CN104566473A - 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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- CN104566473A CN104566473A CN201410843051.0A CN201410843051A CN104566473A CN 104566473 A CN104566473 A CN 104566473A CN 201410843051 A CN201410843051 A CN 201410843051A CN 104566473 A CN104566473 A CN 104566473A
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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 at downstream ends of blades of an inner-layer air cyclone or an outer-layer air cyclone and is communicated with hollow fuel oil channels on the blades of the air cyclones, 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 the 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 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, so that 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, accordingly, 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 downstream of the blade of described inner air cyclone or outer air cyclone offers annular slot passage, and described central fuel pipeline offers fuel oil through hole; Described fuel oil through hole is by fuel oil hollow channel and described annular slot channel connection.
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 blade.
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, the radial position of described annular slot passage is blade center radial position.
Preferably, described outer air cyclone adopts axial blade formula structure, and blade is evenly arranged along the inner periphery of described nozzle ring pipeline; 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; 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 blade downstream of inner air cyclone or outer air cyclone, and annular slot passage is communicated with the fuel oil hollow channel on the blade of air cyclone, 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 one;
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 one;
Fig. 3 is the schematic cross-section of the dual fuel nozzle of the gas-turbine combustion chamber of the embodiment of the present invention two;
Fig. 4 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 two;
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; 11a, fuel oil hollow channel; 11b, 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 invention, 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 invention, the diameter of described fuel orifice 9 is preferably 0.5mm ~ 1mm.
In order to realize double fuel supply, the present invention offers annular slot path 10 in the blade downstream of inner air cyclone 7 or outer air cyclone 6; And described central fuel pipeline 4 offers fuel oil through hole; Described fuel oil through hole is communicated with described annular slot path 10 by fuel oil hollow channel.
Offer the difference of position below according to annular slot path 10, provide two embodiments to be described dual fuel nozzle of the present invention.
Embodiment one
Refer to Fig. 1 and Fig. 2, the dual fuel nozzle of the gas-turbine combustion chamber of the present embodiment one, described annular slot path 10 is opened in the blade downstream of inner air cyclone 7.Correspondingly, the blade of inner air cyclone 7 offers fuel oil hollow channel 11a; Described annular slot path 10 is communicated with described fuel oil hollow channel 11a, 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 11a from fuel oil through hole, then enters internal layer gas channel along annular slot path 10, and enters the tail end of nozzle along internal layer gas channel.
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 11a, and extending to the tail end of blade, blade herein refers to the blade at described annular slot path 10 place; And described fuel gas hollow channel 8 is positioned at the upstream of fuel oil hollow channel 11a.In addition, preferred described fuel gas hollow channel 8 is parallel with described fuel oil hollow channel 11a.
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 internal layer gas channel 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.
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 quantity of the fuel gas hollow channel 8 that the blade of air cyclone is offered and fuel oil hollow channel 11a, 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.
Embodiment two
The present embodiment two provides a kind of dual fuel nozzle of gas-turbine combustion chamber, refers to Fig. 3 and Fig. 4.The present embodiment two and embodiment one difference are, annular slot path 10 is opened in the tract of the blade of outer air cyclone 6, and extend to the tail end of described annular slot path 10 place blade.Correspondingly, the blade of inside and outside layer of air cyclone all offers the fuel oil hollow channel 11b of connection, and described fuel oil hollow channel 11b is communicated with described annular slot path 10, thus fuel oil is finally guided enters among annular slot path 10.The present embodiment two other structure and principle, all identical with embodiment one, repeat no more herein.
In above-described embodiment, the major function that position will realize according to dual fuel nozzle of offering of annular slot path 10 sets.When nozzle major function is used for flame stabilization, then described annular slot path 10 is opened in the blade interior of inner air cyclone 7; When the major function of nozzle is for ensureing to join between burning load and burner inner liner the needing of flame, then described annular slot path 10 is opened in the blade interior of outer air cyclone 6.
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 (9)
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 downstream of the blade of described inner air cyclone or outer air cyclone offers annular slot passage, and described central fuel pipeline offers fuel oil through hole; Described fuel oil through hole is by fuel oil hollow channel and described annular slot channel connection.
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 blade.
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 according to claim 1, is characterized in that, the radial position of described annular slot passage is internal layer blade or outer blade radially position.
8. the dual fuel nozzle of gas-turbine combustion chamber as claimed in any of claims 1 to 7, 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; 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 7, 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; Described inner air cyclone comprises 6 ~ 8 blades, and eddy flow angle is 0 ~ 15 degree.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410843051.0A CN104566473B (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 |
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| CN201410843051.0A CN104566473B (en) | 2014-12-30 | 2014-12-30 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
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| CN104566473A true CN104566473A (en) | 2015-04-29 |
| CN104566473B CN104566473B (en) | 2018-02-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107620979A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | Gas turbine |
Citations (5)
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|---|---|---|---|---|
| CA2154452A1 (en) * | 1994-01-11 | 1995-07-13 | Kenneth H. Maden | Dual fuel injection nozzle with water injection |
| US5833141A (en) * | 1997-05-30 | 1998-11-10 | General Electric Company | Anti-coking dual-fuel nozzle for a gas turbine combustor |
| CN103175220A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Dual-fuel nozzle used for chemical regenerative cycle |
| CN203517806U (en) * | 2013-10-23 | 2014-04-02 | 中国船舶重工集团公司第七�三研究所 | Gas and liquid dual-fuel integrated nozzle |
| CN204438189U (en) * | 2014-12-30 | 2015-07-01 | 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 dual fuel nozzle of gas-turbine combustion chamber |
-
2014
- 2014-12-30 CN CN201410843051.0A patent/CN104566473B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2154452A1 (en) * | 1994-01-11 | 1995-07-13 | Kenneth H. Maden | Dual fuel injection nozzle with water injection |
| US5833141A (en) * | 1997-05-30 | 1998-11-10 | General Electric Company | Anti-coking dual-fuel nozzle for a gas turbine combustor |
| CN103175220A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Dual-fuel nozzle used for chemical regenerative cycle |
| CN203517806U (en) * | 2013-10-23 | 2014-04-02 | 中国船舶重工集团公司第七�三研究所 | Gas and liquid dual-fuel integrated nozzle |
| CN204438189U (en) * | 2014-12-30 | 2015-07-01 | 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 dual fuel nozzle of gas-turbine combustion chamber |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107620979A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | Gas turbine |
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