CN207648851U - A kind of combustion chamber radial multi-stage swirl nozzle using fuel gas - Google Patents
A kind of combustion chamber radial multi-stage swirl nozzle using fuel gas Download PDFInfo
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- CN207648851U CN207648851U CN201721539262.0U CN201721539262U CN207648851U CN 207648851 U CN207648851 U CN 207648851U CN 201721539262 U CN201721539262 U CN 201721539262U CN 207648851 U CN207648851 U CN 207648851U
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Abstract
The utility model provides a kind of combustion chamber radial multi-stage swirl nozzle using fuel gas, and the nozzle includes fuel channel and the coaxial central passage set gradually from inside to outside, second level channel, third level channel, fourth stage channel；The fuel channel includes main fuel channel and secondary grade fuel channel；Central passage swirl-flow devices are provided in the central passage；Second level channel rotational-flow device is provided in the second level channel；Third level channel rotational-flow device is provided in the third level channel；Fourth stage channel rotational-flow device is provided in the fourth stage channel；The main fuel channel corresponds to the central passage；The pair grade fuel channel is provided with inner ring jet port and outer shroud jet port, and the inner ring jet port corresponds to the second level channel and the third level channel, and the outer shroud jet port corresponds to the fourth stage channel.
Description
Technical field
The utility model belongs to low-pollution burning chamber of gas turbine nozzle technology field, and in particular to one kind using gaseous state combustion
The combustion chamber radial multi-stage swirl nozzle of material.
Background technology
Attention with energy shortages and the whole world to environmental protection problem, various countries discharge and fire to gas-turbine combustion chamber
The requirement for burning efficiency is increasingly stringenter, and generally requires gas turbine that can be maintained in 50% and the above load setting, combustion chamber discharge
In reduced levels, while keeping higher efficiency of combustion.
It is nitrogen oxide NOx to have a critically important index in the discharge of combustion chamber, in order to reach the mesh of low NOx drainage
, premixed combustion technology is widely adopted.Lean premixed combustor mostly uses eddy flow hybrid technology to realize the good of fuel and oxidant
Good mixing, but the combustion chamber for being operate on this state extremely easy tos produce combustion instability phenomenon.To solve this problem, work
Generally use sacrifices the halfway measures of NOx emission performance in journey, that is, utilizes stability good but the diffusion fire of NOx emission poor performance
Flame, to stablize premixed flame.In general, the fuel quantity accounting for being used for diffusion combustion is bigger, and burning is more stable, but NOx emission
Also increase therewith.Such burning tissues form, it is desirable that combustion chamber should be located with caution when carrying out the design of low pollution combustor nozzle
Manage contradiction of the diffusion flame to NOx emission and to flame stabilization ability.
In the current energy resource structure in China, most shares are occupied using traditional coal combustion technology.But this biography
That there are efficiency is low for system technology, and pollutant emission height (especially NOx emission) expends the shortcomings of freshwater resources are more.With natural gas etc.
Fuel gas as fuel combustion technology as one of clean energy technology, can be while meeting combustion needs, effectively
Reduction pollutant discharge.Equally, the design of combustion chamber burner burns for tissue, reduces pollutant emission particularly among these
It is important.
In combustion chamber, fuel and air realize premixing and the change of velocity profile by nozzle, reach conjunction in jet expansion
The VELOCITY DISTRIBUTION of reason, and match rational fuel-air mixture example is organized to burn into combustion chamber, formed stable flow field and
Combustion field.In the prior art, to the design form of combustion chamber burner, multiple combustion paths may be used, give each combustion path
Diameter individually adjusts the possibility of load and fuel type, to realize a variety of combustion modes and combination, realizes different workload demands,
But actually this implementation is complicated, and it is also bigger to adjust difficulty.
Utility model content
In order to solve the problems in the existing technology, the utility model provides a kind of novel combustion for using fuel gas
Room radial multi-stage swirl nozzle is burnt, pollutant emission, flow field and combustion field stabilization can be reduced and can easily be accommodated.By with
Lower technical solution is realized.
A kind of combustion chamber radial multi-stage swirl nozzle using fuel gas, the nozzle include fuel channel and coaxially by
The central passage that sets gradually from inside to outside, second level channel, third level channel, fourth stage channel；The fuel channel includes master
Grade fuel channel and secondary grade fuel channel；Central passage swirl-flow devices are provided in the central passage；The second level channel
Inside it is provided with second level channel rotational-flow device；Third level channel rotational-flow device is provided in the third level channel；Described 4th
Grade is provided with fourth stage channel rotational-flow device in channel；The main fuel channel corresponds to the central passage；The pair grade combustion
Material channel is provided with inner ring jet port and outer shroud jet port, and the inner ring jet port corresponds to the second level channel and the third
Grade channel, the outer shroud jet port correspond to the fourth stage channel.
Wherein, the number of inner ring jet port may be configured as multiple, and the number of outer shroud jet port may be set to be multiple.
Further, the fuel gas that the inner ring jet port ejects is according to the fuel flow rate of the secondary grade fuel channel
It is set as individually spurting into the third level channel, or is set as spurting into the second level channel and the third level simultaneously
Channel.
Wherein, the injection of above-mentioned fuel gas is preferably by being emitted ratio of momentum control.Fuel exit velocities when small ratio of momentum
Low, jet path is short, fuel influenced by crossflow after completely into third level channel；Fuel exit velocities when big ratio of momentum
Height, jet path is long, and a fuel part enters third level channel, and another part enters second level channel.
Further, the central passage swirl-flow devices and the main fuel channel are coaxial interconnected in a ring.
Further, the central passage swirl-flow devices are both preferably crescent moon channel type air with the main fuel channel
Channel.
Further, the passages downstream outside wall surface of the central passage is provided with radial direction and helps trepanning.
Wherein, the radial direction helps trepanning that can be arranged multiple, along being arranged circumferentially for the central passage outside wall surface.
Further, the radial direction helps the air-flow exiting angle range of trepanning (14) to be set as radial and helps the outgoing of trepanning air-flow
Direction is with axis normal orientation at 0 to 60 °.
Further, the channel outlet shape of the central passage be contraction type or expanding, the second level channel
Channel outlet shape is contraction type or expanding, and the channel outlet shape in the third level channel is contraction type or expanding, institute
The channel outlet shape for stating fourth stage channel is contraction type or expanding.
Further, the central passage swirl-flow devices include the passage upstream outside wall surface being arranged in the central passage
The hole being connected to the second level channel.
Further, the second level channel rotational-flow device, the third level channel rotational-flow device and the fourth stage are logical
Road swirl-flow devices are both preferably vane type.The second level channel rotational-flow device, the third level channel rotational-flow device and described
Fourth stage channel rotational-flow device may be alternatively provided as beveling cellular type.
Further, the inner ring jet port and outer shroud jet port are staggeredly arranged in the axial direction of secondary grade fuel channel.Institute
It states inner ring jet port and outer shroud jet port is both preferably cellular type, oblique slot type can also be disposed as.
Further, the second level channel rotational-flow device, third level channel rotational-flow device and fourth stage channel rotational-flow dress
It sets and is disposed as axial rotational flow or radial vortex；The second level channel rotational-flow device, third level channel rotational-flow device and the 4th
The eddy flow rotation direction of grade channel rotational-flow device is both preferably clockwise, can also be disposed as counterclockwise.
The beneficial effects of the utility model：
The technical solution of the utility model can realize full premix combustion pattern.Main fuel is with air radial and axial
Mixing outgoing, and using helping the radial incidence of the rotational flow air of rotation to carry out secondary blending, it is empty that the very high fuel of the uniformity can be reached
Gas mixture can obtain excellent igniting, extinguishing performance, while ensure generation and localized heat that the inhibition under big operating mode is smoldered
The formation of point, obtains good Exit temperature distribution characteristic；Secondary grade fuel sprays radially inward and outward, passes through and adjusts fuel
Flow can flexibly control the mixing equivalent proportion of Multi-stage spiral air and fuel, and the burning for being conducive to reach under different operating modes is dirty
Contaminate emission request.
Description of the drawings
The structure of the combustion chamber radial multi-stage swirl nozzle for using fuel gas of Fig. 1 specific embodiments of the present invention
Principle schematic.
The center of the combustion chamber radial multi-stage swirl nozzle for using fuel gas of Fig. 2 specific embodiments of the present invention
Channel design three dimensional sectional view.
The forward direction of the combustion chamber radial multi-stage swirl nozzle for using fuel gas of Fig. 3 specific embodiments of the present invention
View.
The three-dimensional of the combustion chamber radial multi-stage swirl nozzle for using fuel gas of Fig. 4 specific embodiments of the present invention
Sectional view.
Specific implementation mode
1-4 does in detail the combustion chamber radial multi-stage swirl nozzle for using fuel gas of the utility model below in conjunction with the accompanying drawings
It describes in detail bright.
As shown in Figs 1-4, the combustion chamber radial multi-stage swirl nozzle for using fuel gas of the utility model includes fuel
Channel 1 and the coaxial central passage 2 set gradually from inside to outside, second level channel 3, third level channel 4, fourth stage channel 5, combustion
Expect that channel 1 includes main fuel channel 10 and secondary grade fuel channel 11, central passage swirl-flow devices 6 be provided in central passage 2,
It is provided with second level channel rotational-flow device 7 in second level channel 3, third level channel rotational-flow device is provided in third level channel 4
8, fourth stage channel rotational-flow device 9 is provided in fourth stage channel 5, main fuel channel 10 corresponds to central passage 2, secondary grade fuel
Channel 11 is provided with inner ring jet port 12 and outer shroud jet port 13, and inner ring jet port 12 corresponds to second level channel 3 and the third level is logical
Road 4, outer shroud jet port 13 correspond to fourth stage channel 5.
Wherein, the fuel gas that inner ring jet port 12 ejects is set as single according to the fuel flow rate of secondary grade fuel channel 11
Third level channel 4 solely is spurted into, or is set as spurting into second level channel 3 and third level channel 4 simultaneously.Above-mentioned fuel gas
Be ejected through outgoing ratio of momentum control.Fuel exit velocities are low when small ratio of momentum, and jet path is short, and fuel is by crossflow shadow
Completely into third level channel 4 after sound；Fuel exit velocities are high when big ratio of momentum, and jet path is long, and a fuel part enters the
Three-level channel 4, another part enter second level channel 3.
As shown in Figure 1, using the opposite of the secondary grade fuel channel 11 of the combustion chamber radial multi-stage swirl nozzle of fuel gas
The axial medium position of the radial multi-stage swirl nozzle, interior ring spray are extended in the opposite end of fuel inlet end (diagram left end)
Loophole 12 and outer shroud jet port 13 are in staggered configuration.Inner ring jet port 12 configures the axial front half section in secondary grade fuel channel 11, outside
Ring spray loophole 13 configures the axial second half section in secondary grade fuel channel 11.Main fuel channel 10 is opened in central passage 2.It is secondary
Grade fuel channel 11 is opened in the wall surface in third level channel 4.Second level channel 3 equally has wall surface.Fourth stage channel 5 also has
There is wall surface.The length of the wall surface in fourth stage channel 5 in the axial direction be less than third level channel 4 wall surface in the axial direction length (but
More than the half of the wall surface length in the axial direction in third level channel 4), the length of the wall surface in fourth stage channel 5 in the axial direction
Degree is more than the length of the wall surface in second level channel 3 in the axial direction.The outside wall surface in third level channel 4 is arranged in outer shroud jet port 13,
The internal face in third level channel 4 is arranged in inner ring jet port 12.Inner ring jet port 12 and outer shroud jet port 13 are axially offsetting cloth
It sets, inner ring jet port 12 and outer shroud jet port 13 are multiple, such as are 4, and inner ring jet port 12 and outer shroud injection
Mouth 13 is along the circumferential uniformly configuration of the wall surface of third channel 4.
As shown in Fig. 2, central passage swirl-flow devices 6 are coaxial interconnected in a ring with main fuel channel 10.Center is logical
Road swirl-flow devices 6 and main fuel channel 10 are crescent moon channel type air duct.Central passage swirl-flow devices 6 include that setting exists
The hole of the passage upstream outside wall surface of central passage 2 being connected to second level channel 3.The above-mentioned hole of central passage swirl-flow devices 6 exists
It is staggeredly arranged with above-mentioned inner ring jet port 12 in axial direction.The passages downstream outside wall surface of central passage 2 is provided with multiple radial directions and helps rotation
Hole 14, these radial directions help circumferential uniformly configuration of the trepanning 14 along the wall surface of central passage 2.The radial direction helps the air-flow of trepanning (14)
Exiting angle range is set as radial and helps trepanning air-flow exit direction with axis normal orientation at 0 to 60 °, such as 0 °, 10 °,
20 °, 30 °, 60 ° etc..
As shown in Figure 3-4, second level channel rotational-flow device 7, third level channel rotational-flow device 8 and fourth stage channel rotational-flow dress
It is vane type to set 9.And the eddy flow direction of second level channel rotational-flow device 7 is third level channel rotational-flow dress clockwise
The eddy flow direction for setting 8 is that clockwise, the eddy flow direction of fourth stage channel rotational-flow device 9 is counterclockwise.It can by Fig. 2-3
To find out, in present embodiment, the eddy flow direction of the central passage swirl-flow devices 6 of central passage 2 is clockwise.
As shown in figure 4, the downstream passage outlet shapes of central passage 2 are contraction type, the downstream passage in second level channel 3 goes out
Mouth-shaped is expanding, and the downstream passage outlet shapes in third level channel 4 are contraction type, and the downstream passage in fourth stage channel 5 goes out
Mouth-shaped is contraction type.The global shape of the combustion chamber radial multi-stage swirl nozzle for using fuel gas of the utility model is circle
Tubular.
Obviously, the above embodiment is only intended to clearly illustrate the utility model example, and is not to this
The restriction of the embodiment of utility model.For those of ordinary skill in the art, on the basis of the above description also
It can make other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.And this
Protection model of the obvious changes or variations that a little spirit for belonging to the utility model are extended out still in the utility model
Among enclosing.
Claims (10)
1. a kind of combustion chamber radial multi-stage swirl nozzle using fuel gas, which is characterized in that
The nozzle include fuel channel (1) and the coaxial central passage (2) set gradually from inside to outside, second level channel (3),
Third level channel (4), fourth stage channel (5)；
The fuel channel (1) includes main fuel channel (10) and secondary grade fuel channel (11)；
It is provided with central passage swirl-flow devices (6) in the central passage (2)；
It is provided with second level channel rotational-flow device (7) in the second level channel (3)；
It is provided with third level channel rotational-flow device (8) in the third level channel (4)；
It is provided with fourth stage channel rotational-flow device (9) in the fourth stage channel (5)；
The corresponding central passage (2) of the main fuel channel (10)；
The pair grade fuel channel (11) is provided with inner ring jet port (12) and outer shroud jet port (13), the inner ring jet port
(12) the corresponding second level channel (3) and the third level channel (4), the corresponding fourth stage of the outer shroud jet port (13)
Channel (5).
2. the combustion chamber radial multi-stage swirl nozzle as described in claim 1 for using fuel gas, which is characterized in that in described
The fuel gas that ring spray loophole (12) ejects is set as individually spraying according to the fuel flow rate of the secondary grade fuel channel (11)
Enter the third level channel (4), or is set as spurting into the second level channel (3) and the third level channel (4) simultaneously.
3. the combustion chamber radial multi-stage swirl nozzle according to claim 1 or 2 for using fuel gas, which is characterized in that
The central passage swirl-flow devices (6) and the main fuel channel (10) are coaxial interconnected in a ring.
4. the combustion chamber radial multi-stage swirl nozzle according to claim 3 for using fuel gas, which is characterized in that described
Central passage swirl-flow devices (6) and the main fuel channel (10) are crescent moon channel type air duct.
5. the combustion chamber radial multi-stage swirl nozzle according to claim 3 for using fuel gas, which is characterized in that described
The passages downstream outside wall surface of central passage (2) is provided with radial direction and helps trepanning (14).
6. the combustion chamber radial multi-stage swirl nozzle according to claim 5 for using fuel gas, which is characterized in that described
Radially helping the air-flow exiting angle range of trepanning (14) to be set as radial helps trepanning air-flow exit direction with axis normal orientation at 0
To 60 °.
7. the combustion chamber radial multi-stage swirl nozzle according to claim 1 or 2 for using fuel gas, which is characterized in that
The channel outlet shape of the central passage (2) is contraction type or expanding, the channel outlet shape of the second level channel (3)
Channel outlet shape for contraction type or expanding, the third level channel (4) is contraction type or expanding, and the fourth stage is logical
The channel outlet shape in road (5) is contraction type or expanding.
8. the combustion chamber radial multi-stage swirl nozzle according to claim 4 for using fuel gas, which is characterized in that described
Central passage swirl-flow devices (6) include setting in the logical with the second level of the passage upstream outside wall surface of the central passage (2)
The hole of road (3) connection.
9. the combustion chamber radial multi-stage swirl nozzle according to claim 1 or 2 for using fuel gas, which is characterized in that
The second level channel rotational-flow device (7), the third level channel rotational-flow device (8) and the fourth stage channel rotational-flow device
(9) it is vane type.
10. the combustion chamber radial multi-stage swirl nozzle according to claim 1 or 2 for using fuel gas, which is characterized in that
The inner ring jet port (12) and outer shroud jet port (13) are staggeredly arranged in the axial direction of the secondary grade fuel channel (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721539262.0U CN207648851U (en) | 2017-11-16 | 2017-11-16 | A kind of combustion chamber radial multi-stage swirl nozzle using fuel gas |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721539262.0U CN207648851U (en) | 2017-11-16 | 2017-11-16 | A kind of combustion chamber radial multi-stage swirl nozzle using fuel gas |
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| CN207648851U true CN207648851U (en) | 2018-07-24 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107676817A (en) * | 2017-11-16 | 2018-02-09 | 中国航空发动机研究院 | A kind of combustion chamber radial multi-stage swirl nozzle for using fuel gas |
| CN115949970A (en) * | 2023-01-05 | 2023-04-11 | 中国航空发动机研究院 | Swirler vane and swirler |
-
2017
- 2017-11-16 CN CN201721539262.0U patent/CN207648851U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107676817A (en) * | 2017-11-16 | 2018-02-09 | 中国航空发动机研究院 | A kind of combustion chamber radial multi-stage swirl nozzle for using fuel gas |
| CN107676817B (en) * | 2017-11-16 | 2023-02-28 | 中国航空发动机研究院 | Radial multistage swirl nozzle of combustion chamber for burning gaseous fuel |
| CN115949970A (en) * | 2023-01-05 | 2023-04-11 | 中国航空发动机研究院 | Swirler vane and swirler |
| CN115949970B (en) * | 2023-01-05 | 2023-08-22 | 中国航空发动机研究院 | Cyclone blade and cyclone |
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