A nozzle matrix structure for a gas turbine air intake and a method of spraying

Abstract

This invention relates to a nozzle matrix structure for gas turbine intake, comprising a fan-shaped perforated plate (2) vertically disposed within a fan-shaped atomizing chamber (1), on which are provided hexagonal intake channels (21). The intake channels (21) are arranged in a honeycomb matrix structure on the fan-shaped perforated plate (2), and the cavity (22) between adjacent intake channels (21) is also a honeycomb mesh structure. A spray pipe (3) pre-set in the cavity is connected to an atomizing nozzle (4), which includes a nozzle body (41) that cooperates with each other and an automatic rotating device (42) disposed at the spray end of the nozzle body (41). The advantages of this invention are that it can not only interfere with and disperse the airflow, reducing the adverse effects of the airflow on the spray, but also improve the spray treatment effect, which is beneficial for the absorption and removal of nitrogen oxides.

Description

Technical Field

[0001] This invention relates to the field of nozzle technology for gas turbines, and in particular to a matrix structure of nozzles for gas turbine intake and its spraying method. Background Technology

[0002] During the dry autumn season, NO emissions from gas turbine exhaust... x The indicators sometimes exceed the standards, especially NO in the flue gas of large gas turbines. x The maximum emission limit is 50 mg / m³ 3 Nitrogen oxides (NOx) mainly originate from two sources: thermal NOx and fuel-borne NOx. During normal operation of a gas turbine unit, NOx emissions generally do not exceed emission limits. However, in some cases, NOx emissions are unstable, with significant fluctuations, and may even exceed the limits. With increasing environmental pressures, exceeding pollutant emission standards will directly affect the safe and stable operation of the unit.

[0003] To reduce nitrogen oxide emissions, atomizing nozzles are typically used to humidify the intake air of a gas turbine. For example, Chinese Patent No. CN113062799A discloses a gas turbine humidification and emission reduction device and its control method. The atomization chamber is designed as a fan-shaped structure, and several sets of arc-shaped water supply pipes and corresponding atomizing nozzles are fixed on the top of the atomization chamber. When gas enters, the fan-shaped atomization chamber causes the gas entering the chamber through the arc-shaped sidewalls to form a stable gas flow direction, and the air velocity inside the chamber increases from the outside to the inside, accelerating the evaporation and fusion of atomized particles in the gas. The working pressure of the atomizing nozzles on each arc-shaped water supply branch pipe increases sequentially from the gas flow direction, causing the spray particle size of the atomizing nozzles to decrease sequentially from the gas flow direction. This allows the gas to be atomized step by step during the flow, accurately controlling the atomization parameters, saving atomization water, and improving the atomization effect, thereby humidifying the gas turbine intake air and reducing nitrogen oxide emissions. However, because the atomizing nozzle is designed at the top, the spray is easily affected by the airflow when it falls, causing the upper spray to be blown backward. As a result, the amount of spray that reaches the lower layer is relatively small, which means that the lower air intake cannot be effectively humidified and reduced, which undoubtedly reduces the treatment effect of the intake air.

[0004] To avoid the aforementioned problems, Chinese patent CN218177325U discloses a gas turbine nitrogen oxide emission reduction device. Although the technical solution does not specify the exact arrangement of the atomizing nozzles, it can be seen from the attached drawings that the atomizing nozzles are mainly arranged vertically, that is, along the longitudinal section of the air intake. This ensures that a certain amount of spray is emitted from both the upper and lower layers to mix with the gas. However, while using only a longitudinal arrangement can avoid the uneven distribution of spray between the upper and lower layers to some extent, the airflow velocity direction is perpendicular to the surface where the atomizing nozzles are located. In addition, the high intake airflow velocity causes the first airflow to blow the spray backward, resulting in the subsequent airflow not being able to effectively contact the spray. Furthermore, this single-layer vertical arrangement gradually weakens the spray treatment effect as the gas flow velocity increases. Summary of the Invention

[0005] The purpose of this invention is to solve the problems of high intake air velocity and poor spray treatment effect in existing gas turbines. It provides a nozzle matrix structure for gas turbine intake, which can not only interfere with and disperse the airflow, reducing the adverse effects of the airflow on the spray, but also improve the spray treatment effect and facilitate the absorption and removal of nitrogen oxides.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A matrix structure for a gas turbine intake nozzle includes a fan-shaped orifice plate disposed in a fan-shaped atomizing chamber. The fan-shaped orifice plate is vertically arranged and has an intake channel with a regular hexagonal structure. The diameter of the intake channel gradually decreases from the side closer to the arc-shaped sidewall of the fan-shaped atomizing chamber to the side farther away from the arc-shaped sidewall of the fan-shaped atomizing chamber.

[0008] The air inlet channels are arranged in a honeycomb matrix structure on the fan-shaped perforated plate, and there are perforated plate cavities between adjacent air inlet channels, so that the perforated plate cavities on the fan-shaped perforated plate form a honeycomb mesh structure. Spray pipes are pre-set in the perforated plate cavities. An atomizing nozzle is set at the intersection of three adjacent air inlet channels, which includes a nozzle body that cooperates with each other and an automatic rotating device located at the spray end of the nozzle body. The nozzle body is connected to the fan-shaped perforated plate and is connected to the spray pipes in the perforated plate cavity for supplying liquid to the nozzle.

[0009] The atomizing nozzle is located on the side of the fan-shaped orifice plate away from the arc-shaped outer wall, and the spraying end of the atomizing nozzle is also oriented in the opposite direction to the side where the arc-shaped outer wall is located, in order to avoid the airflow directly affecting the nozzle life and spraying effect.

[0010] Furthermore, the air intake channel is provided with a protruding baffle plate. The baffle plate is spirally distributed on the inner wall of the air intake channel from one end of the air intake port. When it is close to the air outlet end of the air intake channel, the baffle plate forms six dispersed baffle plates. The end of each baffle plate is located on one side of a regular hexagonal structure.

[0011] Furthermore, the diffuser includes a connected arc segment and a cut segment. One end of the arc segment is positioned towards the spoiler, and the other end is smoothly tangent to the cut segment. The center of the arc segment is located on the center line of the side of the regular hexagonal structure. The exhaust direction of the end of the cut segment is parallel to the edge of the regular hexagonal structure. The diffuser, spoiler, and air intake channel are integrally formed.

[0012] Furthermore, the nozzle body of the atomizing nozzle includes a connected delivery pipe and a spray nozzle. One end of the delivery pipe is connected to a fan-shaped orifice plate and its cavity is connected to the spray pipe. One end of the spray nozzle extends out of the nozzle body and is fitted with an automatic rotating device. The automatic rotating device is a cylindrical tubular structure with a recessed mounting groove on one side. A nozzle perforation is provided in the middle of the bottom surface of the mounting groove. The nozzle perforation is connected to the dispersion chamber. The mounting groove, the nozzle perforation, and the dispersion chamber are on the same axis as the cylindrical tubular structure. The spray nozzle extends into the mounting groove and passes through the nozzle perforation into the dispersion chamber. The inner wall of the mounting groove is connected to the nozzle body by a bearing. The inner wall of the nozzle perforation is connected to the spray nozzle by a bearing. The spray nozzle extending into the dispersion chamber is provided with an inclined spray port facing the side of the dispersion chamber closer to the delivery pipe. A set of dispersion ports is provided on the outer wall of the dispersion chamber.

[0013] Furthermore, the diameter of the mounting groove is larger than the diameter of the nozzle perforation, the diameter of the nozzle perforation is smaller than the diameter of the dispersion chamber, the front end of the nozzle body is embedded in the mounting groove and the nozzle perforation is just stuck at the connection between the nozzle body and the spray nozzle, the dispersion chamber is provided with a triangular groove on the side near the delivery pipe, and the extended line of the axis of the spray nozzle just intersects the bottom of the triangular groove, so as to drive the automatic rotating device to rotate after spraying water to the bottom of the groove.

[0014] Furthermore, a sealing ring is provided between the nozzle perforation and the spray nozzle to isolate the liquid in the dispersion chamber.

[0015] Furthermore, the delivery pipe is equipped with an orifice flow meter and a shut-off valve for controlling the opening and closing of the nozzle.

[0016] Furthermore, the arc of the fan-shaped perforated plate is the same as the arc of the arc sidewall of the fan-shaped atomizing chamber, and each row of fan-shaped perforated plates forms a concentric fan-shaped ring with the arc sidewall of the fan-shaped atomizing chamber.

[0017] Furthermore, the axis of the air intake channel is the same as the gas turbine's air intake direction, and the fan-shaped perforated plate is set perpendicular to the gas turbine's air intake direction.

[0018] To further achieve the objective of this invention, a spraying method for a gas turbine intake nozzle matrix structure is also provided, the specific steps of which are as follows:

[0019] (1) The gas enters the chamber through the arc-shaped outer wall of the fan-shaped atomizing chamber and passes through the air inlet channel of the first layer of fan-shaped perforated plate. The air inlet channel interferes with the gas flow rate and direction, making it tend to stabilize.

[0020] (2) The gas entering the air intake channel forms a swirling flow under the action of the baffle. When it approaches the air outlet of the air intake channel, the swirling flow forms six dispersed airflows under the action of the splitter plate, which are blown out from the six sides of the regular hexagonal structure.

[0021] (3) The atomizing nozzle on the inner side of the fan-shaped orifice plate sprays out a mist, and the liquid with high pressure gas is shot from the spray nozzle into the dispersion chamber of the automatic rotating device, which drives the automatic rotating device to rotate at high speed around the atomizing nozzle. The liquid with high pressure gas fills the dispersion chamber and is ejected from the dispersion port on the side wall of the dispersion chamber. During the rotation, the sprayed liquid merges with the dispersed airflow.

[0022] (4) After being processed by the first layer of sector-shaped perforated plate, the gas continues to move along the sector-shaped atomization chamber to the second layer of sector-shaped perforated plate. The processing method is the same as that of the first layer of sector-shaped perforated plate, and the cycle is repeated to complete the emission reduction treatment of the gas.

[0023] Compared with the prior art, the advantages of the technical solution of the present invention are as follows:

[0024] (1) The present invention uses spray humidification at the gas turbine inlet to suppress the generation of nitrogen oxides during gas turbine combustion. The fan-shaped orifice plate is arranged vertically to avoid uneven fusion of upper and lower gas layers with the spray, thereby improving the spray treatment effect and facilitating the absorption and removal of nitrogen oxides.

[0025] (2) In this invention, when each stream of air is blown out of the channel, it is treated by at least two atomizing nozzles on the fan-shaped orifice plate. Compared with the overall airflow, the dispersed airflow is less. The small flow of gas interacts with multiple sprays, resulting in better treatment effect.

[0026] (3) The present invention adds an automatic rotating device in front of the atomizing nozzle. No additional power is required. The entire device is rotated by the impact of high-pressure water on the chamber, thereby ensuring that the spray is sprayed out in high-speed rotation. This not only increases the spray speed and range of the spray and improves the air flow that the spray can contact, but also greatly improves the dispersion of the spray, making it more uniform and increasing the contact area between the spray and the gas. Attached Figure Description

[0027] Figure 1 This is an overall assembly structure diagram of the nozzle matrix structure for gas turbine intake according to the present invention;

[0028] Figure 2 This is a partial structural schematic diagram of the sector-shaped perforated plate of the present invention;

[0029] Figure 3This is a schematic diagram of the air intake channel of the present invention along its axial direction;

[0030] Figure 4 This is a schematic diagram of the inner wall structure of 1 / 6 of the air inlet of the air inlet channel of the present invention.

[0031] Figure 5 This is a schematic diagram of the assembly of the atomizing nozzle and the fan-shaped orifice plate of the present invention;

[0032] Figure 6 This is a schematic diagram illustrating the interaction between the atomizing nozzle and the automatic rotating device of the present invention. Detailed Implementation

[0033] Example

[0034] To make the present invention clearer, the following description, in conjunction with the accompanying drawings, further illustrates a gas turbine intake nozzle matrix structure and its spraying method. The specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the invention.

[0035] See Figure 1 A matrix structure for a gas turbine intake nozzle, comprising a sector-shaped perforated plate 2 disposed within a sector-shaped atomizing chamber 1, characterized in that:

[0036] join Figure 1 , Figure 2 and Figure 5 The fan-shaped perforated plate 2 is vertically arranged and has an air intake channel 21 with a regular hexagonal structure. The curvature of the fan-shaped perforated plate 2 is the same as the curvature of the arc side wall 1a of the fan-shaped atomizing chamber 1, and each row of fan-shaped perforated plates 2 and the arc side wall 1a of the fan-shaped atomizing chamber form a concentric fan-shaped ring. The diameter of the air intake channel 21 gradually decreases from the side close to the arc side wall 1a of the fan-shaped atomizing chamber 1 to the side away from the arc side wall 1a of the fan-shaped atomizing chamber 1. The axis of the air intake channel 21 is the same as the gas turbine air intake direction, and the fan-shaped perforated plate 2 is arranged perpendicular to the gas turbine air intake direction.

[0037] See Figure 2 , Figure 3 and Figure 4 The air intake channel 21 is provided with a protruding baffle 5. The baffle 5 is spirally distributed on the inner wall of the air intake channel 21 starting from the air intake port 21a end of the air intake channel 21. When it is close to the air outlet 21b end of the air intake channel 21, the baffle 5 forms six dispersed diverter plates 6. The end of each diverter plate 6 is located on one side of the regular hexagonal structure.

[0038] See Figure 4The diffuser 6 includes a connected arc segment 61 and a cut segment 62. One end of the arc segment 61 is set towards the spoiler 5, and the other end is smoothly tangent to the cut segment 62. The center of the arc segment 61 is set on the side centerline of the regular hexagonal structure. The exhaust direction of the end of the cut segment 62 is set parallel to the edge of the regular hexagonal structure. The diffuser 6, the spoiler 5, and the air intake channel 21 are integrally formed.

[0039] See Figure 2 , Figure 5 and Figure 6 The air inlet channels 21 are arranged in a honeycomb matrix structure on the fan-shaped orifice plate 2, and an orifice plate cavity 22 is provided between adjacent air inlet channels 21, so that the orifice plate cavity 22 on the fan-shaped orifice plate 2 forms a honeycomb mesh structure. The spray pipe 3 is preset in the orifice plate cavity 22. An atomizing nozzle 4 is provided at the intersection of three adjacent air inlet channels 21, which includes a nozzle body 41 that cooperates with each other and an automatic rotating device 42 located at the spray end of the nozzle body 41. The nozzle body 41 is connected to the fan-shaped orifice plate 2 and is connected to the spray pipe 3 in the orifice plate cavity 22 for supplying liquid to the nozzle.

[0040] The atomizing nozzle 4 is located on the side of the fan-shaped orifice plate 2 away from the arc-shaped outer wall 1a, and the spraying end of the atomizing nozzle 4 is also facing the opposite direction to the side where the arc-shaped outer wall 1a is located, so as to avoid the airflow directly affecting the nozzle life and spraying effect.

[0041] See Figure 5 The nozzle body 41 includes a connected delivery pipe 411 and a spray nozzle 412. One end of the delivery pipe 411 is connected to the fan-shaped orifice plate 2 and its cavity is connected to the spray pipe 3. The delivery pipe 411 is equipped with an orifice plate flow meter 10 and a shut-off valve 11 for controlling the opening and closing of the nozzle.

[0042] See Figure 6 One end of the spray nozzle 412 extends out of the nozzle body 41, and an automatic rotating device 42 is provided on its outer sleeve. The automatic rotating device 42 is a cylindrical tubular structure with a recessed mounting groove 421 on one side. A nozzle through-hole 422 is provided in the middle of the bottom surface of the mounting groove 421. The nozzle through-hole 422 is connected to the dispersion chamber 423. The mounting groove 421, the nozzle through-hole 422, and the dispersion chamber 423 are on the same axis as the cylindrical tubular structure. The spray nozzle 412 extends into the mounting groove 421 and... The nozzle passes through the nozzle perforation 422 and enters the dispersion chamber 423. The inner wall of the mounting groove 421 is connected to the nozzle body 41 by bearing 7. The inner wall of the nozzle perforation 422 is connected to the nozzle body 41 by bearing 8. The spray nozzle 412 extending into the dispersion chamber 423 is provided with an inclined spray port 412a. The spray port 412a is set towards the side of the dispersion chamber 423 near the delivery pipe 411. A set of dispersion ports 423a is provided on the outer wall of the dispersion chamber 423.

[0043] The diameter of the mounting groove 421 is larger than the diameter of the nozzle perforation 422, and the diameter of the nozzle perforation 422 is smaller than the diameter of the dispersion chamber 423. The front end of the nozzle body 41 is embedded in the mounting groove 421, and the nozzle perforation 422 is just stuck at the connection between the delivery pipe 411 and the spray nozzle 412. The dispersion chamber 423 is provided with a triangular groove 423b on the side near the delivery pipe 411, and the extended line of the axis of the spray nozzle 412a just intersects the bottom of the triangular groove 423b, so as to drive the automatic rotating device to rotate after spraying water to the bottom of the groove.

[0044] In use, the air intake first passes through the air intake channel 21 of the fan-shaped perforated plate 2, and is successively formed into six dispersed airflows by the baffle 5 and the diverter 6 inside the channel. When each airflow blows out of the channel, since the side length of the regular hexagon it is located on includes two atomizing nozzles 4, each airflow will be processed by at least two atomizing nozzles 4 on the fan-shaped perforated plate 2. Moreover, compared with the overall airflow flow rate, the dispersed airflow flow rate is smaller. The small flow rate of gas interacts with multiple sprays, resulting in better treatment effect. In addition, the spray is first tilted from the spray nozzle 412 into the dispersion chamber 423 of the automatic rotating device 42. The entire device rotates only by the impact of high-pressure water on the chamber, without the need for additional power. The spray filling the dispersion chamber 423 is sprayed out from the dispersion port 423a during high-speed rotation, which increases the spray speed, range and dispersion, and improves the contact area and uniformity between the spray and the gas.

[0045] After adopting the nozzle matrix structure and spraying method of this invention, the air inlet is humidified by spray, which inhibits the formation of nitrogen oxides during gas turbine combustion. After installation, a comparative test was conducted at 30% RH and 21°C. The results showed that after the device was put into operation, NO... x Emissions were reduced by 4 mg / m³, and the power output of the gas turbine was increased.

[0046] In addition to the embodiments described above, the present invention may have other implementations. All technical solutions formed by equivalent substitution or equivalent transformation fall within the protection scope claimed by the present invention.

Claims

1. A nozzle matrix structure for gas turbine intake, comprising a sector-shaped perforated plate (2) disposed within a sector-shaped atomizing chamber (1), characterized in that: The fan-shaped perforated plate (2) is vertically arranged and has an air inlet channel (21) with a regular hexagonal structure. The diameter of the air inlet channel (21) gradually decreases from the side of the arc-shaped sidewall (1a) close to the fan-shaped atomizing chamber (1) to the side away from the arc-shaped sidewall (1a). The air intake channels (21) are arranged in a honeycomb matrix structure on the fan-shaped perforated plate (2), and there is a perforated plate cavity (22) between adjacent air intake channels (21). The perforated plate cavity (22) on the fan-shaped perforated plate (2) forms a honeycomb mesh structure. A spray pipe (3) is preset in the perforated plate cavity (22). An atomizing nozzle (4) is provided at the intersection of three adjacent air intake channels (21). It includes a nozzle body (41) that cooperates with each other and an automatic rotating device (42) located at the spray end of the nozzle body (41). The nozzle body (41) is connected to the fan-shaped perforated plate (2) and it is connected to the spray pipe (3) in the perforated plate cavity (22). The atomizing nozzle (4) is located on the side of the fan-shaped orifice plate (2) away from the arc-shaped sidewall (1a), and the spraying end of the atomizing nozzle (4) is also opposite to the direction of the side where the arc-shaped sidewall (1a) is located. The nozzle body (41) of the atomizing nozzle (4) includes a connected delivery pipe (411) and a spray nozzle (412). One end of the delivery pipe (411) is connected to the fan-shaped orifice plate (2) and its cavity is connected to the spray pipe (3). One end of the spray nozzle (412) extends out of the nozzle body (41) and is fitted with an automatic rotating device (42). The automatic rotating device (42) is a cylindrical tubular structure with a recessed mounting groove (421) on one side. A nozzle perforation (422) is provided in the middle of the bottom surface of the mounting groove (421). The nozzle perforation (422) is connected to the dispersion chamber (423). The mounting groove (421), the nozzle perforation (422), and the dispersion chamber (423) are connected. On the same axis as the cylindrical tubular structure, the spray nozzle (412) extends into the mounting groove (421) and passes through the nozzle perforation (422) to enter the dispersion chamber (423). The inner wall of the mounting groove (421) is connected to the nozzle body (41) by bearing one (7), and the inner wall of the nozzle perforation (422) is connected to the spray nozzle (412) by bearing two (8). The spray nozzle (412) extending into the dispersion chamber (423) is provided with an inclined spray port (412a). The spray port (412a) is set towards the side of the dispersion chamber (423) near the delivery pipe (411). A set of dispersion ports (423a) is provided on the outer wall of the dispersion chamber (423). The diameter of the mounting groove (421) is larger than the diameter of the nozzle perforation (422), and the diameter of the nozzle perforation (422) is smaller than the diameter of the dispersion chamber (423). The front end of the nozzle body (41) is embedded in the mounting groove (421), and the nozzle perforation (422) is just stuck at the connection between the nozzle body (41) and the spray nozzle (412). The dispersion chamber (423) has a triangular groove (423b) on the side near the delivery pipe (411), and the extended line of the axis of the spray nozzle (412a) intersects the bottom of the triangular groove (423b).

2. The nozzle matrix structure for gas turbine intake according to claim 1, characterized in that: The air intake channel (21) is provided with a protruding baffle (5). The baffle (5) is spirally distributed on the inner wall of the air intake channel (21) starting from one end of the air intake port (21a). When it is close to one end of the air intake port (21b), the baffle (5) forms six dispersed diverter plates (6). The end of each diverter plate (6) is located on one side of the regular hexagonal structure.

3. The nozzle matrix structure for gas turbine intake according to claim 2, characterized in that: The diverter plate (6) includes a connected arc segment (61) and a cut segment (62). One end of the arc segment (61) is set towards the spoiler plate (5), and the other end is smoothly tangent to the cut segment (62). The center of the arc segment (61) is set on the side center line of the regular hexagonal structure. The exhaust direction of the end of the cut segment (62) is set parallel to the edge of the regular hexagonal structure. The diverter plate (6), the spoiler plate (5), and the air inlet channel (21) are integrally formed.

4. The nozzle matrix structure for gas turbine intake according to any one of claims 1 to 3, characterized in that: A sealing ring (9) is provided between the nozzle perforation (422) and the spray nozzle (412).

5. The nozzle matrix structure for gas turbine intake according to any one of claims 1 to 3, characterized in that: The delivery pipe (411) is equipped with an orifice flow meter (10) and a shut-off valve (11).

6. The nozzle matrix structure for gas turbine intake according to any one of claims 1 to 3, characterized in that: The arc of the fan-shaped perforated plate (2) is the same as the arc of the arc sidewall (1a) of the fan-shaped atomizing chamber (1), and each row of fan-shaped perforated plates (2) and the arc sidewall (1a) of the fan-shaped atomizing chamber (1) form a concentric fan-shaped ring.

7. The nozzle matrix structure for gas turbine intake according to any one of claims 1 to 3, characterized in that: The axis of the air intake channel (21) is the same as the gas turbine intake direction, and the fan-shaped perforated plate (2) is set perpendicular to the gas turbine intake direction.

8. A spraying method for a gas turbine intake nozzle matrix structure as described in claim 2, comprising the following specific steps, characterized in that: Step 1: The gas enters the chamber through the arc-shaped sidewall (1a) of the fan-shaped atomizing chamber (1), passes through the air inlet channel (21) of the first layer of fan-shaped perforated plate (2), and the air inlet channel (21) interferes with the gas flow rate and direction, making it tend to stabilize; Step 2: The gas entering the air intake channel (21) forms a swirling flow under the action of the baffle (5). When it approaches the air outlet (21b) of the air intake channel (21), the swirling flow forms six dispersed airflows under the action of the splitter plate (6), which are blown out from the six sides of the regular hexagonal structure. Step 3: The atomizing nozzle (4) inside the fan-shaped perforated plate (2) sprays out a mist. The liquid with high-pressure gas is shot from the spray nozzle (412a) to the dispersion chamber (423) of the automatic rotating device (42), which drives the automatic rotating device (42) to rotate at high speed around the atomizing nozzle (4). The liquid with high-pressure gas fills the dispersion chamber (423) and is shot out from the dispersion port (423a) on the side wall of the dispersion chamber (423). During the rotation, the sprayed liquid merges with the dispersed airflow. Step 4: The gas after being processed by the first layer of sector-shaped perforated plates continues to flow along the sector-shaped atomization chamber to the second layer of sector-shaped perforated plates. The processing method is the same as that of the first layer of sector-shaped perforated plates, and the cycle is repeated to complete the emission reduction treatment of the gas.

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