CN109611835B - Multistage gas reverse cyclone burner - Google Patents
Multistage gas reverse cyclone burner Download PDFInfo
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- CN109611835B CN109611835B CN201910015818.3A CN201910015818A CN109611835B CN 109611835 B CN109611835 B CN 109611835B CN 201910015818 A CN201910015818 A CN 201910015818A CN 109611835 B CN109611835 B CN 109611835B
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- air guide
- guide barrel
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- gas
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- 239000000446 fuel Substances 0.000 claims abstract description 88
- 239000007921 spray Substances 0.000 claims abstract description 77
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 16
- 238000002347 injection Methods 0.000 claims description 20
- 239000007924 injection Substances 0.000 claims description 20
- 239000007789 gas Substances 0.000 abstract description 46
- 238000002485 combustion reaction Methods 0.000 abstract description 40
- 239000003344 environmental pollutant Substances 0.000 abstract description 6
- 231100000719 pollutant Toxicity 0.000 abstract description 6
- 239000002737 fuel gas Substances 0.000 abstract description 3
- 238000009826 distribution Methods 0.000 description 12
- 238000005507 spraying Methods 0.000 description 7
- 239000012530 fluid Substances 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000006722 reduction reaction Methods 0.000 description 3
- RAHZWNYVWXNFOC-UHFFFAOYSA-N Sulphur dioxide Chemical compound O=S=O RAHZWNYVWXNFOC-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000004134 energy conservation Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000003345 natural gas Substances 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 239000002817 coal dust Substances 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000008093 supporting effect Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D1/00—Burners for combustion of pulverulent fuel
- F23D1/02—Vortex burners, e.g. for cyclone-type combustion apparatus
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The multi-stage gas reverse swirl burner comprises a fuel spray pipe group and an air guide barrel group, wherein the air guide barrel group specifically comprises a primary air guide barrel, a secondary air guide barrel and a tertiary air guide barrel, the air outlet end of the primary air guide barrel is provided with a flame stabilizing disc for outputting primary swirl gas, the secondary air guide barrel is sleeved outside the primary air guide barrel and is provided with a plurality of second blades for outputting secondary swirl gas, the swirl direction of the primary swirl gas is opposite to that of the secondary swirl gas, and the tertiary air guide barrel is sleeved outside the secondary air guide barrel and is provided with a porous plate for outputting high-speed straight jet gas; the fuel spray pipe group comprises a primary fuel spray pipe, a secondary fuel spray pipe and a tertiary fuel spray pipe, wherein the primary fuel spray pipe is positioned on a primary air guide barrel to spray fuel to primary rotational flow gas; the secondary fuel spray pipe is positioned on the secondary air guide barrel so as to spray fuel to the secondary rotational flow gas; the three-stage fuel spray pipe is positioned on the three-stage air guide barrel. The mixing degree of air and fuel gas is greatly improved, the mixed gas is more uniform, the combustion is more complete, and the pollutant emission is lower.
Description
Technical Field
The invention relates to the field of combustors, in particular to a multistage gas reverse swirl combustor.
Background
The most fundamental survival problem of human society is related to energy and environment, the industrial revolution is continuously advancing, the shortage of energy supply and environmental pollution become the main problems in the field of human society industry, and meanwhile, huge energy waste exists. The gas burner is used as a key device in an industrial furnace and has good pollutant emission characteristics compared with a pulverized coal burner. Meanwhile, environmental awareness is enhanced and environmental protection related laws are perfected, so that the improvement of the emission characteristic of the burner and the improvement of the combustion characteristic and the efficient work of the burner are key problems of research of people. The different burner configurations determine the mixing pattern and mixing speed of the gas and the combustion air, which determine the combustion progress, i.e. the combustion characteristics, of the mixture.
Therefore, the design of the high-efficiency burner structure has very important practical significance and application value for industrial furnaces and even the combustion field.
Disclosure of Invention
The main object of the present invention is to overcome the above drawbacks of the prior art and to propose an improved burner configuration with multi-stage air distribution, burner nozzle arrangement and gas and air counter-rotating mixing. Aims to solve the problems of insufficient combustion of the burner, low fuel energy utilization rate, energy waste reduction, pollutant emission after combustion and the like.
The invention adopts the following technical scheme:
the utility model provides a multistage gas reverse cyclone burner, includes fuel spray pipe group and wind-guiding bucket group, its characterized in that: the air guide barrel group specifically comprises a first-stage air guide barrel, a second-stage air guide barrel and a third-stage air guide barrel, wherein a flame stabilizing disc is arranged at the air outlet end of the first-stage air guide barrel so as to output first-stage rotational flow gas, the second-stage air guide barrel is sleeved outside the first-stage air guide barrel and is provided with a plurality of second blades so as to output second-stage rotational flow gas, the rotational flow directions of the first-stage rotational flow gas and the second-stage rotational flow gas are opposite, and the third-stage air guide barrel is sleeved outside the second-stage air guide barrel and is provided with a porous plate so as to output accelerated high-speed straight jet flow gas; the fuel spray pipe group comprises a primary fuel spray pipe, a secondary fuel spray pipe and a tertiary fuel spray pipe, wherein the primary fuel spray pipe is positioned on a primary air guide barrel to spray fuel to primary rotational flow gas; the secondary fuel spray pipe is positioned on the secondary air guide barrel so as to spray fuel to the secondary rotational flow gas; the tertiary fuel lance is positioned on the tertiary air scoop to inject fuel into the high velocity gas.
The flame stabilizing disc is conical, and is provided with a plurality of first blades which are circumferentially distributed along the injection end of the primary fuel spray pipe.
The injection end of the primary fuel injection pipe is provided with a plurality of first injection holes which are positioned at the periphery of the injection end and are circumferentially distributed.
The section of the air inlet end of the secondary air guide barrel and the section of the air inlet end of the tertiary air guide barrel form a ring shape.
The injection end of the secondary fuel spray pipe is provided with a second spray hole which is positioned at the side part of the injection end and is opposite to the primary air guide barrel.
The second blades are circumferentially distributed around the primary air guide barrel, and the opening directions of the second blades are opposite to the opening directions of the first blades.
The air inlet end of the primary air guide barrel and the air inlet end of the secondary air guide barrel are both provided with reducing parts, and the primary air guide barrel is fixed with the tertiary air guide barrel.
The inner wall of the three-stage air guiding barrel is welded with a connecting rod, and a nut is arranged on the connecting rod; the outer wall of the secondary air guide barrel is connected with a screw rod which is in threaded fit with the screw cap.
The injection end of the three-stage fuel spray pipe faces to the axis of the primary air guide barrel.
The perforated plate is provided with a plurality of perforations.
As can be seen from the above description of the present invention, compared with the prior art, the present invention has the following advantages:
1. gas and air bidirectional high-efficiency mixing and stable combustion characteristics
The primary fuel spray pipe of the burner is arranged in the center of the flame stabilizing disc, primary fuel is sprayed out from the radial direction, air flows through the flame stabilizing disc and then flows into anticlockwise rotary motion through the jet flow, the mixing degree of air and fuel gas is greatly improved, and the concentration distribution of the mixed gas is more uniform. Compared with jet mixing, the rotary mixing causes backflow of the combustion product fluid, and has excellent advantages in stabilizing flame combustion. The optimized opening angle of the flame stabilizing disc blade enhances the rotational flow strength, enhances the mixing uniformity and flame rigidity of the mixed gas, and widens the flame lean quenching boundary.
In the secondary air guide barrel, the circumference of the secondary fuel spray pipe is uniformly distributed in front of the swirl blades, the spraying direction is radial, the fuel spray pipe is mixed with secondary clockwise rotating air at the rear after being sprayed out, the directions of the primary swirl and the secondary swirl are opposite to each other, a boundary shear layer is formed, the speed of the mixed gas flow in the shear layer is firstly reduced from outside to inside, then increased, the combustion stability of the primary mixed gas is improved, and meanwhile, the rapid ignition combustion of the secondary mixed gas is facilitated. When fuel and air are mixed, a high-temperature product of primary combustion flows to the outside under the action of centrifugal force, heat is transferred to secondary mixed gas, a combustion-supporting effect is achieved, the speed of a shear layer changes reversely, the primary high-temperature product is uniformly distributed on the periphery of the secondary mixed gas in the radial direction, the secondary mixed gas is uniformly combusted, the flame propagation speed is consistent with the air flow speed, the problems of flame failure, flame failure and the like of a combustor are solved, and the combustion is more stable and uniform.
The invention designs the concept of the central rotational flow direction and the secondary rotational flow reversely, so that the central mixed gas is stably combusted, the secondary mixed gas is rapidly combusted and has uniform temperature distribution, and the advantages of the two-stage reverse mixing combustor structure in the aspects of combustion efficiency, fuel burnout rate and energy conservation are effectively highlighted.
2. Has low NO x Pollutant emission characteristics
The natural gas is used as a high-efficiency clean energy source, is easy to store and transport, has high heat efficiency compared with coal dust, has low emission of dust and sulfur dioxide, and is widely applied to industrial burners. The burner structure provided by the invention has the advantages that the air distribution device adjusts the primary excess air coefficient, ensures that primary fuel is fully combusted, properly reduces the temperature of combustion products to ensure uniform distribution, inhibits local high temperature, reduces the condition of converting nitrogen element into nitrogen oxide, and reduces NO in primary combustion x Is generated. The secondary swirl vanes and the primary swirl vanes arranged in the secondary air guide barrel are reversed, the boundary shear layer drives the flow direction of primary combustion products to change, the primary swirl vanes and the primary swirl vanes are uniformly distributed in the circumferential direction of secondary mixed gas under the condition of continuous rotation flow, high-temperature products rapidly ignite the mixed gas, the secondary products are synchronously and uniformly combusted due to uniform distribution of the primary combustion products, flame rapidly propagates forwards under the action of axial speed, the residence time of the combustion products in a high-temperature area is shortened, and NO is reduced x And simultaneously enhances flame stiffness and flame fullness. The third-level high-speed air jet conveys the fuel gas to the tail part of the flame, the concentration of the mixed gas is low, and the first-level high-temperature combustion products ignite the mixed gas, so that the products which are not completely combusted are oxidized and combusted and simultaneously nitrogen is generatedOxide reduction, effective inhibition of NO x Resulting in reduced emissions of combustor pollutants and compliance with combustion emission standards.
3. Burner wide load adjustment
The burner provided by the invention is provided with an air distribution mechanism at the air inlet end of the air guide barrel. The tail part of the primary air guide barrel and the tail part of the secondary air guide barrel are designed into variable diameter structures, the included angles between the conical surfaces and the axial lines are unequal, the primary air guide barrel and the tertiary air guide barrel are fixed, the secondary air guide barrel can move back and forth, the air flow area of the secondary air guide barrel is changed, the air flow sectional area of the primary air guide barrel and the air flow sectional area of the tertiary air guide barrel are unchanged, and the secondary air excess coefficient is changed to adjust the load of the burner.
Drawings
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a front view of the present invention;
FIG. 4 is a partial cross-sectional view of the present invention;
the device comprises a three-stage air guiding barrel 1a, a connecting rod 1b and a nut, wherein the three-stage fuel spraying pipe 2 is provided with a perforated plate 3a and perforated holes 4a, the two-stage air guiding barrel 4a, a screw rod 4b, a bearing seat 4c and a bearing 5a second blade 5a and a gasket 6a second fuel spraying pipe 6a and a second spraying hole 7a flame stabilizing disc 7a and a first blade 8a first fuel spraying pipe 8a and a first spraying hole 9a first air guiding barrel 9a and a thin connecting rod.
Detailed Description
The invention is further described below by means of specific embodiments.
Referring to fig. 1 to 4, a multi-stage gas reverse swirl burner comprises a fuel spray pipe group, a wind guiding barrel group and the like, wherein the wind guiding barrel group comprises a primary wind guiding barrel 9, a secondary wind guiding barrel 4 and a tertiary wind guiding barrel 1. The air inlet end of the primary air guide barrel 9 is provided with a reducing section, which is similar to a cone shape, and the inner diameter of the primary air guide barrel is gradually increased or reduced along the air inlet direction. The air outlet end of the primary air guide barrel 9 is provided with a flame stabilizing disc 7, the flame stabilizing disc 7 is conical and is provided with a through hole and a plurality of first blades 7a, the through hole is positioned in the middle of the flame stabilizing disc 7 and is used for allowing a fuel spray pipe to pass through, the first blades 7a are circumferentially distributed along the through hole, and the opening direction of the first blades 7a is anticlockwise or clockwise, so that air flows through the primary air guide barrel 9 to output primary rotational flow air from the flame stabilizing disc 7, and the direction of the air flows is anticlockwise or clockwise.
The secondary air guiding barrel 4 is sleeved outside the primary air guiding barrel 9, the air inlet end of the secondary air guiding barrel is also provided with a reducing section, and the secondary air guiding barrel is similar to a cone shape, and the inner diameter of the secondary air guiding barrel is gradually increased or reduced along the air inlet direction. A plurality of second blades 5 are further arranged between the inner wall of the second-stage wind guiding barrel 4 and the outer wall of the first-stage wind guiding barrel 9, the second blades 5 are circumferentially distributed around the first-stage wind guiding barrel 9, and a certain included angle is formed between the second blades 5 and the axis of the first-stage wind guiding barrel 9. The opening direction of the second vane 5 is clockwise or anticlockwise, that is, opposite to the opening direction of the first vane 7a, so that the air flow passes through the second air guiding barrel 4 to output the second rotational flow air, and the direction of the second rotational flow air is clockwise or anticlockwise opposite to the direction of the first rotational flow air.
The third-stage air guiding barrel 1 is sleeved outside the second-stage air guiding barrel 4, and the section between the air inlet end of the third-stage air guiding barrel 1 and the air inlet end of the second-stage air guiding barrel 4 is annular. A porous plate 3 is fixed between the inner wall of the three-stage air guiding barrel 1 and the outer wall of the two-stage air guiding barrel 4, uniformly distributed perforations 3a are arranged on the porous plate 3, the through-flow sectional area of the perforations 3a is reduced, and the flow velocity of the fluid is increased after the fluid flows through the porous plate 3 according to a hydrodynamic flow equation. Namely, when the gas enters the three-stage wind guiding barrel 1, the accelerated high-speed straight jet gas is output through the perforation 3a on the porous plate 3.
The inner wall of the three-stage air guiding barrel 1 is welded with a connecting rod 1a which extends radially, and a nut 1b is arranged at the end part of the connecting rod 1 a; the outer side wall of the secondary air guide barrel 4 is welded with a bearing seat 4b, a bearing 4c and a screw rod 4a are fixed on the bearing seat 4b, the end part of the screw rod 4a penetrates through the bearing 4c and is in interference fit with the bearing 4c, the screw rod 4a is in spiral fit with the screw cap 1b, the bearing 4c is pushed to horizontally move through the rotary movement of the screw rod 4a, and then the secondary air guide barrel 4 is driven to slide left and right.
The inner wall one end of the second blade 5 relative to the second-stage wind guiding barrel 4, namely the outer ring, is provided with a gasket 5a, the gasket 5a is fixedly connected in a riveted mode, the gasket 5a is made of a low friction coefficient material, friction resistance between the gasket and the inner wall of the second-stage wind guiding barrel 4 is reduced, the inner ring of the second blade 5 is fixedly connected with the outer 9 rings of the first-stage wind guiding barrel through welding, the tail end of the first-stage wind guiding barrel 9 is fixedly connected with the rear end part of the burner through a thin connecting rod 9a, and the thin connecting rod 9a reduces interference to a flow field while guaranteeing connection strength.
The air flow is regulated by the air guide barrel group by adopting an air multi-stage distribution structure, and different air coefficients are matched for each stage of fuel to ensure full combustion. The three-stage air guiding barrel 1 and the one-stage air guiding barrel 9 are relatively fixed, the two-stage air guiding barrel 4 can move relative to the one-stage air guiding barrel 9 and the three-stage air guiding barrel 1, and as the air inlet ends of the one-stage air guiding barrel 9 and the two-stage air guiding barrel 4 are arranged into variable diameter sections, when the two-stage air guiding barrel moves back and forth relative to the one-stage air guiding barrel 9, the through flow sectional area between the two variable diameter sections is changed, and the change of the sectional area changes the air flow. The through-flow cross section of the three-stage air guiding barrel 1 does not change along with the forward and backward movement of the two-stage air guiding barrel, namely the air coefficient of the three-stage fuel is basically unchanged.
The fuel injection pipe group comprises a primary fuel injection pipe 8, a secondary fuel injection pipe 6, a tertiary fuel injection pipe 2 and the like. The primary fuel spray pipe 8 is positioned on the primary air guide barrel 9, the spray end of the primary fuel spray pipe is provided with a plurality of first spray holes 8a, and the plurality of first spray holes 8a are positioned at the periphery of the spray end and are circumferentially distributed so as to realize rapid and uniform mixing of the primary rotational flow gas spray fuel. The number of primary fuel nozzles 8 may be one, two, preferably one; the number of first nozzles may not be the only number of four, eight, ten or even more.
The secondary fuel spray pipe 6 is positioned in the secondary air guide barrel 4 and positioned outside the second blade 5. The secondary fuel pipe is circumferentially distributed around the primary fuel spray pipe 8, the spray end of the secondary fuel pipe is provided with a second spray hole 6a, the second spray hole 6a is positioned at the side part of the spray end and is opposite to the primary air guide barrel 9, namely, the secondary fuel pipe deviates from the circle center, fuel is sprayed to secondary rotational flow gas to realize quick and uniform mixing, the combustion supporting effect of primary combustion high-temperature products is achieved, and the mixed gas is quickly and fully combusted. The number of the secondary fuel nozzles 6 is not limited to two, four or more, and the number of the second nozzle holes 6a on each secondary fuel nozzle 6 may be one, two or more.
The three-stage fuel spray pipe 2 is positioned on the three-stage air guide barrel 1, the tail end of the three-stage fuel spray pipe is used as a spray hole and forms a certain included angle with the axis, and the spray end of the spray hole faces the axis of the first-stage air guide barrel 9, namely points to the axis. The high-speed fluid accelerated by the porous plate 3 sends the tertiary fuel to the flame end burnout zone for combustion, and the incompletely combusted fuel is fully combusted, so that the burnout rate of the fuel and the pollution emission of combustion products are improved.
In practical application, the burner is matched with a fuel conveying device and a gas conveying device. The inner diameters of the first, second and third fuel spray pipes, the inner diameter of the middle section of the first, second and third air guide barrels 1, the opening angle of the first blade 7a, the radial included angle of the second blade 5 and the air guide barrel, the included angle of the conical surface of the air distribution mechanism at the tail of the second air guide barrel 4 and the axis, the included angle of the conical surface of the air distribution mechanism at the tail of the first air guide barrel 9 and the axis, the front-end shrinkage angle of the second air guide barrel 4, the front-end shrinkage angle of the third air guide barrel 1, the included angle between the spraying direction of the third fuel spray pipe 2 and the axis, the outer diameter of the ring formed by the air inlet ends of the second air guide barrel 4 and the third air guide barrel 1, the inner diameter of the porous plate 3, the outer diameter of the porous plate 3, the aperture of the porous plate 3 and other parameters can be set according to practical requirements.
Application example
The burner shown in fig. 1 comprises a primary fuel spray pipe 8, a secondary fuel spray pipe 6, a tertiary fuel spray pipe 2, a primary air guide barrel 9, a secondary air guide barrel 4, a tertiary air guide barrel 1, a porous plate 3, a second blade 5, a flame stabilizing disc 7 and the like. R1, R2 and R3 respectively represent the inner diameters of a first-stage fuel spray pipe, a second-stage fuel spray pipe and a third-stage fuel spray pipe, R4, R5 and R6 respectively represent the inner diameters of the middle sections of the first-stage air guide barrel, the second-stage air guide barrel and the third-stage air guide barrel, and alpha is used 1 The opening angle of the first blade 7a of the flame stabilizing tray 7 is represented by alpha 2 The included angle between the second blade 5 in the secondary air guiding barrel 4 and the axial direction of the air guiding barrel is expressed by alpha 3 The included angle between the conical surface of the air distribution mechanism at the tail part of the secondary air guiding barrel 4 and the axis is expressed by alpha 4 Air distribution mechanism for representing tail part of primary air guide barrel 9Angle between conical surface and axis, alpha 5 Represents the front end shrinkage angle of the secondary air guiding barrel 4 and uses alpha 6 Represents the shrinkage angle of the front end of the three-stage air guiding barrel 1, and alpha is used 7 The included angle between the nozzle direction and the axis of the three-stage fuel spray pipe 2 is represented by R7, the outer diameter of a three-stage air distribution ring of an air distribution mechanism at the tail end of the secondary air guide barrel is represented by R8, the inner diameter of the porous plate 3 is represented by R9, the outer diameter of the porous plate 3 is represented by R10, and the aperture of the porous plate 3 is represented by R10.
In the burner profile, the length is 1000-1200mm, preferably 650mm, and the diameter is 534-600mm. For each stage of combustion spray pipes and spray nozzles, the diameter of each stage of combustion spray pipes is 17.5mm, the diameter of each stage of combustion spray pipes is 5-8mm, the diameter of each stage of combustion spray pipes is 8.5mm, the diameter of each stage of combustion spray pipes is 4-6mm, the diameter of each stage of combustion spray pipes is 3-4mm, the thickness of each stage of combustion spray pipes is 1.5-2mm, the tail ends of each stage of combustion spray pipes are connected with a natural gas inlet pipe, each stage of fuel flow is independently controlled by a throttle valve, the load adjusting range of a combustor is improved, and the accurate combustion and the energy conservation are facilitated. For each stage of air guiding barrels R4 is 17.5mm, R5 is 67mm, R6 is 265mm, the thickness of the primary air guiding barrel 9 is 1.5mm, the thickness of the secondary air guiding barrel 4 is 1.5-2mm, and the thickness of the tertiary air guiding barrel 1 is 2mm, wherein the included angle alpha between the front end and the rear end of each stage of air guiding barrel 3 150 ° -160 °, preferably 159 °, α 4 115-122 DEG, wherein alpha 2 34-40 deg. and blade thickness of 1.5mm, where alpha 2 If the flame is not too large, the loss of fluid kinetic energy is caused, the rigidity of the flame is reduced, the contraction angle at the front end of each stage of air guide barrel is favorable for the combustion flame to gather towards the central axis to form a relatively compact bud shape, the rigidity of the flame is improved, and the combustion stability is favorable, wherein alpha is as follows 5 28-34 °, preferably 32 °, α 6 25-35 °, preferably 30 °, α 7 The thickness of the porous plate is 38-45 degrees, the thickness of the porous plate is 430mm, the thickness of the porous plate is 2mm, the porous plate is 3, the thickness of the porous plate is 380, the thickness of the porous plate is 530mm, the thickness of the porous plate is 6mm, the pore diameter is not suitable for large and small pore diameters accelerate fluid, mixed gas is sent to the tail end of flame for reaction and combustion, the burnout rate of fuel is improved, and meanwhile, the porous plate and high-temperature pollution products are subjected to reduction reaction, so that the emission of pollutants is reduced.
The foregoing is merely illustrative of specific embodiments of the present invention, but the design concept of the present invention is not limited thereto, and any insubstantial modification of the present invention by using the design concept shall fall within the scope of the present invention.
Claims (10)
1. The utility model provides a multistage gas reverse cyclone burner, includes fuel spray pipe group and wind-guiding bucket group, its characterized in that: the air guide barrel group specifically comprises a first-stage air guide barrel, a second-stage air guide barrel and a third-stage air guide barrel, wherein a flame stabilizing disc is arranged at the air outlet end of the first-stage air guide barrel so as to output first-stage rotational flow gas, the second-stage air guide barrel is sleeved outside the first-stage air guide barrel and is provided with a plurality of second blades so as to output second-stage rotational flow gas, the rotational flow directions of the first-stage rotational flow gas and the second-stage rotational flow gas are opposite, and the third-stage air guide barrel is sleeved outside the second-stage air guide barrel and is provided with a porous plate so as to output accelerated high-speed straight jet flow gas; the fuel spray pipe group comprises a primary fuel spray pipe, a secondary fuel spray pipe and a tertiary fuel spray pipe, wherein the primary fuel spray pipe is positioned on a primary air guide barrel to spray fuel to primary rotational flow gas; the secondary fuel spray pipe is positioned on the secondary air guide barrel so as to spray fuel to the secondary rotational flow gas; the tertiary fuel lance is positioned on the tertiary air scoop to inject fuel into the high velocity gas.
2. A multi-stage gas reverse swirl burner as in claim 1 wherein: the flame stabilizing disc is conical, and is provided with a plurality of first blades which are circumferentially distributed along the injection end of the primary fuel spray pipe.
3. A multi-stage gas reverse swirl burner as in claim 1 wherein: the injection end of the primary fuel injection pipe is provided with a plurality of first injection holes which are positioned at the periphery of the injection end and are circumferentially distributed.
4. A multi-stage gas reverse swirl burner as in claim 1 wherein: the section of the air inlet end of the secondary air guide barrel and the section of the air inlet end of the tertiary air guide barrel form a ring shape.
5. A multi-stage gas reverse swirl burner as in claim 1 wherein: the injection end of the secondary fuel spray pipe is provided with a second spray hole which is positioned at the side part of the injection end and is opposite to the primary air guide barrel.
6. A multi-stage gas reverse swirl burner as in claim 2 wherein: the second blades are circumferentially distributed around the primary air guide barrel, and the opening directions of the second blades are opposite to the opening directions of the first blades.
7. A multi-stage gas reverse swirl burner as in claim 1 wherein: the air inlet end of the primary air guide barrel and the air inlet end of the secondary air guide barrel are both provided with reducing parts, and the primary air guide barrel is fixed with the tertiary air guide barrel.
8. A multi-stage gas reverse swirl burner as in claim 1 wherein: the inner wall of the three-stage air guiding barrel is welded with a connecting rod, and a nut is arranged on the connecting rod; the outer wall of the secondary air guide barrel is connected with a screw rod which is in threaded fit with the screw cap.
9. A multi-stage gas reverse swirl burner as in claim 1 wherein: the injection end of the three-stage fuel spray pipe faces to the axis of the primary air guide barrel.
10. A multi-stage gas reverse swirl burner as in claim 1 wherein: the perforated plate is provided with a plurality of perforations.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910015818.3A CN109611835B (en) | 2019-01-08 | 2019-01-08 | Multistage gas reverse cyclone burner |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910015818.3A CN109611835B (en) | 2019-01-08 | 2019-01-08 | Multistage gas reverse cyclone burner |
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| CN109611835A CN109611835A (en) | 2019-04-12 |
| CN109611835B true CN109611835B (en) | 2024-02-27 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110388643A (en) * | 2019-07-26 | 2019-10-29 | 合肥工业大学 | The gas-air premixed device of hydrogen-enriched fuel gas combustion with reduced pollutants |
| CN111288448B (en) * | 2020-03-20 | 2022-03-29 | 东营富润智能科技有限公司 | Ultralow nitrogen burner for oil field heating furnace |
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