CN203837024U - Low swirl nozzle for gas turbine combustion chamber - Google Patents
Low swirl nozzle for gas turbine combustion chamber Download PDFInfo
- Publication number
- CN203837024U CN203837024U CN201420092032.4U CN201420092032U CN203837024U CN 203837024 U CN203837024 U CN 203837024U CN 201420092032 U CN201420092032 U CN 201420092032U CN 203837024 U CN203837024 U CN 203837024U
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- China
- Prior art keywords
- nozzle
- fuel
- flow passage
- fuel nozzle
- low swirl
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Abstract
The utility model discloses a low swirl nozzle for a gas turbine combustion chamber, and belongs to the technical field of gas turbine structural designs. According to the lower swirl nozzle, a fuel spray pipe device is additionally arranged on the basis of an existing low swirl nozzle structure, the fuel spray pipe device is located on the upstream of a restriction orifice and a swirler and comprises an inner pipe of a fuel spray pipe and an outer pipe of the fuel spray pipe; the inner pipe of the fuel spray pipe is located in an internal flow passage of the nozzle, and the outer pipe of the fuel spray pipe is located in an external flow passage of the nozzle. On the premise that hybrid performance is guaranteed, the length of the low swirl nozzle is greatly reduced, and installation harmony of the low swirl nozzle is improved; by controlling the number of fuel injection holes in the fuel spray pipe and the ratio of fuel entering the internal flow passage of the nozzle and the external flow passage of the nozzle to air entering the internal flow passage of the nozzle and the external flow passage of the nozzle, the amount of fuel entering a backflow region at the center of a downstream combustion expansion region can be reduced, a high-temperature in the backflow region is reduced, generated nitrogen oxide is reduced, and pollution is reduced.
Description
Technical field
The utility model relates to the low swirl nozzle of a kind of gas-turbine combustion chamber, belongs to gas turbine structure design field.
Background technology
Patent WO2012141982A1 has described the low swirl nozzle that is applied to gas-turbine combustion chamber.As mistake! Do not find Reference source.Shown in, in low swirl nozzle 10, fuel enters by fuel inlet tube 101, and air enters by air intlet 501, and fuel and air are in the interior mixing of Venturi tube 601.Venturi tube 601 downstreams are double-decker, and wherein nozzle inner flow passage 401 arranges a restriction orifice 301, are evenly arranged a plurality of metering holes 302 on restriction orifice 301; Nozzle outer flow passage 402 arranges cyclone 201, and cyclone 201 is comprised of a plurality of swirl vanes.The even gaseous mixture in upstream by cyclone 201 and restriction orifice 301, produces low eddy flow gaseous mixture respectively, enters 403 burnings of burning expansion regions.For fuel and air are mixed, Venturi tube 601 axial length L
1be generally between 150mm～220mm, cause nozzle long, when being used in conjunction with other types nozzle, to installing, bring inconvenience; In addition, the fuel-air mixture example that enters nozzle inner flow passage 401 and nozzle outer flow passage 402 is consistent, the fuel quantity being entered by fuel inlet tube 101 completely and the air capacity being entered by air intlet 501 determine, can not carry out reasonable distribution to the fuel-air mixture example of outer flow passage in nozzle.
Patent WO2012141982A1 discloses another embodiment, as shown in Figure 2, fuel directly enters burning expansion regions 403 from cyclone 201 and restriction orifice 301 downstreams, can not form in time premix gas with air, the interior partial combustion excess Temperature in burning expansion regions 403, usually above 2000K, cause the content of nitrogen oxide in combustion chamber to uprise, contaminated environment.
Utility model content
In order to solve problems of the prior art, the utility model proposes the low swirl nozzle of a kind of gas-turbine combustion chamber, can reduce nozzle length, and can carry out reasonable distribution to the fuel-air mixture example of outer flow passage in nozzle, further to reduce burning indoor pollutant.
The technical scheme that the utility model adopts is as follows:
The low swirl nozzle of gas-turbine combustion chamber, comprises fuel inlet tube, air intlet, nozzle inner flow passage, nozzle outer flow passage, restriction orifice, cyclone and burning expansion segment, described restriction orifice is arranged in described nozzle inner flow passage, described cyclone is arranged in nozzle outer flow passage, described burning expansion segment is arranged on the downstream of nozzle inner flow passage and nozzle outer flow passage, it is characterized in that: the low swirl nozzle in this combustion chamber comprises a fuel nozzle device, this fuel nozzle device is arranged at the upstream of restriction orifice and cyclone, this fuel nozzle device comprises at least four fuel nozzles, and fuel nozzle distributes along fuel inlet tube even circumferential, one end of every fuel nozzle is connected with fuel inlet tube, the other end is connected with low swirl nozzle outer flow passage outer wall, described every fuel nozzle is divided into fuel nozzle inner tube and fuel nozzle outer tube, and fuel nozzle inner tube is in described nozzle inner flow passage, and fuel nozzle outer tube is in nozzle outer flow passage, propellant spray hole is set in fuel nozzle inner tube, propellant spray hole is set on fuel nozzle outer tube.
In technique scheme, described fuel nozzle device is apart from the axial distance L of described cyclone
2between 15mm～30mm,
Technical characterictic of the present utility model is also, the diameter that the diameter in propellant spray hole, described inner side and propellant spray hole, outside is 1～2mm is 1～2mm; The center line in propellant spray hole, described inner side and propellant spray hole, outside and the center line of fuel inlet tube are 90 °; Propellant spray hole in fuel nozzle inner tube is evenly arranged or the both sides that are arranged in fuel nozzle inner tube wall straggly along the radial position of nozzle inner flow passage; Propellant spray hole on fuel nozzle outer tube along the radial position of nozzle outer flow passage be evenly arranged or arranged crosswise in the both sides of fuel nozzle wall.
Another technical characterictic of the present utility model is: the quantity of described fuel nozzle and described swirler blades quantity are consistent, and are preferably 6～20, and it is shaped as pipe, conical pipe or oval pipe.
The utility model compared with prior art has following outstanding advantage and beneficial effect:
It is two sections that fuel nozzle described in the low swirl nozzle device that the utility model relates to is separated by the wall of outer flow passage in nozzle, fuel enters described fuel nozzle rear section and enters fuel nozzle inner tube, propellant spray hole by fuel nozzle inner tube enters nozzle inner flow passage, all the other enter fuel nozzle outer tube, and the propellant spray hole by fuel nozzle outer tube enters nozzle outer flow passage.Described fuel nozzle is apart from the axial distance L of described cyclone
2between 15mm～30mm, although mixing distance at described cyclone and described restriction orifice upstream fuel and air shortens, but can continue to mix at described cyclone and described restriction orifice downstream fuel and air, under the prerequisite that guarantees mixing mixed performance, greatly reduce the length of low swirl nozzle, improved the installation harmony of low swirl nozzle; The fuel-air ratio that enters the fuel-air of described nozzle inner flow passage and enter described nozzle outer flow passage can be controlled by aperture, propellant spray hole and the quantity controlling on fuel nozzle, reduce the fuel-air ratio that enters described nozzle inner flow passage, can reduce the fuel quantity entering in recirculating zone, center, burning expansion regions, downstream, reduce the high-temperature region in recirculating zone, and then the generation of reduction nitrogen oxide, reduce and pollute.
Accompanying drawing explanation
Fig. 1 is a low swirl nozzle sketch in prior art.
Fig. 2 is another low swirl nozzle sketch in prior art.
The structure diagram of the low swirl nozzle embodiment of gas-turbine combustion chamber that Fig. 3 provides for the utility model.
Fig. 4 is the A-A profile of Fig. 3.
The low swirl nozzle of symbol description in figure: 10-; 101-fuel inlet tube; 102a-fuel nozzle inner tube; 102b-fuel nozzle outer tube; Propellant spray hole inside 103a-; Propellant spray hole outside 103b-; 201-cyclone; 301-restriction orifice; 302-metering hole; 401-nozzle inner flow passage; 402-nozzle outer flow passage; The 403-expansion regions of burning; 501-air intlet; 601-Venturi tube.
The specific embodiment
Below in conjunction with accompanying drawing, structure of the present utility model, principle and the course of work are elaborated:
The structure diagram of the low swirl nozzle embodiment of gas-turbine combustion chamber that Fig. 3 and Fig. 4 provide for the utility model, the low swirl nozzle in this combustion chamber comprises fuel inlet tube 101, air intlet 501, nozzle inner flow passage 401, nozzle outer flow passage 402, restriction orifice 301, cyclone 201, burning expansion segment 403 and fuel nozzle device; Described restriction orifice 301 is arranged in described nozzle inner flow passage 401, is evenly arranged a plurality of metering holes 302 on restriction orifice; Described cyclone 201 is arranged in nozzle outer flow passage 402, and cyclone is comprised of a plurality of swirl vanes; Described burning expansion segment 403 is arranged on the downstream of nozzle inner flow passage 401 and nozzle outer flow passage 402.Described fuel nozzle device is arranged at the upstream of restriction orifice 301 and cyclone 201, fuel nozzle device comprises at least four fuel nozzles, and fuel nozzle distributes along fuel inlet tube 101 even circumferentials, one end of every fuel nozzle is connected with fuel inlet tube 101, and the other end is connected with the outer flow passage outer wall of low swirl nozzle; Described every fuel nozzle is divided into fuel nozzle inner tube 102a and fuel nozzle outer tube 102b, and described fuel nozzle inner tube 102a is connected with fuel nozzle outer tube 102b; Fuel nozzle inner tube 102a is in described nozzle inner flow passage 401, and fuel nozzle outer tube 102b is in nozzle outer flow passage 402; Fuel nozzle can adopt one, also can divide two sections of processing, is welded on respectively in the interior outer flow passage of nozzle; Inner side propellant spray hole 103a is set on fuel nozzle inner tube 102a, outside propellant spray hole 103b (as shown in Figure 4) is set on fuel nozzle outer tube 102b.
Fuel nozzle device is apart from the axial distance L of cyclone 201
2preferably between 15mm～30mm, fuel and air mix before without outer flow passage in entering nozzle, can continue to mix at cyclone 201 and restriction orifice 301 downstreams, under the prerequisite that guarantees mixed performance, greatly reduce the length of low swirl nozzle, improved the installation harmony of low swirl nozzle.The diameter of inner side propellant spray hole 103a and propellant spray hole, outside 103b is generally 1～2mm, and the center line in propellant spray hole is 90 ° with low swirl nozzle center line, the depth of penetration and the blending performance of assurance fuel.General and cyclone 201 blade quantities of the quantity of fuel nozzle are consistent, and are preferably 6～20, fuel nozzle be shaped as pipe, conical pipe or oval pipe.
Propellant spray hole, inner side 103a on fuel nozzle inner tube 102a is evenly arranged or the both sides that are arranged in fuel nozzle inner tube wall straggly along 401 radial positions of nozzle inner flow passage; Propellant spray hole, outside 103b on fuel nozzle outer tube 102b along 402 radial positions of nozzle outer flow passage be evenly arranged or arranged crosswise in the both sides of fuel nozzle outer tube wall; Propellant spray hole is all arranged in both sides in fuel nozzle inner tube, can guarantee that fuel nozzle inner tube both sides fuel ratio is even compared with convergence, guarantee when the fuel depth of penetration is not high, still to there is good mixed performance, because internal layer fuel quantity is lower, for guaranteeing that it still has the reasonably depth of penetration, it is fewer that the hole count in propellant spray hole need to arrange.
The course of work of the present utility model is as follows:
Fuel enters from fuel inlet tube 101, by the fuel nozzle device being connected with fuel inlet tube 101, enter respectively fuel nozzle inner tube 102a and fuel nozzle outer tube 102b, a part enters nozzle inner flow passage 401 by propellant spray hole, the inner side 103a on fuel nozzle inner tube 102a, another part flows into fuel nozzle outer tube 102b, and by inner side propellant spray hole 103a and propellant spray hole, outside 103b, sprays into nozzle inner flow passage 401 and nozzle outer flow passage 402 respectively, air enters respectively nozzle inner flow passage 401 and nozzle outer flow passage 402 from the place ahead air intlet 501, during through fuel nozzle device with the fuel mix formation fuel-air mixture of ejection, fuel-air mixture in nozzle inner flow passage 401 restriction orifice 301 of flowing through, fuel-air mixture in nozzle outer flow passage 402 cyclone 201 of flowing through, two strands of gaseous mixtures converge in nozzle downstream and form low vortex gas-flow, flowing into burning expansion regions 403 burns, by control the aperture in the propellant spray hole on fuel nozzle inner tube 102a and fuel nozzle outer tube 102b and quantity can be to nozzle in the fuel quantity of outer flow passage control, and then control enters the fuel-air ratio of outer flow passage in nozzle, control enters the fuel-air ratio of nozzle inner flow passage 401 lower than the fuel-air ratio that enters nozzle outer flow passage 402.Even if the recirculating zone of low swirl nozzle is less, still there is recirculating zone in the center of combustion zone, controls and enter the fuel quantity in recirculating zone, can reduce the high-temperature region in recirculating zone, and then reduce the generation of NOX, reduces and pollute.
Claims (8)
1. the low swirl nozzle of gas-turbine combustion chamber, comprises fuel inlet tube (101), air intlet (501), nozzle inner flow passage (401), nozzle outer flow passage (402), restriction orifice (301), cyclone (201) and burning expansion segment (403), described restriction orifice (301) is arranged in described nozzle inner flow passage (401), described cyclone (201) is arranged in nozzle outer flow passage (402), described burning expansion segment (403) is arranged on the downstream of nozzle inner flow passage (401) and nozzle outer flow passage (402), it is characterized in that: the low swirl nozzle in this combustion chamber comprises a fuel nozzle device, this fuel nozzle device is arranged at the upstream of restriction orifice (301) and cyclone (201), this fuel nozzle device comprises at least four fuel nozzles, and fuel nozzle distributes along fuel inlet tube even circumferential, one end of every fuel nozzle is connected with fuel inlet tube (101), the other end is connected with low swirl nozzle outer flow passage outer wall, described every fuel nozzle is divided into fuel nozzle inner tube (102a) and fuel nozzle outer tube (102b), fuel nozzle inner tube (102a) is in described nozzle inner flow passage (401), and fuel nozzle outer tube (102b) is in nozzle outer flow passage (402), propellant spray hole (103a), inner side is set in fuel nozzle inner tube (102a), propellant spray hole (103b), outside is set on fuel nozzle outer tube (102b).
2. the low swirl nozzle of a kind of gas-turbine combustion chamber according to claim 1, is characterized in that: described fuel nozzle device is apart from the axial distance L of described cyclone (201)
2between 15mm～30mm.
3. the low swirl nozzle of a kind of gas-turbine combustion chamber according to claim 1 and 2, is characterized in that: the diameter in propellant spray hole, described inner side (103a) and propellant spray hole, outside (103b) is 1～2mm.
4. the low swirl nozzle of a kind of gas-turbine combustion chamber according to claim 3, is characterized in that: the center line in propellant spray hole, described inner side (103a) and propellant spray hole, outside (103b) and the center line of fuel inlet tube (101) are 90 °.
5. the low swirl nozzle of a kind of gas-turbine combustion chamber according to claim 4, is characterized in that: the propellant spray hole, inner side (103a) in fuel nozzle inner tube (102a) is evenly arranged or the both sides that are arranged in fuel nozzle inner tube (102a) wall straggly along nozzle inner flow passage (401) radial position; Propellant spray hole, outside (103b) on fuel nozzle outer tube (102b) along nozzle outer flow passage (402) radial position be evenly arranged or arranged crosswise in the both sides of fuel nozzle outer tube (102b) wall.
6. the low swirl nozzle of a kind of gas-turbine combustion chamber according to claim 1, is characterized in that: the quantity of fuel nozzle and cyclone (201) blade quantity is consistent.
7. the low swirl nozzle of a kind of gas-turbine combustion chamber according to claim 1, is characterized in that: the quantity of fuel nozzle is 6～20.
8. according to the low swirl nozzle of a kind of gas-turbine combustion chamber described in claim 1,6 or 7, it is characterized in that: fuel nozzle is pipe, conical pipe or oval pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420092032.4U CN203837024U (en) | 2014-02-28 | 2014-02-28 | Low swirl nozzle for gas turbine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420092032.4U CN203837024U (en) | 2014-02-28 | 2014-02-28 | Low swirl nozzle for gas turbine combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203837024U true CN203837024U (en) | 2014-09-17 |
Family
ID=51514856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420092032.4U Withdrawn - After Issue CN203837024U (en) | 2014-02-28 | 2014-02-28 | Low swirl nozzle for gas turbine combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203837024U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110160083A (en) * | 2019-05-24 | 2019-08-23 | 西安航天动力研究所 | The steady flame device of gas-air mixer |
| CN113551265A (en) * | 2021-08-11 | 2021-10-26 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle and gas turbine |
-
2014
- 2014-02-28 CN CN201420092032.4U patent/CN203837024U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103822229B (en) * | 2014-02-28 | 2017-11-03 | 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 low swirl nozzle of gas-turbine combustion chamber |
| CN110160083A (en) * | 2019-05-24 | 2019-08-23 | 西安航天动力研究所 | The steady flame device of gas-air mixer |
| CN113551265A (en) * | 2021-08-11 | 2021-10-26 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle and gas turbine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Low swirl nozzle for combustion chamber of gas turbine Effective date of registration: 20161104 Granted publication date: 20140917 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140917 Effective date of abandoning: 20171103 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20140917 Effective date of abandoning: 20171103 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20140917 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |