CN106090914A - Combustion nozzle and injection method thereof - Google Patents
Combustion nozzle and injection method thereof Download PDFInfo
- Publication number
- CN106090914A CN106090914A CN201610380783.XA CN201610380783A CN106090914A CN 106090914 A CN106090914 A CN 106090914A CN 201610380783 A CN201610380783 A CN 201610380783A CN 106090914 A CN106090914 A CN 106090914A
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- pure oxygen
- fuel
- nozzle body
- zle
- barrier film
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/60—Devices for simultaneous control of gas and combustion air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/62—Mixing devices; Mixing tubes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The present invention provides a combustion nozzle and a method of injecting the same, the combustion nozzle comprising: a nozzle body having a fuel inlet and a pure oxygen inlet at one end thereof and a plurality of diaphragm outer chambers formed at the other end thereof; wherein, a fuel channel is arranged in the nozzle body, one end of the fuel channel is communicated with the fuel inlet, the other end of the fuel channel is communicated with the plurality of diaphragm outer cavities through a plurality of fuel inclined holes, and the fuel inclined holes are arranged in an inclined way along the radial direction of the injection direction of the fuel; the nozzle body is also internally provided with a pure oxygen channel, one end of the pure oxygen channel is communicated with the pure oxygen inlet, the other end of the pure oxygen channel is communicated with the plurality of diaphragm outer cavities through a plurality of pure oxygen inclined holes, and the pure oxygen inclined holes are arranged along the radial inward inclination of the injection direction of the pure oxygen. The combustion nozzle and the injection method thereof can uniformly atomize the pure oxygen and the natural gas, so that the uniformly atomized pure oxygen and the uniformly atomized natural gas can be fully combusted in the generator.
Description
Technical field
The present invention is related to a kind of nozzle and injection method thereof, more particularly to the combustion in a kind of high-pressure combustion technical field
Burn nozzle and injection method thereof.
Background technology
Multielement hot fluid technology heating power heavy crude producing is the very efficient new technology of one, its have efficiency of combustion high, zero
Carbon injects the advantage of environmental protection and energy saving, and the high temperature polyol hot fluid of multielement hot fluid technology export has comprehensive stimulation machanism, can be big
Width improves single well productivity and improves oil recovery factor.
Multielement hot fluid technology is exploited for oil-sand, and its Core equipment is generator, at present, many to the output of this generator
Unit's hot fluid component requirements removes nitrogen or reduces nitrogen content, mainly by with the pure oxygen of oxygen content more than 90% and natural gas
The mode blending realizes the clean-burning needs of high pressure.
The burner noz(zle) of this generator is to realize pure oxygen, the clean-burning core component of natural gas high temperature, in prior art,
The easy scaling loss of nozzle that this generator is used, and blend pure oxygen, natural gas effect bad, be easily caused combustion instability.
Therefore, it is necessary to provide a kind of new nozzle and injection method, overcome drawbacks described above.
Content of the invention
It is an object of the invention to provide a kind of burner noz(zle), pure oxygen and natural gas can be carried out uniform atomizing, make homogeneous by it
The pure oxygen of atomization and natural gas fully burn in generator, and this burner noz(zle) is rational in infrastructure, safe and reliable, service life is long.
It is a further object of the present invention to provide a kind of injection method, pure oxygen and natural gas can be carried out uniformly by this injection method
Atomization, makes the pure oxygen of homogeneous atomization and natural gas fully burn in generator.
The above-mentioned purpose of the present invention can use following technical proposal to realize:
The present invention provides a kind of burner noz(zle), and described burner noz(zle) includes:
Nozzle body, its one end has fuel inlet and pure oxygen inlet, and its other end is formed with multiple barrier film exocoel；
Wherein, being provided with fuel channel in described nozzle body, one end of described fuel channel is connected with described fuel inlet
Logical, its other end is connected with multiple described barrier film exocoels by multiple fuel inclined holes, and described fuel inclined hole is along the injection of fuel
Direction is radially outwardly sloping setting；Being additionally provided with pure oxygen passage in described nozzle body, one end of described pure oxygen passage is pure with described
Oxygen entrance is connected, and the other end of described pure oxygen passage is connected with multiple described barrier film exocoels by multiple pure oxygen inclined holes, institute
The injection direction stating pure oxygen inclined hole along pure oxygen is radially-inwardly obliquely installed.
In a preferred embodiment, described pure oxygen passage is circular passage, and described pure oxygen passage encloses and is located at described fuel
The periphery of passage.
In a preferred embodiment, the ratio of the diameter with described pure oxygen inclined hole for the ring cavity width of described pure oxygen passage is
2.83。
In a preferred embodiment, the diameter of described fuel channel and the ratio of the diameter of described fuel inclined hole are 2.0.
In a preferred embodiment, multiple described barrier film exocoels are circumferentially disposed in the end of described nozzle body
Face, the outer contour shape of described barrier film exocoel is fan shape, and the central angle of described sector is 60 °～90 °.
In a preferred embodiment, described barrier film exocoel is the spherical groove being arranged on described nozzle body end, institute
The spherical radius stating spherical groove is 50mm～100mm.
In a preferred embodiment, institute between the outward flange tangent line of described spherical groove and the end face of described nozzle body
The acute angle being formed is 5 °～15 °.
In a preferred embodiment, multiple described pure oxygen inclined holes are circumferentially spaced is arranged on described nozzle body
In, the acute angle being formed between the axis of described pure oxygen inclined hole and the axis of described nozzle body is 15 °～45 °.
In a preferred embodiment, multiple described fuel inclined holes are circumferentially spaced is arranged on described nozzle body
In, the obtuse angle being formed between the axis of described fuel inclined hole and the axis of described nozzle body is 135 °～175 °.
In a preferred embodiment, a diameter of 1.25mm～4.35mm of described pure oxygen inclined hole；Described fuel inclined hole
A diameter of 0.25mm～1.35mm.
The present invention also provides the injection method of a kind of above-mentioned burner noz(zle), and described injection method comprises the steps:
A) in the fuel channel of nozzle body, inject natural gas, inject pure in the pure oxygen passage of described nozzle body
Oxygen；
B) described natural gas radially outward sprays multiple barrier film exocoels of described nozzle body through multiple fuel inclined holes, described
Pure oxygen radially-inwardly sprays the multiple described barrier film exocoel of described nozzle body by multiple pure oxygen inclined holes.
In a preferred embodiment, in described step b), described natural gas is after the ejection of described fuel inclined hole, in institute
Form a grate firing material membrane layer in stating barrier film exocoel.
In a preferred embodiment, the thickness of described fuel membrane layer is 0.5mm～1.5mm.
The feature of the burner noz(zle) of the present invention and injection method thereof and advantage be:
First, the present invention is oblique by pure oxygen inclined hole and the fuel being radially outwardly sloping setting being radially-inwardly obliquely installed
Hole, it is ensured that from nozzle body ejection pure oxygen and natural gas fully blend atomization, be effectively ensured natural gas ejection after with pure
The head-on collision of oxygen blends；In addition, by the multiple barrier film exocoels being arranged on nozzle body end face, the sky from the ejection of fuel inclined hole can be made
Right gas forms a grate firing material membrane layer in barrier film exocoel, and pure oxygen, natural gas high-temp combustion can be radiated by this fuel membrane layer
Heat is taken away, and has effectively completely cut off pure oxygen and directly contacting under nozzle body high temperature, has improve the service life of burner noz(zle).
2nd, the present invention is by designing and to combustion with the ratio of the diameter of pure oxygen inclined hole to the ring cavity width of pure oxygen passage
The diameter of material passage and the ratio design of the diameter of fuel inclined hole, can make the natural gas from nozzle body ejection and pure oxygen, according to
After certain proportioning and speed head-on collision blend, fully burn in the combustion chamber of generator and generate carbon dioxide, in combustion product
Nitrogen content is few, meets the requirement of later stage production operation.
3rd, the present invention is by being designed as spherical groove shape by barrier film exocoel, and natural gas can be made to spray into barrier film from fuel inclined hole
It after exocoel, is interior receipts during the end face of natural gas exits nozzle body in the barrier film exocoel of spherical groove shape, whole afterwards skies
Right gas blends delivery nozzle body the end face leaving nozzle body with the pure oxygen head-on collision from the ejection of pure oxygen inclined hole, is pure oxygen, natural
Fully burning in the combustion chamber of generator for the gas provides safeguard.
Brief description
For the technical scheme being illustrated more clearly that in the embodiment of the present invention, required in embodiment being described below make
Accompanying drawing be briefly described, it should be apparent that, below describe in accompanying drawing be only some embodiments of the present invention, for
From the point of view of those of ordinary skill in the art, on the premise of not paying creative work, can also be obtained other according to these accompanying drawings
Accompanying drawing.
Fig. 1 is the sectional structure schematic diagram of the burner noz(zle) of the present invention.
Fig. 2 is the stereogram of the embodiment one of the burner noz(zle) of the present invention.
Fig. 3 is the stereogram of the embodiment two of the burner noz(zle) of the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Describe, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments wholely.Based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of not making creative work
Embodiment, broadly falls into the scope of protection of the invention.
Embodiment one
As shown in Figure 1 to Figure 3, the present invention provides a kind of burner noz(zle), and it includes nozzle body 1, the one of this nozzle body 1
End has fuel inlet 11 and pure oxygen inlet 12, and its other end is formed with multiple barrier film exocoel 13；Wherein, described nozzle body 1
Inside being provided with fuel channel 14, one end of described fuel channel 14 is connected with described fuel inlet 11, and its other end passes through multiple
Fuel inclined hole 141 is connected with multiple described barrier film exocoels 13, described fuel inclined hole 141 along fuel injection direction radially outward
It is obliquely installed；It is additionally provided with pure oxygen passage 15, one end of described pure oxygen passage 15 and described pure oxygen inlet 12 in described nozzle body 1
Being connected, the other end of described pure oxygen passage 15 is connected with multiple described barrier film exocoels 13 by multiple pure oxygen inclined holes 151, institute
The injection direction stating pure oxygen inclined hole 151 along pure oxygen is radially-inwardly obliquely installed.
Specifically, nozzle body 1 is substantially in cylindrical, and one end is provided with fuel inlet 11 and pure oxygen inlet 12, its
Other end is provided with multiple barrier film exocoel 13.In the present embodiment, this barrier film exocoel 13 is for being arranged on the recessed of nozzle body 1 end
Groove.
Fuel channel 14 is arranged at the central axis of nozzle body 1, and its one end is connected with fuel inlet 11, its another
End is communicated with multiple fuel inclined hole 141, and those fuel inclined holes 141 are connected with multiple barrier film exocoels 13 respectively, in the present invention,
The quantity of fuel inclined hole 141 is identical with the quantity of barrier film exocoel 13, each barrier film exocoel 13 correspondence and fuel inclined hole 141 phase
Logical.Those fuel inclined holes 141 are along the circumferential direction arranged in nozzle body 1 at equal intervals, and this fuel inclined hole 141 is along the injection of fuel
Direction is radially outwardly sloping setting, that is, centered on the axis of nozzle body 1, this fuel inclined hole 141 is from nozzle body 1
Axis with radially outward and towards barrier film exocoel 13 direction injection fuel so that fuel is, divergent shape is from nozzle body 1
End face sprays.In the present embodiment, it is used in fuel channel 14 being passed through natural gas gas.
Pure oxygen passage 15 is arranged in nozzle body 1, and in the present embodiment, this pure oxygen passage 15 is circular passage, and this is pure
Oxygen passage 15 encloses the periphery being located at fuel channel 14.In the present invention, one end of nozzle body 1 can be provided with multiple pure oxygen inlet
12, in nozzle body 1, each pure oxygen inlet 12 corresponding can be provided with a pure oxygen and enter passage 152, the one of this pure oxygen passage 15
End enters passage 152 by multiple pure oxygens and is connected with multiple pure oxygen inlet 12, and those pure oxygens enter passage 152 can be for circumferentially
Direction is arranged on the independent through-hole in nozzle body 1 at equal intervals；The other end of this pure oxygen passage 15 is communicated with multiple pure oxygen inclined hole
151, those pure oxygen inclined holes 151 are connected with multiple barrier film exocoels 13 respectively, in the present invention, the quantity of pure oxygen inclined hole 151 with
The quantity of barrier film exocoel 13 is identical, and each barrier film exocoel 13 correspondence communicates with a pure oxygen inclined hole 151.Those pure oxygen inclined holes 151
Along the circumferential direction being arranged at equal intervals in nozzle body 1, this pure oxygen inclined hole 151 radially-inwardly tilts to set along the injection direction of pure oxygen
Putting, that is, centered on the axis of nozzle body 1, this pure oxygen inclined hole 151 is with radially-inwardly and towards the axis of nozzle body 1
Pure oxygen is ejected from barrier film exocoel 13 in direction, so that pure oxygen is the contraction-like end face ejection from nozzle body 1.At the present embodiment
In, it is used for being passed through pure oxygen gas in pure oxygen passage 15, this pure oxygen gas is the pure oxygen gas of oxygen content more than 90%.
The burner noz(zle) of the present invention, can be applicable on pure oxygen composite heat carrier generator, this burner noz(zle) can by pure oxygen and
Natural gas carries out uniform atomizing, makes the pure oxygen of homogeneous atomization and natural gas realize that high pressure fills in pure oxygen composite heat carrier generator
Divided combustion, this burner noz(zle) achieves multielement hot fluid technology answering in oil-sand exploitation on the basis of reducing operating cost
With.
The present invention is oblique by pure oxygen inclined hole 151 and the fuel being radially outwardly sloping setting being radially-inwardly obliquely installed
Hole 141, it is ensured that fully blend atomization from pure oxygen and the natural gas of nozzle body 1 ejection, after natural gas ejection has been effectively ensured
Head-on collision with pure oxygen blends；In addition, by the multiple barrier film exocoels 13 being arranged on nozzle body 1 end face, can make from fuel inclined hole
The natural gas of 141 ejections forms a grate firing material membrane layer, in the present invention, the thickness of this fuel membrane layer in barrier film exocoel 13
For 0.5mm～1.5mm, its can block nozzle body 1 by fire end face directly by fire, this fuel membrane layer can be by pure oxygen, natural
The heat of gas high-temp combustion radiation is taken away, and has effectively completely cut off pure oxygen and directly contacting under nozzle body 1 high temperature, has served reduction
The effect of the metal end surface temperature of nozzle body 1, improves the service life of burner noz(zle).
In one embodiment of the present invention, the ring cavity width D of described pure oxygen passage 15 and described pure oxygen inclined hole 151 is straight
The ratio of footpath R1 is 2.83, that is, D/R1=2.83.Make to be passed through the compression ratio according to 1:8 for the pure oxygen in high pressure in pure oxygen passage 15
Spraying in pure oxygen inclined hole 151 from pure oxygen passage 15, finally injection forms jet and sprays from the barrier film exocoel 13 of nozzle body 1.
Further, the diameter R2 of described fuel channel 14 and the ratio of the diameter R3 of described fuel inclined hole 141 are 2.0,
That is, R2/R3=2.0.The high-pressure natural gas being passed through in fuel channel 14 is made to spray into from fuel channel 14 according to the compression ratio of 1:4
In fuel inclined hole 141, finally injection forms jet and sprays from the barrier film exocoel 13 of nozzle body 1.
The present invention by the ratio design of the ring cavity width D of pure oxygen passage 15 and the diameter R1 of pure oxygen inclined hole 151 and
Ratio design to the diameter R2 of the fuel channel 14 and diameter R3 of fuel inclined hole 141, can make from nozzle body 1 ejection is natural
Gas and pure oxygen, after blending with speed head-on collision according to a certain ratio, fully fire in the combustion chamber of pure oxygen composite heat carrier generator
Burning and generating carbon dioxide, in combustion product, nitrogen content is few, meets the requirement of later stage production operation.
In an embodiment of the invention, multiple described barrier film exocoels 13 are circumferentially disposed in described nozzle originally
The end face of body 1, the outer contour shape of described barrier film exocoel 13 is fan shape, the central angle θ of described sector1It is 60 °～90 °.
Specifically, this barrier film exocoel 13 is to be located at the arc groove by fire end face for the nozzle body 1, as in figure 2 it is shown, at nozzle
The end face of body 1 is provided with four barrier film exocoels 13, and this four barrier film exocoels 13 are along the circumferential direction sequentially connected with；As it is shown on figure 3, should
The end face of nozzle body 1 is provided with eight barrier film exocoels 13, and this eight barrier film exocoels 13 are along the circumferential direction sequentially connected with.Certainly, exist
In other embodiments of the present invention, nozzle body 1 by fire end face according to needs of production can be provided with five, six or other
The barrier film exocoel 13 of quantity, this is not restricted.
From nozzle body 1 by fire end face in terms of, the outer contour shape of this barrier film exocoel 13 is fan shape, be sparged into every
Gas flow in film exocoel 13 is fan shape flowing, the central angle θ of this sector1It is 60 °～90 °, central angle θ1Size
Can be according to being arranged on nozzle body 1 by depending on the quantity of the barrier film exocoel 13 in fire end face.
Further, in the present invention, this barrier film exocoel 13 is the spherical groove being arranged on nozzle body 1 end, this ball
The spherical radius of face groove is 50mm～100mm.The outward flange tangent line F of this spherical groove and nozzle body 1 by fire end face it
Between the acute angle theta that formed2It is 5 °～15 °.
The present invention by barrier film exocoel 13 is designed as spherical groove shape, can make natural gas from fuel inclined hole 141 spray into every
After film exocoel 13, natural gas can form natural gas air film along spherical-concave-surface, and this natural gas air film is fuel membrane layer, and natural
Gas in the barrier film exocoel 13 of spherical groove shape exits nozzle body 1 by fire end face when be interior receipts, afterwards all natural gas
With spray from pure oxygen inclined hole 151 pure oxygen head-on collision blend delivery nozzle body 1 and leave nozzle body 1 by fire end face, be pure oxygen,
Fully burning in the combustion chamber of generator for the natural gas provides safeguard.
In an embodiment of the invention, multiple pure oxygen inclined holes 151 are along the circumferential direction arranged on nozzle originally at equal intervals
In body 1, the acute angle theta that formed between the axis of this pure oxygen inclined hole 151 and the axis of nozzle body 13It is 15 °～45 °.Further
, multiple fuel inclined holes 141 are circumferentially spaced to be arranged in nozzle body 1, and the axis of this fuel inclined hole 141 is with nozzle originally
The obtuse angle θ being formed between the axis of body 14It is 135 °～175 °.
Specifically, the substantially perpendicular state of the axis of the axis of this pure oxygen inclined hole 151 and fuel inclined hole 141 is arranged, and
The axis of this fuel inclined hole 141 and the acute angle theta by formation between fire end face of nozzle body 15It it is 5 °～45 °, it is preferred that acute angle
θ5It can be 30 °.
The present invention passes through multiple fuel inclined holes 141 by high-pressure natural gas according to 135 °～175 ° firing angle exits nozzle body 1,
And form the fan-shaped air-flow face of 60 °～90 ° at the barrier film exocoel 13 of nozzle body 1, it is ensured that natural gas to nozzle body 1 by fire
End face forms fuel membrane layer, blends atomization with the pure oxygen gas flow head-on collision spraying from pure oxygen inclined hole 151 afterwards, utilizes fan-shaped air-flow
The heat that pure oxygen and natural gas high-temp combustion radiate is taken away, has completely cut off pure oxygen and directly contacting under nozzle body 1 high temperature, carried
The high service life of burner noz(zle).
In an embodiment of the invention, the diameter R1 of this pure oxygen inclined hole 151 is 1.25mm～4.35mm；This fuel
The diameter R3 of inclined hole 141 is 0.25mm～1.35mm.
Embodiment two
As shown in Figure 1 to Figure 3, the present invention also provides the injection method of a kind of burner noz(zle), and described injection method uses real
Executing the burner noz(zle) of mode one, structure, the operation principle of described burner noz(zle) are identical with embodiment one with beneficial effect,
This repeats no more.Described injection method comprises the steps:
A) in the fuel channel 14 of nozzle body 1, inject natural gas, note in the pure oxygen passage 15 of described nozzle body 1
Enter pure oxygen；
B) described natural gas radially outward sprays multiple barrier film exocoels of described nozzle body 1 through multiple fuel inclined holes 141
13, described pure oxygen radially-inwardly sprays the multiple described barrier film exocoel 13 of described nozzle body 1 by multiple pure oxygen inclined holes 151.
Specifically, in step a), the pure oxygen gas that the pure oxygen in pure oxygen passage 15 is oxygen content more than 90% is injected.
In step b), the high-pressure natural gas injecting fuel channel 14 passes through multiple fuel inclined holes 141 with 135 °～175 °
Firing angle exits nozzle body 1, and form the fan-shaped air-flow face of 60 °～90 ° at the barrier film exocoel 13 of nozzle body 1；Meanwhile, inject
The pure oxygen in high pressure of pure oxygen passage 15 from multiple pure oxygen inclined holes 151 with 15 °～45 ° firing angle exits nozzle body 1.
Finally, from high-pressure natural gas and the pure oxygen gas flow from pure oxygen inclined hole 151 ejection of fuel inclined hole 141 ejection, in spray
Being atomized in the face of hitting blending by fire end of mouth body 1.
In the present invention, in above-mentioned steps b), due to barrier film exocoel 13 for be arranged on nozzle body 1 by fire end face
Arc groove, this natural gas sprays after barrier film exocoel 13 through fuel inclined hole 141, can barrier film exocoel 13 in formation one grate firing material
Membrane layer, in the present embodiment, the thickness of this fuel membrane layer is 0.5mm～1.5mm, and this fuel membrane layer can block nozzle originally
Directly being subject to by fire end face of body 1 is fiery, and the heat that pure oxygen, natural gas high-temp combustion radiate can be taken away by it, has effectively completely cut off pure oxygen
With directly contacting under nozzle body 1 high temperature, serve the effect of the metal end surface temperature reducing nozzle body 1, improve combustion
Burn the service life of nozzle.
The injection method of the present invention, by the pure oxygen inclined hole 151 being radially-inwardly obliquely installed and the radial direction of burner noz(zle)
The fuel inclined hole 141 of outward-dipping setting, it is ensured that fully blend atomization from pure oxygen and the natural gas of nozzle body 1 ejection, have
Imitating the head-on collision with pure oxygen after ensure that natural gas ejection to blend, the abundant burning for natural gas and pure oxygen provides safeguard.
The foregoing is only several embodiments of the present invention, those skilled in the art is according to application documents disclosure
The embodiment of the present invention can be carried out various change or modification without departing from the spirit and scope of the present invention.
Claims (13)
1. a burner noz(zle), it is characterised in that described burner noz(zle) includes:
Nozzle body, its one end has fuel inlet and pure oxygen inlet, and its other end is formed with multiple barrier film exocoel；
Wherein, being provided with fuel channel in described nozzle body, one end of described fuel channel is connected with described fuel inlet, its
The other end is connected with multiple described barrier film exocoels by multiple fuel inclined holes, and described fuel inclined hole is along the injection direction footpath of fuel
To outward-dipping setting；It is additionally provided with pure oxygen passage, one end of described pure oxygen passage and described pure oxygen inlet in described nozzle body
Being connected, the other end of described pure oxygen passage is connected with multiple described barrier film exocoels by multiple pure oxygen inclined holes, described pure oxygen
Inclined hole is radially-inwardly obliquely installed along the injection direction of pure oxygen.
2. burner noz(zle) as claimed in claim 1, it is characterised in that described pure oxygen passage is circular passage, and described pure oxygen leads to
Road encloses the periphery being located at described fuel channel.
3. burner noz(zle) as claimed in claim 2, it is characterised in that the ring cavity width of described pure oxygen passage is oblique with described pure oxygen
The ratio of the diameter in hole is 2.83.
4. burner noz(zle) as claimed in claim 2, it is characterised in that the diameter of described fuel channel and described fuel inclined hole
The ratio of diameter is 2.0.
5. burner noz(zle) as claimed in claim 1, it is characterised in that multiple described barrier film exocoels are circumferentially disposed in institute
Stating the end face of nozzle body, the outer contour shape of described barrier film exocoel is fan shape, the central angle of described sector is 60 °～
90°。
6. the burner noz(zle) as described in claim 1 or 5, it is characterised in that described barrier film exocoel is for being arranged on described nozzle originally
The spherical groove of body end, the spherical radius of described spherical groove is 50mm～100mm.
7. burner noz(zle) as claimed in claim 6, it is characterised in that the outward flange tangent line of described spherical groove and described nozzle
The acute angle being formed between the end face of body is 5 °～15 °.
8. burner noz(zle) as claimed in claim 2, it is characterised in that the circumferentially spaced setting of multiple described pure oxygen inclined holes
In described nozzle body, the acute angle being formed between the axis of described pure oxygen inclined hole and the axis of described nozzle body is 15 °
～45 °.
9. burner noz(zle) as claimed in claim 2, it is characterised in that the circumferentially spaced setting of multiple described fuel inclined holes
In described nozzle body, the obtuse angle being formed between the axis of described fuel inclined hole and the axis of described nozzle body is 135 °
～175 °.
10. burner noz(zle) as claimed in claim 1, it is characterised in that a diameter of 1.25mm of described pure oxygen inclined hole～
4.35mm；A diameter of 0.25mm～1.35mm of described fuel inclined hole.
The injection method of 11. 1 kinds of burner noz(zle)s as according to any one of claim 1～10, it is characterised in that described spray
Shooting method comprises the steps:
A) in the fuel channel of nozzle body, inject natural gas, in the pure oxygen passage of described nozzle body, inject pure oxygen；
B) described natural gas radially outward sprays multiple barrier film exocoels of described nozzle body, described pure oxygen through multiple fuel inclined holes
Radially-inwardly sprayed the multiple described barrier film exocoel of described nozzle body by multiple pure oxygen inclined holes.
12. injection methods as claimed in claim 11, it is characterised in that in described step b), described natural gas is through described
After the ejection of fuel inclined hole, in described barrier film exocoel, form a grate firing material membrane layer.
13. injection methods as claimed in claim 12, it is characterised in that the thickness of described fuel membrane layer be 0.5mm～
1.5mm。
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610380783.XA CN106090914B (en) | 2016-06-01 | 2016-06-01 | Combustion nozzle and injection method thereof |
| PCT/CN2016/089996 WO2017206283A1 (en) | 2016-06-01 | 2016-07-14 | Combustion nozzle and ejection method thereof, generator head construction, pure oxygen composite heat carrier generator, and method for generating composite heat carrier |
| EA201792637A EA035825B1 (en) | 2016-06-01 | 2016-07-14 | Combustion nozzle and ejection method, generator head construction, pure oxygen composite heat carrier generator and method for generating composite heat carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610380783.XA CN106090914B (en) | 2016-06-01 | 2016-06-01 | Combustion nozzle and injection method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106090914A true CN106090914A (en) | 2016-11-09 |
| CN106090914B CN106090914B (en) | 2018-05-18 |
Family
ID=57229886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610380783.XA Active CN106090914B (en) | 2016-06-01 | 2016-06-01 | Combustion nozzle and injection method thereof |
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| CN (1) | CN106090914B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109442399A (en) * | 2018-07-20 | 2019-03-08 | 北京航空航天大学 | One kind, which liquidates, directly sprays low NO |
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| JP2006275334A (en) * | 2005-03-28 | 2006-10-12 | Osaka Gas Co Ltd | Combustion device for heating furnace |
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| CN106090914B (en) | 2018-05-18 |
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