CN104566473B - A kind of dual fuel nozzle of gas-turbine combustion chamber - Google Patents
A kind of dual fuel nozzle of gas-turbine combustion chamber Download PDFInfo
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- CN104566473B CN104566473B CN201410843051.0A CN201410843051A CN104566473B CN 104566473 B CN104566473 B CN 104566473B CN 201410843051 A CN201410843051 A CN 201410843051A CN 104566473 B CN104566473 B CN 104566473B
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Abstract
The present invention relates to gas turbine technology field, there is provided a kind of dual fuel nozzle of gas-turbine combustion chamber.The nozzle opens up annular slot passage in the blade downstream of inner air cyclone or outer air cyclone, and annular slot passage connects with the fuel oil hollow channel on the blade of air cyclone, to supply fuel oil；The fuel gas hollow pipeline of connection, and the fuel orifice connected with the fuel gas hollow pipeline are offered in inner air cyclone and outer air cyclone, on blade, to supply fuel gas.Wherein, the annular slot passage has membranae praeformativa effect, and suitable droplet size and well distributed offer condition are formed after entering combustion zone for fuel oil.Above-mentioned fuel oil and fuel gas cooperate, and meet the requirement to fuel under different load；On this basis, air cyclone and double fuel supply cooperate, and obtain rational nozzle exit velocity distribution and Exit temperature distribution, the final stability for ensureing burning.
Description
Technical field
The present invention relates to gas turbine technology field, more particularly to a kind of dual fuel nozzle of gas-turbine combustion chamber.
Background technology
In the current energy resource structure in China, most shares are occupied using the thermal power generation of traditional coal combustion technology.
But generating efficiency to be present low for this traditional generation technology, pollutant emission height (especially NOx emission), freshwater resources are expended
The shortcomings of more.Using the gas turbine power generation technology that natural gas is fuel as one of clean energy technology, generating can met
While burden requirement, the discharge of pollutant is effectively reduced, the design of gas-turbine combustion chamber nozzle is for tissue among these
Burning, reduction pollutant emission are particularly important.
In gas-turbine combustion chamber, fuel and air realize premixing and the change of velocity profile by nozzle, go out in nozzle
Mouth reaches rational VELOCITY DISTRIBUTION, and matches rational fuel-air mixture example, organizes to burn into combustion chamber, is formed stable
Flow field and combustion field.Dual fuel nozzle requirement is burnt under different loads using different fuel, ensures that flame is steady
Fixed and good combustibility.Currently, to the design form of gas-turbine combustion chamber dual fuel nozzle, such as patent
CN102261673A, the form of centrifuging temperature nozzle is installed using nozzle center, and by atomizer atomized fuel, ensures combustion
Oil has good combustibility after entering combustion chamber.
But fuel distribution effect of the centrifuging temperature nozzle under some loading condictions is not so good as the effect of pre- membrane type nozzle
It is preferable：The distribution of centrifuging temperature port fuel is spread, it is necessary to be made by atomizer centered on nozzle center region to surrounding
Fuel oil reaches suitable droplet size and distribution before combustion, and atomizer is higher to the difficulty of nozzle center's bleed.
In view of this, it would be highly desirable to provide it is a kind of will the more reasonable dual fuel nozzle of effective gas-turbine combustion chamber, so as to
Tissue burning simultaneously controls pollutant emission.
The content of the invention
(1) technical problems to be solved
The technical problem to be solved in the present invention is how to provide a kind of more reasonable effective gas-turbine combustion chamber
Dual fuel nozzle.
(2) technical scheme
In order to solve the above-mentioned technical problem, the invention provides a kind of dual fuel nozzle of gas-turbine combustion chamber, including
Nozzle ring pipeline；The nozzle ring pipeline is internally provided with annular and separation pipeline；It is upper in the annular and separation pipeline
Trip end is provided with annular fuel gas pipeline, and the central fuel pipeline inside the annular fuel gas pipeline；The annular combustion
Feed channel connects a rotary body plug with the downstream of central fuel pipeline；
Upstream end between the nozzle ring pipeline and annular and separation pipeline is provided with outer air cyclone；It is described outer
The inner side of layer of air cyclone, inner air cyclone is provided between annular and separation pipeline and annular fuel gas pipeline；In described,
The fuel gas hollow channel of connection is offered on the blade of outer air cyclone, and is connected with the fuel gas hollow channel
And fuel orifice at an angle to each other；The fuel gas hollow channel and the fuel vent hole opened up on the annular fuel gas pipeline
Connection；
The downstream of the blade of the inner air cyclone or outer air cyclone offers annular slot passage,
And offer fuel oil hole on the central fuel pipeline；The fuel oil hole passes through fuel oil hollow channel and the ring
Shape slot passage connects.
Preferably, the nozzle ring pipeline, annular and separation pipeline, annular fuel gas pipeline and central fuel pipeline are coaxial
Distribution.
Preferably, the rotary body plug is cone, and the plug is coaxially distributed with the central fuel pipeline, and circle
The summit of cone is located at downstream.
Preferably, the annular slot passage originates in the axial location of the fuel oil hollow channel, and extends to institute
State the tail end of blade.
Preferably, the height of the annular slot passage is consistent from upstream end to downstream, is 0.5mm~1mm.
Preferably, the fuel gas hollow channel is located at the upstream of fuel oil hollow channel, and both are parallel to each other.
Preferably, the radial position of the annular slot passage is blade center radial position.
Preferably, the outer air cyclone uses axial blade type structure, and blade is along the nozzle ring pipe
The inner periphery in road is evenly arranged；The outer air cyclone includes 6~8 blades, and eddy flow angle is 0~45 degree.
Preferably, the inner air cyclone uses axial blade type structure, and blade is along the annular and separation pipe
The inner periphery in road is evenly arranged；The inner air cyclone includes 6~8 blades, and eddy flow angle is 0~15 degree.
(3) beneficial effect
Technical scheme has advantages below：The dual fuel nozzle of the gas-turbine combustion chamber of the present invention, inside
The blade downstream of layer of air cyclone or outer air cyclone opens up annular slot passage, and annular slot passage and air
Fuel oil hollow channel connection on the blade of cyclone, to supply fuel oil；Inner air cyclone and outer air eddy flow
The fuel gas hollow pipeline of connection, and the fuel orifice connected with the fuel gas hollow pipeline are offered in device, on blade,
To supply fuel gas.Wherein, the annular slot passage has membranae praeformativa effect, is formed suitably after entering combustion zone for fuel oil
Droplet size and well distributed offer condition.Above-mentioned fuel oil and fuel gas cooperate, and meet under different load to fuel
Requirement；On this basis, air cyclone and double fuel supply cooperate, obtain the distribution of rational nozzle exit velocity and
Exit temperature distribution, the final stability for ensureing burning.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are 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 schematic cross-sectional view 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 schematic cross-sectional view of the dual fuel nozzle of the gas-turbine combustion chamber of the embodiment of the present invention two；
In figure：1st, nozzle ring pipeline；2nd, annular and separation pipeline；3rd, annular fuel gas pipeline；4th, central fuel pipeline；5th, revolve
Turn plug；6th, outer air cyclone；7th, inner air cyclone；8th, fuel gas hollow channel；9th, fuel orifice；10、
Annular slot passage；11a, fuel oil hollow channel；11b, fuel oil hollow channel.
Embodiment
Embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples.Following examples are used for
Illustrate the present invention, but can not be used for limiting the scope of the present invention.
In the description of the invention, it is necessary to explanation, term " " center ", "front", "rear", " interior ", " outer ", " axial direction " etc.
The orientation or position relationship of instruction are based on orientation shown in the drawings or position relationship, are for only for ease of the description present invention and letter
Change description, rather than instruction or imply signified device or element must have specific orientation, with specific azimuth configuration and
Operation, therefore be not considered as limiting the invention.
A kind of dual fuel nozzle of gas-turbine combustion chamber of the present invention, including nozzle ring pipeline 1；The nozzle ring
Pipeline 1 is internally provided with annular and separation pipeline 2, will be separated out multiple gas channels inside nozzle ring pipeline 1；It is the multiple
Gas channel finally converges in the tail end of annular and separation pipeline 2.Upstream end inside the annular and separation pipeline 2 is provided with ring
Shape gas pipeline 3, and the central fuel pipeline 4 inside the annular fuel gas pipeline 3；Wherein, annular fuel gas pipeline 3
Effect is 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 are straight
The downstream axially into nozzle along nozzle is connect, one is connected in the downstream of annular fuel gas pipeline 3 with central fuel pipeline 4
Individual rotary body plug 5.Thus, outer gas flow passage is formed between nozzle ring pipeline 1 and annular and separation pipeline 2, and annular is divided
Internal layer gas channel is formed between pipe road 2, with annular fuel gas pipeline 3 and rotary body plug 5.
Secondly, the upstream end of (namely in outer gas flow passage) is set between nozzle ring pipeline 1 and annular and separation pipeline 2
It is equipped with outer air cyclone 6；The inner side of the outer air cyclone 6, annular and separation pipeline 2 and annular fuel gas pipeline 3 it
Between (namely in internal layer gas channel) it is provided with inner air cyclone 7.Opened on the blade of the inside and outside layer of air cyclone 6
The fuel gas hollow channel 8 being communicated with, and connect with the fuel gas hollow channel 8 and fuel orifice at an angle to each other
9.The fuel gas hollow channel 8 connects with the fuel vent hole opened up on the annular fuel gas pipeline 3.Annular fuel gas pipeline 3
In fuel gas from fuel vent hole incoming fuel gas hollow channel 8, and in the presence of air cyclone, from fuel orifice
9 enter internal layer gas channel and outer gas flow passage.In the present invention, the diameter of the fuel orifice 9 be preferably 0.5mm~
1mm。
In order to realize that double fuel is supplied, the present invention is under the blade of inner air cyclone 7 or outer air cyclone 6
Trip end offers annular slot passage 10；And offer fuel oil hole on the central fuel pipeline 4；The fuel oil hole
Connected by fuel oil hollow channel with the annular slot passage 10.
The difference of position is opened up below according to annular slot passage 10, there is provided two embodiments are sprayed to the double fuel of the present invention
Mouth illustrates.
Embodiment one
Fig. 1 and Fig. 2, the dual fuel nozzle of the gas-turbine combustion chamber of the present embodiment one are referred to, the annular slot leads to
Road 10 is opened in the blade downstream of inner air cyclone 7.Correspondingly, opened up on the blade of inner air cyclone 7
There is fuel oil hollow channel 11a；The annular slot passage 10 connects with the fuel oil hollow channel 11a, and with it is described in
The fuel oil hole connection opened up on heart fuel passage 4.Fuel oil in central fuel pipeline 4 is from fuel oil hole incoming fuel
Oily hollow channel 11a, enter internal layer gas channel then along annular slot passage 10, and enter along internal layer gas channel and spray
The tail end of mouth.
It should be noted that in order to avoid being interfered between annular slot passage 10 and fuel gas hollow channel 8, preferably
The annular slot passage 10 originates in the axial location of the fuel oil hollow channel 11a, and extends to the tail end of blade, this
The blade at place refers to the blade where the annular slot passage 10；And the fuel gas hollow channel 8 is located in fuel oil
Empty passage 11a upstream.Furthermore it is preferred that the fuel gas hollow channel 8 is parallel with the fuel oil hollow channel 11a.
It is emphasized that annular slot passage 10 acts on membranae praeformativa, formed properly after entering combustion zone for fuel oil
Droplet size and well distributed offer condition.Fuel oil after being acted on by membranae praeformativa, from going out for annular slot passage 10
Mouth enters internal layer gas channel.It is preferred that the height of annular slot passage 10 is consistent from front end to rear end, it is 0.5mm~1mm.
In the present embodiment, annular fuel gas pipeline 3, central fuel pipeline 4 and rotary body plug 5 are preferred but are necessarily integrated
Formula structure.The rotary body plug 5 is preferably but not limited to arranged to the good conical plug of water conservancy diversion effect, and the summit of circular cone
Positioned at downstream.In addition, the annular fuel gas pipeline 3, central fuel pipeline 4, rotary body plug 5, annular and separation pipeline 2
Preferably it is coaxially disposed with nozzle ring pipeline 1.
It should be noted that in the present embodiment, the fuel gas hollow channel 8 and fuel that are opened up on the blade of air cyclone
Oily hollow channel 11a quantity, is not limited by the view of the present embodiment.And it is preferred that the outer air cyclone 6, ring
It is integral type structure that shape, which separates pipeline 2 and inner air cyclone 7, so as to be directly integrally formed by casting technique.
In the present embodiment, air divides two layers and enters dual fuel nozzle, and outer layer of the outer air by outer gas flow in logical is empty
Cyclonic current device 6, blended with the fuel gas of penetrating and form strong eddy flow；Inner air is by the inner air in internal layer gas channel
Cyclone 7, blended with the fuel gas of penetrating and form weak eddy flow.Two layer of air converge in the exit of annular and separation pipeline 2, and
Fuel oil after membranae praeformativa is atomized and blended, forms matching two kinds of fuel-air mixing effects of fuel gas and fuel oil.
Wherein, outlet refers to downstream close to the port of combustion zone.
The dual fuel nozzle of the present embodiment, the eddy flow angle of inner air cyclone 7 is smaller, to prevent nozzle interior low speed
The appearance in area；The eddy flow angle of outer air cyclone 6 is larger, ensures the good blending of fuel gas and air.Specifically, internal layer
Air cyclone 7 preferably uses axial blade type structure, and inner periphery of the blade along the annular and separation pipeline 2 is evenly arranged,
Wherein blade quantity is 6~8, and eddy flow angle is 0~15 degree；Outer air cyclone 6 is 0~45 degree except eddy flow angle
In addition, other specification is as inner air eddy flow.The swirl angle that the inside and outside layer gas channel of the present invention passes through air cyclone
The adjustment of degree, coordinate the supply of fuel oil and fuel gas, form rational fuel distribution and VELOCITY DISTRIBUTION.
The dual fuel nozzle of the gas-turbine combustion chamber of the present embodiment, two kinds of fuel of fuel gas and fuel cooperate, full
Requirement of the foot under different load to fuel.Different fuel methods of supplying, fuel gas and combustion are selected under different load requirement
Material oil can simultaneously be supplied and can also be used alone.Into double-layer air-flow passage, (including internal layer gas channel and outer gas flow lead to
Road) in fuel gas and fuel oil, violent blending effect occurs with inside and outside two layers of rotational flow air, fuel oil reaches suitable
Droplet size and distribution, when reaching jet expansion, two kinds of fuel can reach the VELOCITY DISTRIBUTION of suitable fuel distribution and matching.
In the present embodiment, air cyclone and double fuel supply cooperate, and obtain rational nozzle exit velocity distribution and outlet temperature
Degree distribution, the final stability for 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 the difference of embodiment one be that annular slot passage 10 is opened in the tract of the blade of outer air cyclone 6, and
Extend to the tail end of the place blade of annular slot passage 10.Correspondingly, inside, on the blade of outer air cyclone
The fuel oil hollow channel 11b of connection is offered, and the fuel oil hollow channel 11b connects with the annular slot passage 10
It is logical, so as to fuel oil finally be led among annular slot passage 10.Two other structures of the present embodiment and principle, all and
Embodiment one is identical, and here is omitted.
In above-described embodiment, the major function to be realized according to dual fuel nozzle of position that opens up of annular slot passage 10 is entered
Row setting.When nozzle major function is used for flame stabilization, then the annular slot passage 10 is opened in inner air eddy flow
The blade interior of device 7；When nozzle major function be used for ensure between burning load and burner inner liner join when needing of flame, then will
The annular slot passage 10 is opened in the blade interior of outer air cyclone 6.
Embodiment of above is merely to illustrate the present invention, rather than limitation of the present invention.Although with reference to embodiment to this hair
It is bright to be described in detail, it will be understood by those within the art that, to technical scheme carry out it is various combination,
Modification or equivalent substitution, without departure from the spirit and scope of technical solution of the present invention, the right that all should cover in the present invention is wanted
Ask among scope.
Claims (9)
1. a kind of dual fuel nozzle of gas-turbine combustion chamber, it is characterised in that including nozzle ring pipeline；The nozzle ring
Pipeline is internally provided with annular and separation pipeline；Upstream end in the annular and separation pipeline is provided with annular fuel gas pipeline, with
And the central fuel pipeline inside the annular fuel gas pipeline；The downstream of the annular fuel gas pipeline and central fuel pipeline
One rotary body plug of end connection；
Upstream end between the nozzle ring pipeline and annular and separation pipeline is provided with outer air cyclone；The outer layer is empty
The inner side of cyclonic current device, inner air cyclone is provided between annular and separation pipeline and annular fuel gas pipeline；The inside and outside layer
The fuel gas hollow channel of connection is offered on the blade of air cyclone, and is connected with the fuel gas hollow channel and mutually
Angled fuel orifice；The fuel gas hollow channel connects with the fuel vent hole opened up on the annular fuel gas pipeline
It is logical；
The downstream of the blade of the inner air cyclone or outer air cyclone offers annular slot passage, and institute
State and fuel oil hole is offered on central fuel pipeline；The fuel oil hole passes through fuel oil hollow channel and the annulus
Groove passage connects.
2. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, it is characterised in that the nozzle ring pipe
Road, annular and separation pipeline, annular fuel gas pipeline and central fuel pipeline are coaxially distributed.
3. the dual fuel nozzle of gas-turbine combustion chamber according to claim 2, it is characterised in that the rotary body plug
For cone, the plug is coaxially distributed with the central fuel pipeline, and the summit of circular cone is located at downstream.
4. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, it is characterised in that the annular slot leads to
Road originates in the axial location of the fuel oil hollow channel, and extends to the tail end of the blade.
5. the dual fuel nozzle of gas-turbine combustion chamber according to claim 4, it is characterised in that the annular slot leads to
The height in road is consistent from upstream end to downstream, is 0.5mm~1mm.
6. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, it is characterised in that the fuel gas is hollow
Passage is located 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, it is characterised in that the annular slot leads to
The radial position in road is inner air swirler blades or outer air swirler blades radially position.
8. the dual fuel nozzle of gas-turbine combustion chamber as claimed in any of claims 1 to 7, it is characterised in that
The outer air cyclone uses axial blade type structure, and inner periphery uniform cloth of the blade along the nozzle ring pipeline
Put；The outer air cyclone includes 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, it is characterised in that
The inner air cyclone uses axial blade type structure, and inner periphery uniform cloth of the blade along the annular and separation pipeline
Put；The inner air cyclone includes 6~8 blades, and eddy flow angle is 0~15 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410843051.0A CN104566473B (en) | 2014-12-30 | 2014-12-30 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Publication Number | Publication Date |
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| CN104566473A CN104566473A (en) | 2015-04-29 |
| CN104566473B true CN104566473B (en) | 2018-02-09 |
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| CN201410843051.0A Active CN104566473B (en) | 2014-12-30 | 2014-12-30 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107620979B (en) * | 2017-09-05 | 2019-12-06 | 中国联合重型燃气轮机技术有限公司 | Gas turbine |
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 |
-
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 |
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Effective date of registration: 20200121 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. |