CN117433015A - Ultra-low oxygen concentration lobe type multi-spray gun fuel burner - Google Patents
Ultra-low oxygen concentration lobe type multi-spray gun fuel burner Download PDFInfo
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- CN117433015A CN117433015A CN202311543317.5A CN202311543317A CN117433015A CN 117433015 A CN117433015 A CN 117433015A CN 202311543317 A CN202311543317 A CN 202311543317A CN 117433015 A CN117433015 A CN 117433015A
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- Prior art keywords
- lobe
- type
- combustion cylinder
- flame stabilizing
- fuel
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- 239000000446 fuel Substances 0.000 title claims abstract description 75
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 28
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 28
- 239000001301 oxygen Substances 0.000 title claims abstract description 28
- 239000007921 spray Substances 0.000 title claims abstract description 17
- 238000002485 combustion reaction Methods 0.000 claims abstract description 92
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 53
- 230000000149 penetrating effect Effects 0.000 claims abstract description 6
- 239000000295 fuel oil Substances 0.000 claims description 19
- 239000000779 smoke Substances 0.000 claims description 16
- 239000002184 metal Substances 0.000 claims description 11
- 239000011261 inert gas Substances 0.000 description 15
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 14
- 239000003546 flue gas Substances 0.000 description 14
- 238000000034 method Methods 0.000 description 13
- 230000008569 process Effects 0.000 description 11
- 230000000694 effects Effects 0.000 description 9
- 238000005555 metalworking Methods 0.000 description 8
- 239000003921 oil Substances 0.000 description 7
- 238000002347 injection Methods 0.000 description 6
- 239000007924 injection Substances 0.000 description 6
- 238000000889 atomisation Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 4
- 238000010008 shearing Methods 0.000 description 4
- 238000004880 explosion Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 239000003595 mist Substances 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000002309 gasification Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 239000006229 carbon black Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
- F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/42—Starting devices
Landscapes
- 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 invention discloses an ultralow oxygen concentration lobe type multi-spray gun fuel burner, which comprises: lobe-type flame stabilizing disc, fuel atomizing nozzle, lobe-type combustion cylinder, ignition electrode and flame stabilizing disc fixing branch pipe. One end of the lobe type combustion cylinder is provided with trough and wave crest which are distributed at intervals to form a lobe structure. The lobe-type flame stabilizing disc is coaxially arranged at the outlet of the peak of the lobe-type combustion cylinder, and the lobe-type structure and the lobe-type flame stabilizing disc structure form a lobe-type jet channel. An inclined downward slope is formed between the trough and the outer wall of the lobe type combustion cylinder, a plurality of through holes are formed in the slope along the circumferential direction, a plurality of fuel atomizing nozzles are arranged on the through holes, and a plurality of spray holes are formed in the fuel atomizing nozzles. The ignition electrode is arranged inside the lobe-type combustion cylinder in a penetrating way. The flame stabilizing disc fixing branch pipes are uniformly arranged on the lobe-type flame stabilizing disc, and the lobe-type flame stabilizing disc can axially move along the flame stabilizing disc fixing branch pipes.
Description
Technical Field
The invention belongs to the technical field of ships, and particularly relates to an ultralow oxygen concentration lobe type multi-spray gun fuel burner.
Background
The LNG carrier is equipped with a plurality of large-scale cargo tanks, and the easy leakage of LNG takes place in transportation and harbour unloading in-process, in order to prevent cargo ship conflagration and explosion in order to ensure LNG carrier's safety, international Maritime Organization (IMO) stipulates through international regulations such as chapter II-2 of International maritime life safety convention (SOLAS convention) that large-scale LNG carrier must be equipped with special inert gas system and be used for producing and carrying inert gas, sweeps, replace the cargo tank, reduces the oxygen concentration in the cabin to below the explosion lower limit to effectively restrain the inflammable gas that leaks and take place burning and explosion, ensure cabin environmental safety.
The combustion type inert gas system consumes oxygen in the air by means of combustion of fuel to generate inert gas, and the inert gas is cooled, purified and dried and then conveyed into the cabin to realize inerting of the cargo tank and surrounding space. Because the combustion type inert gas system is provided with an independent combustion device and a control system, the fuel can be fully combusted, so that the produced inert gas has higher quality, the oxygen content is below 5 percent, and the inert gas basically contains no NOx, SOx, particulate matters and other impurities.
The burner body of the conventional inert gas generator includes: fuel nozzles, flame stabilizing discs, ignition guns, burner cartridges, and the like. In the burner, fuel oil from the main oil pump and air are mixed and combusted to form a chemical reaction, and the fuel oil consumes oxygen in the air through combustion in the combustion chamber, so that inert gas with low oxygen content is obtained.
The oil ship inert gas generator is usually in the form of a traditional fuel oil burner, is mainly characterized by adopting a central single spray gun structure and a swirl flame stabilizing disc, adopts a diffusion combustion mode, generally adopts a mechanical atomization nozzle for fuel oil atomization, sprays fuel oil into the burner under a certain pressure, and then utilizes swirling air to divide and mix oil mist while the oil mist flows forwards.
The use of conventional burners typically results in the following phenomena or problems:
1. in the central diffusion type combustion process, the contact area of central fuel oil and outer ring air is small, the mixing effect is poor, and the concentration of generated pollutants is high (NOx is high).
2. The atomization mode is realized by completely depending on the pressure of an oil pump, and often needs to operate under the pressure of more than 2MPa, and the atomized particle size can only reach about 200 mu m, so that the phenomena of low combustion efficiency and incomplete combustion are brought, the burnout rate is low, the carbon black generation amount is high, and the coking is easy.
3. In the combustion process, the inner side of the boundary of the burner is air, the outer side of the boundary of the burner is smoke, a large amount of smoke around the burner is accumulated, the injection perimeter of the traditional burner to the smoke is 2 pi R (R is the radius of the burner), and the injection perimeter is small.
4. The oxygen concentration and the CO concentration in the flue gas are high.
Compared with a common cargo tank, the LNG ship has higher performance requirements on inert gas, such as ultra-low oxygen content is less than or equal to 1%, so that the common inert gas generator for the oil ship cannot meet the matching requirements.
Disclosure of Invention
In order to solve the technical problems, the invention provides the ultralow oxygen concentration lobe type multi-spray gun fuel burner, which strengthens the atomization effect of fuel oil by mixing air and fuel oil entering a combustion chamber and strengthens the injection mixing of flue gas and air by arranging a plurality of lobes and nozzles adjacent to each other, solves the problems of poor mixing effect and incomplete combustion caused by a single spray gun structure in the traditional center, and greatly reduces the oxygen content in the flue gas after combustion.
The invention aims at realizing the following technical scheme, and discloses an ultralow oxygen concentration lobe type multi-spray gun fuel burner, which comprises the following components: lobe-type flame stabilizing disc, fuel atomizing nozzle, lobe-type combustion cylinder, ignition electrode and flame stabilizing disc fixing branch pipe.
The lobe type combustion cylinder is a cylindrical combustion cylinder, one end of the lobe type combustion cylinder is provided with a plurality of wave troughs and wave crests which are distributed at intervals to form a lobe structure, the tips of the wave troughs and the wave crests are positioned on the arc of the same circle, the wave crests and the wave crests are consistent in shape and size between the wave troughs and the wave crests.
The lobe-type flame stabilizing disc is processed according to the shapes of the wave crests and the wave troughs of the lobe-type combustion cylinder, the lobe-type flame stabilizing disc is coaxially arranged at the outlet of the wave crests of the lobe-type combustion cylinder, and the lobe-type structure and the lobe-type flame stabilizing disc structure form a lobe-type jet channel.
An inclined downward slope is formed between the trough and the outer wall of the lobe-type combustion cylinder, a plurality of through holes are formed in the slope along the circumferential direction, a plurality of fuel atomizing nozzles are arranged in the through holes, and the end parts of the fuel atomizing nozzles are kept flush with the end parts of the lobe-type combustion cylinder.
The fuel atomizing nozzle is provided with a plurality of spray holes.
The ignition electrode is arranged inside the lobe-type combustion cylinder in a penetrating way.
The flame stabilizing disc fixing branch pipes are uniformly arranged on the lobe-type flame stabilizing disc, and the lobe-type flame stabilizing disc can axially move along the flame stabilizing disc fixing branch pipes.
Preferably, the ignition electrode is arranged in the lobe-type combustion cylinder in a penetrating way, and the ignition electrode is arranged close to the adjacent trough of any fuel atomizing nozzle.
Preferably, the flame stabilizing disc fixing branch pipe penetrates through the inside of the lobe-type flame stabilizing disc, and a plurality of smoke flow through holes are formed in the lobe-type flame stabilizing disc.
Preferably, the lobe-type structure is formed by die stamping and sheet metal working.
Preferably, the lobe configuration comprises a plurality of lobes that taper outwardly or inwardly or flat.
Preferably, the tips of the valleys may not lie on the arc of the same circle, the peaks and peaks, and the shape and size may be inconsistent from valley to valley.
Preferably, the fuel atomizing nozzle is a medium atomizing nozzle.
Preferably, the fuel atomizing nozzle has a fuel atomizing nozzle aperture of 3.2mm and a number of holes of 6.
Compared with the prior art, the invention has the following advantages:
compared with the traditional fuel burner structure, the ultra-low oxygen concentration lobe type multi-spray gun fuel burner provided by the invention has the advantages that the special structure of the lobe type fuel burner increases the contact area of two airflows under the condition of the same outlet area, so that the viscous shearing mixing between smoke and air is enhanced, and the injected smoke volume is greatly increased. The burner is bounded by lobe profiles, the internal combustion air and the external flue gas flow velocity have opposite radial components, so that a plurality of pairs of opposite flow direction vortices are formed at two sides of the lobe; because of the speed difference between the combustion air and the smoke inside and outside the lobe boundary, under the action of the shearing force, orthogonal vortex is formed along the boundary line by winding, the convection mixing effect caused by the flow direction vortex and the orthogonal vortex is enhanced, the injection flow ratio can be greatly improved, the mixing efficiency of the smoke and the air is improved, and the problems of poor mixing effect, incomplete combustion and O are solved 2 High content.
Drawings
FIG. 1 is a schematic diagram of a straight-through lobe type multi-gun fuel burner employing a sheet metal processing technique in an embodiment of the invention;
FIG. 2 is a top view of a straight-through lobe type multi-gun fuel burner employing a sheet metal working process in an embodiment of the present invention;
FIG. 3 is a side view of a straight-through lobe type multi-lance fuel burner employing a sheet metal working process in an embodiment of the invention;
FIG. 4 is a schematic diagram of a multi-lance fuel burner with an outer diverging channel lobe in an embodiment of the invention using a die stamping process;
FIG. 5 is a top view of an outer diverging channel lobe type multi-lance fuel burner employing a die stamping process in accordance with an embodiment of the present invention;
FIG. 6 is a side view of an outer diverging channel lobe type multi-lance fuel burner employing a sheet metal working process in an embodiment of the invention;
FIG. 7 is a top view of an outer diverging channel lobe type multi-gun fuel burner employing a sheet metal machining process in an embodiment of the present invention;
FIG. 8 is a side view of an outer diverging channel lobe type multi-lance fuel burner employing a sheet metal working process in an embodiment of the invention;
FIG. 9 is a schematic diagram of a multi-gun fuel burner with a lobe-type circular channel with a sheet metal working process according to an embodiment of the present invention;
FIG. 10 is a top view of an inverted circular channel lobe type multi-lance fuel burner employing a sheet metal working process in accordance with an embodiment of the present invention;
FIG. 11 is a side view of an inverted circular channel lobe type multi-lance fuel burner employing a sheet metal machining process in an embodiment of the invention;
FIG. 12 is a schematic diagram of a multi-lobe multi-lance fuel burner using a die stamping process in an embodiment of the invention;
FIG. 13 is a top view of a multi-lobe multi-lance fuel burner using a die stamping process in an embodiment of the invention;
FIG. 14 is a schematic view of a multi-wave lobe type multi-lance fuel burner in accordance with an embodiment of the invention;
FIG. 15 is a top view of a multi-wave lobe multi-lance fuel burner in accordance with an embodiment of the invention.
In the figure, 1 is a lobe-type flame stabilizing disk; 2 is a fuel atomizing nozzle; 3 is a lobe type combustion cylinder; 4 is an ignition electrode; 5 is a flame stabilizing disc fixing branch pipe; 6 is a trough; 7 is a peak; 8 is a first multi-waveform trough; and 9 is a second multi-waveform trough.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present invention are shown in the drawings.
The technical scheme of the invention provides an ultralow oxygen concentration fuel oil burner on an LNG carrier, which is mainly used for inert gas generator equipment, wherein the burner comprises a lobe-type flame stabilizing disc 1, a fuel oil atomizing nozzle 2, a lobe-type combustion cylinder 3, an ignition electrode 4 and a flame stabilizing disc fixing branch pipe 5.
The lobe type combustion cylinder 3 is a cylindrical combustion cylinder, one end of the lobe type combustion cylinder 3 is provided with a plurality of wave troughs 6 and wave crests 7 which are distributed at intervals to form a lobe structure, the wave crests 7 and the wave crests 7 are consistent in shape and size between the wave troughs 6 and the wave troughs 6.
The lobe-type flame stabilizing disc 1 is processed according to the shapes of the wave crests 7 and the wave troughs 6 of the lobe-type combustion cylinder 3, the lobe-type flame stabilizing disc 1 is coaxially arranged at the outlet of the wave crests 7 of the lobe-type combustion cylinder 3, and a lobe-type structure and the lobe-type flame stabilizing disc 1 form a lobe-type jet channel.
An inclined downward slope is formed between the trough 6 and the outer wall of the lobe type combustion cylinder 3, a plurality of through holes are formed in the slope along the circumferential direction, a plurality of fuel atomizing nozzles 2 are arranged in the through holes, and the end parts of the fuel atomizing nozzles 2 are kept flush with the end parts of the lobe type combustion cylinder 3.
The fuel atomizing nozzle 2 is provided with a plurality of nozzle holes.
The ignition electrode 4 is disposed penetrating inside the lobe-type combustion cylinder 3.
The flame stabilizing disc fixing branch pipes 5 are uniformly arranged on the lobe-type flame stabilizing disc 1, play a supporting role on the lobe-type flame stabilizing disc 1, and the lobe-type flame stabilizing disc 1 can axially move along the flame stabilizing disc fixing branch pipes 5, so that the position can be conveniently adjusted.
In one embodiment of the invention, the ignition electrode 4 is disposed throughout the interior of the lobed combustion cylinder 3, the ignition electrode 4 being disposed adjacent to any one of the fuel atomizing nozzles 2 adjacent the trough 6.
In one embodiment of the invention, the flame stabilizing tray fixing branch pipe 5 penetrates through the inside of the lobe-type flame stabilizing tray 1, and a plurality of smoke flow through holes are formed on the lobe-type flame stabilizing tray 1.
In one embodiment of the invention, the lobe-type structure is formed by die stamping and sheet metal. In this embodiment, the lobe configuration comprises a plurality of lobes that taper outwardly or inwardly or flat.
The structure (i.e. straight lobe) of the straight-through lobe-shaped multi-spray gun fuel burner adopting the sheet metal processing technology is shown in fig. 1 to 3, and the burner comprises a lobe-shaped flame stabilizing disc 1, a fuel atomizing nozzle 2, a lobe-shaped combustion cylinder 3, an ignition electrode 4 and a flame stabilizing disc fixing branch pipe 5.
The lobe type combustion cylinder 3 is a burner cylinder body, and a plurality of through holes are uniformly formed in the circumferential direction on an inclined plane formed by the trough 6 and the outer wall surface of the lobe type combustion cylinder 3, and the number of through holes is generally 3 or more, and in this embodiment, the number of through holes is 3. The fuel atomizing nozzle 2 protrudes from the through hole for a certain length, and the end of the fuel atomizing nozzle is kept flush with the end of the lobe-type combustion cylinder 3. The fuel atomizing nozzle 2 adopts a medium atomizing nozzle with the aperture of 3.2mm and the aperture number of 6, the fuel atomizing nozzle 2 adopts a medium atomizing nozzle, and the lobe type multi-spray gun fuel burner adopts a multi-fuel atomizing nozzle 2 structure, so that the atomizing effect is better.
The fuel can be atomized better, in this example, 3 fuel atomizing nozzles 2 penetrate from the through holes of the lobe-type combustion cylinder 3, so that the nozzles are arranged on the inclined plane formed by the lobe-type combustion cylinder 3 and the trough 6, and the trough 6 of the lobe-type combustion cylinder 3 is used as an injection channel of high-temperature flue gas. After a certain amount of compressed air is mixed with fuel oil and sprayed out through the fuel oil atomizing nozzle 2 under a certain pressure, the formed primary atomized oil mist is directly sheared and crushed at the outlet of the nozzle by the compressed air, so that secondary atomization of the fuel oil is realized, and then the fuel oil is sprayed into a combustion chamber, so that the fuel oil and part of air are mixed while the fuel oil atomizing effect is enhanced, the stability of flame is ensured, and the flame is prevented from being taken off.
The lobe type combustion cylinder 3 is used as the center of the fuel oil burner, fluid outside the lobe boundary is collected smoke formed after fuel oil is combusted in the combustion process, and combustion air is arranged inside the lobe boundary. In fig. 1 to 3, the lobe-type structure is constituted by a plurality of straight-through lobes. At the outlet end face of the lobe-type combustion cylinder 3, the lobe-type structure greatly increases the contact perimeter of the flue gas and the air under the same outlet area, so that the ejected flue gas amount is increased. The lobe profile is used as a boundary, and the internal combustion air and the external flue gas flow velocity have opposite radial components, so that a plurality of pairs of opposite flow direction vortexes are formed at two sides of the lobe; due to the speed difference between the combustion air and the flue gas inside and outside the lobe boundary, orthogonal vortex is formed by winding along the boundary line under the action of shearing force. Under the combined action of the flow direction vortex and the orthogonal vortex, the lobe type structure continuously injects the smoke and the combustion air from the trough 6 of the lobe type combustion cylinder 3 to mix, so that the mixing degree of the smoke and the combustion air is greatly improved, the temperature of the combustion air is improved, and the combustion temperature is more uniform. The temperature of the mixed gas is increased, which is more favorable for the temperature rise, gasification and combustion of the fuel atomized particles, thereby consuming a great deal of combustion air and injecting oxygen in the flue gas, and the oxygen concentration in the flue gas is less than or equal to 1 percent.
In this embodiment, the ignition electrode 4 is disposed throughout the lobe-type combustion cylinder 3, near the adjacent trough 6 of any one of the fuel atomizing nozzles 3, for igniting the atomized fuel. The flame stabilizing disc fixing branch pipe 5 penetrates through the lobe-type flame stabilizing disc 1 to play a role in fixing the flame stabilizing disc. The lobe-type flame stabilizing disc 1 is arranged at the outlet position of the lobe-type combustion cylinder 3, and a plurality of smoke flow through holes are formed in the lobe-type flame stabilizing disc 1. The special structural design of the lobe-type flame stabilizing disc 1, the fuel atomizing nozzle 2 and the lobe-type sheet metal cylinder 3 is adopted to achieve forced active mixing and injection passive mixing required by design.
In the implementation form of the straight-through lobe type combustion cylinder 3 structure in this embodiment, that is, the outer wall surface of the lobe forms a positive angle with the axis of the lobe type combustion cylinder 3, the adopted processing technology is sheet metal.
In still another embodiment of the present invention, the structure of the outwardly expanding lobe-shaped multi-gun fuel burner adopting the sheet metal processing technology is shown in fig. 4 to 5, namely, the outwardly expanding lobe-shaped structure, namely, the outer wall surface of the lobe forms a positive angle with the axis of the lobe-shaped combustion cylinder 3, the die stamping processing needs a long processing period, the processing difficulty is high, and the whole structure is smooth. The structure of the outward-expansion lobe-shaped multi-spray gun fuel burner adopting the die sheet metal processing technology is shown in fig. 6 to 8, the sheet metal processing greatly shortens the processing period, reduces the processing difficulty and can select the processing mode according to engineering requirements.
In one embodiment of the present invention, the structure of the lobe-type combustion cylinder 3 employing the shrinking shape of the sheet metal working process is shown in fig. 9 to 11, that is, the outer wall surface of the lobe forms a negative angle with the axis of the lobe-type combustion cylinder 3.
As shown in fig. 12 to 13, in some embodiments of the present invention, a multi-lobe implementation manner of the lobe-type combustion cylinder 3 is further provided, where the number of peak-to-valley waveform periods is set to be different according to the ejection effect, and in this example, the number of peak-to-valley waveform periods is set to be 8.
In one embodiment of the invention, the tips of the peaks 7 may exceed the outer wall surface of the lobe-type combustion bowl 3 and the peaks 7, the valleys 6 and the valleys 6 may be non-uniform in shape and size, i.e., a multi-wave-shaped lobe-type combustion bowl 3 structure. As shown in fig. 14 to 15, the first multi-waveform trough 8 and the second multi-waveform trough 9 of the multi-waveform lobe combustion can 3 are not limited to be on the same diameter circle, and can be applied to combustors with different structures, so that the use and assembly are more flexible.
In the above-described embodiment of the invention, the lobe-type combustion cans 3 provide the air passages required for fuel combustion. In the combustion process, the fluid outside the lobe boundary is flue gas, and the fluid inside the lobe structure is air. The lobe-type structure is made up of a plurality of lobes that taper outwardly or inwardly or flat. Lobe-type structures have unique structures and mixing mechanisms, and a plurality of very complex vortex flows exist: flow direction vortices, orthogonal vortices, etc. At the exit cross section of the lobe-type structure, the main flow velocity and the secondary flow velocity have opposite radial components by taking the lobe profile as a boundary, so that a plurality of pairs of opposite vortexes (flow direction vortexes) are formed at two sides of the lobe; and due to the speed difference of the two fluids inside and outside the lobe boundary, vortex (orthogonal vortex) is formed by winding along the boundary line under the action of shearing force. Under the effect of the vortex, the lobe-type structure continuously injects the smoke to mix with the combustion air, so that the mixing degree of the smoke and the air is greatly improved, the temperature of the combustion air is improved, and the combustion temperature is more uniform. The temperature of the mixed gas is increased, which is more favorable for the temperature rise, gasification and combustion of the atomized fuel particles, thereby greatly consuming air and injecting oxygen in the flue gas and achieving the condition that the inert gas with the oxygen concentration less than or equal to 1% in the flue gas is conveyed to the cargo hold.
The foregoing is a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention and are intended to be comprehended within the scope of the present invention.
Claims (8)
1. An ultra-low oxygen concentration lobe type multi-spray gun fuel burner is characterized in that: the burner includes: the device comprises a lobe-type flame stabilizing disc (1), a fuel oil atomizing nozzle (2), a lobe-type combustion cylinder (3), an ignition electrode (4) and a flame stabilizing disc fixing branch pipe (5);
the lobe type combustion cylinder (3) is a cylindrical combustion cylinder, one end of the lobe type combustion cylinder (3) is provided with a plurality of wave troughs (6) and wave crests (7) which are distributed at intervals to form a lobe structure, the tips of the wave troughs (6) and the wave crests (7) are positioned on the same circular arc, the wave crests (7) and the wave crests (7), and the shapes and the sizes between the wave troughs (6) and the wave troughs (6) are consistent;
the lobe-type flame stabilizing disc (1) is processed according to the shapes of the wave crest (7) and the wave trough (6) of the lobe-type combustion cylinder (3), the lobe-type flame stabilizing disc (1) is coaxially arranged at the outlet of the wave crest (7) of the lobe-type combustion cylinder (3), and a lobe-type structure and the lobe-type flame stabilizing disc (1) structure form a lobe-type jet channel;
an inclined downward slope is formed between the trough (6) and the outer wall of the lobe-type combustion cylinder (3), a plurality of through holes are formed in the slope along the circumferential direction, a plurality of fuel atomizing nozzles (2) are arranged on the through holes, and the holding end parts of the fuel atomizing nozzles (2) are level with the end parts of the lobe-type combustion cylinder (3);
a plurality of spray holes are formed in the fuel atomizing nozzle (2);
the ignition electrode (4) is arranged inside the lobe-type combustion cylinder (3) in a penetrating way;
the stable flame disk fixing branch pipes (5) are uniformly arranged on the lobe-type stable flame disk (1), and the lobe-type stable flame disk (1) can axially move along the stable flame disk fixing branch pipes (5).
2. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 1 wherein: the ignition electrode (4) is arranged inside the lobe-type combustion cylinder (3) in a penetrating mode, and the ignition electrode (4) is arranged close to any position, adjacent to the trough (6), of the fuel atomizing nozzle (2).
3. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 1 wherein: the fixed branch pipe (5) of the flame stabilizing disk penetrates through the inside of the lobe-type flame stabilizing disk (1), and a plurality of smoke flow through holes are formed in the lobe-type flame stabilizing disk (1).
4. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 1 wherein: the processing mode of the lobe-shaped structure comprises die stamping processing and sheet metal processing.
5. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 1 wherein: the lobe configuration includes a plurality of lobes that taper outwardly or inwardly or flat.
6. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 1 wherein: the tips of the wave troughs (6) may not be on the arc of the same circle, the wave crests (7) and the wave crests (7), and the shape and the size between the wave troughs (6) and the wave troughs (6) may be inconsistent.
7. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 1 wherein: the fuel atomizing nozzle (2) adopts a medium atomizing nozzle.
8. An ultra low oxygen concentration lobe type multi-lance fuel burner as set forth in claim 7 wherein: the aperture of the fuel atomizing nozzle (2) is 3.2mm, and the number of the apertures is 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311543317.5A CN117433015A (en) | 2023-11-17 | 2023-11-17 | Ultra-low oxygen concentration lobe type multi-spray gun fuel burner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311543317.5A CN117433015A (en) | 2023-11-17 | 2023-11-17 | Ultra-low oxygen concentration lobe type multi-spray gun fuel burner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117433015A true CN117433015A (en) | 2024-01-23 |
Family
ID=89546054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311543317.5A Pending CN117433015A (en) | 2023-11-17 | 2023-11-17 | Ultra-low oxygen concentration lobe type multi-spray gun fuel burner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117433015A (en) |
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2023
- 2023-11-17 CN CN202311543317.5A patent/CN117433015A/en active Pending
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