CN206001524U - A kind of combustor radial direction two-stage swirl nozzle - Google Patents
A kind of combustor radial direction two-stage swirl nozzle Download PDFInfo
- Publication number
- CN206001524U CN206001524U CN201620999380.9U CN201620999380U CN206001524U CN 206001524 U CN206001524 U CN 206001524U CN 201620999380 U CN201620999380 U CN 201620999380U CN 206001524 U CN206001524 U CN 206001524U
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- Prior art keywords
- fuel
- nozzle
- peripheral
- radial
- swirl
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- 230000002093 peripheral Effects 0.000 claims abstract description 69
- 238000009826 distribution Methods 0.000 claims description 10
- 239000011148 porous material Substances 0.000 claims description 6
- 230000001413 cellular Effects 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 4
- 238000005507 spraying Methods 0.000 claims description 2
- 238000004140 cleaning Methods 0.000 abstract description 2
- 239000003345 natural gas Substances 0.000 abstract description 2
- 239000007788 liquid Substances 0.000 abstract 1
- 238000002485 combustion reaction Methods 0.000 description 27
- 239000007921 spray Substances 0.000 description 12
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitrogen oxide Substances 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- 238000011105 stabilization Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N carbon Chemical compound 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[C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 230000001808 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006011 modification reaction Methods 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Abstract
The utility model discloses a kind of oligosaprobic combustor radial direction two-stage swirl nozzle, it includes the center fuel passage of radially coaxial arrangement, peripheral fuel channel and annular air channel, and annular air channel is split plate and is separated into central air passage and peripheral air passage；It is respectively disposed with Swirl device and peripheral swirl-flow devices in central air passage and peripheral air passage；Center fuel channel outlet arranges premix chamber, ensure that the stability of burning and good discharge performance by this nozzle arrangements, using the such as more gaseous state of cleaning or the liquid fuel such as natural gas, and can have the advantages that working condition is easily adjusted.
Description
Technical field
This utility model is related to field of combustion technology, more particularly to a kind of oligosaprobic combustor radial direction two-stage eddy flow spray
Mouth.
Background technology
With the attention to environmental protection problem for the whole world, various countries discharge to the nitrogen oxides (NOx) of field of combustion technology
Require more and more stricter.
In order to reach the purpose of low NOx drainage, premixed combustion technology is widely adopted.For reaching low NOx, premixed combustion
The many good mixing to realize fuel and oxidant using eddy flow hybrid technology in room, but it is operate on the combustor pole of this state
It easily produces combustion instability phenomenon.For solving this problem, engineering is generally arranged using sacrifice the compromise of NOx emission performance
Apply, that is, utilize good stability but the diffusion flame of NOx emission poor performance, to stablize premixed flame.In general, for diffusion combustion
The fuel quantity accounting burnt is bigger, and burning is more stable, but NOx emission also increases therewith.Such burning tissues form is it is desirable to burn
Exercise due diligence diffusion flame, when carrying out the design of low pollution combustor nozzle, is answered to NOx emission with to flame stabilization ability in room
Contradiction.
In the current energy resource structure of China, most shares are occupied using traditional coal combustion technology.But this biography
There are the shortcomings of efficiency is low, and pollutant emission is high (especially NOx emission), consuming freshwater resources are many in system technology.With natural gas etc.
For fuel combustion technology as one of clean energy technology, pollution can be effectively reduced while meeting combustion needs
The discharge of thing.Equally, the design of combustion chamber burner is particularly important for tissue burning, reduction pollutant emission among these.
In combustor, fuel and air realize premixing and the change of velocity profile by nozzle, reach conjunction in jet expansion
The VELOCITY DISTRIBUTION of reason, and mates rational fuel-air mixture example, enters combustor tissue burning, formed stable flow field and
Combustion field.In prior art, design form to combustion chamber burner, such as mention in patent CN103542427 can adopt many
Individual combustion path, each combustion path utilizes at least one premix burner, to solve the operation interference of adjacent premix burner
Problem, individually adjusts load and the probability of fuel type to give each combustion path, but actually this implementation knot
Structure is complicated, adjusts difficulty also than larger.
Content of the invention
(1) goal of the invention
Provide a kind of combustor radial direction two-stage swirl nozzle, contradiction between NOx emission and flame stabilization for the solution
Technical problem is in prior art.
(2) technical scheme
In order to solve above-mentioned technical problem, this utility model provides a kind of combustor radial direction two-stage swirl nozzle, and it is special
Levy including：Radially coaxially arranged center fuel passage, peripheral fuel channel, annular air channel；Center fuel delivery pipe,
Central fuel nozzle；Peripheral fuel -supply pipe, peripheral fuel nozzle；Outer nozzle wall；
Described outer nozzle wall is the outer wall of described two-stage swirl nozzle；
It is coaxially disposed inside described annular air channel and described annular air channel is separated into central air passage with outward
Enclose the flow distribution plate of air duct；
Described center fuel delivery pipe connects described central fuel nozzle；Described center fuel delivery pipe is sprayed with center fuel
The region that mouth limits is as described center fuel passage；Described central fuel nozzle end is provided with center fuel spray-hole；
Described periphery fuel -supply pipe connects described periphery fuel nozzle；Described periphery fuel -supply pipe and peripheral fuel spray
The region that mouth limits is as described periphery fuel channel；Described periphery fuel nozzle is arranged on described flow distribution plate and described outer nozzle wall
Between area, its end is provided with peripheral fuel orifice；
It is disposed with described Swirl device in described central air passage；
It is disposed with described periphery swirl-flow devices in described peripheral air passage；
Setting premix chamber inside described two-stage swirl nozzle, for the fuel that sprays described center fuel spray-hole and warp
The air mixing of the described central air passage of described Swirl device eddy flow.
Further, also include the first demarcation strip, the second demarcation strip being arranged on described central air passage region；
Described first demarcation strip is arranged on the radial outside of described central fuel nozzle；Described second demarcation strip is arranged on institute
State the radial outside of the first demarcation strip；
Described first demarcation strip, the second demarcation strip form the region for limiting described premix chamber；
On described first demarcation strip, the first discharge orifice is set；
On described second demarcation strip, the second discharge orifice is set.
Further, also include being provided with the first plate washer positioned at the first discharge orifice axial downstream, be provided with positioned at second
Second plate washer of discharge orifice axial downstream.
Further, the peripheral fuel injection hole site on described peripheral fuel nozzle can be radial inward, radially
Outwardly, circumference combines towards downstream or a few person.
Further, described peripheral swirl-flow devices can be axial rotational flow or radial vortex, and form can be vane type
Or cellular type of cutting sth. askew, eddy flow angular range be 0～15 degree.
Further, described Swirl device to be axial rotational flow or radial vortex, form can be vane type or
Cut sth. askew cellular type.
Further, the first described discharge orifice is evenly distributed, pore size is Φ 2～Φ 4mm.
Further, the second described discharge orifice is evenly distributed, pore size is Φ 2～Φ 4mm.
Further, described central air passage and peripheral air passage current limliting area are 1 than scope：(7.5～
9.5).
Further, the first described discharge orifice and the second earial drainage hole area are 1～5 than scope.
(3) beneficial effect
This technical scheme swirl-flow devices radially divides two stage arrangement it is ensured that while mixing effect, coupling jet expansion
VELOCITY DISTRIBUTION.By two-stage swirl-flow devices ensure nozzle exit velocity be reasonably distributed, fuel-air even blend, rationally control combustion
Burn region, maintain combustion chamber flow field structure, thus ensureing the stability of burning and good discharge performance.
Center fuel passage of the present utility model can by center fuel spray regime coordinate Swirl device and
Premix chamber, makes center and periphery just decouple from flowing, realizes the combustion mode of injection diffusion combustion+swirl flame, reaching can
Reduce the effect of discharge by igniting and maximum.
Peripheral swirl-flow devices can enhanced fuel gas and air eddy flow mixing, reduced by the premix of fuel and air
Discharge.
The structure of central fuel nozzle, Swirl device and premix chamber composition can also reduce central passage and periphery is led to
Influencing each other between road, it is to avoid peripheral channel is interfered, the peripheral annular simultaneously being formed between flow distribution plate and outer nozzle wall face
Gas channel, limits the air velocity of peripheral annular air duct it is ensured that outer circumferential side gas velocity degree type is distributed with aisle spare, from
And continual and steady burning is not it is ensured that whole combustor stops working during adjusting.
Can be used as cooling air cooling premix chamber wall via the air that discharge orifice sprays, and this portion gas is acceptable
Realize anti-backfire technique effect, further enhance combustion stability.
Central fuel nozzle and peripheral fuel nozzle are individually adjusted, and coordinate the adjustment of each fuel injection hole site and size,
Broader design space can be provided for nozzle, meet the needs that different fuel and air blend.
Brief description
Fig. 1 is this utility model structural representation；
Fig. 2 is the partial enlarged drawing of this utility model structural representation.
In figure mark is described as follows：
1：Center fuel passage；2：Peripheral fuel channel；3：Annular air channel；4：Flow distribution plate；5：Central air passage；
6：Peripheral air passage；7：Center fuel delivery pipe；8：Central fuel nozzle；9：Center fuel spray-hole；10：Peripheral fuel is defeated
Send pipe；11：Peripheral fuel nozzle；12：Peripheral fuel orifice；13：Outer nozzle wall；14：Swirl device；15：Outer spinning
Stream device；16：Premix chamber；17：First demarcation strip；18：Second demarcation strip；19：First discharge orifice；20：Second discharge orifice；21：
First plate washer；22：Second plate washer.
Specific embodiment
Below in conjunction with the accompanying drawings principle of the present utility model, structure and specific embodiment are described further.Below
Example is used for this utility model is described, but is not limited to scope of the present utility model.
In description of the present utility model, it should be noted that term " " center ", " peripheral ", " interior ", " outward " " downstream " etc.
The orientation indicating or position relationship are based on orientation shown in the drawings or position relationship, are for only for ease of description this utility model
Describe with simplifying, rather than the device of instruction or hint indication or element must have specific orientation, with specific orientation structure
Make and operate, therefore it is not intended that to restriction of the present utility model.Additionally, term " first ", " second " etc. are only used for describing
Purpose, and it is not intended that indicating or hint relative importance.
As shown in figure 1, a kind of combustor radial direction two-stage swirl nozzle designing for this utility model, this nozzle is included along footpath
To coaxially arranged center fuel passage 1, peripheral fuel channel 2, annular air channel 3；Center fuel delivery pipe 7, center combustion
Material nozzle 8；Peripheral fuel -supply pipe 10, peripheral fuel nozzle 11；Outer nozzle wall 13；Outer nozzle wall 13 is described two-stage eddy flow spray
The outer wall of mouth；It is coaxially disposed inside annular air channel 3 and described annular air channel 3 is separated into central air passage 5 with outward
Enclose the flow distribution plate 4 of air duct 6；Center fuel delivery pipe 7 connects described central fuel nozzle 8；Described center fuel delivery pipe 7
The region limiting with central fuel nozzle 8 is as described center fuel passage 1；Described central fuel nozzle 8 end is provided with center
Fuel orifice 9；Peripheral fuel -supply pipe 10 connects described periphery fuel nozzle 11；Peripheral fuel -supply pipe 10 and peripheral fuel
The region that nozzle 11 limits is as described periphery fuel channel 2；Peripheral fuel nozzle 11 is arranged on described flow distribution plate 4 and described nozzle
Between outer wall 13, its end is provided with peripheral fuel orifice 12；It is disposed with described Swirl device in central air passage 5
14；It is disposed with described periphery swirl-flow devices 15 in peripheral air passage 6；Setting premix chamber 16 inside swirl nozzle, for by institute
State the fuel of center fuel spray-hole 9 ejection and the sky of the described central air passage 5 through described Swirl device 14 eddy flow
Gas mixes.
Preferably, first demarcation strip 17 in central air passage 5 region, the second demarcation strip 18；First demarcation strip 17 is arranged
Radial outside in described central fuel nozzle 8；Second demarcation strip 18 is arranged on the radial outside of described first demarcation strip 17；The
One demarcation strip 17, the second demarcation strip 18 form the region for limiting described premix chamber 16；First is arranged on first demarcation strip 17
Discharge orifice 19；Second discharge orifice 20 is arranged on the second demarcation strip 18.
Preferably, nozzle also includes being provided with the first plate washer 21 positioned at the first discharge orifice 19 axial downstream, is provided with position
The second plate washer 22 (partial enlarged drawing referring in Fig. 1) in the second discharge orifice 20 axial downstream.
Preferably, peripheral fuel orifice 12 position on peripheral fuel nozzle 11 can be radial inward, radially,
Circumference combines towards downstream or a few person.
Preferably, peripheral swirl-flow devices 15 can be axial rotational flow or radial vortex, and form can be vane type or cut sth. askew
Cellular type, eddy flow angular range is 0～15 degree.
Preferably, to be axial rotational flow or radial vortex, form can be vane type or hole of cutting sth. askew to Swirl device 14
Formula.
Preferably, the first discharge orifice 19 is evenly distributed, pore size is Φ 2～Φ 4mm.
Preferably, the second discharge orifice 20 is evenly distributed, pore size is Φ 2～Φ 4mm.
Preferably, central air passage 5 and peripheral air passage 6 area are 1 than scope：(7.5～9.5).
Preferably, the first discharge orifice 19 and the second discharge orifice 20 area are 1～5 than scope.
Operation principle of the present utility model is as follows：
Center fuel approach center fuel passage 1, reaches central fuel nozzle 8 by center fuel delivery pipe 7, is fired by center
Center fuel spray-hole 9 on material nozzle 8 sprays；Peripheral fuel pathways periphery fuel channel 2, by peripheral fuel -supply pipe 10 to
Reach peripheral fuel nozzle 11, sprayed by peripheral fuel orifice 12；
Air enters annular air channel 3, is split plate 4 and shunts, is partly into peripheral air passage 6, remaining entrance
Central air passage 5；
Enter the fuel that the air of peripheral air passage 6 is sprayed with peripheral fuel orifice 12, through peripheral swirl-flow devices 11
Fired downstream is entered after strengthening blending；
The air entering central air passage 5 is then further divided into several parts, and a part is through Swirl device 14 and center combustion
The fuel that material nozzle 8 sprays enters downstream together and carries out ignition, and a part enters downstream by the first Cooling Holes 19, a part
Downstream is entered by the second discharge orifice 20；
Via discharge orifice spray air can as cooling air cooling be used for limit premix chamber 16 the first demarcation strip 17,
Second demarcation strip 18 wall, and this part cool down gas can be spaced apart central passage and peripheral channel air current flow so as to
It does not interfere with each other, the first plate washer 21 of additional setting and the second plate washer 22 can strengthen this technique effect.In addition, this structure sets
Meter can also realize anti-backfire technique effect using this partial air, further enhances combustion stability.
Peripheral channel fuel, central passage fuel can be adjusted respectively, compares demand to meet different combustion equivalents.
Operation principle of the present utility model is as follows：
Center fuel approach center fuel passage 1, reaches central fuel nozzle 8 by center fuel delivery pipe 7, is fired by center
Center fuel spray-hole 9 on material nozzle 8 sprays；Peripheral fuel pathways periphery fuel channel 2, by peripheral fuel -supply pipe 10 to
Reach peripheral fuel nozzle 11, sprayed by peripheral fuel orifice 12；
Air enters annular air channel 3, is split plate 4 and shunts, is partly into peripheral air passage 6, remaining entrance
Central air passage 5；
Enter the fuel that the air of peripheral air passage 6 is sprayed with peripheral fuel orifice 12, through peripheral swirl-flow devices 11
Fired downstream is entered after strengthening blending；
The air entering central air passage 5 is then further divided into several parts, and a part is through Swirl device 14 and center combustion
The fuel that material nozzle 8 sprays enters premix chamber 16 together and carries out ignition, and a part enters downstream by the first discharge orifice 19, and one
Part enters downstream by the second discharge orifice 20；
Via discharge orifice spray air can as cooling air cooling be used for limit premix chamber 16 the first demarcation strip 17,
Second demarcation strip 18 wall, in addition, this structure design can also realize anti-backfire technology effect using this part earial drainage air
Really, further enhance combustion stability.
Peripheral channel, the fuel of central passage blends the work process of burning with air, is divided by this structure of premix chamber 16
Separate to come, the first demarcation strip 17 limiting premix chamber 16 is separated in solid form with the second demarcation strip 18, the first demarcation strip 17
Can be with gas with the earial drainage air spraying in the first discharge orifice 19 of setting on the second demarcation strip 18 and the second discharge orifice 20
Form is spaced apart the air current flow of central passage and peripheral channel so as to not interfere with each other, the first discharge orifice 19 and the second discharge orifice
20 and first plate washer 21 coordinate with the second plate washer 22, increase air-flow radial flow direction, strengthening separate this technique effect.
Peripheral channel fuel, central passage fuel can be adjusted respectively, compares demand to meet different combustion equivalents.
Finally it should be noted that：Above example only in order to the technical solution of the utility model to be described, is not intended to limit；
Although being described in detail to this utility model with reference to the foregoing embodiments, it will be understood by those within the art that：
It still can be modified to the technical scheme described in foregoing embodiments, or wherein some technical characteristics are carried out etc.
With replacement；And these modifications or replacement, do not make the essence of appropriate technical solution depart from this utility model each embodiment technology
The spirit and scope of scheme.
Claims (10)
1. a kind of combustor radial direction two-stage swirl nozzle, its feature includes：Radially coaxially arranged center fuel passage (1),
Peripheral fuel channel (2), annular air channel (3)；Center fuel delivery pipe (7), central fuel nozzle (8)；Peripheral fuel is defeated
Send pipe (10), peripheral fuel nozzle (11)；Outer nozzle wall (13)；
Described outer nozzle wall (13) is the outer wall of described two-stage swirl nozzle；
It is coaxially disposed inside described annular air channel (3) and described annular air channel (3) is separated into central air passage (5)
Flow distribution plate (4) with peripheral air passage (6)；
Described center fuel delivery pipe (7) connects described central fuel nozzle (8)；Described center fuel delivery pipe (7) and center
The region that fuel nozzle (8) limits is as described center fuel passage (1)；Described central fuel nozzle (8) end is provided with center
Fuel orifice (9)；
Described periphery fuel -supply pipe (10) connects described periphery fuel nozzle (11)；Described periphery fuel -supply pipe (10) is with outward
Enclose the region that fuel nozzle (11) limits as described periphery fuel channel (2)；Described periphery fuel nozzle (11) is arranged on described
Between flow distribution plate (4) and described outer nozzle wall (13), its end is provided with peripheral fuel orifice (12)；
It is disposed with described Swirl device (14) in described central air passage (5)；
It is disposed with described periphery swirl-flow devices (15) in described peripheral air passage (6)；
Setting premix chamber (16) inside described two-stage swirl nozzle, for the fuel spraying described center fuel spray-hole (9)
Mix with the air of the described central air passage (5) through described Swirl device (14) eddy flow.
2. as claimed in claim 1 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that also include be arranged on described
First demarcation strip (17) in central air passage (5) region, the second demarcation strip (18)；
Described first demarcation strip (17) is arranged on the radial outside of described central fuel nozzle (8)；Described second demarcation strip (18)
It is arranged on the radial outside of described first demarcation strip (17)；
Described first demarcation strip (17), the second demarcation strip (18) form the region for limiting described premix chamber (16)；
Described first demarcation strip (17) is upper to arrange the first discharge orifice (19)；
Described second demarcation strip (18) is upper to arrange the second discharge orifice (20).
3. a kind of combustor radial direction two-stage swirl nozzle as claimed in claim 2, its feature also includes being provided with positioned at first
First plate washer (21) of discharge orifice (19) axial downstream, is provided with the second plate washer positioned at the second discharge orifice (20) axial downstream
(22).
4. as claimed in claim 1 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：Peripheral fuel nozzle (11)
On peripheral fuel orifice (12) position can be radial inward, radially, circumference combines towards downstream or a few person.
5. as claimed in claim 1 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：Peripheral swirl-flow devices (15)
Can be axial rotational flow or radial vortex, form can be vane type or cellular type of cutting sth. askew, eddy flow angular range is 0～15 degree.
6. as claimed in claim 1 or 2 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：Swirl device
(14) to be axial rotational flow or radial vortex, form is vane type or cellular type of cutting sth. askew.
7. as claimed in claim 2 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：First discharge orifice (19) edge
Circumference is uniform, pore size is Φ 2～Φ 4mm.
8. as claimed in claim 2 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：Second discharge orifice (20) edge
Circumference is uniform, pore size is Φ 2～Φ 4mm.
9. as claimed in claim 1 or 2 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：Central air passage
(5) and peripheral air passage (6) current limliting area than scope be 1：(7.5～9.5).
10. as claimed in claim 2 or claim 3 a kind of combustor radial direction two-stage swirl nozzle it is characterised in that：First discharge orifice
(19) with the second discharge orifice (20) area than scope be 1～5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620999380.9U CN206001524U (en) | 2016-08-30 | 2016-08-30 | A kind of combustor radial direction two-stage swirl nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620999380.9U CN206001524U (en) | 2016-08-30 | 2016-08-30 | A kind of combustor radial direction two-stage swirl nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206001524U true CN206001524U (en) | 2017-03-08 |
Family
ID=58195126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620999380.9U Active CN206001524U (en) | 2016-08-30 | 2016-08-30 | A kind of combustor radial direction two-stage swirl nozzle |
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| CN (1) | CN206001524U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106678871A (en) * | 2016-08-30 | 2017-05-17 | 林宇震 | Radial two-stage rotational flow spray nozzle of combustion chamber |
| CN106895407A (en) * | 2017-04-14 | 2017-06-27 | 北京智燃天成科技有限公司 | A kind of multitube fuel gas mixing machine using blender in pipe |
| CN107036098A (en) * | 2017-04-14 | 2017-08-11 | 北京智燃天成科技有限公司 | A kind of multitube fuel gas mixing machine of monocline tubular type outlet |
| CN107702147A (en) * | 2017-09-05 | 2018-02-16 | 中国联合重型燃气轮机技术有限公司 | The fuel nozzle of gas turbine |
| JP2018184950A (en) * | 2017-03-16 | 2018-11-22 | ゼネラル・エレクトリック・カンパニイ | Dual-fuel fuel nozzle with liquid fuel tip |
| CN109611891A (en) * | 2018-12-16 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of dry low emission combustor |
-
2016
- 2016-08-30 CN CN201620999380.9U patent/CN206001524U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106678871A (en) * | 2016-08-30 | 2017-05-17 | 林宇震 | Radial two-stage rotational flow spray nozzle of combustion chamber |
| JP2018184950A (en) * | 2017-03-16 | 2018-11-22 | ゼネラル・エレクトリック・カンパニイ | Dual-fuel fuel nozzle with liquid fuel tip |
| CN106895407A (en) * | 2017-04-14 | 2017-06-27 | 北京智燃天成科技有限公司 | A kind of multitube fuel gas mixing machine using blender in pipe |
| CN107036098A (en) * | 2017-04-14 | 2017-08-11 | 北京智燃天成科技有限公司 | A kind of multitube fuel gas mixing machine of monocline tubular type outlet |
| CN107036098B (en) * | 2017-04-14 | 2019-10-11 | 北京智燃天成科技有限公司 | A kind of multitube fuel gas mixing machine of monocline tubular type outlet |
| CN107702147A (en) * | 2017-09-05 | 2018-02-16 | 中国联合重型燃气轮机技术有限公司 | The fuel nozzle of gas turbine |
| CN109611891A (en) * | 2018-12-16 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of dry low emission combustor |
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| C14 | Grant of patent or utility model | ||
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