CN106016364B - A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) - Google Patents
A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) Download PDFInfo
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- CN106016364B CN106016364B CN201610551146.4A CN201610551146A CN106016364B CN 106016364 B CN106016364 B CN 106016364B CN 201610551146 A CN201610551146 A CN 201610551146A CN 106016364 B CN106016364 B CN 106016364B
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- fuel injection
- fuel
- pipe fitting
- swirler assembly
- swirl
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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
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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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle), is related to a kind of gas turbine combustion nozzle.The present invention in order to solve existing gas turbine lean premixed combustor combustion instability, easily occur tempering, be furious the problems such as higher with disposal of pollutants.Apparatus of the present invention include fuel injection assemblies, swirler assembly, end divergent nozzle, center purging part, outer cover, the first pipe fitting, the second pipe fitting and third pipe fitting, first pipe fitting, the second pipe fitting and third pipe fitting are set on the left of fuel injection assemblies, and are connect respectively with fuel injection assemblies；It is provided with swirler assembly on the right side of fuel injection assemblies；End divergent nozzle, center purging part and outer cover are provided on the right side of swirler assembly.Apparatus of the present invention reduce unit two and divide the tempering of swirl-flow premixed burner noz(zle), the possibility being furious, and flameholding when underload reduces the disposal of pollutants of combustion chamber, simple in structure, probability of malfunction is small.The present invention is suitable for gas-turbine combustion chamber.
Description
Technical field
The present invention relates to a kind of gas turbine dry low pollution combustor units two to divide swirl-flow premixed burner noz(zle).
Background technology
Existing low stain gas turbine operation principle is：Air is delivered to the combustion of dry type low stain after being compressed in compressor
Room is burnt, fuel is pre-mixed in combustion chamber burner with compressed air, and being ignited device in the burner inner liner of nozzle downstream lights, production
Raw high-temperature high-pressure fuel gas, is delivered to the turbine in downstream, the thermal energy of high-temperature high-pressure fuel gas and pressure energy are converted by turbine makes axis
The mechanical energy of rotation drives generator or pump to generate power with this.
Currently, certain known fuel nozzles are all mainly to use cyclone using swirl-flow premixed.Swirler assembly is main
Including surrounding the outer cover of swirl vane and connecting the centerbody of multiple swirl vanes, outer cover, centerbody and swirl vane form
Guide the annular chamber of compressed air flowing.Wherein swirl vane is internally provided with fuel cavity, the table that gaseous fuel passes through swirl vane
In the small hole injection to annular chamber of face, rotation is carried out in cyclone downstream with compressed air and mixed.But since hole injection is brought
Two important problems：First, it is close to swirl vane surface, forms the dense fuel tape centered on hole, this fuel tape can also
It is dissolved into the tail of swirl vane, it is poor or when using the higher fuel of activity and leading to tempering in combustion chambers burn stability,
It is easy to form swirl vane surface and be furious, burn premixing nozzle, can further burn other components such as combustion chamber, turbine guide vane；
Second, the adherent surface current of fuel is dynamic, reduces the contact area of fuel and ring cavity air, reduces the diffusion property of fuel, no
Conducive to the mixing of fuel and air, swirl-flow premixed performance is reduced.
Invention content
The present invention is in order to solve existing gas turbine lean premixed combustor combustion instability, tempering easily occurs, be furious and dirty
The problems such as dye discharge is higher, and propose a kind of gas turbine dry low pollution combustor unit two and divide swirl-flow premixed burning spray
Mouth.
A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle), including fuel injection group
Part, swirler assembly, end divergent nozzle, center purging part, outer cover, the first pipe fitting, the second pipe fitting and third pipe fitting；
The fuel injection assemblies, swirler assembly, end divergent nozzle, center purging part, outer cover, the first pipe fitting, the
Two pipe fittings and third pipe fitting are coaxial；Second pipe fitting is set to the first inside pipe fitting, and third pipe fitting is set to the second inside pipe fitting, the
One pipe fitting, the second pipe fitting and third pipe fitting are set on the left of fuel injection assemblies, and are connect respectively with fuel injection assemblies；Fuel
It is provided with swirler assembly on the right side of ejection assemblies；End divergent nozzle is provided on the right side of swirler assembly, center purges part and outer
Cover；End divergent nozzle is set to inside outer cover, and center purging part is set to inside the divergent nozzle of end；First pipe fitting and second
Pipe fitting forms and premixes fuel channel outside second, and the second pipe fitting forms with third pipe fitting and premixes fuel channel in second；Third pipe fitting
Inside is the second diffusion fuel passage；
The fuel injection assemblies include several fuel injection blades, tubular fuel injection assemblies centerbody and fuel injection
Package shell；Fuel injection blade is uniformly arranged around fuel injection assemblies centerbody is circumferentially equidistant；Fuel injection assemblies center
Body and fuel injection assemblies shell constitute the first compressed air flow annulus；Fuel injection assemblies centerbody center is burner noz(zle)
Central passage；Fuel injection blade inlet edge both sides, which are provided with outside the first of blade height direction, premixes fuel channel, and inside is set
It is equipped with along the first of blade height direction and premixes fuel channel；It is to be set to fuel that premix fuel channel is externally ported outside first
First fuel injection hole of eject blade both sides, first premixes premix fuel passage outside fuel channel and second outside；First
Externally ported interior premix fuel channel is the second fuel injection hole for being set to fuel injection blade both sides, and fuel is premixed in first
Fuel passage is premixed in channel and second, fuel premixes premix fuel channel difference in fuel channel and second outside second
Fuel channel is premixed outside into first in premix fuel channel and first, finally along the first fuel injection hole and the second fuel injection
Hole sprays；The first fuel injection hole export direction is tilted perpendicular to fuel injection blade or to fuel injection trailing edge；
The second fuel injection hole export direction is tilted perpendicular to fuel injection blade or to fuel injection trailing edge；The burning
Nozzle center passageway and the connection of the second diffusion fuel passage；
The swirler assembly includes several swirl vanes, tubular swirler assembly centerbody and swirler assembly shell；
Swirl vane is uniformly arranged around swirler assembly centerbody is circumferentially equidistant；Swirl vane equidistantly misplaces with fuel injection blade
Setting；Swirler assembly centerbody and swirler assembly shell constitute the second compressed air flow annulus；Swirler assembly center
Body center is swirler assembly central passage, is provided on swirler assembly centerbody barrel flat with swirler assembly central passage
Capable several axial passages, swirler assembly left end are provided with the circular cavity coaxial with swirler assembly central passage；Eddy flow
Compressed air inlet channel is provided in blade, compressed air inlet channel extends out to swirler assembly shell, inwardly prolongs
Swirler assembly central passage is extended to, wherein axial passage is not connected to compressed air inlet channel；The swirler assembly is
Whole precision castings or weldment；
End divergent nozzle right side is provided with several diffused fuel spray orifices, and end divergent nozzle and center purge part
The first diffusion fuel passage for forming annular forms premix ring cavity between end divergent nozzle and outer cover；
The length of the premix ring cavity is L1, end divergent nozzle right side is L at a distance from outer cover right side2, pass through tune
Save L1The mixed characteristic that swirl-flow premixed burner noz(zle) can be adjusted, by adjusting L2It may be implemented to adjust flame holding and constraint
The function of flame profile, can also be by adjusting the fuel between premix fuel channel in second outside premix fuel channel and second
Flow proportional, adjustment unit two divide swirl-flow premixed burner noz(zle) Fuel-air premix concentration radial distribution.
Center purging part right side is provided with several purge holes, and round purging is logical centered on center purges part inside
Road；Central circular purge passage is connected to swirler assembly central passage；
The fuel injection assemblies are whole precision castings or weldment；The fuel injection assemblies pass through with swirler assembly
It is threadedly coupled or is welded to connect；The swirler assembly is connected through a screw thread or is welded to connect with end divergent nozzle；The rotation
Stream device assembly is connect with center purging part by grafting, welding or screw thread twist-on；
The quantity of the fuel injection blade is 10；The number of first fuel injection hole on every fuel injection blade
Amount is every 6, blade, and the quantity of the second fuel injection hole is 2 on every fuel injection blade, shape be it is round, rectangular,
Ellipse or other shapes；The quantity of swirl vane is 10；The quantity of the axial passage is 10；The diffused fuel spray
The quantity in hole is 10, and diffused fuel spray orifice is inclined hole or straight inclined hole with rotation direction.
The operation principle of apparatus of the present invention is：
When work, when light a fire 20% or less load of operating mode when, gas fuel from the second diffusion fuel passage flow into fuel
Ejection assemblies are successively behind radial cavities, axial passage, the first diffusion fuel passage, diffused fuel hole, from portion's divergent nozzle
It sprays, the compressed air come out with premix ring cavity is burnt on nozzle face downstream side blending side, is formed and is stablized diffusion flame；
When switching operating mode 20%-35% loads, part of fuel enters from the second diffusion fuel passage, is formed and stablizes diffusion
Flame, premix fuel is logical in premix fuel channel inflow first outside premix fuel channel and second out of second for another part fuel
Fuel channel is premixed outside road and first, is sprayed from the second fuel injection hole and the first fuel injection hole, with the first compressed air stream
The compressed air of rotating ring intracavitary is mixed, and radially even fuel tape is formed, by the swirler assembly in downstream, by fuel
The radially uniform fuel tape that ejection assemblies are formed is by rotational flow, by diameter in the premix ring cavity positioned at swirler assembly downstream
It is circumferentially uniformly mixed with air to dense fuel tape, ensures that unit two divides the uniformity of swirl-flow premixed burner noz(zle) outlet fuel,
Unit two divides swirl-flow premixed burner noz(zle) downstream to form recirculating zone and stablize diffusion and premixed combustion flame, in the process, by
Decrescence lack the second diffusion fuel passage fuel flow rate, increases and premix premix fuel channel outside fuel channel and second in second
Fuel quantity divides swirl-flow premixed burner noz(zle) downstream to form recirculating zone until the second diffusion fuel passage flow is zero in unit two
With stablize premixed combustion flame；
When premix operation 35%-100% loads, all fuel premix combustion out of second outside premix fuel channel and second
Material channel flows into unit two and premix fuel channel and first in first in swirl-flow premixed burner noz(zle) is divided to premix fuel channel outside, from
Second fuel injection hole and the first fuel injection hole spray, and are mixed with the compressed air of the first compressed air stream rotating ring intracavitary
It closes, forms radially even fuel tape, by the swirler assembly in downstream, the radially uniform combustion that fuel injection assemblies are formed
Material strip is circumferentially mixed radial dense fuel tape with air in the premix ring cavity positioned at swirler assembly downstream by rotational flow
Uniformly, ensure that unit two divides the uniformity of swirl-flow premixed burner noz(zle) outlet fuel, divide swirl-flow premixed burner noz(zle) in unit two
Downstream forms recirculating zone and stablizes premixed combustion flame, and by adjusting, premix fuel is logical outside premix fuel channel and second in second
The fuel quantity ratio in road, adjustment unit two divides swirl-flow premixed burner noz(zle) outlet fuel radially distributed, so as to adjust NOXPollution
Discharge；
Divide in each operating mode of swirl-flow premixed burner noz(zle) in unit two, most compressed airs pass through the first compressed air
Flow annulus, the second air flow annulus and premix ring cavity are mixed to form the uniform premix gas with eddy flow with fuel；Fraction
Compressed air is purged logical by the compressed air inlet channel in swirl vane to swirler assembly central passage and central circular
Road blows out from end face purge hole, divides swirl-flow premixed burner noz(zle) end face to be damaged by high-temperature flue gas calcination for protection location two；
The present invention has following advantageous effect：
One, fuel injection assemblies include outer cover, centerbody and are uniformly circumferentially arranged in more between outer cover and centerbody
A symmetrical low flow resistance blade, by the teasehole of symmetrical low flow resistance blade both sides by fuel injection between outer cover and centerbody
Air in ring cavity and in ring cavity is mixed, and radially even fuel tape is formed；
Two, the symmetrically arranged multiple fuel injection blades of fuel injection assemblies, which is low flow resistance blade, in its leading edge
Flow velocity maximum has set the first fuel injection hole and the second fuel injection hole, is conducive to increase fuel column Jet Penetration Depth, is formed wide
Radially even fuel tape, increase premix uniformity；
Three, swirler assembly includes outer cover, centerbody and is uniformly circumferentially arranged in multiple between outer cover and centerbody
Swirl vane, swirler assembly are located at fuel injection assemblies downstream, and function is the radially uniform combustion for forming fuel injection assemblies
Radial dense fuel tape is uniformly mixed with air in the premix ring cavity positioned at cyclone downstream, is protected by rotational flow by material strip
Card unit two divides the uniformity of swirl-flow premixed burner noz(zle) outlet fuel, divides swirl-flow premixed burner noz(zle) downstream to realize in unit two
Fuel and air uniform premixed combustion, reduce combustion zone highest flame temperature, to reduce the disposal of pollutants of combustion chamber；
Four, blade Heterogeneous Permutation in fuel injection assemblies and swirler assembly, ensures that fuel injection assemblies are formed by diameter
It is located among swirl vane to fuel tape so that fuel concentration is less than Flammability limits in swirl vane surface and tail, greatly
Reduce the possibility that unit two divides swirl-flow premixed burner noz(zle) to be tempered, be furious；
Five, the fuel channel being arranged in the low flow resistance blade of fuel injection assemblies, each fuel channel correspond to accordingly on edge
The teasehole of blade height direction arrangement, the fuel flow rate of each fuel channel is entered by adjusting, it will be able to which control and adjusting are single
The radial fuel concentration distribution of first two points of swirl-flow premixed burner noz(zle)s, reaches the mesh for adjusting nozzle discharge performance and combustion characteristics
's；
Six, divide swirl-flow premixed burner noz(zle) exit end face to be equipped with divergent nozzle in invention unit two, compressed with ring cavity empty
Gas coordinates, and the recirculating zone formed using ring cavity eddy flow and centerbody is formed and stablizes diffusion combustion, and expansion unit two divides swirl-flow premixed
Burner noz(zle) stablizes the load range of burning, especially solves the problems, such as flameholding when gas turbine underload；
Seven, divide swirl-flow premixed burner noz(zle) to be provided with center in invention unit two and purge part, center purging part end face is set
There is more intensive purge hole, high-temperature fuel gas calcination centerbody surface can be prevented, cause centerbody surface damage, purging air
It is directed to the cavity compressed air of head of combustion chamber, purging air channel is entered by the channel in swirl vane, is tied
Structure is simple, and probability of malfunction is small.
Description of the drawings
Fig. 1 is that unit two divides swirl-flow premixed burner noz(zle) front view；
Fig. 2 is that unit two divides swirl-flow premixed burner noz(zle) to remove outer cover 5, fuel injection assemblies shell 1-3 and cyclone group
Front view after part shell 2-3；
Fig. 3 is that unit two divides swirl-flow premixed burner noz(zle) sectional view；
Fig. 4 is the front view of fuel injection assemblies 1；
Fig. 5 is the left view of fuel injection assemblies 1；
Fig. 6 be fuel injection assemblies 1 A-A to fold sectional view；
Fig. 7 is the front view of swirler assembly 2；
Fig. 8 is the left view of swirler assembly 2；
Fig. 9 is that the B-B direction of swirler assembly 2 folds sectional view.
Specific implementation mode
Technical solution of the present invention is not limited to act specific implementation mode set forth below, further includes between each specific implementation mode
Arbitrary reasonable combination.
Specific implementation mode one：Illustrate that present embodiment, a kind of gas turbine dry of present embodiment are low in conjunction with Fig. 1~9
Contamination combustion chamber unit two divides swirl-flow premixed burner noz(zle), including fuel injection assemblies 1, swirler assembly 2, end diffusion spray
Mouth 3, center purging part 4, outer cover 5, the first pipe fitting 6, the second pipe fitting 7 and third pipe fitting 8；
The fuel injection assemblies 1, swirler assembly 2, end divergent nozzle 3, center purging part 4, outer cover 5, first are managed
Part 6, the second pipe fitting 7 and third pipe fitting 8 are coaxial；Second pipe fitting 7 is set to inside the first pipe fitting 6, and third pipe fitting 8 is set to second
Inside pipe fitting 7, the first pipe fitting 6, the second pipe fitting 7 and third pipe fitting 8 are set to the left side of fuel injection assemblies 1, and respectively with fuel
Ejection assemblies 1 connect；1 right side of fuel injection assemblies is provided with swirler assembly 2；2 right side of swirler assembly is provided with end expansion
Dissipate nozzle 3, center purging part 4 and outer cover 5；End divergent nozzle 3 is set to inside outer cover 5, and center purging part 4 is set to end
Inside divergent nozzle 3；First pipe fitting 6 and the second pipe fitting 7 form premix fuel channel 6-1 outside second, the second pipe fitting 7 and third pipe
Part 8 forms premix fuel channel 7-1 in second；8 inside of third pipe fitting is the second diffusion fuel passage 8-1；
The fuel injection assemblies 1 include several fuel injection blade 1-1, tubular fuel injection assemblies centerbody 1-2 and
Fuel injection assemblies shell 1-3；Fuel injection blade 1-1 is uniformly arranged around fuel injection assemblies centerbody 1-2 is circumferentially equidistant；
Fuel injection assemblies centerbody 1-2 and fuel injection assemblies shell 1-3 constitute the first compressed air flow annulus 1-4；Fuel sprays
It is burner noz(zle) central passage 1-9 to penetrate the centers component centerbody 1-2；Fuel injection blade 1-1 leading edges both sides are provided with along blade
Fuel channel 1-5 is premixed outside the first of short transverse, is internally provided with along the first of blade height direction and is premixed fuel channel
1-6；It is the first fuel injection hole for being set to the both sides fuel injection blade 1-1 that premix fuel channel 1-5 is externally ported outside first
1-7, first premixes fuel channel 1-5 outside is connected to premix fuel channel 6-1 outside second；In first outside premix fuel channel 1-6
Portion outlet is to be set to the second fuel injection hole 1-8 of the both sides fuel injection blade 1-1, in first premix fuel channel 1-6 with
Premix fuel channel 7-1 connections in second, fuel premix premix fuel channel 7-1 in fuel channel 6-1 and second outside second
It respectively enters and premixes fuel channel 1-6 in premix fuel channel 1-5 and first outside first, finally along the first fuel injection hole 1-7
It is sprayed with the second fuel injection hole 1-8；The burner noz(zle) central passage 1-9 and the second diffusion fuel passage 8-1 connections；
The swirler assembly 2 includes several swirl vane 2-1, tubular swirler assembly centerbody 2-2 and cyclone group
Part shell 2-3；Swirl vane 2-1 is uniformly arranged around swirler assembly centerbody 2-2 is circumferentially equidistant；Swirl vane 2-1 and combustion
Material eject blade 1-1 is equidistantly shifted to install；Swirler assembly centerbody 2-2 and swirler assembly shell 2-3 constitutes the second pressure
Stream of compressed air rotating ring chamber 2-4；The centers swirler assembly centerbody 2-2 are swirler assembly central passage 2-6, in swirler assembly
The several axial passage 2-8s parallel with swirler assembly central passage 2-6 are provided on heart body 2-2 barrels, swirler assembly 2 is left
End is provided with the circular cavity 2-7 coaxial with swirler assembly central passage 2-6；It is provided with compressed air in swirl vane 2-1
Inlet channel 2-5, compressed air inlet channel 2-5 extend out to swirler assembly shell 2-3, extend inwardly to cyclone group
Part central passage 2-6, wherein axial passage 2-8 are not connected to compressed air inlet channel 2-5；
3 right side of end divergent nozzle is provided with several diffused fuel spray orifice 3-1, end divergent nozzle 3 and center
Purging part 4 forms the first diffusion fuel passage 3-2 of annular, and premix ring cavity 3-3 is formed between end divergent nozzle 3 and outer cover 5；
4 right side of the center purging part is provided with several purge hole 4-1, and circle is blown centered on 4 inside of purging part of center
Sweep channel 4-2；Central circular purge passage 4-2 is connected to swirler assembly central passage 2-6.
Present embodiment has following advantageous effect：
One, fuel injection assemblies include outer cover, centerbody and are uniformly circumferentially arranged in more between outer cover and centerbody
A symmetrical low flow resistance blade, by the teasehole of symmetrical low flow resistance blade both sides by fuel injection between outer cover and centerbody
Air in ring cavity and in ring cavity is mixed, and radially even fuel tape is formed；
Two, the symmetrically arranged multiple fuel injection blades of fuel injection assemblies, which is low flow resistance blade, in its leading edge
Flow velocity maximum has set the first fuel injection hole and the second fuel injection hole, is conducive to increase fuel column Jet Penetration Depth, is formed wide
Radially even fuel tape, increase premix uniformity；
Three, swirler assembly includes outer cover, centerbody and is uniformly circumferentially arranged in multiple between outer cover and centerbody
Swirl vane, swirler assembly are located at fuel injection assemblies downstream, and function is the radially uniform combustion for forming fuel injection assemblies
Radial dense fuel tape is uniformly mixed with air in the premix ring cavity positioned at cyclone downstream, is protected by rotational flow by material strip
Card unit two divides the uniformity of swirl-flow premixed burner noz(zle) outlet fuel, divides swirl-flow premixed burner noz(zle) downstream to realize in unit two
Fuel and air uniform premixed combustion, reduce combustion zone highest flame temperature, to reduce the disposal of pollutants of combustion chamber；
Four, blade Heterogeneous Permutation in fuel injection assemblies and swirler assembly, ensures that fuel injection assemblies are formed by diameter
It is located among swirl vane to fuel tape so that fuel concentration is less than Flammability limits in swirl vane surface and tail, greatly
Reduce the possibility that unit two divides swirl-flow premixed burner noz(zle) to be tempered, be furious；
Five, the fuel channel being arranged in the low flow resistance blade of fuel injection assemblies, each fuel channel correspond to accordingly on edge
The teasehole of blade height direction arrangement, the fuel flow rate of each fuel channel is entered by adjusting, it will be able to which control and adjusting are single
The radial fuel concentration distribution of first two points of swirl-flow premixed burner noz(zle)s, reaches the mesh for adjusting nozzle discharge performance and combustion characteristics
's；
Six, swirl-flow premixed burner noz(zle) exit end face is divided to be equipped with divergent nozzle in present embodiment unit two, with ring cavity pressure
Contracting air coordinates, and the recirculating zone formed using ring cavity eddy flow and centerbody is formed and stablizes diffusion combustion, is expanded unit two and is divided eddy flow
Premixed combustion nozzle stablizes the load range of burning, especially solves the problems, such as flameholding when gas turbine underload；
Seven, divide swirl-flow premixed burner noz(zle) to be provided with center in present embodiment unit two and purge part, center purges part end
Face is equipped with more intensive purge hole, can prevent high-temperature fuel gas calcination centerbody surface, cause centerbody surface damage, purges
Air is directed to the cavity compressed air of head of combustion chamber, and it is logical to enter purging air by the channel in swirl vane
Road, simple in structure, probability of malfunction is small.
Specific implementation mode two：Embodiment is described with reference to Fig. 2, and present embodiment is different from specific implementation mode one
It is：The first fuel injection hole 1-7 export directions are perpendicular to fuel injection blade 1-1 or to fuel injection blade 1-1 rears
It tilts；The second fuel injection hole 1-8 export directions are perpendicular to fuel injection blade 1-1 or to after fuel injection blade 1-1
Edge tilts.Other steps and parameter are same as the specific embodiment one.
Specific implementation mode three：Embodiment is described with reference to Fig. 3, and present embodiment and specific implementation mode one or two are not
Be：The length of the premix ring cavity 3-3 is L1, divergent nozzle 3 right side in end is L at a distance from 5 right side of outer cover2, lead to
Overregulate L1The mixed characteristic that swirl-flow premixed burner noz(zle) can be adjusted, by adjusting L2May be implemented adjust flame holding and
The function of flame profile is constrained, it can also be by adjusting premix fuel channel 7-1 in second outside premix fuel channel 6-1 and second
Between fuel flow rate ratio, adjustment unit two divides swirl-flow premixed burner noz(zle) Fuel-air premix concentration radial distribution.Other
Step and parameter are the same as one or two specific embodiments.
Specific implementation mode four：Illustrate present embodiment in conjunction with Fig. 4~9, present embodiment and specific implementation mode one to
Unlike one of three：The fuel injection assemblies 1 and swirler assembly 2 are whole precision castings or weldment.Other steps and
Parameter is identical as one of specific implementation mode one to three.
Specific implementation mode five：Embodiment is described with reference to Fig. 3, present embodiment and specific implementation mode one to four it
Unlike one：The fuel injection assemblies 1 are connected through a screw thread or are welded to connect with swirler assembly 2；Swirler assembly 2 with
End divergent nozzle 3 is connected through a screw thread or is welded to connect；Swirler assembly 2 passes through grafting, welding or spiral shell with center purging part 4
Line twist-on connects.Other steps and parameter are identical as one of specific implementation mode one to four.
Specific implementation mode six：Illustrate present embodiment in conjunction with Fig. 1~9, present embodiment and specific implementation mode one to
Unlike one of five：The quantity of the fuel injection blade 1-1 is 10；Every fuel injection blade 1-1 upper first
The quantity of fuel injection hole 1-7 is every 6, blade, the quantity of every upper second fuel injection hole 1-8 of fuel injection blade 1-1
It it is 2, shape is round, rectangular or oval；The quantity of swirl vane 2-1 is 10；The quantity of the axial passage 2-8 is
10；The quantity of the diffused fuel spray orifice 3-1 is 10, and diffused fuel spray orifice 3-1 is inclined hole or straight inclined hole with rotation direction.
Other steps and parameter are identical as one of specific implementation mode one to five.
Claims (4)
1. a kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle), it is characterised in that：The combustion
Gas-turbine dry low NO_x combustor unit two divides swirl-flow premixed burner noz(zle) to include fuel injection assemblies (1), cyclone group
Part (2), end divergent nozzle (3), center purging part (4), outer cover (5), the first pipe fitting (6), the second pipe fitting (7) and third pipe fitting
(8)；
The fuel injection assemblies (1), swirler assembly (2), end divergent nozzle (3), center purging part (4), outer cover (5),
First pipe fitting (6), the second pipe fitting (7) and third pipe fitting (8) are coaxial；Second pipe fitting (7) is set to the first pipe fitting (6) inside, the
Three pipe fittings (8) are set to the second pipe fitting (7) inside, and the first pipe fitting (6), the second pipe fitting (7) and third pipe fitting (8) are set to fuel
On the left of ejection assemblies (1), and it is connect respectively with fuel injection assemblies (1)；It is provided with cyclone group on the right side of fuel injection assemblies (1)
Part (2)；End divergent nozzle (3), center purging part (4) and outer cover (5) are provided on the right side of swirler assembly (2)；It spreads end
Nozzle (3) is set to outer cover (5) inside, and it is internal that center purging part (4) is set to end divergent nozzle (3)；First pipe fitting (6) with
Second pipe fitting (7) forms premix fuel channel (6-1) outside second, and the second pipe fitting (7) forms premix in second with third pipe fitting (8)
Fuel channel (7-1)；It is the second diffusion fuel passage (8-1) inside third pipe fitting (8)；
The fuel injection assemblies (1) include several fuel injection blades (1-1), tubular fuel injection assemblies centerbody (1-2)
With fuel injection assemblies shell (1-3)；Fuel injection blade (1-1) is circumferentially equidistant around fuel injection assemblies centerbody (1-2)
It is uniformly arranged；Fuel injection assemblies centerbody (1-2) and fuel injection assemblies shell (1-3) constitute the first compressed air stream rotating ring
Chamber (1-4)；The center fuel injection assemblies centerbody (1-2) is burner noz(zle) central passage (1-9)；Fuel injection blade (1-1)
Leading edge both sides, which are provided with outside the first of blade height direction, premixes fuel channel (1-5), is internally provided with along blade height side
To first in premix fuel channel (1-6)；It is to be set to fuel injection leaf that premix fuel channel (1-5) is externally ported outside first
First fuel injection hole (1-7) of the both sides piece (1-1), first premixes premix fuel channel outside fuel channel (1-5) and second outside
(6-1) is connected to；It is to be set to the second of the both sides fuel injection blade (1-1) that premix fuel channel (1-6) is externally ported in first
Fuel injection hole (1-8), in first premix fuel channel (1-6) with premix fuel channel (7-1) in second and be connected to, fuel is along the
Premix fuel channel (7-1) respectively enters premix fuel channel (1-5) outside first in premix fuel channel (6-1) and second outside two
With the first interior premix fuel channel (1-6), finally sprayed along the first fuel injection hole (1-7) and the second fuel injection hole (1-8)；
The burner noz(zle) central passage (1-9) is connected to the second diffusion fuel passage (8-1)；
The swirler assembly (2) includes several swirl vanes (2-1), tubular swirler assembly centerbody (2-2) and cyclone
Package shell (2-3)；Swirl vane (2-1) is uniformly arranged around swirler assembly centerbody (2-2) is circumferentially equidistant；Swirl vane
(2-1) is equidistantly shifted to install with fuel injection blade (1-1)；Swirler assembly centerbody (2-2) and swirler assembly shell
(2-3) constitutes the second compressed air flow annulus (2-4)；The center swirler assembly centerbody (2-2) is swirler assembly center
Channel (2-6) is provided with the number parallel with swirler assembly central passage (2-6) on swirler assembly centerbody (2-2) barrel
A axial passage (2-8), it is empty that swirler assembly (2) left end is provided with the circle coaxial with swirler assembly central passage (2-6)
Chamber (2-7)；Compressed air inlet channel (2-5) is provided in swirl vane (2-1), compressed air inlet channel (2-5) is outside
Swirler assembly shell (2-3) is extended to, swirler assembly central passage (2-6), wherein axial passage (2-8) are extended inwardly to
It is not connected to compressed air inlet channel (2-5)；
End divergent nozzle (3) right side is provided with several diffused fuel spray orifices (3-1), end divergent nozzle (3) and in
The heart purges the first diffusion fuel passage (3-2) that part (4) forms annular, is formed between end divergent nozzle (3) and outer cover (5) pre-
Mixed ring cavity (3-3)；
Center purging part (4) right side is provided with several purge holes (4-1), and center purges circle centered on part (4) inside
Purge passage (4-2)；Central circular purge passage (4-2) is connected to swirler assembly central passage (2-6)；
First fuel injection hole (1-7) export direction is perpendicular to fuel injection blade (1-1) or to fuel injection blade (1-
1) rear tilts；Second fuel injection hole (1-8) export direction is perpendicular to fuel injection blade (1-1) or to fuel injection
Blade (1-1) rear tilts；
The fuel injection assemblies (1) are connected through a screw thread or are welded to connect with swirler assembly (2)；Swirler assembly (2) with
End divergent nozzle (3) is connected through a screw thread or is welded to connect；Swirler assembly (2) passes through grafting, weldering with center purging part (4)
It connects or screw thread twist-on connects.
2. gas turbine dry low pollution combustor unit two according to claim 1 divides swirl-flow premixed burner noz(zle),
It is characterized in that：The length of the premix ring cavity (3-3) is L1, end divergent nozzle (3) right side and outer cover (5) right side
Distance is L2, by adjusting L1The mixed characteristic that swirl-flow premixed burner noz(zle) can be adjusted, by adjusting L2It may be implemented to adjust fire
The function of flame stability and constraint flame profile, can also be by adjusting pre- in second outside premix fuel channel (6-1) and second
Fuel flow rate ratio between mixed fuel channel (7-1), adjustment unit two divide swirl-flow premixed burner noz(zle) Fuel-air premix dense
Spend radial distribution.
3. gas turbine dry low pollution combustor unit two according to claim 1 divides swirl-flow premixed burner noz(zle),
It is characterized in that：The fuel injection assemblies (1) and swirler assembly (2) are whole precision castings or weldment.
4. gas turbine dry low pollution combustor unit two according to claim 1 divides swirl-flow premixed burner noz(zle),
It is characterized in that：The quantity of the fuel injection blade (1-1) is 10；First on every fuel injection blade (1-1)
The quantity of fuel injection hole (1-7) is every 6, blade, the second fuel injection hole (1-8) on every fuel injection blade (1-1)
Quantity be 2, shape be it is round, rectangular or oval；The quantity of swirl vane (2-1) is 10；Axial passage (the 2-
8) quantity is 10；The quantity of the diffused fuel spray orifice (3-1) is 10, and diffused fuel spray orifice (3-1) is with rotation direction
Inclined hole or straight inclined hole.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610551146.4A CN106016364B (en) | 2016-07-13 | 2016-07-13 | A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610551146.4A CN106016364B (en) | 2016-07-13 | 2016-07-13 | A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) |
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| Publication Number | Publication Date |
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| CN106016364A CN106016364A (en) | 2016-10-12 |
| CN106016364B true CN106016364B (en) | 2018-07-27 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109210535A (en) * | 2018-09-11 | 2019-01-15 | 中国人民解放军国防科技大学 | Supersonic jet flame stabilizing device |
| CN109519919B (en) * | 2018-09-25 | 2024-05-07 | 天津大学 | Cracking-proof ceramic flame cyclone for methanol burner |
| CN111059573B (en) * | 2019-12-31 | 2024-06-04 | 新奥能源动力科技（上海）有限公司 | Gas turbine combustor and gas turbine |
| CN112082175B (en) * | 2020-10-16 | 2024-08-27 | 中国科学院上海高等研究院 | Fuel nozzle of gas turbine |
| CN113701194B (en) * | 2021-08-16 | 2022-11-22 | 中国航发沈阳发动机研究所 | Premixing device for combustion chamber of gas turbine |
| CN113606607B (en) * | 2021-08-20 | 2023-05-16 | 中国联合重型燃气轮机技术有限公司 | Nozzle, and combustion chamber and gas turbine having the same |
| CN114811656A (en) * | 2022-05-19 | 2022-07-29 | 上海和兰透平动力技术有限公司 | Fuel nozzle |
| CN115451432B (en) * | 2022-09-22 | 2024-03-12 | 中国联合重型燃气轮机技术有限公司 | Micro-mixing nozzle assembly and system for fuel in combustion chamber of gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6993916B2 (en) * | 2004-06-08 | 2006-02-07 | General Electric Company | Burner tube and method for mixing air and gas in a gas turbine engine |
| US7836698B2 (en) * | 2005-10-20 | 2010-11-23 | General Electric Company | Combustor with staged fuel premixer |
| US20080083224A1 (en) * | 2006-10-05 | 2008-04-10 | Balachandar Varatharajan | Method and apparatus for reducing gas turbine engine emissions |
| US7908864B2 (en) * | 2006-10-06 | 2011-03-22 | General Electric Company | Combustor nozzle for a fuel-flexible combustion system |
| US20080276622A1 (en) * | 2007-05-07 | 2008-11-13 | Thomas Edward Johnson | Fuel nozzle and method of fabricating the same |
| US20090056336A1 (en) * | 2007-08-28 | 2009-03-05 | General Electric Company | Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine |
| CN205825112U (en) * | 2016-07-13 | 2016-12-21 | 哈尔滨汽轮机厂有限责任公司 | A kind of two points of swirl-flow premixed burner noz(zle)s of gas turbine dry low pollution combustor unit |
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Effective date of registration: 20221220 Address after: 150000 building 3, high tech production base, Nangang District, Harbin City, Heilongjiang Province Patentee after: HARBIN TURBINE Co.,Ltd. Patentee after: HADIAN POWER EQUIPMENT NATIONAL ENGINEERING RESEARCH CENTER CO.,LTD. Address before: 150046 No. three power road 345, Xiangfang District, Heilongjiang, Harbin Patentee before: HARBIN TURBINE Co.,Ltd. |