustion chamber of gas turbine |
| CN104373962A (en) * | 2014-10-28 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Blade type air inlet swirl nozzle for combustion chamber of gas turbine |
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| CN114110662A (en) * | 2021-11-25 | 2022-03-01 | 同济大学 | Low-nitrogen combustion chamber of gas turbine |
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