CN104566469B - 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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- CN104566469B CN104566469B CN201410843615.0A CN201410843615A CN104566469B CN 104566469 B CN104566469 B CN 104566469B CN 201410843615 A CN201410843615 A CN 201410843615A CN 104566469 B CN104566469 B CN 104566469B
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Abstract
The present invention relates to gas turbine technology fields, provide a kind of dual fuel nozzle of gas-turbine combustion chamber.The nozzle opens up annular slot channel inside the tube wall of annular and separation pipeline, and is connected to the fuel oil hollow channel opened up on the blade of inner air cyclone, to supply fuel oil；The fuel gas hollow pipeline of connection is offered in inner air cyclone and outer air cyclone, on blade, and the fuel injection hole being connected to the fuel gas hollow pipeline, to supply fuel gas.Wherein, the annular slot channel has membranae praeformativa effect, enters behind combustion zone for fuel oil and forms suitable droplet size and good distribution provides condition.Above-mentioned fuel oil and fuel gas cooperate, and meet under different load to the requirement of fuel；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 nozzles 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 that there are generating efficiencies is low for this traditional generation technology, pollutant emission height (especially NOx emission) expends freshwater resources
The shortcomings of more.It is the gas turbine power generation technology of fuel as one of clean energy technology using natural gas, can generates electricity meeting
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 and stablized
Flow field and combustion field.Dual fuel nozzle requires to burn using different fuel under different loads, 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 is installed the form of centrifuging temperature nozzle 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 certain loading condictions is not so good as the effect of pre- membrane type nozzle
It is ideal：The distribution of centrifuging temperature port fuel is spread around centered on nozzle center region, needs to make by atomizer
Fuel oil reaches suitable droplet size and distribution before combustion, and the difficulty of atomizer to nozzle center's bleed is higher.
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, to
Tissue burns and controls pollutant emission.
Invention content
(1) technical problems to be solved
The technical problem to be solved in the present invention is to how provide a kind of more reasonable effective gas-turbine combustion chamber
Dual fuel nozzle.
(2) technical solution
In order to solve the above technical problem, the present invention provides a kind of dual fuel nozzles 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 inside of layer air cyclone, is provided with inner air cyclone 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 to the fuel gas hollow channel
And fuel injection hole at an angle to each other；The fuel vent hole opened up on the fuel gas hollow channel and the annular fuel gas pipeline
Connection；
Annular slot channel is offered inside the tube wall of the annular and separation pipeline, and in the inner air cyclone
Fuel oil hollow channel is offered on blade；The annular slot channel and the fuel oil hollow channel and the center
The fuel oil hole opened up on fuel passage is sequentially communicated.
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 vertex of cone is located at downstream.
Preferably, the annular slot channel originates in the axial position of the fuel oil hollow channel, and extends to institute
State the tail end of annular and separation pipeline.
Preferably, the height in the annular slot channel 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 the two is parallel to each other.
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.
Preferably, 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.
Preferably, the inner air cyclone includes 6~8 blades, and eddy flow angle is 0~15 degree.
(3) advantageous effect
Technical scheme of the present invention has the following advantages：The dual fuel nozzle of the gas-turbine combustion chamber of the present invention, in ring
Shape separates opens up annular slot channel inside the tube wall of pipeline, and in the fuel oil that is opened up on the blade of inner air cyclone
Empty channel connection, to supply fuel oil；The combustion of connection is offered in inner air cyclone and outer air cyclone, on blade
Gas hollow pipeline is expected, and the fuel injection hole being connected to the fuel gas hollow pipeline, to supply fuel gas.Wherein, the ring
Shape slot channel has membranae praeformativa effect, enters behind combustion zone for fuel oil and forms suitable droplet size and good distribution provides
Condition.Above-mentioned fuel oil and fuel gas cooperate, and meet under different load to the requirement of fuel；On this basis, air
Cyclone and double fuel supply cooperate, and obtain rational nozzle exit velocity distribution and Exit temperature distribution, final to ensure
The stability of burning.
Description of the drawings
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
Obtain other attached drawings according to these attached 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 schematic cross-sectional view 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, it revolves
Turn plug；6, outer air cyclone；7, inner air cyclone；8, fuel gas hollow channel；9, fuel injection hole；10、
Annular slot channel；11, fuel oil hollow channel.
Specific implementation mode
Embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples.Following embodiment is used for
Illustrate the present invention, but cannot be used for limiting the scope of the invention.
In the description of the present invention, it should be noted that term "center", "front", "rear", "inner", "outside", " axial direction " etc.
The orientation or positional relationship of instruction is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of the description present invention and letter
Change description, do not indicate or imply the indicated device or element must have a particular 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 embodiment, including nozzle ring pipeline 1；The annular spray
Mouth 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 described more
A 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
Annular fuel gas pipeline 3, and the central fuel pipeline 4 inside the annular fuel gas pipeline 3；Wherein, annular fuel gas pipeline 3
Effect be to input fuel gas, the effect of central fuel pipeline 4 is to input fuel oil.In order to avoid fuel gas and fuel oil
Directed along the downstream axially into nozzle of nozzle, connected with the downstream of central fuel pipeline 4 in annular fuel gas pipeline 3
One rotary body plug 5.Outer gas flow channel is formed between nozzle ring pipeline 1 and annular and separation pipeline 2 as a result, and it is annular
Separate and forms internal layer gas channel between pipeline 2, with annular fuel gas pipeline 3 and rotary body plug 5.
Secondly, the upstream end in (namely in outer gas flow channel) is set between nozzle ring pipeline 1 and annular and separation pipeline 2
It is equipped with outer air cyclone 6；The inside 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.It is opened on the blade of the inside and outside layer air cyclone 6
Fuel gas hollow channel 8 equipped with connection, and be connected to the fuel gas hollow channel 8 and fuel injection hole at an angle to each other
9.The fuel gas hollow channel 8 is connected to the fuel vent hole opened up on the annular fuel gas pipeline 3.Annular fuel gas pipeline 3
In fuel gas enter fuel gas hollow channel 8 from fuel vent hole, and under the action of air cyclone, from fuel injection hole
9 enter internal layer gas channel and outer gas flow channel.In the present embodiment, the diameter of the fuel injection hole 9 be preferably 0.5mm~
1mm。
In order to realize that double fuel is supplied, annular slot channel 10 is offered inside the tube wall of the annular and separation pipeline 2, and
Fuel oil hollow channel 11 is offered on the blade of the inner air cyclone 7；The annular slot channel 10 with it is described
Fuel oil hollow channel 11 is connected to, and is connected to the fuel oil hole opened up on the central fuel pipeline 4.Central fuel pipeline
Fuel oil in 4 enters fuel oil hollow channel 11 from fuel oil hole, then along annular slot channel 10 from annular and separation
The downstream of pipeline 2 enters the tail end of nozzle.It should be noted that in order to avoid annular slot channel 10 and fuel gas are hollow logical
It is interfered between road 8, preferably the annular slot channel 10 originates in the axial position of the fuel oil hollow channel 11, and
Extend to the tail end of the annular and separation pipeline 2；And the fuel gas hollow channel 8 is located at the upper of fuel oil hollow channel 11
Trip.Furthermore it is preferred that the fuel gas hollow channel 8 is parallel with the fuel oil hollow channel 11.
It is emphasized that annular slot channel 10 has membranae praeformativa effect, formed properly after entering combustion zone for fuel oil
Droplet size and good distribution provide condition.Fuel oil after being acted on by membranae praeformativa, from going out for annular slot channel 10
Mouth enters in double-layer air-flow channel.It is preferred that the height in annular slot channel 10 is consistent from front end to rear end, be 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 excellent
It selects but is necessarily an integral structure.The rotary body plug 5 is preferably but not limited to set as the good cone of water conservancy diversion effect
Plug, and the vertex of circular cone is located at downstream.In addition to this, the annular fuel gas pipeline 3, central fuel pipeline 4, rotary body are stifled
First 5, annular and separation pipeline 2 and the preferred coaxial arrangement of 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
The quantity of oily hollow channel 11 is not limited by the view of the present embodiment.And it is preferred that the outer air cyclone 6, ring
Shape separates pipeline 2 and inner air cyclone 7 is an integral structure, 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 air is empty by outer layer of the outer gas flow in logical
Cyclonic current device 6 blends with the fuel gas of penetrating and forms strong eddy flow；Inner air is by the inner air in internal layer gas channel
Cyclone 7 blends with the fuel gas of penetrating and forms weak eddy flow.Two layers of air converges in the exit of annular and separation pipeline 2, and
Fuel oil after membranae praeformativa is atomized and is blended, matching two kinds of fuel-air mixing effects of fuel gas and fuel oil are formed.
Wherein, outlet refers to port of the downstream close to combustion zone.
The eddy flow angle of the dual fuel nozzle of the present embodiment, 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, blade to be evenly arranged along the inner periphery of the annular and separation pipeline 2,
Wherein blade quantity is 6~8, and eddy flow angle is 0~15 degree；Outer air cyclone 6 is 0~45 degree in addition to eddy flow angle
In addition, other parameters are 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 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, two kinds of fuel of fuel gas and fuel cooperate, full
Foot is under different load to the requirement of fuel.Different fuel methods of supplying, fuel gas and combustion are selected under different load requirement
Material oil can be supplied and can also be used alone simultaneously.Into double-layer air-flow channel, (including internal layer gas channel and outer gas flow are logical
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 suitable fuel distribution and matched VELOCITY DISTRIBUTION.
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 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 of ordinary skill in the art that, to technical scheme of the present invention carry out it is various combination,
Modification or equivalent replacement, without departure from the spirit and scope of technical solution of the present invention, the right that should all cover in the present invention is wanted
It asks in range.
Claims (10)
1. a kind of dual fuel nozzle of gas-turbine combustion chamber, which is characterized 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 inside of cyclonic current device is provided with inner air cyclone 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 to the fuel gas hollow channel and mutually
Angled fuel injection hole；The fuel vent hole opened up on the fuel gas hollow channel and the annular fuel gas pipeline connects
It is logical；
Annular slot channel is offered inside the tube wall of the annular and separation pipeline, and in the blade of the inner air cyclone
On offer fuel oil hollow channel；The annular slot channel and the fuel oil hollow channel and the central fuel
The fuel oil hole opened up on pipeline is sequentially communicated.
2. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, which is characterized 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, which is characterized in that the rotary body plug
For cone, the rotary body plug is coaxially distributed with the central fuel pipeline, and the vertex of circular cone is located at downstream.
4. the dual fuel nozzle of gas-turbine combustion chamber according to claim 1, which is characterized in that the annular slot is logical
Road originates in the axial position of the fuel oil hollow channel, and extends to the tail end of the annular and separation pipeline.
5. the dual fuel nozzle of gas-turbine combustion chamber according to claim 4, which is characterized in that the annular slot is logical
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, which is characterized in that the fuel gas is hollow
Channel is located at the upstream of fuel oil hollow channel, and the two is parallel to each other.
7. the dual fuel nozzle of gas-turbine combustion chamber as claimed in any of claims 1 to 6, which is characterized in that
The outer air cyclone uses axial blade type structure, and blade is along the uniform cloth of inner periphery of the nozzle ring pipeline
It sets.
8. the dual fuel nozzle of gas-turbine combustion chamber according to claim 7, which is characterized in that the outer air rotation
It includes 6~8 blades to flow device, 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, which is characterized in that
The inner air cyclone uses axial blade type structure, and blade is along the uniform cloth of inner periphery of the annular and separation pipeline
It sets.
10. the dual fuel nozzle of gas-turbine combustion chamber according to claim 9, which is characterized in that 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 |
|---|---|---|---|
| CN201410843615.0A CN104566469B (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 |
|---|---|---|---|
| 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 CN104566469A (en) | 2015-04-29 |
| CN104566469B true CN104566469B (en) | 2018-09-14 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017116266A1 (en) * | 2015-12-30 | 2017-07-06 | General Electric Company | Liquid fuel nozzles for dual fuel combustors |
| 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 |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0905443A3 (en) * | 1997-09-30 | 1999-06-23 | General Electric Company | Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine |
| US7165405B2 (en) * | 2002-07-15 | 2007-01-23 | Power Systems Mfg. Llc | Fully premixed secondary fuel nozzle with dual fuel capability |
| CN101080596A (en) * | 2005-06-06 | 2007-11-28 | 三菱重工业株式会社 | Gas turbine combustor |
| JP2010255944A (en) * | 2009-04-27 | 2010-11-11 | Kawasaki Heavy Ind Ltd | Fuel spray apparatus for gas turbine engine |
| CN103672969A (en) * | 2013-12-13 | 2014-03-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Dual-fuel combustion chamber nozzle of combustion gas turbine |
| CN203586283U (en) * | 2013-07-10 | 2014-05-07 | 辽宁省燃烧工程技术中心（有限公司） | Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel |
| CN104075344A (en) * | 2013-03-25 | 2014-10-01 | 通用电气公司 | Fuel nozzle system and method for starting and operating gas turbine by using low-heat value fuel |
| CN104110699A (en) * | 2014-07-09 | 2014-10-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Premixing nozzle of gas turbine combustion chamber |
| CN204438194U (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 CN201410843615.0A patent/CN104566469B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0905443A3 (en) * | 1997-09-30 | 1999-06-23 | General Electric Company | Dual-fuel nozzle for inhibiting carbon deposition onto combustor surfaces in a gas turbine |
| US7165405B2 (en) * | 2002-07-15 | 2007-01-23 | Power Systems Mfg. Llc | Fully premixed secondary fuel nozzle with dual fuel capability |
| CN101080596A (en) * | 2005-06-06 | 2007-11-28 | 三菱重工业株式会社 | Gas turbine combustor |
| JP2010255944A (en) * | 2009-04-27 | 2010-11-11 | Kawasaki Heavy Ind Ltd | Fuel spray apparatus for gas turbine engine |
| CN104075344A (en) * | 2013-03-25 | 2014-10-01 | 通用电气公司 | Fuel nozzle system and method for starting and operating gas turbine by using low-heat value fuel |
| CN203586283U (en) * | 2013-07-10 | 2014-05-07 | 辽宁省燃烧工程技术中心（有限公司） | Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel |
| CN103672969A (en) * | 2013-12-13 | 2014-03-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Dual-fuel combustion chamber nozzle of combustion gas turbine |
| CN104110699A (en) * | 2014-07-09 | 2014-10-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Premixing nozzle of gas turbine combustion chamber |
| CN204438194U (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: 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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