CN104214799A - Axial swirl nozzle of combustion chamber of gas turbine - Google Patents
Axial swirl nozzle of combustion chamber of gas turbine Download PDFInfo
- Publication number
- CN104214799A CN104214799A CN201410446283.2A CN201410446283A CN104214799A CN 104214799 A CN104214799 A CN 104214799A CN 201410446283 A CN201410446283 A CN 201410446283A CN 104214799 A CN104214799 A CN 104214799A
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- China
- Prior art keywords
- fuel
- rotational flow
- axial rotational
- fuel injection
- combustion chamber
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 34
- 239000000446 fuel Substances 0.000 claims abstract description 102
- 238000002347 injection Methods 0.000 claims abstract description 45
- 239000007924 injection Substances 0.000 claims abstract description 45
- 230000008602 contraction Effects 0.000 claims description 6
- 238000009827 uniform distribution Methods 0.000 claims 1
- 238000005507 spraying Methods 0.000 abstract description 8
- 239000012530 fluid Substances 0.000 abstract description 3
- 239000002737 fuel gas Substances 0.000 description 13
- 238000002156 mixing Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 8
- 230000000694 effects Effects 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 7
- 239000000203 mixture Substances 0.000 description 6
- 239000003344 environmental pollutant Substances 0.000 description 5
- 239000008246 gaseous mixture Substances 0.000 description 5
- 231100000719 pollutant Toxicity 0.000 description 5
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000013505 freshwater Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000003134 recirculating effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Abstract
The invention relates to the technical field of a gas turbine, and provides an axial swirl nozzle of a combustion chamber of the gas turbine. The axial swirl nozzle has a structure of comprising an outer wall of the nozzle and a fuel injection body inserted into the outer wall of the nozzle, wherein the fuel injection body is internally provided with a center fuel channel; a plurality of fuel spraying pipes which are communicated with the center fuel channel are arranged along the radial direction of the fuel injection body; the side wall of each fuel spraying pipe is provided with fuel spraying holes; a first stage ring-shaped airflow channel is formed between the tops of the fuel spraying pipes and the outer wall of the nozzle; an axial rotational flow device is arranged on the inner wall of the outer wall of the nozzle behind the fuel spraying pipes along the air inlet direction; a second stage ring-shaped airflow channel is formed between the axial rotational flow device and the fuel injection body. Due to the combined action of the fuel spraying pipes and the axial rotational flow device, the fluid speed is reasonably distributed at a fuel spraying outlet, the fuel and the air are evenly mixed, and a combustion area is reasonably controlled, so that combustion stability and good exit temperature distribution are guaranteed.
Description
Technical field
The present invention relates to gas turbine technology field, a kind of gas-turbine combustion chamber axial rotational flow nozzle is provided especially.
Background technology
In the energy resource structure that China is current, the thermal power generation of traditional coal combustion technology is adopted to occupy most share.But it is low to there is generating efficiency in this traditional generation technology, high (the especially NO of pollutant emission
xdischarge), expend the shortcomings such as freshwater resources are many.Be that the gas turbine power generation technology of fuel is as one of clean energy technology with natural gas, can while meeting generation load requirement, effectively reduce the discharge of pollutant, this wherein gas-turbine combustion chamber axial rotational flow nozzle design for tissue burning, reduce pollutant emission particularly important.
In gas-turbine combustion chamber, fuel gas and air realize the change of premixed and velocity profile by nozzle, reach rational VELOCITY DISTRIBUTION at jet expansion, and mate rational fuel-air mixture example, enter combustion chamber tissue burning, form stable flow field and combustion field.Current, such as, to the design form of gas-turbine combustion chamber axial rotational flow nozzle, patent CN100567823C, adopt the notched air swirling vanes in bottom, improve the speed of air duct inner circumferential side, coupling nozzle exit velocity type and fuel-air mixture example.
But owing to there is breach bottom air swirling vanes, the air flow deflector angle of passage inner circumferential side is little, and swirl strength is weak, the mixing effect of this side fuel and air is caused to be deteriorated; Fuel gas is in the spray of hollow blade two STH simultaneously, and the blending distance of fuel gas and air is shorter, and adds the difficulty of blade processing, the tissue of impact burning and the generation of pollutant.Therefore, more rationally effective gas-turbine combustion chamber axial rotational flow form of nozzle is still needed to organize burning and control polluted articles discharge.
Summary of the invention
(1) technical problem that will solve
The air swirling vanes swirl strength that the object of the invention is to solve existing gas turbine is weak, and the mixing effect of fuel and air is poor, the problem of the tissue of impact burning and the generation of pollutant.
(2) technical scheme
A kind of gas-turbine combustion chamber axial rotational flow nozzle provided by the invention, comprises outer nozzle wall and the fuel be plugged in described outer nozzle wall injects body; The inside that described fuel injects body is provided with center fuel passage, that injects body at described fuel is provided with the fuel injection pipe that multiple and described center fuel passage communicates in the radial direction, the sidewall of each described fuel injection pipe is equipped with fuel orifice, is provided with first order annular air-flow path between fuel gas playpipe top and outer nozzle wall; On airintake direction, the inwall of the outer nozzle wall at the rear of described fuel injection pipe is provided with axial rotational flow device, and axial rotational flow dress and fuel inject between body and is provided with second level annular air-flow path.
Preferably, described axial rotational flow device comprises the swirl vane that multiple circumference is laid.
Preferably, the width of described second level annular air-flow path is 10% ~ 50% of described swirl vane length.
Preferably, the quantity of described swirl vane is 6 ~ 12.
Preferably, multiple described swirl vane and multiple described fuel injection pipe in the axial direction staggered relative arrange.
Preferably, the width of described first order annular air-flow path is 10% ~ 50% of the height of described fuel injection pipe.
Preferably, the distance between the opening of described fuel injection pipe and described outer nozzle wall is 50% ~ 100% of the length of fuel injection pipe.
Preferably, the distance between described fuel injection pipe and described axial rotational flow device is 50% ~ 100% of the length of described fuel injection pipe.
Preferably, on airintake direction, and the described combustion chamber being positioned at the rear of described axial rotational flow device has radial contraction section.
Preferably, one end that described fuel injection body is inserted into described outer nozzle wall is taper.
(3) beneficial effect
A kind of gas-turbine combustion chamber axial rotational flow nozzle provided by the invention, this technical scheme in axial direction fuel arranged playpipe and axial rotational flow device successively, fuel injection pipe top is provided with fuel orifice, is provided with first order annular air-flow path between itself and outer nozzle wall inwall; Axial rotational flow device is fixed on outer nozzle wall face, and axial rotational flow device and fuel inject between body second level annular air-flow path, and axial rotational flow device is circumferentially evenly arranged.By the acting in conjunction of fuel injection pipe and axial rotational flow device, ensure that the fluid velocity distribution of fuel jet exit place is reasonable, fuel-air blending is even, conservative control combustion zone, maintains combustion chamber flow field structure, thus ensures the stability of burning and good Exit temperature distribution.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of gas-turbine combustion chamber axial rotational flow nozzle of the embodiment of the present invention;
Fig. 2 is the three-dimensional cutaway view of a kind of gas-turbine combustion chamber axial rotational flow nozzle of the embodiment of the present invention.
Reference numeral: 1, center fuel passage; 2, annular air channel; 3, fuel injects body; 4, fuel injection pipe; 5, axial rotational flow device; 6, fuel orifice; 7, outer nozzle wall; 8, first order annular air-flow path; 9, second level annular air-flow path; 10, gaseous mixture annular air-flow path; 11, radial contraction section; 12, air inlet passage.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
In describing the invention, except as otherwise noted, term " on ", the orientation of the instruction such as D score, "left", "right" or state relation be based on orientation shown in the drawings or state relation, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.
In describing the invention, it should be noted that, unless otherwise clearly defined and limited, term " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be directly be connected, also indirectly can be connected by intermediary.For the ordinary skill in the art, concrete condition above-mentioned term concrete meaning in the present invention can be understood.
Shown in composition graphs 1 and Fig. 2, a kind of gas-turbine combustion chamber axial rotational flow nozzle provided by the invention, comprise the fuel that outer nozzle wall 7 and one end be plugged in outer nozzle wall 7 and inject body 3, outer nozzle wall 7 sends into gases at high pressure by air compressor machine, the inside that fuel injects body 3 is provided with center fuel passage 1, fuel inject body 3 be provided with multiple fuel injection pipe 4 communicated with center fuel passage 1 in the radial direction, the sidewall of each fuel injection pipe 4 is equipped with fuel orifice 6, fuel is injected in outer nozzle wall 7 by fuel orifice 6 and mixes with air, first order annular air-flow path 8 is formed between fuel gas playpipe top and outer nozzle wall 7, and the width of first order annular air-flow path 8 is preferably 10% ~ 50% of the height of fuel injection pipe 4, thereby increase the air-flow axial velocity of peripheral annular air duct 2 outer circumferential side, reduce the boundary effect of internal face of combustion chamber, ensure the distribution of outer circumferential side gas velocity degree type.
Air is entered by the air inlet of outer nozzle wall, start to mix with fuel at fuel injection pipe place, on the inwall of outer nozzle wall 7, and be positioned at the rear of described fuel injection pipe 4, be provided with axial rotational flow device 5, it is multiple swirl vanes that axial rotational flow device 5 is preferably quantity, and the quantity of swirl vane is preferably 6 ~ 12, because axial rotational flow device 5 is positioned at the rear of fuel injection pipe airflow direction, the fuel of mixing can be made fully to mix with air; Axial rotational flow device 5 and fuel inject between body 3 and are formed with second level annular air-flow path 9, the width of second level annular air-flow path 9 is preferably 10% ~ 50% of swirl vane length, thereby increase the air-flow axial velocity of peripheral annular air duct 2 inner circumferential side, reduce fuel and inject body 3 boundary-layer to the impact of nozzle exit velocity type, and one end that fuel injection body 3 is inserted into outer nozzle wall 7 is taper, ensure that conical inner body downstream does not produce recirculating zone, improve burning reliability.Thus, fuel injection pipe 4 and axial rotational flow device 5 can the eddy flow of enhanced fuel gas and air mix, ensure fluid velocity distribution rationally, fuel-air blending is even, and then promotes combustion stability.
Multiple swirl vane and multiple fuel injection pipe 4 in the axial direction staggered relative are arranged, coordinate the adjustment of fuel orifice 6 height and position, wider design space can be provided for nozzle, meet the needs of different fuel and air blending, improve the VELOCITY DISTRIBUTION of nozzle center's cone to nozzle outlet portion.
Preferably, be 50% ~ 100% of the length of fuel injection pipe 4 by the distance between fuel injection pipe 4 and the opening of outer nozzle wall 7, prevent shunting fuel jetting nozzle outer wall 7; And between fuel injection pipe 4 and the air inlet of outer nozzle wall 7, forming air inlet passage 12 thus, the fuel gas spraying to air inlet and the air entered liquidate and produce eddy current, thus in air inlet passage 12, a small amount of mixing occur.The combustion gas of certain above-mentioned shunting is just a small amount of, and the Main Function of air inlet passage 12 is that the air making to enter returns to axis.
Preferably, distance between fuel injection pipe 4 and axial rotational flow device 5 is 50% ~ 100% of the length of fuel injection pipe 4, annular air-flow path is formed thus between fuel injection pipe 4 and axial rotational flow device 5, achieve fuel gas and air enter swirl-flow devices before premixed, for ensureing that the mixing effect of jet expansion fuel gas and air plays facilitation.
Preferably, on airintake direction, the combustion chamber at the rear of axial rotational flow device 5 has radial contraction section 11, instantaneous compression is being there is in the gaseous mixture of air and fuel gas through this mirror image contraction structure, the concentration of fuel gas increases, relatively add mixability, compression can also be the warm-up movement aggravation of gas in addition, further increases the melting concn of fuel gas.
Operation principle of the present invention is as follows:
For clean energy resource gas fuel, gas fuel enters center fuel passage 1, and the wall perforate of being injected body 3 by fuel enters each fuel injection pipe 4, then is sprayed by each fuel orifice 6.Air enters annular air channel 2, axis is returned to by air inlet passage 12 airflow direction, the passage inner circumferential side air pressing close to fuel injection body 3 mixes with fuel in fuel gas playpipe front end, enters gaseous mixture annular air-flow path 10 and strengthens mixed effect; Air away from the air duct outer circumferential side of conical inner body keeps axial velocity by first order annular air-flow path 8, enters gaseous mixture annular air-flow path 10.Through fuel and the air Mixture of gaseous mixture annular air-flow path 10, outer circumferential side part acts on through axial rotational flow device 5 and produces eddy flow, and mixed effect strengthens further; Inner periphery side portion divides the original airflow direction of maintenance by second level annular air-flow path 9, and axial velocity is maintained.Fuel and air Mixture in axial rotational flow device 5 exit blending, through nozzle contraction section until jet expansion.Thus form nozzle exit velocity distribution and the fuel-air mixing effect of coupling, ensure the stability of burning and good Exit temperature distribution.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and replacement, these improve and replace and also should be considered as protection scope of the present invention.
Claims (10)
1. a gas-turbine combustion chamber axial rotational flow nozzle, is characterized in that, comprises the fuel that outer nozzle wall (7) and one end be plugged in described outer nozzle wall (7) and injects body (3); The inside that described fuel injects body (3) is provided with center fuel passage (1), that injects body (3) at described fuel is provided with the fuel injection pipe (4) that multiple and described center fuel passage (1) communicates in the radial direction, the sidewall of each described fuel injection pipe (4) is equipped with fuel orifice (6), is formed with first order annular air-flow path (8) between the top of described fuel injection pipe (4) and described outer nozzle wall (7); On the inwall of outer nozzle wall (7), and be positioned at the rear of described fuel injection pipe (4), be provided with axial rotational flow device (5), axial rotational flow device (5) and fuel inject between body (3) and are formed with second level annular air-flow path (9).
2. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1, is characterized in that, described axial rotational flow device (5) is swirl vane, and quantity is multiple; Multiple swirl vane is along the circumference uniform distribution of described outer nozzle wall (7).
3. gas-turbine combustion chamber axial rotational flow nozzle according to claim 2, is characterized in that, the width of described second level annular air-flow path (9) is 10% ~ 50% of described swirl vane length.
4. gas-turbine combustion chamber axial rotational flow nozzle according to claim 2, is characterized in that, the quantity of described swirl vane is 6 ~ 12.
5. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1, is characterized in that, multiple described swirl vane and multiple described fuel injection pipe (4) in the axial direction staggered relative are arranged.
6. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1, is characterized in that, the width of described first order annular air-flow path (8) is 10% ~ 50% of the height of described fuel injection pipe (4).
7. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1, it is characterized in that, the distance between the opening of described fuel injection pipe (4) and described outer nozzle wall (7) is 50% ~ 100% of the length of fuel injection pipe (4).
8. gas-turbine combustion chamber axial rotational flow nozzle according to claim 1, it is characterized in that, the distance between described fuel injection pipe (4) and described axial rotational flow device (3) is 50% ~ 100% of the length of described fuel injection pipe (4).
9. the gas-turbine combustion chamber axial rotational flow nozzle according to any one of claim 1-8, is characterized in that, on airintake direction, the described outer nozzle wall (7) at the rear of described axial rotational flow device (3) has radial contraction section.
10. the gas-turbine combustion chamber axial rotational flow nozzle according to any one of claim 1-8, is characterized in that, one end that described fuel injection body (3) is inserted into described outer nozzle wall (7) is taper.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410446283.2A CN104214799B (en) | 2014-09-03 | 2014-09-03 | Axial swirl nozzle of combustion chamber of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410446283.2A CN104214799B (en) | 2014-09-03 | 2014-09-03 | Axial swirl nozzle of combustion chamber of gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104214799A true CN104214799A (en) | 2014-12-17 |
| CN104214799B CN104214799B (en) | 2017-01-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410446283.2A Active CN104214799B (en) | 2014-09-03 | 2014-09-03 | Axial swirl nozzle of combustion chamber of gas turbine |
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| Country | Link |
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| CN (1) | CN104214799B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106196059A (en) * | 2016-08-26 | 2016-12-07 | 中能服能源科技股份有限公司 | A kind of low nitrogen oxide burner structure |
| CN106247408A (en) * | 2016-07-27 | 2016-12-21 | 中国科学院工程热物理研究所 | A kind of widening is tempered the nozzle of nargin, nozzle array and burner |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5590529A (en) * | 1994-09-26 | 1997-01-07 | General Electric Company | Air fuel mixer for gas turbine combustor |
| CN1187600A (en) * | 1996-12-20 | 1998-07-15 | 联合工艺公司 | Method of disgorging flames from two stream tangential entry nozzle |
| EP0935095A2 (en) * | 1998-02-09 | 1999-08-11 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| CN1464958A (en) * | 2001-07-10 | 2003-12-31 | 三菱重工业株式会社 | Premixing nozzle, burner and gas turbine |
| CN1464959A (en) * | 2001-06-07 | 2003-12-31 | 三菱重工业株式会社 | Combustor |
| CN204176681U (en) * | 2014-09-03 | 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 | Gas-turbine combustion chamber axial rotational flow nozzle |
-
2014
- 2014-09-03 CN CN201410446283.2A patent/CN104214799B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5590529A (en) * | 1994-09-26 | 1997-01-07 | General Electric Company | Air fuel mixer for gas turbine combustor |
| CN1187600A (en) * | 1996-12-20 | 1998-07-15 | 联合工艺公司 | Method of disgorging flames from two stream tangential entry nozzle |
| EP0935095A2 (en) * | 1998-02-09 | 1999-08-11 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| CN1464959A (en) * | 2001-06-07 | 2003-12-31 | 三菱重工业株式会社 | Combustor |
| CN1464958A (en) * | 2001-07-10 | 2003-12-31 | 三菱重工业株式会社 | Premixing nozzle, burner and gas turbine |
| CN204176681U (en) * | 2014-09-03 | 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 | Gas-turbine combustion chamber axial rotational flow nozzle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106247408A (en) * | 2016-07-27 | 2016-12-21 | 中国科学院工程热物理研究所 | A kind of widening is tempered the nozzle of nargin, nozzle array and burner |
| CN106247408B (en) * | 2016-07-27 | 2019-01-18 | 中国科学院工程热物理研究所 | A kind of nozzle, nozzle array and burner for widening tempering nargin |
| CN106196059A (en) * | 2016-08-26 | 2016-12-07 | 中能服能源科技股份有限公司 | A kind of low nitrogen oxide burner structure |
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| Publication number | Publication date |
|---|---|
| CN104214799B (en) | 2017-01-18 |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Axial swirl nozzle of combustion chamber of gas turbine Effective date of registration: 20171115 Granted publication date: 20170118 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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Effective date of registration: 20190820 Granted publication date: 20170118 |
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Date of cancellation: 20191230 Granted publication date: 20170118 |
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Effective date of registration: 20200116 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20170118 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |