CN106678871A - Radial two-stage rotational flow spray nozzle of combustion chamber - Google Patents
Radial two-stage rotational flow spray nozzle of combustion chamber Download PDFInfo
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- CN106678871A CN106678871A CN201610772902.6A CN201610772902A CN106678871A CN 106678871 A CN106678871 A CN 106678871A CN 201610772902 A CN201610772902 A CN 201610772902A CN 106678871 A CN106678871 A CN 106678871A
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- fuel
- nozzle
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- combustion chamber
- central
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a low-pollution radial two-stage rotational flow spray nozzle of a combustion chamber. The radial two-stage rotational flow spray nozzle comprises a central fuel channel, a peripheral fuel channel and an annular air channel which are coaxially arranged in the radial direction, and the annular air channel is separated into a central air channel body and a peripheral air channel body by a splitter plate; the central air channel body and the peripheral air channel body are internally provided with a central rotational flow device and a peripheral rotational flow device respectively; and an outlet of the central fuel channel is provided with a premixing cavity. By means of the spray nozzle structure, combustion stability and good discharging performance are guaranteed, gas or liquid fuel, such as natural gas which is cleaner, can be utilized, and the radial two-stage rotational flow spray nozzle has the advantage that the work state is easy to adjust.
Description
Technical field
The present invention relates to field of combustion technology, more particularly to a kind of oligosaprobic combustion chamber radial direction two-stage swirl nozzle.
Background technology
With attention of the whole world to environmental protection problem, 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.To reach low NOx, premixed combustion
The good mixing of fuel and oxidant is realized more than room using eddy flow hybrid technology, but is operate on the combustion chamber pole of this state
It easily produces combustion instability phenomenon.To solve this problem, generally arranged using sacrifice the compromise of NOx emission performance in engineering
Apply, i.e., using good stability but NOx emission poor performance diffusion flame stablizing premixed flame.In general, fire for spreading
The fuel quantity accounting of burning is bigger, burns more stable, but NOx emission also increases therewith.Such burning tissues form, it is desirable to burn
Room should with caution process diffusion flame to NOx emission and to flame stabilization ability when the design of low pollution combustor nozzle is carried out
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 more in system technology.With natural gas etc.
For fuel combustion technology as one of clean energy technology, pollution can be effectively reduced while combustion needs are met
The discharge of thing.Equally, among these the design of combustion chamber burner is particularly important for tissue burning, reduction pollutant emission.
In combustion chamber, fuel and air realize premixing and the change of velocity profile by nozzle, and in jet expansion conjunction is reached
The VELOCITY DISTRIBUTION of reason, and match rational fuel-air mixture example, burns into combustion chamber tissue, formed stable flow field and
Combustion field.In prior art, mentioning in the design form to combustion chamber burner, such as 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, to give the possibility that each combustion path individually adjusts load and fuel type, but actually this implementation knot
Structure is complicated, adjusts difficulty also than larger.
The content of the invention
(1) goal of the invention
There is provided a kind of combustion chamber radial direction two-stage swirl nozzle, contradiction of the solution between NOx emission and flame stabilization
Technical problem is in prior art.
(2) technical scheme
In order to solve above-mentioned technical problem, the invention provides a kind of combustion chamber radial direction two-stage swirl nozzle, its feature bag
Include：Radially coaxially arranged center fuel passage, peripheral fuel channel, annular air channel；Center fuel delivery pipe, center
Fuel nozzle；Peripheral fuel -supply pipe, peripheral fuel nozzle；Outer nozzle wall；
The outer nozzle wall is the outer wall of the two-stage swirl nozzle；
It is coaxially disposed inside the annular air channel and the annular air channel is separated into central air passage and outer
Enclose the flow distribution plate of air duct；
The center fuel delivery pipe connects the central fuel nozzle；The center fuel delivery pipe is sprayed with center fuel
The region that mouth is limited is the center fuel passage；The central fuel nozzle end is provided with center fuel spray-hole；
The peripheral fuel -supply pipe connects the peripheral fuel nozzle；The peripheral fuel -supply pipe and peripheral fuel spray
The region that mouth is limited is the peripheral fuel channel；The peripheral fuel nozzle is arranged on the flow distribution plate with the outer nozzle wall
Between area, its end is provided with peripheral fuel orifice；
The Swirl device is disposed with the central air passage；
The peripheral swirl-flow devices are disposed with the peripheral air passage；
Two-stage swirl nozzle inside arranges premix chamber, for the fuel that sprays the center fuel spray-hole and Jing
The air mixing of the central air passage of the Swirl device eddy flow.
Further, also including the first demarcation strip, the second demarcation strip for being arranged on the central air passage region；
First demarcation strip is arranged on the radial outside of the central fuel nozzle；Second demarcation strip is arranged on institute
State the radial outside of the first demarcation strip；
First demarcation strip, the second demarcation strip form the region for limiting the premix chamber；
The first discharge orifice is set on first demarcation strip；
The second discharge orifice is set on second demarcation strip.
Further, also it is provided with positioned at second including the first plate washer being provided with positioned at the first discharge orifice axial downstream
Second plate washer of discharge orifice axial downstream.
Further, the peripheral fuel injection hole site on described peripheral fuel nozzle can be radial inward, radial direction
Outwardly, it is circumferential to combine towards downstream or a few persons.
Further, described peripheral swirl-flow devices can be axial rotational flow or radial vortex, and form can be vane type
Or beveling cellular type, eddy flow angular range is 0~15 degree.
Further, described Swirl device to be axial rotational flow or radial vortex, form can be vane type or
Beveling 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
The technical scheme swirl-flow devices radially divide two stage arrangement, it is ensured that while mixing effect, match jet expansion
VELOCITY DISTRIBUTION.Ensure that nozzle exit velocity is reasonably distributed, fuel-air blending uniformly, rationally controls combustion by two-stage swirl-flow devices
Region is burnt, combustion chamber flow field structure is maintained, so as to ensure the stability and good discharge performance of burning.
The center fuel passage of the present invention can coordinate Swirl device and premix by center fuel spray regime
Chamber, makes center and periphery just decouple from flowing, realizes the combustion mode of injection diffusion combustion+swirl flame, reaches reliable point
Fire and maximum reduce the effect of discharge.
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 logical
Influencing each other between road, it is to avoid peripheral channel is interfered, while the peripheral annular formed between flow distribution plate and outer nozzle wall face
Gas channel, with the air velocity that aisle spare limits peripheral annular air duct, it is ensured that outer circumferential side gas velocity degree type is distributed, from
And continual and steady burning, it is ensured that do not stop working during regulation whole combustion chamber.
The air sprayed via discharge orifice can be used as cooling air cooling premix chamber wall, and this portion gas can be with
Anti-backfire technique effect is realized, combustion stability is further enhanced.
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 of different fuel and air blending.
Description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is the partial enlarged drawing of schematic structural view of the invention.
Mark is described as follows in figure：
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
Principle of the invention, structure and specific embodiment are described further below in conjunction with the accompanying drawings.Following instance
For illustrating the present invention, but it is not limited to the scope of the present invention.
In describing the invention, it should be noted that the term " instruction such as " center ", " periphery ", " interior ", " outward " " downstream "
Orientation or position relationship be based on orientation shown in the drawings or position relationship, be for only for ease of description the present invention and simplification retouch
State, rather than indicate or imply indication device or element must have specific orientation, with specific azimuth configuration and operation,
Therefore it is not considered as limiting the invention.Additionally, term " first ", " second " etc. are only used for describing purpose, and can not manage
Solve to indicate or implying relative importance.
As shown in figure 1, a kind of combustion chamber radial direction two-stage swirl nozzle designed for the present invention, the nozzle includes radially same
The center fuel passage 1 of axle arrangement, peripheral fuel channel 2, annular air channel 3；Center fuel delivery pipe 7, center fuel is sprayed
Mouth 8；Peripheral fuel -supply pipe 10, peripheral fuel nozzle 11；Outer nozzle wall 13；Outer nozzle wall 13 is the two-stage swirl nozzle
Outer wall；It is coaxially disposed inside annular air channel 3 and the annular air channel 3 is separated into central air passage 5 and periphery sky
The flow distribution plate 4 of gas passage 6；Center fuel delivery pipe 7 connects the central fuel nozzle 8；The center fuel delivery pipe 7 is with
The region that heart fuel nozzle 8 is limited is the center fuel passage 1；The end of the central fuel nozzle 8 is provided with center fuel
Spray-hole 9；Peripheral fuel -supply pipe 10 connects the peripheral fuel nozzle 11；Peripheral fuel -supply pipe 10 and peripheral fuel nozzle
11 regions for limiting are the peripheral fuel channel 2；Peripheral fuel nozzle 11 is arranged on the flow distribution plate 4 with the outer nozzle wall
Between 13, its end is provided with peripheral fuel orifice 12；The Swirl device 14 is disposed with central air passage 5；
The peripheral swirl-flow devices 15 are disposed with peripheral air passage 6；Swirl nozzle inside arranges premix chamber 16, in will be described
The fuel that heart fuel orifice 9 sprays is mixed with the air of the central air passage 5 of the eddy flow of Swirl device 14 described in Jing
Close.
Preferably, first demarcation strip 17 in the region of central air passage 5, the second demarcation strip 18；First demarcation strip 17 is arranged
In the radial outside of the central fuel nozzle 8；Second demarcation strip 18 is arranged on the radial outside of first demarcation strip 17；The
One demarcation strip 17, the second demarcation strip 18 form the region for limiting the premix chamber 16；First is arranged on first demarcation strip 17
Discharge orifice 19；Second discharge orifice 20 is set on second demarcation strip 18.
Preferably, nozzle also includes being provided with the first plate washer 21 positioned at the axial downstream of the first discharge orifice 19, is provided with position
In the second plate washer 22 (referring to the partial enlarged drawing in Fig. 1) of the axial downstream of the second discharge orifice 20.
Preferably, the position of peripheral fuel orifice 12 on peripheral fuel nozzle 11 can be radial inward, radially,
It is circumferential to combine towards downstream or a few persons.
Preferably, peripheral swirl-flow devices 15 can be axial rotational flow or radial vortex, and form can be vane type or beveling
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 beveling hole 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 the area of peripheral air passage 6 are 1 than scope：(7.5~9.5).
Preferably, the first discharge orifice 19 and the area of the second discharge orifice 20 are 1~5 than scope.
The operation principle of the present invention is as follows：
Center fuel approach center fuel passage 1, by center fuel delivery pipe 7 central fuel nozzle 8 is reached, and 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
Up to peripheral fuel nozzle 11, sprayed by peripheral fuel orifice 12；
Air enters annular air channel 3, is split plate 4 and shunts, and is partly into peripheral air passage 6, remaining entrance
Central air passage 5；
Into the fuel that the air of peripheral air passage 6 sprays with peripheral fuel orifice 12, Jing peripheries swirl-flow devices 11
Strengthen entering fired downstream after blending；
Air into central air passage 5 is then further divided into several parts, and a part of Jing Swirls device 14 fires with center
The fuel that material nozzle 8 sprays carries out ignition into downstream together, 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,
The wall of second demarcation strip 18, and this part cooling gas can be spaced apart the air current flow of central passage and peripheral channel so as to
It does not interfere with each other, first plate washer 21 and the second plate washer 22 of additional setting can strengthen this technique effect.In addition, this structure sets
Meter can also realize anti-backfire technique effect using this partial air, further enhance combustion stability.
Peripheral channel fuel, central passage fuel can be adjusted respectively, and to meet different combustion equivalents demand is compared.
The operation principle of the present invention is as follows：
Center fuel approach center fuel passage 1, by center fuel delivery pipe 7 central fuel nozzle 8 is reached, and 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
Up to peripheral fuel nozzle 11, sprayed by peripheral fuel orifice 12；
Air enters annular air channel 3, is split plate 4 and shunts, and is partly into peripheral air passage 6, remaining entrance
Central air passage 5；
Into the fuel that the air of peripheral air passage 6 sprays with peripheral fuel orifice 12, Jing peripheries swirl-flow devices 11
Strengthen entering fired downstream after blending；
Air into central air passage 5 is then further divided into several parts, and a part of Jing Swirls device 14 fires with center
The fuel that material nozzle 8 sprays carries out ignition into premix chamber 16 together, 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,
The wall of second demarcation strip 18, in addition, this structure design can also realize anti-backfire technology effect using this part earial drainage air
Really, combustion stability is further enhanced.
Peripheral channel, fuel and the air of central passage blend the course of work of burning, by this structure point of premix chamber 16
Separate and, the first demarcation strip 17 for limiting premix chamber 16 separates in solid form with the second demarcation strip 18, the first demarcation strip 17
Can be with gas with the earial drainage air sprayed in the first discharge orifice 19 and the second discharge orifice 20 arranged on the second demarcation strip 18
The air current flow of form central passage spaced apart and peripheral channel so as to do 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, reinforcing separate this technique effect.
Peripheral channel fuel, central passage fuel can be adjusted respectively, and to meet different combustion equivalents demand is compared.
Finally it should be noted that：Above example only to illustrate technical scheme, rather than a limitation；Although
The present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：It still may be used
To modify to the technical scheme described in foregoing embodiments, or equivalent is carried out to which part technical characteristic；
And these modification or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (10)
1. a kind of combustion chamber 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)；
The outer nozzle wall (13) is the outer wall of the two-stage swirl nozzle；
It is coaxially disposed inside the annular air channel (3) and the annular air channel (3) is separated into central air passage (5)
With the flow distribution plate (4) of peripheral air passage (6)；
The center fuel delivery pipe (7) connects the central fuel nozzle (8)；The center fuel delivery pipe (7) and center
The region that fuel nozzle (8) is limited is the center fuel passage (1)；Central fuel nozzle (8) end is provided with center
Fuel orifice (9)；
The peripheral fuel -supply pipe (10) connects the peripheral fuel nozzle (11)；The peripheral fuel -supply pipe (10) with it is outer
Region that fuel nozzle (11) limits is enclosed as the peripheral fuel channel (2)；The peripheral fuel nozzle (11) is arranged on described
Between flow distribution plate (4) and the outer nozzle wall (13), its end is provided with peripheral fuel orifice (12)；
The Swirl device (14) is disposed with the central air passage (5)；
The peripheral swirl-flow devices (15) are disposed with the peripheral air passage (6)；
The two-stage swirl nozzle inside arranges premix chamber (16), for the fuel for spraying the center fuel spray-hole (9)
Mix with the air of the central air passage (5) of Swirl device (14) eddy flow described in Jing.
2. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 1, it is characterised in that also described including being arranged on
First demarcation strip (17) in central air passage (5) region, the second demarcation strip (18)；
First demarcation strip (17) is arranged on the radial outside of the central fuel nozzle (8)；Second demarcation strip (18)
It is arranged on the radial outside of first demarcation strip (17)；
First demarcation strip (17), the second demarcation strip (18) form the region for limiting the premix chamber (16)；
The first discharge orifice (19) is set on first demarcation strip (17)；
The second discharge orifice (20) is set on second demarcation strip (18).
3. a kind of combustion chamber 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. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 1, it is characterised in that：Peripheral fuel nozzle (11)
On peripheral fuel orifice (12) position can be radial inward, radially, circumferential combine towards downstream or a few persons.
5. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 1, it is characterised in that：Peripheral swirl-flow devices (15)
Can be axial rotational flow or radial vortex, form can be vane type or beveling cellular type, and eddy flow angular range is 0~15 degree.
6. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 1 or 2, it is characterised in that：Swirl device
(14) to be axial rotational flow or radial vortex, form is vane type or beveling cellular type.
7. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 2, it is characterised in that：First discharge orifice (19) edge
Circumferential uniform, pore size is Φ 2~Φ 4mm.
8. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 2, it is characterised in that：Second discharge orifice (20) edge
Circumferential uniform, pore size is Φ 2~Φ 4mm.
9. a kind of combustion chamber radial direction two-stage swirl nozzle as claimed in claim 1 or 2, 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 combustion chamber 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 |
|---|---|---|---|
| CN201610772902.6A CN106678871A (en) | 2016-08-30 | 2016-08-30 | Radial two-stage rotational flow spray nozzle of combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610772902.6A CN106678871A (en) | 2016-08-30 | 2016-08-30 | Radial two-stage rotational flow spray nozzle of combustion chamber |
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| Publication Number | Publication Date |
|---|---|
| CN106678871A true CN106678871A (en) | 2017-05-17 |
Family
ID=58840005
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610772902.6A Pending CN106678871A (en) | 2016-08-30 | 2016-08-30 | Radial two-stage rotational flow spray nozzle of combustion chamber |
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| Country | Link |
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| CN (1) | CN106678871A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107687652A (en) * | 2017-07-25 | 2018-02-13 | 西北工业大学 | A kind of poor premix low pollution combustor head construction of dual-fuel gas turbine |
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN114459032A (en) * | 2022-01-28 | 2022-05-10 | 佛山仙湖实验室 | Ammonia gas combustion control method, system, equipment and medium |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107687652A (en) * | 2017-07-25 | 2018-02-13 | 西北工业大学 | A kind of poor premix low pollution combustor head construction of dual-fuel gas turbine |
| CN107687652B (en) * | 2017-07-25 | 2019-07-05 | 西北工业大学 | A kind of poor premix low pollution combustor head construction of dual-fuel gas turbine |
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN114459032A (en) * | 2022-01-28 | 2022-05-10 | 佛山仙湖实验室 | Ammonia gas combustion control method, system, equipment and medium |
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