CN204006117U - A kind of pre-mixing nozzle for gas-turbine combustion chamber - Google Patents
A kind of pre-mixing nozzle for gas-turbine combustion chamber Download PDFInfo
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- CN204006117U CN204006117U CN201420378241.5U CN201420378241U CN204006117U CN 204006117 U CN204006117 U CN 204006117U CN 201420378241 U CN201420378241 U CN 201420378241U CN 204006117 U CN204006117 U CN 204006117U
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- nozzle
- centerbody
- mixing
- gas
- gradual shrinkage
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Abstract
For a pre-mixing nozzle for gas-turbine combustion chamber, relate to the nozzle structure of combustion chamber with radial vortex.This pre-mixing nozzle has been evenly arranged a plurality of inner air imports in radial swirler upstream, gradual shrinkage centerbody in mixing section outer is arranged with the ring pipe coaxially arranged with gradual shrinkage centerbody, the front end of ring pipe is connected with nozzle head, the outer wall of the inwall of ring pipe and gradual shrinkage centerbody forms circular passage, and circular passage is connected with inner air import.The utility model is by introducing air duct in radial swirler upstream, and increase one deck circulation passage in mixing section inner side, can effectively eliminate the low regime of the central part causing due to cyclone rotary centrifugal force, thereby effectively prevent the tempering problem of premixed combustion, extend the life-span of pre-mixing nozzle.
Description
Technical field
The utility model relates to the gas-turbine combustion chamber structure of using gaseous fuel premixed combustion, particularly a kind of nozzle arrangements with radial vortex.
Background technology
Because the requirement of environmental protection is more and more stricter, in gas turbine burner in recent years, by the mode of premixed combustion, reduce more and more the discharge of nitrogen oxide (NOx).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 a plurality of 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 the combustion chamber of employing eddy flow hybrid technology, need to adopt particular design means to avoid the generation of this phenomenon.
Prior art is common to be adopted the nozzle vane design of lower swirl strength and adjusts fuel nozzle mode, reaches and eliminates the object that the interior flame of mixing section exists possibility.In design, by adopting the fuel of major diameter high pressure ratio to spray, make fuel away from center low speed district in early days; 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.When 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.
In patent CN101713549A, by introducing Venturi tube chamber, make mist first accelerate rear deceleration.Mist has been eliminated low regime after accelerating.Although this structure can prevent that flame from entering head zone, due to the existence of Venturi tube chamber expansion segment, this zone velocity is lower, may cause flame to exist in this region.If there is no suitable cooling provision, nozzle may be burnt.
Utility model content
The purpose of this utility model is for shortcomings and deficiencies of the prior art, a kind of pre-mixing nozzle structure for 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.
The technical solution of the utility model is as follows:
A kind of pre-mixing nozzle for gas-turbine combustion chamber, this nozzle comprises nozzle head, gradual shrinkage centerbody and mixing section, wherein, on nozzle head, be provided with peripheral gaseous fuel import and radial swirler, on radial swirler, be provided with outer air entrance, on gradual shrinkage centerbody, be provided with center gas fuel inlet and center gas fuel outlet, it is characterized in that: in radial swirler upstream, be evenly arranged a plurality of inner air imports, gradual shrinkage centerbody in mixing section outer is arranged with the ring pipe coaxially arranged with gradual shrinkage centerbody, the front end of ring pipe is connected with nozzle head, the outer wall of the inwall of ring pipe and gradual shrinkage centerbody forms circular passage, circular passage is connected with inner air import.
Technical characterictic of the present utility model is also: the length that described ring pipe extends vertically surpasses the length of gradual shrinkage centerbody, and is less than or equal to the length of mixing tube, and the length surpassing is at least 0.2 times of gradual shrinkage centerbody diameter.
Another technical characterictic of the present utility model is: the excursion of the circulation area of circular passage is: 0～10%.The circulation area of circular passage is 5%～50% of mixing section circulation area.
Another technical characterictic of the present utility model is: the circulation area sum of a plurality of inner air imports is more than or equal to the circulation area of circular passage.
The utility model compared with prior art, have the following advantages and high-lighting effect: for the nozzle arrangements that adopts the individual layer eddy flow hybrid channel of 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 utility model, by in the import of radial swirler upstream arrangement inner air, at the ring pipe of mixing section disposed inboard gradual shrinkage, on gradual shrinkage centerbody, arrange center gas fuel outlet, thereby in mixing section inner side, formed the mixed zone of a new fuel and air.Pass through to control further the circulation area of circular passage, thereby can control the distribution of gas flow rate, effectively reduce low regime.By the three-dimensional pneumatic analysis to this nozzle, show, rationally controlling in the eddy flow angle of cyclone and the circulation area situation of circular passage, can substantially eliminate the low regime in centerbody downstream, effectively pre-anti-backfire; Owing to having reduced the low regime of nozzle interior, therefore can utilize more fully the blending space of nozzle interior.Fuel and air were just fully mixed before entering burner inner liner simultaneously, thereby when burning, had suppressed the existence of localized hyperthermia, effectively suppressed the discharge of NOx.
Accompanying drawing explanation
The structural principle schematic diagram of a kind of pre-mixing nozzle for gas-turbine combustion chamber that Fig. 1 provides for the utility model.
Fig. 2 is the A-A cutaway view of Fig. 1.
Fig. 3 is the generalized section of pre-mixing nozzle stereochemical structure.
In figure: 1-nozzle head; The peripheral gaseous fuel import of 11-; 12-radial swirler; 121-outer air entrance; The import of 13-inner air; 2-gradual shrinkage centerbody; The fuel inlet of 21-center gas; 22-center gas fuel outlet; 3-mixing section; 4-ring pipe; 5-circular passage.
The specific embodiment
Below in conjunction with accompanying drawing, to principle of the present utility model, structure and the specific embodiment are described further.
The structural principle schematic diagram of the pre-mixing nozzle for gas-turbine combustion chamber that Fig. 1 provides for the utility model, this pre-mixing nozzle comprises nozzle head 1, gradual shrinkage centerbody 2 and mixing section 3, wherein, on nozzle head 1, be provided with peripheral gaseous fuel import 11 and radial swirler 12; On radial swirler 12, be provided with outer air entrance 121, on gradual shrinkage centerbody 2, be provided with center gas fuel inlet 21 and center gas fuel outlet 22; In radial swirler 12 upstream arrangement, there is inner air import 13, gradual shrinkage centerbody 2 in mixing section 3 outer is arranged with the ring pipe 4 coaxially arranged with gradual shrinkage centerbody 2, the front end of ring pipe 4 is connected with nozzle head 1, the outer wall of the inwall of ring pipe 4 and gradual shrinkage centerbody 2 forms circular passage 5, and circular passage 5 is connected with inner air import 13.
Premixing nozzle structure for using radial swirler, due to flow rotation effect, can form low regime in nozzle center, and gradual shrinkage centerbody 2 can reduce low regime to a certain extent, but its tail region still inevitably has low regime.Only have by improving the mobile of centerbody tail district and could fundamentally eliminate low regime.Based on above analysis, the utility model proposes nozzle passage radial grading, introduce circular passage 5, by controlling the circulation area of circular passage 5, carry out flowing of control centre's body tail district; The circulation area of circular passage 5 is generally 5%～50% of mixing section 3 circulation areas.Because the circulation area of circular passage 5 is less, (being generally no more than 30% of mixing section 3 circulation areas) less circulation road can guarantee that the axial velocity of gas in whole passage is higher, thereby can eliminate the low regime in gradual shrinkage centerbody 2 tail districts.
In order to guarantee 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 described ring pipe 4 extends vertically should surpass the length of gradual shrinkage centerbody 2, and being less than or equal to the length of mixing tube 3, the length surpassing is at least 0.2 times of gradual shrinkage centerbody 2 diameters.Fined away and also can, in minor betterment mobile performance, reduce the low regime of end in ring pipe 4 ends.
In such scheme, the circulation area sum of a plurality of inner air imports 13 should be more than or equal to the circulation area of circular passage 5, and guarantee has enough air to enter into circular passage 5 like this, thereby guarantees that the gas in circular passage 5 has higher axial velocity.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 peripheral gaseous fuel import 11 is with rotational flow air from outer air entrance 121 mixes, from the fuel of center gas fuel outlet 22 also with air from inner air import 13 in circular passage 5 interior mixing.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 peripheral gaseous fuel import 11 and center gas fuel outlet 22, can control the distribution of gaseous fuel in mixing section, this will be conducive to produce the benefit of the aspects such as operability, discharge in given combustion chamber.Because fuel and air had just reached good mixed effect before entering burner inner liner, thereby when burning, suppress the existence of localized hyperthermia, can effectively suppress like this discharge of NOx.
Fig. 2 is the A-A cutaway view of Fig. 1.Inner air import 13 is from radially air being incorporated into circular passage 5, and peripheral gaseous fuel import 11 is from axially gaseous fuel being incorporated into mixing section 3, the two arranged crosswise.
Claims (5)
1. the pre-mixing nozzle for gas-turbine combustion chamber, this nozzle comprises nozzle head (1), gradual shrinkage centerbody (2) and mixing section (3), wherein, on nozzle head (1), be provided with peripheral gaseous fuel import (11) and radial swirler (12), on radial swirler (12), be provided with outer air entrance (121), on gradual shrinkage centerbody (2), be provided with center gas fuel inlet (21) and center gas fuel outlet (22), it is characterized in that: in radial swirler (12) upstream, be evenly arranged a plurality of inner air imports (13), gradual shrinkage centerbody (2) in mixing section (3) outer is arranged with the ring pipe (4) coaxially arranged with gradual shrinkage centerbody (2), the front end of ring pipe (4) is connected with nozzle head (1), the outer wall of the inwall of ring pipe (4) and gradual shrinkage centerbody (2) forms circular passage (5), circular passage (5) is connected with inner air import (13).
2. a kind of pre-mixing nozzle for gas-turbine combustion chamber as claimed in claim 1, it is characterized in that: the length that described ring pipe (4) extends vertically surpasses the length of gradual shrinkage centerbody (2), and being less than or equal to the length of mixing tube (3), the length surpassing is at least 0.2 times of gradual shrinkage centerbody (2) diameter.
3. a kind of pre-mixing nozzle for gas-turbine combustion chamber as claimed in claim 1, is characterized in that: the excursion of the circulation area of circular passage (5) is: 0～10%.
4. a kind of pre-mixing nozzle for gas-turbine combustion chamber as described in claim 1 or 3, is characterized in that: the circulation area of circular passage (5) is 5%～50% of mixing section (3) circulation area.
5. a kind of pre-mixing nozzle for gas-turbine combustion chamber as claimed in claim 1, is characterized in that: the circulation area sum of a plurality of inner air imports (13) is more than or equal to the circulation area of circular passage (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420378241.5U CN204006117U (en) | 2014-07-09 | 2014-07-09 | A kind of pre-mixing nozzle for gas-turbine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420378241.5U CN204006117U (en) | 2014-07-09 | 2014-07-09 | A kind of pre-mixing nozzle for gas-turbine combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204006117U true CN204006117U (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420378241.5U Withdrawn - After Issue CN204006117U (en) | 2014-07-09 | 2014-07-09 | A kind of pre-mixing nozzle for gas-turbine combustion chamber |
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| CN (1) | CN204006117U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104110698A (en) * | 2014-07-09 | 2014-10-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Pre-mixing nozzle used for combustion gas turbine combustor |
| CN104696986A (en) * | 2015-02-26 | 2015-06-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Anti-tempering nozzle for combustion chamber of gas turbine |
| CN114904408A (en) * | 2022-06-10 | 2022-08-16 | 中国石油化工股份有限公司 | Ethylene and oxygen mixer |
-
2014
- 2014-07-09 CN CN201420378241.5U patent/CN204006117U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104110698A (en) * | 2014-07-09 | 2014-10-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Pre-mixing nozzle used for combustion gas turbine combustor |
| CN104110698B (en) * | 2014-07-09 | 2017-11-07 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of pre-mixing nozzle for gas-turbine combustion chamber |
| CN104696986A (en) * | 2015-02-26 | 2015-06-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Anti-tempering nozzle for combustion chamber of gas turbine |
| CN114904408A (en) * | 2022-06-10 | 2022-08-16 | 中国石油化工股份有限公司 | Ethylene and oxygen mixer |
| CN114904408B (en) * | 2022-06-10 | 2023-11-03 | 中国石油化工股份有限公司 | Ethylene and oxygen mixer |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141210 Effective date of abandoning: 20171107 |