A two-stage cyclone incinerator combustion device with flame color tracing function

Abstract

This utility model discloses a two-stage cyclone incinerator combustion device with flame color tracing function, including a two-stage cyclone structure, which is set inside the outlet end to apply rotational driving force to the passing fluid. It includes a flow divider ring, a first-stage cyclone blade, and a second-stage cyclone blade. The flow divider ring is coaxially set inside the burner shell. The inner ends of the first-stage and second-stage cyclone blades are fixed on the flow divider ring, and the outer ends are fixed on the inner wall of the burner shell. The two-stage cyclone blades are arranged in the same direction of rotation. The fuel pipe structure includes a central fuel pipe, a radial fuel pipe, a first internal fuel channel, and a second internal fuel channel. This utility model uses straight holes injected at the leading edge of the blades to fully mix the fuel with the air in the channel between the blades, forming a uniform and fully mixed gas at the burner outlet. This can form a stable premixed flame with a moderate maximum flame temperature in the furnace, improving combustion efficiency and reducing NOx emissions.

Description

Technical Field

[0001] This utility model relates to the field of burner technology, specifically to a two-stage swirl incinerator combustion device with flame color tracing function. Background Technology

[0002] In existing incinerator burner technologies, key combustion parameters such as the mixing state of fuel and combustion air, the distribution of the combustion zone, and flame stability lack direct and intuitive monitoring methods. Current technologies typically rely on indirect data obtained from equipment such as temperature sensors and oxygen analyzers within the furnace to infer the combustion state. However, this indirect monitoring method has significant limitations: firstly, the fixed sensor placement makes it difficult to comprehensively reflect the complex flow and combustion field distribution within the furnace, easily leading to misjudgments of localized combustion states; secondly, data acquisition and analysis are delayed, failing to capture instantaneous changes during the combustion process in real time.

[0003] The aforementioned defects stem from the fact that in existing burner designs, the mixing process of fuel and combustion air within the swirl vane channel, the boundaries of the staged combustion zones formed by the two-stage swirl vanes, and the specific morphology of the flame within the furnace are all invisible. For example, when the fuel and combustion air are not mixed uniformly, localized areas of rich or lean combustion may appear. However, current technology cannot directly observe the location and extent of these areas; they can only be indirectly determined through subsequent pollutant emission data (such as increased NOx and CO concentrations) or localized temperature anomalies, resulting in a lack of precise basis for controlling the mixing state. Furthermore, issues such as whether the flow-dividing ring between the two-stage swirl vanes effectively separates the combustion zone and whether the swirl intensity matches the fuel characteristics are also difficult to verify intuitively using existing monitoring methods.

[0004] These defects can lead to a series of consequences: uneven mixing can reduce combustion efficiency and increase fuel consumption; the presence of local high-temperature zones can promote the generation of large amounts of NOx and exacerbate pollutant emissions; and if fluctuations in flame stability are not detected and adjusted in time, they may cause safety hazards such as backfire and flameout, and even affect the continuous and stable operation of the incinerator.

[0005] To compensate for the above shortcomings, existing technologies often employ periodic shutdowns for maintenance, indirectly assessing combustion status by manually observing coking and corrosion inside the furnace, or optimizing combustion through empirical adjustments to parameters such as fuel supply, combustion air flow, and swirl blade angle. However, this approach not only affects the continuous operating efficiency of the incinerator and increases maintenance costs, but also relies heavily on operator experience, making precise control difficult. It fails to fundamentally address the issues of delayed and unintuitive combustion status monitoring, hindering further improvements in combustion efficiency and environmental performance.

[0006] For the reasons mentioned above, it is necessary to propose a two-stage swirl incinerator combustion device with flame color tracing function to solve the above problems. Utility Model Content

[0007] The purpose of this invention is to overcome the defects in the existing technology and provide a two-stage cyclone incinerator combustion device with flame color tracing function.

[0008] To achieve the above objectives, the technical solution of this utility model is as follows:

[0009] A two-stage cyclone incinerator combustion device with flame color tracing function includes:

[0010] The burner shell has a cylindrical structure with a through-hole cavity, with one end being the inlet and the other end being the outlet.

[0011] The two-stage cyclone separator structure is located inside the outlet end and applies a rotational driving force to the fluid passing through it. It includes a flow divider ring, a first-stage cyclone blade, and a second-stage cyclone blade. The flow divider ring is coaxially located inside the burner housing. The inner ends of the first-stage and second-stage cyclone blades are fixed on the flow divider ring, and the outer ends are fixed on the inner wall of the burner housing. The two stages of cyclone blades are arranged in the same direction of rotation.

[0012] The fuel pipe structure includes a central fuel pipe, a radial fuel pipe, a first internal fuel channel, and a second internal fuel channel. The central fuel pipe is arranged along the axis of the burner shell, and two stages of swirl blades are centrally symmetrically distributed around the central fuel pipe. The radial fuel pipe is connected to one end of the central fuel pipe near the inlet. The first internal fuel channel is formed inside the first stage swirl blade, and the second internal fuel channel is formed inside the second stage swirl blade. The first internal fuel channel is connected to the central fuel pipe. Fuel injection holes are provided on both sides of the first stage swirl blade, and the fuel injection holes are connected to the first internal fuel channel.

[0013] Furthermore, it also includes a rectifier structure, which is a perforated plate structure disposed inside the burner housing and perpendicular to the axial direction. The rectifier structure is disposed between the radial fuel pipe and the swirl blades.

[0014] Furthermore, the first-stage swirl blades and the second-stage swirl blades are arranged alternately in sequence. The inner end of the second-stage swirl blade is fixedly connected to the outer wall of the flow divider ring, and the first-stage swirl blade passes through the flow divider ring and is fixedly connected to the central fuel pipe. The front end of the central fuel pipe is set as a spherical structure.

[0015] Furthermore, the extension lines of the first-stage swirl blade and the second-stage swirl blade toward the center are both externally tangent to the imaginary circle, and the diameter of the imaginary circle is smaller than the inner diameter of the central fuel pipe.

[0016] Furthermore, the fuel pipe structure is provided with an outer ring cavity, and the outer ring cavity is connected to a feed pipe. One end of the second internal fuel channel passes through the burner housing and is connected to the outer ring cavity, and the other end passes through the side wall of the split ring and is connected to the inner ring of the split ring.

[0017] Furthermore, a color-developing fuel is introduced into the outer annular cavity. The color-developing fuel includes a main fuel and a color-developing additive. The color-developing fuel is fed into the inner side of the split ring for combustion, causing the burner flame to form an observable flame with a color-developing flame core.

[0018] Furthermore, the diversion ring is cylindrical in shape, and the outer ring cavity is fed to the diversion ring by a pressurized feeding method.

[0019] Furthermore, the inner wall of the flow divider ring has a reduced diameter ring section, and the second internal fuel passage is connected at the point where the diameter of the reduced diameter ring section is the smallest, so that the flow divider ring forms a Venturi tube structure.

[0020] Furthermore, the rectifier structure includes two flow regulating plates, namely a fixed plate and a rotating plate. The two flow regulating plates are distributed with rectifier holes whose diameters change radially in a gradient manner, and the diameter of the rectifier holes gradually increases from the center to the edge. The rotating plate is controlled to rotate relative to the fixed plate, thereby changing the overlap of the rectifier holes on the two flow regulating plates.

[0021] The advantages and beneficial effects of this utility model are as follows:

[0022] This invention employs a straight injection hole at the leading edge of the blades to thoroughly mix the fuel with the air in the channel between the blades, forming a uniform and well-mixed gas mixture at the burner outlet. This allows for the formation of a stable premixed flame with a suitable maximum flame temperature within the furnace, improving combustion efficiency and reducing NOx emissions. This invention also presents a novel burner structure with advantages such as simple structure, convenient processing, ease of implementation, and low cost.

[0023] This invention, through the coordinated structure of a color-indicating fuel supply system, a flow divider ring, and a rectifier, retains the advantages of the original burner's efficient mixing and staged combustion while enabling visual monitoring of the combustion state via a color-indicating flame core. The two implementation methods are designed to address the requirements of pressurized stability and low-cost self-priming, respectively, significantly improving the device's practicality and adaptability to various operating conditions, and providing a direct basis for precise control and safe operation of the incinerator. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the structure of a two-stage cyclone incinerator combustion device with flame color tracing function according to this utility model;

[0025] Figure 2 This is an exploded view of a two-stage cyclone incinerator combustion device with flame color tracing function according to this utility model;

[0026] Figure 3 This is a longitudinal cross-sectional schematic diagram of Embodiment 1 of this utility model;

[0027] Figure 4 This is a utility model Figure 3 Schematic diagram of section AA;

[0028] Figure 5 This is a longitudinal cross-sectional schematic diagram of Embodiment 2 of this utility model.

[0029] In the diagram: 1. Burner shell; 2. Inlet end; 3. Outlet end; 4. Diverter ring; 5. First-stage swirl vane; 6. Second-stage swirl vane; 7. Central fuel pipe; 8. Radial fuel pipe; 9. First internal fuel passage; 10. Second internal fuel passage; 11. Fuel nozzle; 12. Rectifier structure; 13. Spherical structure; 14. Imaginary circle; 15. Outer annular cavity; 16. Feed pipe; 17. Reduced diameter ring; 18. Fixed plate; 19. Rotating plate; 20. Rectifier hole. Detailed Implementation

[0030] The specific embodiments of this utility model will be further described below with reference to examples. These examples are only used to more clearly illustrate the technical solution of this utility model and should not be construed as limiting the scope of protection of this utility model.

[0031] Example 1:

[0032] This application relates to a novel burner in which fuel flows through an internal channel of swirl blades and is then injected at the edge of the swirl blades, mixing with swirling air to form a terminal mixture, which is then burned in the furnace. Combustion air, after being rectified by a rectifier, mixes with the fuel injected at the edge of the swirl blades and enters the burner outlet, uniformly entering the furnace.

[0033] Specifically, it includes two-stage swirl blades, fuel pipes, a rectifier, and burner housing 1, such as... Figure 1-4 As shown, where:

[0034] The fuel pipe includes a radial fuel pipe 8 and a central fuel pipe 7, which are connected and have the same diameter. The central fuel pipe 7 is located on the central axis of the burner, and its front end is connected to the swirl vane and communicates with the internal fuel channel inside the corresponding swirl vane. The central fuel pipe 7 has holes with the same cross-sectional shape, size, channel direction, and uniform distribution as the internal fuel channel of the corresponding swirl vane, thereby reducing flow resistance. At the very front of the swirl vane, the central fuel pipe 7 is set as a spherical structure 13, which is close to the trailing edge of the swirl vane. This structure is used to reduce flow separation and prevent the formation of a low-pressure zone at the swirl outlet 3. It communicates with the radial fuel pipe 8 at a certain position at the rear end. A plug is provided at the rear end of the central fuel pipe 7 to facilitate the processing of the central fuel. The radial fuel pipe 8 passes through the shell and communicates with the central fuel pipe 7. A flange connection structure is provided at a certain distance from the burner shell 1 at the outer end of the radial fuel pipe 8 for connecting to the flange of the external fuel supply system outlet. Fuel enters the radial fuel pipe 8 through the supply system, passes through the fuel channel of the swirl vanes in the central fuel pipe 7, and is finally injected into the channel between the swirl vanes to mix with the combustion air.

[0035] The rectifier employs a uniformly arranged straight perforated plate or honeycomb structure. The outer ring of the rectifier contacts the inner surface of the casing, and the fuel pipe passes through the rectifier. The inner ring of the rectifier contacts the outer surface of the fuel pipe, and all combustion air passes through the rectifier. The rectifier is positioned between the radial fuel pipe 8 and the swirl vanes, and is perpendicular to the centerline of the entire burner. Sufficient distance is maintained between the rectifier and the leading edge of the swirl vanes to ensure adequate rectification and create a uniform inflow at the inlet of the swirl vanes.

[0036] The cyclone separator employs two-stage cyclone blades, consisting of a primary cyclone blade 5 and a secondary cyclone blade 6. It also includes a flow divider ring 4 coaxially mounted inside the burner housing 1. The primary cyclone blade 5 and the secondary cyclone blade 6 are alternately arranged. The inner end of the secondary cyclone blade 6 is fixedly connected to the outer wall of the flow divider ring 4. The primary cyclone blade 5 passes through the flow divider ring 4 and is fixedly connected to the central fuel pipe 7. The front end of the central fuel pipe 7 is configured with a spherical structure 13. The primary cyclone blade 5 passes through the flow divider ring 4 towards the center and is connected to the central fuel pipe 7. The secondary cyclone blade 6 does not pass through the flow divider ring 4 but is only connected to the outer wall of the flow divider ring 4. The cyclone blades are arranged with the same blade shape and installation angle. The primary cyclone blade 5 has fuel injection holes 11 on both sides for fuel to be injected at the blade and mixed with combustion air. The secondary cyclone blade 6 does not have fuel injection holes 11 but also has a second internal fuel channel 10. The secondary cyclone blade 6 is mainly used to improve the consistency of the cyclone separator blades and increase the mixing degree of fuel and air.

[0037] The radial position of the splitter ring 4 needs to be determined based on the number of blades and combustion requirements. The first internal fuel channel 9 of the first-stage swirl blade 5 has small holes (fuel nozzles 11) evenly distributed on both sides along the radial direction. Fuel is directly injected through these holes and mixed with air in the swirl channel to form a uniform mixture. Simultaneously, the holes reduce the impact of combustion backfire. The swirl blades are arranged in a rotating configuration at a certain angle to the radial direction. The blade arrangement ensures that the extension lines of the first-stage swirl blade 5 and the second-stage swirl blade 6 towards the center are externally tangent to the imaginary circle 14, and the diameter of this imaginary circle 14 is smaller than the inner diameter of the central fuel pipe 7, as shown in the figure. With this configuration, when fuel flows from the central fuel pipe 7 into the internal channel of the blades, it is subjected to a tangential force, resulting in smoother fuel flow within the channel. Stable fuel flow is crucial for supply stability. The tangentially extended blade structure provides a stable fuel delivery path, reducing fuel supply fluctuations caused by flow instability, ensuring a uniform and continuous fuel supply under different operating conditions, and maintaining stable operation of the combustion process.

[0038] Specifically, the extensions of the first-stage swirl blade 5 and the second-stage swirl blade 6 towards the center are both externally tangent to the same imaginary circle 14, and the diameter of this imaginary circle 14 is smaller than the inner diameter of the central fuel pipe 7. This design is based on the correlation between flow deflection and pressure loss in fluid mechanics. By optimizing the transition pattern of fuel from the central fuel pipe 7 into the internal channel of the blade, the stability of fuel supply is improved. When fuel flows axially in the central fuel pipe 7, it needs to undergo a flow deflection from the axial direction to the tangential direction to enter the swirl-distributed internal channel of the blade. Since the diameter of the imaginary circle 14 externally tangent to the blade extension is smaller than the inner diameter of the central fuel pipe 7, the connection point between the blade and the central fuel pipe 7 is closer to the center of the pipe rather than close to the inner wall. This results in a smaller deflection angle for fuel entering the blade channel and a gentler curvature of the flow path. Based on Bernoulli's equation and the principle of momentum conservation in fluid mechanics, a gentle turn can reduce local eddies and pressure surges caused by abrupt changes in direction, lowering energy loss during the turn and resulting in a more uniform fuel velocity distribution within the blade channels, avoiding flow fluctuations caused by local resistance differences. Simultaneously, in the axial flow within the central fuel pipe 7, the fluid near the center is less affected by pipe wall friction, resulting in a more stable velocity. The blade connection point being located in this region allows fuel entering the blade channels to be directly drawn from the stable mainstream flow area, reducing interference from the pipe wall boundary layer (with lower and unstable velocity) on fuel supply and further ensuring consistent flow distribution among the blade channels. The advantages of this design are: firstly, lower and more uniform fuel flow resistance within the channels reduces pressure requirements on the fuel supply system, decreasing energy consumption; secondly, more consistent fuel injection rates across blade channels and a more uniform mixing ratio with combustion air prevent localized rich or lean combustion, helping to reduce NOx and other pollutant emissions; and thirdly, a stable fuel supply enhances flame stability, reduces safety hazards such as backfire and flameout, and extends the burner's service life.

[0039] Example 2:

[0040] Based on the core structure of "two-stage swirl vanes, flow splitter ring 4, and rectifier" in Embodiment 1, this system constructs an independent color-developing fuel supply system by adding an outer annular cavity 15 and a second internal fuel channel 10, thereby achieving controllable generation of the flame color-developing core. Figure 5 As shown, the specific structure is as follows:

[0041] An outer annular cavity 15 is arranged around the fuel pipe structure and connected to an external color-indicating fuel supply system via a feed pipe 16, serving as a temporary storage and distribution chamber for the color-indicating fuel. The second internal fuel channel 10 within the secondary swirl vanes 6 has one outer end passing through the burner housing 1 and communicating with the outer annular cavity 15, and the other inner end extending through the side wall of the splitter ring 4 to the inner ring of the splitter ring 4. This channel is used to directionally deliver the color-indicating fuel into the splitter ring 4, where it is ultimately mixed with the main fuel and combusted with the swirling air to form an observable flame with a color-indicating flame core. This design can convert the key combustion states inside the burner and furnace into directly observable visual signals.

[0042] Specifically, color-developing fuels can be made by mixing main fuels, such as natural gas or propane, with color-developing additives, such as organic compounds containing metal elements like sodium, copper, and strontium, such as sodium ethoxide and copper acetate. The additives account for 0.1%-0.5% of the total amount, which ensures stable flame color without interfering with the main combustion process.

[0043] In one implementation method, specifically, the diversion ring 4 adopts the cylindrical annular design of Embodiment 1, with an inner diameter of 80mm and a height of 50mm; the second internal fuel channel 10 has a diameter of 6mm and is connected to the outer annular cavity 15; an electromagnetic regulating valve is installed on the feed pipe 16 to control the supply pressure of the color-indicating fuel to 0.2-0.5Mpa. The color-indicating fuel enters the outer annular cavity 15 through the feed pipe 16 and, under pressure, is injected into the inner ring of the diversion ring 4 through the second internal fuel channel 10, mixing with the air and main fuel flowing out through the first-stage swirl vanes 5. After combustion, a stable color-indicating flame core is formed (e.g., bright yellow when containing sodium ethoxide). By adjusting the opening of the electromagnetic regulating valve, the flow rate of the color-indicating fuel can be controlled at 0.5-2m³ / h, and the corresponding flame intensity increases with the increase of the flow rate. This implementation method is suitable for incinerator load fluctuations, such as mixed treatment of medical waste and industrial waste residue. Stable pressurized feeding ensures a clear flame core color, facilitating real-time observation of the boundary changes of the two-stage combustion zones.

[0044] As another implementation, a Venturi-type flow divider ring 4 is used in conjunction with an adjustable flow meter. Specifically, the flow divider ring 4 adopts a Venturi tube structure, that is, a reduced-diameter ring section 17 is formed on the inner wall of the flow divider ring 4, and the second internal fuel channel 10 is connected to the center of the reduced-diameter ring section 17. The fixed plate 18 and the rotating plate 19 of the rectifier are both circular plates with a diameter of 200mm. The rectifier orifice 20 increases in size from the center to the edge. The rotating plate 19 is driven by a servo motor (not shown in the figure), thereby achieving the purpose of controlling the size of the rectifier orifice 20, thereby changing the amount of combustion air entering the flow divider ring 4. Then, the negative pressure formed by the Venturi tube structure also changes accordingly, thereby adjusting the amount of color-developing fuel entering.

[0045] Combustion air, after being rectified by the rectifier, enters the distribution ring 4. Its velocity increases sharply as it flows through the narrowing ring 17, creating a negative pressure on the second internal fuel channel 10. This draws the color-producing fuel, such as propane containing copper acetate, from the outer ring cavity 15 into the inner ring of the distribution ring 4, where it burns to form a blue-green flame core. By rotating the rotating plate 19 relative to the fixed plate 18, such as rotating it 30°, the overlap of the rectifier orifices 20 decreases by 50%, allowing adjustment of the airflow through the distribution ring 4 (range 1000-3000 m³ / h). The negative pressure intensity increases with the airflow, and the amount of color-producing fuel introduced increases accordingly (0.3-1.8 m³ / h), achieving dynamic adjustment of flame intensity. This embodiment is more suitable for small and medium-sized incinerators, as it does not require additional pressurization equipment. Through airflow self-absorption and linkage with the rectifier, it achieves low-cost matching of flame core brightness and combustion state. For example, at low loads, the airflow can be reduced to decrease flame intensity and avoid interfering with observation.

[0046] On the one hand, the characteristic color of the flame core can serve as a "boundary marker" for the staged combustion zones formed by the two-stage swirl blades. Since the colored fuel is directly fed into the inner ring of the splitting ring 4 through the second internal fuel channel 10, the flame core is mainly concentrated in the combustion zone corresponding to the second-stage swirl blade 6. If the splitting ring 4 does not effectively separate the two-stage combustion zones or if the airflow in the incinerator is turbulent, the flame core color will diffuse towards the first-stage combustion zone. Based on this, the working status of the splitting ring 4, the independence of staged combustion, and the working status inside the furnace can be intuitively judged. On the other hand, the uniformity of the flame core distribution can reflect the mixing quality of fuel and combustion air in real time. If the color is too dark or too light in a local area, it indicates that there is a rich or lean combustion phenomenon in that area. Mixing defects can be located without relying on lagging sensor data. Thus, the state inside the incinerator can be judged by intuitive observation. This improves the timeliness and accuracy of combustion status monitoring, avoiding misjudgments caused by sensor limitations or data lag in traditional indirect monitoring methods. It allows operators to quickly identify problems such as localized high temperatures and uneven mixing, providing direct evidence for real-time adjustments to parameters such as combustion airflow and swirl blade angles. Furthermore, it enhances the precision of staged combustion control. The flame core boundary allows for direct verification of whether the radial position of the flow divider ring 4 is suitable for combustion requirements, facilitating the optimization of fuel distribution ratios between the two-stage swirl blades and reducing combustion efficiency decline caused by improper zone division. Simultaneously, changes in flame core stability (such as flashing or breakage) can provide timely warnings of risks such as backfire and flameout, reducing the probability of equipment damage caused by combustion fluctuations.

[0047] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A two-stage cyclone incinerator combustion device with flame color tracing function, characterized in that, include: The burner shell has a cylindrical structure with a through-hole cavity, with one end being the inlet and the other end being the outlet. The two-stage cyclone separator structure is located inside the outlet end and applies a rotational driving force to the fluid passing through it. It includes a flow divider ring, a first-stage cyclone blade, and a second-stage cyclone blade. The flow divider ring is coaxially located inside the burner housing. The inner ends of the first-stage and second-stage cyclone blades are fixed on the flow divider ring, and the outer ends are fixed on the inner wall of the burner housing. The two stages of cyclone blades are arranged in the same direction of rotation. The fuel pipe structure includes a central fuel pipe, a radial fuel pipe, a first internal fuel channel, and a second internal fuel channel. The central fuel pipe is arranged along the axis of the burner shell, and two stages of swirl blades are centrally symmetrically distributed around the central fuel pipe. The radial fuel pipe is connected to one end of the central fuel pipe near the inlet. The first internal fuel channel is formed inside the first stage swirl blade, and the second internal fuel channel is formed inside the second stage swirl blade. The first internal fuel channel is connected to the central fuel pipe. Fuel injection holes are provided on both sides of the first stage swirl blade, and the fuel injection holes are connected to the first internal fuel channel.

2. The two-stage cyclone incinerator combustion device with flame color tracing function according to claim 1, characterized in that, It also includes a rectifier structure, which is a perforated plate structure disposed inside the burner housing and perpendicular to the axial direction, the rectifier structure being disposed between the radial fuel pipe and the swirl blades.

3. The two-stage cyclone incinerator combustion device with flame color tracing function according to claim 1, characterized in that, The primary swirl blades and secondary swirl blades are arranged alternately in sequence. The inner end of the secondary swirl blade is fixedly connected to the outer wall of the flow divider ring. The primary swirl blade passes through the flow divider ring and is fixedly connected to the central fuel pipe. The front end of the central fuel pipe is set as a spherical structure.

4. The two-stage cyclone incinerator combustion device with flame color tracing function according to claim 3, characterized in that, The extension lines of the first-stage and second-stage swirl blades toward the center are both externally tangent to the imaginary circle, and the diameter of the imaginary circle is smaller than the inner diameter of the central fuel pipe.

5. A two-stage cyclone incinerator combustion device with flame color tracing function according to claim 1 or 2, characterized in that, The fuel pipe structure has an outer ring cavity outside, and the outer ring cavity is connected to a feed pipe. One end of the second internal fuel channel passes through the burner shell and is connected to the outer ring cavity, and the other end passes through the side wall of the split ring and is connected to the inner ring of the split ring.

6. The two-stage rotational flow incinerator combustion device with flame color tracer function according to claim 5, characterized in that, Color-developing fuel, which includes main fuel and color-developing additives, is introduced into the outer annular cavity. The color-developing fuel is fed into the inner side of the split ring for combustion, causing the burner flame to form an observable flame with a color-developing flame core.

7. The two-stage rotational flow incinerator combustion device with flame color tracer function according to claim 5, characterized in that, The diversion ring is cylindrical in shape, and the material is fed into the diversion ring by pressurized feeding in the outer ring cavity.

8. The two-stage rotational flow incinerator combustion device with flame color tracer function according to claim 5, characterized in that, The inner wall of the flow divider ring has a reduced diameter ring section, and the second internal fuel passage is connected at the smallest diameter of the reduced diameter ring section, so that the flow divider ring forms a Venturi tube structure.

9. The two-stage rotational flow incinerator combustion device with flame color tracer function according to claim 2, characterized in that, The rectifier structure includes two flow regulating plates, namely a fixed plate and a rotating plate. The two flow regulating plates are distributed with rectifier holes whose diameters change radially in a gradient manner, and the diameter of the rectifier holes gradually increases from the center to the edge. The rotating plate is controlled to rotate relative to the fixed plate, thereby changing the overlap of the rectifier holes on the two flow regulating plates.

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