CN104566469A - Double-fuel spray nozzle of combustion chamber of gas turbine - Google Patents
Double-fuel spray nozzle of combustion chamber of gas turbine Download PDFInfo
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- CN104566469A CN104566469A CN201410843615.0A CN201410843615A CN104566469A CN 104566469 A CN104566469 A CN 104566469A CN 201410843615 A CN201410843615 A CN 201410843615A CN 104566469 A CN104566469 A CN 104566469A
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- 239000000446 fuel Substances 0.000 title claims abstract description 73
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 35
- 239000007921 spray Substances 0.000 title abstract 6
- 239000002737 fuel gas Substances 0.000 claims abstract description 64
- 239000000295 fuel oil Substances 0.000 claims abstract description 42
- 238000000926 separation method Methods 0.000 claims description 33
- 230000009977 dual effect Effects 0.000 claims description 24
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 239000007789 gas Substances 0.000 abstract description 17
- 230000000694 effects Effects 0.000 abstract description 10
- 239000007788 liquid Substances 0.000 abstract 2
- 230000015572 biosynthetic process Effects 0.000 abstract 1
- 238000005192 partition Methods 0.000 abstract 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 7
- 238000002156 mixing Methods 0.000 description 6
- 239000003344 environmental pollutant Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 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
- 238000000034 method Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 239000013505 freshwater Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Abstract
The invention relates to the technical field of gas turbines, and provides a double-fuel spray nozzle of a combustion chamber of a gas turbine. The double-fuel spray nozzle is characterized in that an annular slot channel is arranged inside a pipe wall of an annular partition pipeline of the spray nozzle and is communicated with hollow fuel oil channels arranged on blades of an inner-layer air cyclone, so that fuel oil can be supplied; hollow fuel gas pipelines which are communicated with one another are arranged on the blades of the inner-layer air cyclone and blades of an outer-layer air cyclone, and fuel jet holes which are communicated with the hollow fuel gas pipelines are formed in the blades of the inner-layer air cyclone and the blades of the outer-layer air cyclone, so that fuel gas can be supplied. The double-fuel spray nozzle has the advantages that film preliminary formation effects can be realized by the annular slot channel, and accordingly conditions can be provided for forming liquid droplets with appropriate sizes and excellently distributing the liquid droplets after the fuel oil flows into combustion regions; the fuel oil and the fuel gas are matched with each other, so that requirements on fuel under different load conditions can be met; the air cyclones are matched with supply of the fuel oil and the fuel gas on the basis that the requirements on the fuel under the different load conditions are met, so that outlet speeds and outlet temperatures of the spray nozzle can be reasonably distributed, and the combustion stability can be ultimately guaranteed.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of dual fuel nozzle of gas-turbine combustion chamber.
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 that this traditional generation technology exists generating efficiency, pollutant emission high (especially NOx emission), expends 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 nozzle design for tissue burning, reduce pollutant emission particularly important.
In gas-turbine combustion chamber, fuel 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.Dual fuel nozzle requires under different loads, adopt different fuel to burn, and ensures flame stabilization and good combustibility.Current, such as, to the design form of gas-turbine combustion chamber dual fuel nozzle, patent CN102261673A, adopt nozzle center that the form of centrifuging temperature nozzle is installed, and by atomizer atomized fuel, ensure that fuel oil has good combustibility after entering combustion chamber.
But, the fuel distribution effect of centrifuging temperature nozzle under some loading condiction is satisfactory for result not as pre-membrane type nozzle: the distribution of centrifuging temperature port fuel is spread to surrounding centered by nozzle center region, need to make fuel oil reach applicable droplet size and distribution before combustion by atomizer, and atomizer is higher to the difficulty of nozzle center's bleed.
In view of this, urgently provide a kind of will the dual fuel nozzle of more reasonable effective gas-turbine combustion chamber, thus tissue burning control polluted articles discharge.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention is exactly the dual fuel nozzle how providing a kind of more rationally effective gas-turbine combustion chamber.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of dual fuel nozzle of gas-turbine combustion chamber, comprise nozzle ring pipeline; Described nozzle ring pipe interior is provided with annular and separation pipeline; Upstream extremity in described annular and separation pipeline is provided with annular fuel gas pipeline, and is positioned at the central fuel pipeline of described annular fuel gas pipe interior; Described annular fuel gas pipeline is connected a rotary body plug with the downstream of central fuel pipeline;
Upstream extremity between described nozzle ring pipeline and annular and separation pipeline is provided with outer air cyclone; The inner side of described outer air cyclone, is provided with inner air cyclone between annular and separation pipeline and annular fuel gas pipeline; The blade of described inside and outside layer of air cyclone offers the fuel gas hollow channel of connection, and be communicated with and fuel orifice at an angle to each other with described fuel gas hollow channel; Described fuel gas hollow channel is communicated with the fuel gas through hole that described annular fuel gas pipeline is offered;
The tube wall inside of described annular and separation pipeline offers annular slot passage, and offers fuel oil hollow channel on the blade of described inner air cyclone; Described annular slot passage and described fuel oil hollow channel, and the fuel oil through hole that described central fuel pipeline is offered is communicated with successively.
Preferably, described nozzle ring pipeline, annular and separation pipeline, annular fuel gas pipeline and central fuel pipeline coaxially distribute.
Preferably, described rotary body plug is conical, and described plug and described central fuel pipeline coaxially distribute, and the summit of circular cone is positioned at downstream.
Preferably, described annular slot passage originates in the axial location of described fuel oil hollow channel, and extends to the tail end of described annular and separation pipeline.
Preferably, the height of described annular slot passage is consistent from upstream extremity to downstream, is 0.5mm ~ 1mm.
Preferably, described fuel gas hollow channel is positioned at the upstream of fuel oil hollow channel, and both are parallel to each other.
Preferably, described outer air cyclone adopts axial blade formula structure, and blade is evenly arranged along the inner periphery of described nozzle ring pipeline.
Preferably, described outer air cyclone comprises 6 ~ 8 blades, and eddy flow angle is 0 ~ 45 degree.
Preferably, described inner air cyclone adopts axial blade formula structure, and blade is evenly arranged along the inner periphery of described annular and separation pipeline.
Preferably, described inner air cyclone comprises 6 ~ 8 blades, and eddy flow angle is 0 ~ 15 degree.
(3) beneficial effect
Technical scheme of the present invention has the following advantages: the dual fuel nozzle of gas-turbine combustion chamber of the present invention, annular slot passage is offered in the tube wall inside of annular and separation pipeline, and be communicated with the fuel oil hollow channel that the blade of inner air cyclone is offered, to supply fuel oil; In inner air cyclone and outer air cyclone, blade offers the fuel gas hollow pipeline of connection, and the fuel orifice be communicated with described fuel gas hollow pipeline, to supply fuel gas.Wherein, described annular slot passage has membranae praeformativa effect, for fuel oil enter combustion zone after form suitable droplet size and well distributedly provide condition.Above-mentioned fuel oil and fuel gas cooperatively interact, and meet the requirement to fuel under different load; On this basis, air cyclone and double fuel supply cooperatively interact, and obtain the distribution of rational nozzle exit velocity and Exit temperature distribution, the final stability ensureing burning.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the schematic cross-section of the dual fuel nozzle of the gas-turbine combustion chamber of the embodiment of the present invention;
Fig. 2 is the structure three-dimensional cross-sectional schematic of the dual fuel nozzle of the gas-turbine combustion chamber of the embodiment of the present invention;
In figure: 1, nozzle ring pipeline; 2, annular and separation pipeline; 3, annular fuel gas pipeline; 4, central fuel pipeline; 5, rotary body plug; 6, outer air cyclone; 7, inner air cyclone; 8, fuel gas hollow channel; 9, fuel orifice; 10, annular slot passage; 11, fuel oil hollow channel.
Detailed description of the invention
Below in conjunction with drawings and Examples, embodiments of the present invention are described in further detail.Following examples for illustration of the present invention, but can not be used for limiting the scope of the invention.
In describing the invention, it should be noted that, term " " center ", "front", "rear", " interior ", " outward ", " axis " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.
The dual fuel nozzle of a kind of gas-turbine combustion chamber of the present embodiment, comprises nozzle ring pipeline 1; Described nozzle ring pipeline 1 inside is provided with annular and separation pipeline 2, so that nozzle ring pipeline 1 interior separation is gone out multiple gas channel; Described multiple gas channel finally converges at the tail end of annular and separation pipeline 2.The upstream extremity of described annular and separation pipeline 2 inside is provided with annular fuel gas pipeline 3, and is positioned at the central fuel pipeline 4 of described annular fuel gas pipeline 3 inside; Wherein, the effect of annular fuel gas pipeline 3 is to input fuel gas, and the effect of central fuel pipeline 4 is to input fuel oil.In order to avoid fuel gas and fuel oil directly enter the downstream of nozzle along the axis of nozzle, be connected a rotary body plug 5 at annular fuel gas pipeline 3 with the downstream of central fuel pipeline 4.Thus, between nozzle ring pipeline 1 and annular and separation pipeline 2, form outer gas flow passage, and annular and separation pipeline 2, and form internal layer gas channel between annular fuel gas pipeline 3 and rotary body plug 5.
Secondly, between nozzle ring pipeline 1 and annular and separation pipeline 2, the upstream extremity of (being also in outer gas flow passage) is provided with outer air cyclone 6; The inner side of described outer air cyclone 6, between annular and separation pipeline 2 and annular fuel gas pipeline 3, (being also in internal layer gas channel) is provided with inner air cyclone 7.The blade of described inside and outside layer of air cyclone 6 offers the fuel gas hollow channel 8 of connection, and be communicated with and fuel orifice 9 at an angle to each other with described fuel gas hollow channel 8.Described fuel gas hollow channel 8 is communicated with the fuel gas through hole that described annular fuel gas pipeline 3 is offered.Fuel gas in annular fuel gas pipeline 3 enters fuel gas hollow channel 8 from fuel gas through hole, and under the effect of air cyclone, enters internal layer gas channel and outer gas flow passage from fuel orifice 9.In the present embodiment, the diameter of described fuel orifice 9 is preferably 0.5mm ~ 1mm.
In order to realize double fuel supply, the tube wall inside of described annular and separation pipeline 2 offers annular slot path 10, and offers fuel oil hollow channel 11 on the blade of described inner air cyclone 7; Described annular slot path 10 is communicated with described fuel oil hollow channel 11, and is communicated with the fuel oil through hole that described central fuel pipeline 4 is offered.Fuel oil in central fuel pipeline 4 enters fuel oil hollow channel 11 from fuel oil through hole, then enters the tail end of nozzle along annular slot path 10 from the downstream of annular and separation pipeline 2.It should be noted that, in order to avoid interfering between annular slot path 10 and fuel gas hollow channel 8, preferred described annular slot path 10 originates in the axial location of described fuel oil hollow channel 11, and extends to the tail end of described annular and separation pipeline 2; And described fuel gas hollow channel 8 is positioned at the upstream of fuel oil hollow channel 11.In addition, preferred described fuel gas hollow channel 8 is parallel with described fuel oil hollow channel 11.
It is emphasized that annular slot path 10 has membranae praeformativa effect, for fuel oil enter combustion zone after form suitable droplet size and well distributedly provide condition.Fuel oil after membranae praeformativa effect, enters double-layer air-flow passage from the outlet of annular slot path 10.The height of preferred annular slot path 10 is consistent from front end to rear end, is 0.5mm ~ 1mm.
Refer to Fig. 1 and Fig. 2, in the present embodiment, annular fuel gas pipeline 3, central fuel pipeline 4 and rotary body plug 5 are preferably but must not be integral type structure.Described rotary body plug 5 is preferably but not limited to being set to the effective conical plug of water conservancy diversion, and the summit of circular cone is positioned at downstream.In addition, described annular fuel gas pipeline 3, central fuel pipeline 4, rotary body plug 5, annular and separation pipeline 2 and nozzle ring pipeline 1 are preferably coaxial is arranged.
It should be noted that in the present embodiment, the fuel gas hollow channel 8 that the blade of air cyclone is offered and the quantity of fuel oil hollow channel 11, not by the restriction of the view of the present embodiment.And preferred described outer air cyclone 6, annular and separation pipeline 2 and inner air cyclone 7 are integral type structure, thus can be directly one-body molded by casting technique.
In the present embodiment, air divides and two-layerly enters dual fuel nozzle, the outer air cyclone 6 of outer air in outer gas flow leads to, and forms strong eddy flow with the fuel gas blending sprayed into; The inner air cyclone 7 of inner air in internal layer gas channel, forms weak eddy flow with the fuel gas blending sprayed into.Two layer of air converge in the exit of annular and separation pipeline 2, and are atomized and blending the fuel oil after membranae praeformativa, form coupling fuel gas and fuel oil two kinds of fuel-air mixing effects.Wherein, outlet refers to the port of downstream near combustion zone.
The dual fuel nozzle of the present embodiment, the eddy flow angle of inner air cyclone 7 is less, to prevent the appearance of nozzle interior low regime; The eddy flow angle of outer air cyclone 6 is comparatively large, ensures the good blending of fuel gas and air.Particularly, inner air cyclone 7 preferably adopts axial blade formula structure, and blade is evenly arranged along the inner periphery of described annular and separation pipeline 2, and wherein blade quantity is 6 ~ 8, and eddy flow angle is 0 ~ 15 degree; Outer air cyclone 6 is except eddy flow angle is 0 ~ 45 degree, and other parameters are the same with inner air eddy flow.Inside and outside layer gas channel of the present invention, by the adjustment of the eddy flow angle of air cyclone, coordinates the supply of fuel oil and fuel gas, forms rational fuel distribution and VELOCITY DISTRIBUTION.
The dual fuel nozzle of the gas-turbine combustion chamber of the present embodiment, fuel gas and fuel two kinds of fuel cooperatively interact, and meet the requirement to fuel under different load.Under different load requires, select different fuel methods of supplying, fuel gas and fuel oil can be supplied simultaneously also can be used alone.Enter the fuel gas in double-layer air-flow passage (comprising internal layer gas channel and outer gas flow passage) and fuel oil, violent blending effect is there is with inside and outside two-layer rotational flow air, fuel oil reaches applicable droplet size and distribution, when arriving jet expansion, two kinds of fuel all can reach applicable fuel distribution and the VELOCITY DISTRIBUTION of coupling.In the present embodiment, air cyclone and double fuel supply cooperatively interact, and obtain the distribution of rational nozzle exit velocity and Exit temperature distribution, the final stability ensureing burning.
Above embodiment is only for illustration of the present invention, but not limitation of the present invention.Although with reference to embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, various combination, amendment or equivalent replacement are carried out to technical scheme of the present invention, do not depart from the spirit and scope of technical solution of the present invention, all should be encompassed in the middle of right of the present invention.
Claims (10)
1. a dual fuel nozzle for gas-turbine combustion chamber, is characterized in that, comprises nozzle ring pipeline; Described nozzle ring pipe interior is provided with annular and separation pipeline; Upstream extremity in described annular and separation pipeline is provided with annular fuel gas pipeline, and is positioned at the central fuel pipeline of described annular fuel gas pipe interior; Described annular fuel gas pipeline is connected a rotary body plug with the downstream of central fuel pipeline;
Upstream extremity between described nozzle ring pipeline and annular and separation pipeline is provided with outer air cyclone; The inner side of described outer air cyclone, is provided with inner air cyclone between annular and separation pipeline and annular fuel gas pipeline; The blade of described inside and outside layer of air cyclone offers the fuel gas hollow channel of connection, and be communicated with and fuel orifice at an angle to each other with described fuel gas hollow channel; Described fuel gas hollow channel is communicated with the fuel gas through hole that described annular fuel gas pipeline is offered;
The tube wall inside of described annular and separation pipeline offers annular slot passage, and offers fuel oil hollow channel on the blade of described inner air cyclone; Described annular slot passage and described fuel oil hollow channel, and the fuel oil through hole that described central fuel pipeline is offered is communicated with successively.
2. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, is characterized in that, described nozzle ring pipeline, annular and separation pipeline, annular fuel gas pipeline and central fuel pipeline coaxially distribute.
3. the dual fuel nozzle of gas-turbine combustion chamber according to claim 2, is characterized in that, described rotary body plug is conical, and described plug and described central fuel pipeline coaxially distribute, and the summit of circular cone is positioned at downstream.
4. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, is characterized in that, described annular slot passage originates in the axial location of described fuel oil hollow channel, and extends to the tail end of described annular and separation pipeline.
5. the dual fuel nozzle of gas-turbine combustion chamber according to claim 4, is characterized in that, the height of described annular slot passage is consistent from upstream extremity to downstream, is 0.5mm ~ 1mm.
6. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, is characterized in that, described fuel gas hollow channel is positioned at the upstream of fuel oil hollow channel, and both are parallel to each other.
7. the dual fuel nozzle of gas-turbine combustion chamber as claimed in any of claims 1 to 6, is characterized in that, described outer air cyclone adopts axial blade formula structure, and blade is evenly arranged along the inner periphery of described nozzle ring pipeline.
8. the dual fuel nozzle of gas-turbine combustion chamber according to claim 7, is characterized in that, described outer air cyclone comprises 6 ~ 8 blades, and eddy flow angle is 0 ~ 45 degree.
9. the dual fuel nozzle of gas-turbine combustion chamber as claimed in any of claims 1 to 6, is characterized in that, described inner air cyclone adopts axial blade formula structure, and blade is evenly arranged along the inner periphery of described annular and separation pipeline.
10. the dual fuel nozzle of gas-turbine combustion chamber according to claim 9, is characterized in that, described inner air cyclone comprises 6 ~ 8 blades, and eddy flow angle is 0 ~ 15 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410843615.0A CN104566469B (en) | 2014-12-30 | 2014-12-30 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410843615.0A CN104566469B (en) | 2014-12-30 | 2014-12-30 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
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| CN104566469A true CN104566469A (en) | 2015-04-29 |
| CN104566469B CN104566469B (en) | 2018-09-14 |
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| CN201410843615.0A Active CN104566469B (en) | 2014-12-30 | 2014-12-30 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108224473A (en) * | 2017-12-28 | 2018-06-29 | 中国航发四川燃气涡轮研究院 | A kind of integrated after-burner of sudden expansion inner cone flame stabilization structure |
| CN108474558A (en) * | 2015-12-30 | 2018-08-31 | 通用电气公司 | Liquid fuel nozzle for dual fuel burner |
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| EP0905443A2 (en) * | 1997-09-30 | 1999-03-31 | General Electric Company | Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine |
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| CN108474558A (en) * | 2015-12-30 | 2018-08-31 | 通用电气公司 | Liquid fuel nozzle for dual fuel burner |
| CN108474558B (en) * | 2015-12-30 | 2020-08-04 | 通用电气公司 | Liquid fuel nozzle for dual fuel burner |
| CN108224473A (en) * | 2017-12-28 | 2018-06-29 | 中国航发四川燃气涡轮研究院 | A kind of integrated after-burner of sudden expansion inner cone flame stabilization structure |
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|---|---|
| CN104566469B (en) | 2018-09-14 |
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Effective date of registration: 20200117 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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