CN204213971U - Premixed swirl formula nozzle on duty - Google Patents
Premixed swirl formula nozzle on duty Download PDFInfo
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- CN204213971U CN204213971U CN201420699752.7U CN201420699752U CN204213971U CN 204213971 U CN204213971 U CN 204213971U CN 201420699752 U CN201420699752 U CN 201420699752U CN 204213971 U CN204213971 U CN 204213971U
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- air swirl
- gaseous fuel
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Abstract
The utility model proposes premixed swirl formula nozzle on duty.Gaseous fuel nozzle is connected by screw thread with air swirl pipe, premix chamber on duty, petal type cyclone and pantographic nozzle are connected with air swirl pipe by welding, gaseous fuel nozzle stretches into premix cavity segment circumferencial direction on duty and has some fuel orifices be evenly arranged, air swirl pipe has two symmetrical air swirl entrances along tube wall tangential direction, some oblique pores are had, the nozzle throat of an inside protuberance ring-type in the middle part of the tube wall of pantographic nozzle in petal type cyclone inside.This offset class nozzle is installed in the main burner using fuel gas gas turbine by structural adjustment, directly can realize the steady operation of nozzle on duty and the low emission characteristic of gas turbine by fuel adjustment, this type nozzle can under the prerequisite of smooth combustion at self, effectively can also be ignited main burner, the lean combustion simultaneously widening combustion chamber is stopped working scope, greatly improves the job stability of combustion chamber.
Description
technical field:
The utility model relates to Thermal Energy and Power Engineering field, specifically a kind of premixed swirl formula nozzle on duty of low emission gas turbine combustion chamber gaseous fuel nozzle core component.
background technology:
Along with the variation of variety of energy sources, the going from bad to worse of the extensive use of gas turbine and environmental pollution, the environmental protection ideas of people strengthens day by day, more and more stricter pollutant emission standard is constantly released in countries in the world, industry gas turbine is to pollutant, especially more strict to the emission request of NOx and CO, low emission has become one of important performance indexes of advanced gas turbine;
From the angle that pollutant emission controls, combustion chamber preferably adopts lean fuel premixed combustion technology, this needs abundant air to enter primary zone by fuel nozzle, so burner inner liner no longer retains primary holes and blending hole, reduce combustion zone temperature by the tissue of burning, be conducive to reducing NOx emission.But when in combustion zone, temperature is lower; combustion stability is just deteriorated; the danger that easy generation is flame-out; the greatest problem that lean fuel premixed combustion technology faces is exactly the tempering in combustion stability decline and premix chamber; unit is because the change of the change of load or fuel value and composition often there will be flame-out danger in running, and it significantly threatens the security of operation of gas turbine.Because the combustion process in combustion chamber is difficult to tissue, special measure must be taked for this reason, while the discharge of guarantee low stain thing, ensure the stability of flame, in order to the lean combustion solving lean fuel premixed combustion nozzle is stopped working problem and tempering problem, need to take special mode to carry out somewhat complex design to nozzle arrangements, the mode of nozzle on duty is introduced at main burner center, effectively can improve the stability of flame, but the structural shape of nozzle on duty and working method have significant impact to the service behaviour of combustion chamber and pollutant emission, therefore the research of premixed swirl formula nozzle on duty has important using value.
utility model content:
The utility model to stop working problem for solving the lean combustion of low emission combustor, and be improve flame holding, the technical characterstic of comprehensive fuel gas main burner is developed.
The technical solution of the utility model is: premixed swirl formula nozzle on duty, comprise gaseous fuel nozzle, gaseous fuel nozzle is connected by screw thread with air swirl pipe, and premix chamber on duty, petal type cyclone and pantographic nozzle are connected with air swirl pipe by welding.
Described gaseous fuel nozzle, center has the fuel inlet of a counterbore shape, and gaseous fuel nozzle stretches into premix cavity segment circumferencial direction on duty and has some fuel orifices be evenly arranged.
Described air swirl pipe, has two symmetrical long hole shape air swirl entrances along tube wall tangential direction.
Described petal type cyclone, has some centrally radial oblique pores, offers straight hole at center in petal type cyclone inside.
Described pantographic nozzle, inboard at jet expansion, the nozzle throat of an inside protuberance ring-type in the middle part of its tube wall.
The utility model has following beneficial effect: the premixed swirl formula nozzle on duty that the utility model proposes, this offset class nozzle is installed in the main burner using fuel gas gas turbine by structural adjustment, directly can realize the steady operation of nozzle on duty and the low emission characteristic of gas turbine by fuel adjustment, adopt petal type cyclone, solve cyclone design small hub than time underfed and big hub than time do not meet the technological deficiency of cyclone design criterion; Fuel and air pre-mixing form is adopted to reduce pollutant emission; Twin-stage cyclone mode is adopted to strengthen gaseous mixture eddy flow; Pantographic nozzle is adopted to make air-flow accelerate to prevent tempering in throat, low speed recirculating zone is formed at divergent segment, stablize flame on duty, this type nozzle can under the prerequisite of smooth combustion at self, effectively can also be ignited main burner, the lean combustion simultaneously widening combustion chamber is stopped working scope, greatly improves the job stability of combustion chamber.
accompanying drawing illustrates:
Fig. 1 is structural representation of the present utility model;
Accompanying drawing 2 is M direction view of accompanying drawing 1;
Accompanying drawing 3 is A-A profiles of accompanying drawing 1;
Accompanying drawing 4 is B-B profiles of accompanying drawing 1.
1-gaseous fuel nozzle in figure; 2-air swirl pipe; 3-premix chamber on duty; 4-petal type cyclone; 5-pantographic nozzle; 6-fuel inlet; 7-air swirl entrance; 8-fuel orifice; The oblique pore of 9-; 10-nozzle throat; 11-jet expansion; 12-screw thread.
detailed description of the invention:
Below in conjunction with accompanying drawing, the utility model is described in further detail:
Shown in Fig. 1 composition graphs 2 ~ Fig. 4, premixed swirl formula nozzle on duty, comprise gaseous fuel nozzle 1, gaseous fuel nozzle 1 is connected by screw thread 12 with air swirl pipe 2, and premix chamber 3 on duty, petal type cyclone 4 are connected with air swirl pipe 2 by welding with pantographic nozzle 5.
Described gaseous fuel nozzle 1, center has the fuel inlet 6 of a counterbore shape, and gaseous fuel nozzle 1 stretches into part-circular periphery direction, premix chamber 3 on duty and has some fuel orifices 8 be evenly arranged.
Described air swirl pipe 2, has two symmetrical long hole shape air swirl entrances 7 along tube wall tangential direction.
Described petal type cyclone 4, offers some oblique pores 9 in petal type cyclone 4 inside, offers straight hole at center, can improve nozzle flow on duty on the one hand, can assist on the other hand and prevent flame on duty tempering, in case the ablation of petal type cyclone.
Described pantographic nozzle 5, inboard at jet expansion 11, the nozzle throat 10 of an inside protuberance ring-type in the middle part of its tube wall.
Fuel gas enters gaseous fuel nozzle 1 by fuel inlet 6, is ejected into premix chamber 3 on duty from fuel orifice 8; Simultaneously, air enters premix chamber 3 on duty through eddy flow entrance 7 with cyclonic form, blending is carried out with fuel gas, then flow through petal type cyclone 4, further reinforcement eddy flow, by pantographic nozzle 5, accelerate at nozzle throat 10, after flowing out at a high speed, slow down through divergent segment sudden expansion and form recirculating zone, premix gas forms the flame of smooth combustion in divergent segment recirculating zone, this flame sprays from jet expansion 11, be connected with main burner recirculating zone, and then the main burner that can ignite, the lean combustion blowoff limit of main burner can be widened simultaneously.
This offset class fuel nozzle flow can regulate according to operating mode, and under high operating mode comparatively stable state, fuel quantity can reduce, and leaked-in air directly enters combustion zone supplemental oxygen, reduces pollutant emission; When low operating mode, fuel quantity suitably increases, and forms stable flame on duty, improves the combustion stability of main flame.
Claims (5)
1. a premixed swirl formula nozzle on duty, comprise gaseous fuel nozzle (1), it is characterized in that: gaseous fuel nozzle (1) is connected by screw thread (12) with air swirl pipe (2), premix chamber (3) on duty, petal type cyclone (4) and pantographic nozzle (5) are connected with air swirl pipe (2) by welding.
2. premixed swirl formula according to claim 1 nozzle on duty, it is characterized in that: described gaseous fuel nozzle (1), center has the fuel inlet (6) of a counterbore shape, and gaseous fuel nozzle (1) stretches into premix chamber (3) part-circular periphery direction on duty and has some fuel orifices (8) be evenly arranged.
3. premixed swirl formula according to claim 1 nozzle on duty, is characterized in that: described air swirl pipe (2), has two symmetrical long hole shape air swirl entrances (7) along tube wall tangential direction.
4. premixed swirl formula according to claim 1 nozzle on duty, it is characterized in that: described petal type cyclone (4), have some centrally radial oblique pores (9) in petal type cyclone (4) inside, offer straight hole at center.
5. premixed swirl formula according to claim 1 nozzle on duty, it is characterized in that: described pantographic nozzle (5), inboard at jet expansion (11), the nozzle throat (10) of an inside protuberance ring-type in the middle part of its tube wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420699752.7U CN204213971U (en) | 2014-11-20 | 2014-11-20 | Premixed swirl formula nozzle on duty |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420699752.7U CN204213971U (en) | 2014-11-20 | 2014-11-20 | Premixed swirl formula nozzle on duty |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204213971U true CN204213971U (en) | 2015-03-18 |
Family
ID=52982637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420699752.7U Active CN204213971U (en) | 2014-11-20 | 2014-11-20 | Premixed swirl formula nozzle on duty |
Country Status (1)
| Country | Link |
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| CN (1) | CN204213971U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390235A (en) * | 2014-11-20 | 2015-03-04 | 中国船舶重工集团公司第七�三研究所 | Premixing swirl duty nozzle |
| CN106969379A (en) * | 2015-09-23 | 2017-07-21 | 通用电气公司 | Premix fuel nozzle assembly cylinder |
-
2014
- 2014-11-20 CN CN201420699752.7U patent/CN204213971U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390235A (en) * | 2014-11-20 | 2015-03-04 | 中国船舶重工集团公司第七�三研究所 | Premixing swirl duty nozzle |
| CN104390235B (en) * | 2014-11-20 | 2017-06-27 | 中国船舶重工集团公司第七�三研究所 | Premixed swirl formula nozzle on duty |
| CN106969379A (en) * | 2015-09-23 | 2017-07-21 | 通用电气公司 | Premix fuel nozzle assembly cylinder |
| CN106969379B (en) * | 2015-09-23 | 2021-08-10 | 通用电气公司 | Premix fuel nozzle assembly cartridge |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151209 Address after: 150090 No. 35, Honghu Road, Yingbin Road, Harbin hi tech Development Zone, Heilongjiang, China Patentee after: Harbin broad power technology development Co., Ltd. Address before: 150000 Honghu Road, Daoli District, Heilongjiang, No. 35, Harbin Patentee before: No.703 Inst. China Ship Heavy Industry Group Co. |