CN203731484U - Low-cyclone nozzle of combustor - Google Patents
Low-cyclone nozzle of combustor Download PDFInfo
- Publication number
- CN203731484U CN203731484U CN201420092067.8U CN201420092067U CN203731484U CN 203731484 U CN203731484 U CN 203731484U CN 201420092067 U CN201420092067 U CN 201420092067U CN 203731484 U CN203731484 U CN 203731484U
- Authority
- CN
- China
- Prior art keywords
- nozzle
- fuel
- jet pipe
- combustion chamber
- flow passage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
- 239000000446 fuel Substances 0.000 claims abstract description 157
- 238000002485 combustion reaction Methods 0.000 claims abstract description 30
- 239000003380 propellant Substances 0.000 claims description 27
- 239000007921 spray Substances 0.000 claims description 27
- 230000008676 import Effects 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 4
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract description 11
- 238000009434 installation Methods 0.000 abstract description 3
- 238000005507 spraying Methods 0.000 abstract 8
- 230000003247 decreasing effect Effects 0.000 abstract 1
- 239000000203 mixture Substances 0.000 description 7
- 230000003134 recirculating effect Effects 0.000 description 6
- 239000007789 gas Substances 0.000 description 3
- 239000008246 gaseous mixture Substances 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000035515 penetration Effects 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Abstract
The utility model provides a low-cyclone nozzle of a combustor, and belongs to the technical field of structural design of combustors of gas turbines. On the basis of the existing low-cyclone nozzle structure, the low-cyclone nozzle is provided with a fuel inlet device, wherein the fuel inlet device at least comprises an axial fuel spraying tube and an annular fuel spraying tube; the inner wall and the outer wall of the annular fuel spraying tube are respectively provided with a plurality of inner radial fuel spraying tubes and a plurality of outer radial fuel spraying tubes; and fuel is respectively supplied to two flow channels of the nozzle through fuel jetting holes formed in the inner radial fuel spraying tubes and the outer radial fuel spraying tubes. On the premise of guaranteeing mixing performance, the length of the low-cyclone nozzle is greatly reduced, and the installation harmony of the low-cyclone nozzle is improved; the proportion of fuel and air which enter the inner flow channel and the outer flow channel of the nozzle is controlled by controlling the number of the fuel jetting holes in the fuel spraying tubes; the quantity of the fuel entering a central flow returning area of a downstream combustion expansion area can be reduced; and a high-temperature area in the flow returning area is reduced, so that the quantity of nitric oxide is reduced, and pollution is decreased.
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 shown in Figure 1, in low swirl combustion chamber nozzle 10, fuel enters by fuel inlet tube 102, and air enters by air intlet 101, and fuel and air are in the interior mixing of Venturi tube 701.Venturi tube 701 downstreams are double-decker, and wherein nozzle inner flow passage 201 arranges a restriction orifice 301, are evenly arranged multiple metering holes 302 on restriction orifice 301; Nozzle outer flow passage 202 arranges cyclone 401, and cyclone 401 is made up of multiple swirl vanes.The even gaseous mixture in upstream by cyclone 401 and restriction orifice 301, produces low eddy flow gaseous mixture respectively, enters burning expansion regions 403 and burns.For fuel and air are mixed, Venturi tube 701 axial length L
1be generally between 150mm～220mm, cause nozzle long, in the time being used in conjunction with other types nozzle, bring inconvenience to installing; In addition, the fuel-air mixture example that enters nozzle inner flow passage 201 and nozzle outer flow passage 202 is consistent, the fuel quantity being entered by fuel inlet tube 102 completely and the air capacity being entered by air intlet 101 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 203 from cyclone 401 and restriction orifice 301 downstreams, can not form in time premix gas with air, the interior partial combustion excess Temperature in burning expansion regions 203, generally, higher than 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:
A kind of low swirl combustion chamber nozzle, comprises center air intlet, peripheral air import, fuel inlet device, nozzle inner flow passage, nozzle outer flow passage, restriction orifice, cyclone and burning expansion segment; Described restriction orifice is arranged in nozzle inner flow passage, cyclone is arranged in nozzle outer flow passage, it is characterized in that: described fuel inlet device comprises annular fuel jet pipe and at least one axial fuel jet pipe, and described axial fuel jet pipe is connected with annular fuel jet pipe; On annular fuel nozzle wall along even circumferential arrange multiple in fuel nozzle radially; On annular fuel jet pipe outer wall, arrange multiple outer radial fuel nozzles along even circumferential, one end of outer radial fuel nozzle is connected with annular fuel jet pipe, and the other end is connected with nozzle outer flow passage internal face; In each, radially the both sides of fuel nozzle and outer radial fuel nozzle tube wall are provided with sidewall propellant spray hole.
Technical characterictic of the present utility model is also: in described radially fuel nozzle apart from the axial distance L of restriction orifice
1and outer radial fuel nozzle is apart from the distance L of cyclone
2all between 15mm～30mm.In described radially the axial distance of fuel nozzle and described outer radial fuel nozzle between 0～10cm.The center line in described sidewall propellant spray hole and the center line of combustion chamber burner are 90 °.
Another technical characterictic of the present utility model is: inside radially the sidewall propellant spray hole on fuel nozzle along the radial position of nozzle inner flow passage be evenly arranged or straggly being arranged in fuel nozzle wall both sides radially; In each, radially the top of fuel nozzle at least arranges propellant spray hole, a top; Sidewall propellant spray hole on outer radial fuel nozzle along the radial position of nozzle outer flow passage be evenly arranged or arranged crosswise in the wall both sides of outer radial fuel nozzle.The diameter in propellant spray hole, top and sidewall propellant spray hole is 1～2mm.
Another technical characterictic of the present utility model is: the quantity of described axial fuel jet pipe and swirler blades quantity are consistent, or swirler blades quantity is 2～4 times of axial fuel jet pipe quantity.The quantity of axial fuel jet pipe is preferably 4～12.Inside radially fuel nozzle and outer radial fuel nozzle are pipe, conical pipe, oval pipe or blade type pipe.
The utility model compared with prior art has following outstanding advantage and beneficial effect: in the low swirl combustion chamber nozzle that 1. the utility model relates to radially fuel nozzle and outer radial fuel nozzle to be separated by annular fuel jet pipe be two sections, fuel collects at annular fuel jet pipe after entering axial fuel jet pipe, then part enter in fuel nozzle radially, propellant spray hole by interior radially fuel nozzle enters nozzle inner flow passage, all the other enter outer radial fuel nozzle, enter nozzle outer flow passage by the propellant spray hole of outer radial fuel nozzle.In described radially fuel nozzle apart from described restriction orifice axial distance L
1with the distance L of described outer radial fuel nozzle apart from described cyclone
2all between 15mm～30mm, although mixing distance at cyclone and restriction orifice upstream fuel and air shortens, but can continue to mix at cyclone and restriction orifice downstream fuel and air, under the prerequisite that ensures to mix mixed performance, greatly reduce the length of low swirl nozzle, improved the installation harmony of low swirl nozzle.2. enter the fuel-air ratio of nozzle inner flow passage and enter nozzle outer flow passage fuel-air ratio can by controlling radially aperture, propellant spray hole and the hole count on fuel nozzle and outer radial fuel nozzle control, reduce the fuel-air ratio that enters 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.
Brief description of the drawings
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 combustion chamber nozzle of the gas turbine embodiment that Fig. 3 provides for the utility model.
Fig. 4 is the A-A diagrammatic cross-sectional view of Fig. 3.
The low swirl combustion chamber nozzle of symbol description in figure: 10-; 101-air intlet; 102-fuel inlet tube; 201-nozzle inner flow passage; 202-nozzle outer flow passage; The 203-expansion segment that burns; 301-restriction orifice; 302-metering hole; 401-cyclone; 501-axial fuel jet pipe; Fuel nozzle radially in 502-; 503-outer radial fuel nozzle; 504-annular fuel jet pipe; 601a-sidewall propellant spray hole; Propellant spray hole, 601b-top; 701-Venturi tube.
Detailed description of the invention
Describe in detail below in conjunction with specific embodiment:
Fig. 3 is a typical embodiment of the low swirl nozzle 10 of gas-turbine combustion chamber described in the utility model.This low swirl combustion chamber nozzle 10 comprises center air intlet 101a, peripheral air import 101b, nozzle inner flow passage 201, nozzle outer flow passage 202, restriction orifice 301, cyclone 401 and burning expansion segment 203 and fuel inlet device, this fuel inlet device comprises at least one axial fuel jet pipe 501 and an annular fuel jet pipe 504, in the present embodiment, contain four axial fuel jet pipes 501, four axial fuel jet pipes are circumferentially uniformly distributed along the center line of low swirl combustion chamber nozzle 10, its end is connected with annular fuel jet pipe 504, junction sealing, annular fuel jet pipe 504 is connected with the end face of low swirl combustion chamber nozzle 10 inner flow passage walls, processing mode can be the processing mode such as monoblock cast or welding.
On annular fuel jet pipe 504, at least arrange in one radially fuel nozzle 502 and at least one outer radial fuel nozzle 503, inside radially fuel nozzle 502 and outer radial fuel nozzle 503 are all arranged at the upstream of restriction orifice 301 and cyclone 401, in the present embodiment, on annular fuel jet pipe 504 inwalls, arrange 8 along even circumferential in fuel nozzle 502 radially; On annular fuel jet pipe 504 outer walls, arrange 8 outer radial fuel nozzles 503 along even circumferential; One end of outer radial fuel nozzle 503 is connected with annular fuel jet pipe 504, and the other end is connected with nozzle outer flow passage 202 internal faces; In each, radially the both sides of fuel nozzle 502 and outer radial fuel nozzle 503 tube walls are provided with sidewall propellant spray hole 601a; In each, radially the top of fuel nozzle at least arranges top propellant spray hole 601b.
Preferably, inside radially fuel nozzle 502 apart from restriction orifice 301 axial distance L
1with the distance L of outer radial fuel nozzle 503 apart from cyclone 401
2all between 15mm～30mm, fuel and air are without mixing before outer flow passage entering in nozzle, can continue to mix at cyclone 401 and restriction orifice 301 downstreams, under the prerequisite that ensures mixed performance, greatly reduce the length of low swirl combustion chamber nozzle, improved the installation harmony of low swirl nozzle; Inside radially the axial location of fuel nozzle 502 and outer radial fuel nozzle 503 between 0～10cm.
Preferably, the diameter in propellant spray hole is 1～2mm, and its center line and low swirl combustion chamber nozzle 10 center lines are 90 °, guarantee that fuel has the suitable depth of penetration and mixed performance.Inside radially the propellant spray hole 601a on fuel nozzle 502 along 201 radial positions of nozzle inner flow passage be evenly arranged or straggly being arranged in fuel nozzle 502 wall both sides radially; Inside radially the top of fuel nozzle 502 at least arranges a propellant spray hole 601b; Propellant spray hole 601a on outer radial fuel nozzle 503 along 202 radial positions of nozzle outer flow passage be evenly arranged or arranged crosswise in outer radial fuel nozzle 503 wall both sides, guaranteeing has good mixed performance in nozzle axis, and still has good mixed performance when the fuel depth of penetration of interior radially fuel nozzle 502 and outer radial fuel nozzle 503 is not high.
The another preferred version of the utility model is, axial fuel jet pipe 501 is consistent with cyclone 401 blade quantities, or cyclone 401 blade quantities are 2～4 times of axial fuel jet pipe 501 quantity, guarantees that jet pipe and cyclone have good adaptability; Usually, the quantity of axial fuel jet pipe 501 is 4～12; Inside radially fuel nozzle 502 can adopt pipe, conical pipe, oval pipe or blade type pipe with outer radial fuel nozzle 503.
The course of work of the present utility model is as follows: fuel enters from axial fuel jet pipe 501, the backward surrounding diffusion of the annular fuel jet pipe 504 of flowing through, a part flows to interior radially fuel nozzle 502 and the outer radial fuel nozzle 503 with axial fuel jet pipe 501 close together nearby, another part is to both sides circumferential flow, then flow to interior radially fuel nozzle 502 and outer radial fuel nozzle 503 far away, finally enter respectively nozzle inner flow passage 201 and nozzle outer flow passage 202 by the propellant spray hole on interior radially fuel nozzle 502 and outer radial fuel nozzle 503 both sides and interior radially fuel nozzle 502 tops, air enters respectively nozzle inner flow passage 201 and nozzle outer flow passage 202 from center air intlet 101a and peripheral air import 101b, forms fuel-air mixture with the fuel mix of two runners.Fuel-air mixture in nozzle inner flow passage 201 restriction orifice 301 of flowing through, 401, the two strands of gaseous mixtures of cyclone of flowing through of the fuel-air mixture in nozzle outer flow passage 202 converge in nozzle downstream and form low vortex gas-flow, flow into burning expansion regions 203 and burn.By in controlling radially on fuel nozzle 502 and outer radial fuel nozzle 503 hole count and the aperture in propellant spray hole control the fuel quantity that enters outer flow passage in nozzle, and then control the fuel-air ratio that enters outer flow passage in nozzle, control the fuel-air ratio that enters nozzle inner flow passage 201 lower than the fuel-air ratio that enters nozzle outer flow passage 202.Even if the recirculating zone of low swirl nozzle is less, still there is recirculating zone in the center of combustion zone, controls the fuel quantity entering in recirculating zone, can reduce the high-temperature region in recirculating zone, and then reduce the generation of nitrogen oxide, reduces and pollute.
Claims (9)
1. a low swirl combustion chamber nozzle, comprises center air intlet (101a), peripheral air import (101b), fuel inlet device, nozzle inner flow passage (201), nozzle outer flow passage (202), restriction orifice (301), cyclone (401) and burning expansion segment (203); Described restriction orifice (301) is arranged in nozzle inner flow passage (201), cyclone (401) is arranged in nozzle outer flow passage (202), it is characterized in that: described fuel inlet device comprises annular fuel jet pipe (504) and at least one axial fuel jet pipe (501), and described axial fuel jet pipe (501) is connected with annular fuel jet pipe (504); On annular fuel jet pipe (504) inwall along even circumferential arrange multiple in fuel nozzle (502) radially; On annular fuel jet pipe (504) outer wall, arrange multiple outer radial fuel nozzles (503) along even circumferential, one end of outer radial fuel nozzle (503) is connected with annular fuel jet pipe (504), and the other end is connected with nozzle outer flow passage (202) outside wall surface; In each, radially the both sides of fuel nozzle (502) and outer radial fuel nozzle (503) tube wall are provided with sidewall propellant spray hole (601a).
2. low swirl combustion chamber nozzle according to claim 1, is characterized in that: in described radially fuel nozzle (502) apart from the axial distance L of restriction orifice (301)
1and outer radial fuel nozzle (503) is apart from the distance L of cyclone (401)
2all between 15mm～30mm.
3. low swirl combustion chamber nozzle according to claim 1 and 2, is characterized in that: in described radially the axial distance of fuel nozzle (502) and described outer radial fuel nozzle (503) between 0～10cm.
4. low swirl combustion chamber nozzle according to claim 1 and 2, is characterized in that: the center line in described sidewall propellant spray hole (601a) and the center line of combustion chamber burner are 90 °.
5. low swirl combustion chamber nozzle according to claim 4, is characterized in that: inside radially the sidewall propellant spray hole (601a) on fuel nozzle (502) along nozzle inner flow passage (201) radial position be evenly arranged or straggly being arranged in fuel nozzle (502) wall both sides radially; In each, radially the top of fuel nozzle (502) at least arranges propellant spray hole, a top (601b); Sidewall propellant spray hole (601a) on outer radial fuel nozzle (503) along nozzle outer flow passage (202) radial position be evenly arranged or arranged crosswise in the wall both sides of outer radial fuel nozzle (503).
6. low swirl combustion chamber nozzle according to claim 5, is characterized in that: the diameter in propellant spray hole, top (601b) and sidewall propellant spray hole (601a) is 1～2mm.
7. low swirl combustion chamber nozzle according to claim 1, it is characterized in that: the quantity of described axial fuel jet pipe (501) and cyclone (401) blade quantity are consistent, or cyclone (401) blade quantity is 2～4 times of axial fuel jet pipe (501) quantity.
8. low swirl combustion chamber nozzle according to claim 1, is characterized in that: the quantity of axial fuel jet pipe (501) is 4～12.
9. according to the low swirl combustion chamber nozzle described in claim 1,2,7 or 8, it is characterized in that: inside radially fuel nozzle (502) is pipe, conical pipe, oval pipe or blade type pipe with outer radial fuel nozzle (503).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420092067.8U CN203731484U (en) | 2014-02-28 | 2014-02-28 | Low-cyclone nozzle of combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420092067.8U CN203731484U (en) | 2014-02-28 | 2014-02-28 | Low-cyclone nozzle of combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203731484U true CN203731484U (en) | 2014-07-23 |
Family
ID=51201553
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420092067.8U Withdrawn - After Issue CN203731484U (en) | 2014-02-28 | 2014-02-28 | Low-cyclone nozzle of combustor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203731484U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103822230A (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-flow nozzle of combustion chamber |
| CN111520757A (en) * | 2020-03-31 | 2020-08-11 | 西北工业大学 | Direct type concave cavity swirl nozzle |
| CN113179652A (en) * | 2018-12-12 | 2021-07-27 | 索拉透平公司 | Fuel injector with perforated plate |
| CN114413282A (en) * | 2021-12-15 | 2022-04-29 | 西安航天动力研究所 | Stabilizer for strengthening oil-gas mixing for stamping engine |
-
2014
- 2014-02-28 CN CN201420092067.8U patent/CN203731484U/en not_active Withdrawn - After Issue
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103822230A (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-flow nozzle of combustion chamber |
| CN103822230B (en) * | 2014-02-28 | 2017-11-24 | 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 combustion chamber nozzle |
| CN113179652A (en) * | 2018-12-12 | 2021-07-27 | 索拉透平公司 | Fuel injector with perforated plate |
| CN113179652B (en) * | 2018-12-12 | 2022-09-20 | 索拉透平公司 | Fuel injector with perforated plate |
| CN111520757A (en) * | 2020-03-31 | 2020-08-11 | 西北工业大学 | Direct type concave cavity swirl nozzle |
| CN111520757B (en) * | 2020-03-31 | 2022-06-10 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN114413282A (en) * | 2021-12-15 | 2022-04-29 | 西安航天动力研究所 | Stabilizer for strengthening oil-gas mixing for stamping engine |
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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-flow nozzle of combustion chamber Effective date of registration: 20161104 Granted publication date: 20140723 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 |
Granted publication date: 20140723 Effective date of abandoning: 20171124 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20140723 Effective date of abandoning: 20171124 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20140723 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |