An exhaust gas treatment device suitable for rocket launch sites

Abstract

This application discloses an exhaust gas treatment device suitable for a rocket launch site, belonging to the field of exhaust gas treatment technology. The exhaust gas treatment device is connected to an exhaust gas pipeline and includes a combustion furnace insulation member and a burner. The combustion furnace has a first section, a second section, and a third section connected sequentially in a first direction. The outer periphery of the second section is provided with a first air distribution port, and the outer periphery of the third section is provided with a second air distribution port. The insulation member is connected to the inner periphery of one end of the first section away from the second section. The burner penetrates the insulation member and is connected to the exhaust gas pipeline. This application fully treats the exhaust gas through three-stage combustion, optimizes the combustion state during treatment, reduces the amount of nitrogen oxides generated during the incineration process, improves the treatment efficiency of the propellant exhaust gas, and ensures that the treated exhaust gas meets the emission standards.

Description

Technical Field

[0001] The present application relates to the field of waste gas treatment technology, and in particular to a waste gas treatment device suitable for rocket launch sites. Background Art

[0002] Unsymmetrical dimethylhydrazine (UDMH) and dinitrogen tetroxide (N2O4) are widely used as propellants in rocket engines in the defense and aerospace industries. UDMH serves as the combustion agent, while N2O4 serves as the oxidizer. These two propellants are commonly used at rocket launch sites. Rocket fueling systems easily generate large amounts of UDMH and N2O4 waste gases during filling, transfer, gas testing, and tank depressurization. At room temperature and reduced pressure, N2O4 readily decomposes into nitrogen dioxide, which primarily exists in the oxidizer waste gas as nitrogen dioxide.

[0003] Both UDMH and nitrogen tetroxide are Class III toxic substances. UDMH is volatile, and inhaling high concentrations of UDMH waste gas can cause poisoning to humans. If nitrogen tetroxide waste gas is directly discharged into the atmosphere, it will pollute the environment and even form acid rain in severe cases. Inhaling or coming into contact with air containing high concentrations of oxidant waste gas can also cause poisoning or skin damage.

[0004] Therefore, a treatment device that can effectively treat propellant exhaust gases such as unsymmetrical dimethylhydrazine and nitrogen tetroxide is needed. Summary of the Invention

[0005] The main purpose of this application is to provide an exhaust gas treatment device suitable for rocket launch sites, aiming to solve the problem that the exhaust gases of unsymmetrical dimethylhydrazine and nitrogen tetroxide are difficult to treat.

[0006] To achieve the above-mentioned purpose, the present application provides an exhaust gas treatment device suitable for a rocket launch site, which is connected to an exhaust gas pipeline. The exhaust gas treatment device includes a combustion furnace, an insulation component and a burner. The combustion furnace has a first section, a second section and a third section connected in sequence in a first direction. The outer periphery of the second section is provided with a first air distribution port, and the outer periphery of the third section is provided with a second air distribution port; the insulation component is connected to the inner periphery of one end of the first section away from the second section; the burner passes through the insulation component and is connected to the exhaust gas pipeline.

[0007] Optionally, the exhaust gas treatment device also includes an igniter, which is arranged throughout the periphery of the first section; the burner includes five pipes that are connected in sequence, the inner periphery of the pipe located in the center is a channel, and the gap between adjacent pipes is a channel, and both ends of each channel are located on both sides of the insulation component in the first direction; wherein, from the center to the periphery, fuel oil, central air, inner primary air, exhaust gas, and outer primary air are introduced into each channel in sequence, and the channel for the exhaust gas is connected to the exhaust gas pipeline.

[0008] Optionally, the burner further includes swirl blades, which are arranged in a one-to-one correspondence with the channels for the external primary air and the internal primary air, and the swirl blades are arranged in a surrounding manner in the corresponding channels.

[0009] Optionally, the exhaust gas is UDMH, and the burner further includes a ring, which is arranged at one end of the channel for introducing the exhaust gas close to the first section, and the ring is provided with a plurality of micropores, which are arranged in a surrounding manner.

[0010] Optionally, the exhaust gas is nitrogen tetroxide, and the swirl blades are also provided in the channel through which the nitrogen tetroxide flows.

[0011] Optionally, the cross-sectional area of the inner circumference of the third segment perpendicular to the first direction is smaller than the cross-sectional area of the inner circumference of the second segment perpendicular to the first direction.

[0012] Optionally, the combustion furnace further includes a connecting section connecting the second section and the third section; wherein, in the first direction, the connecting section gradually shrinks from the second section to the third section.

[0013] Optionally, a plurality of air inlets are arranged around the inner periphery of the thermal insulation component and the first section; wherein the air inlets are connected to two opposite sides of the thermal insulation component in the first direction.

[0014] Optionally, on a cross section perpendicular to the first direction, the flame in the second section burns concentratedly in a first circle; there are multiple first air distribution outlets that are arranged in a surrounding manner, and the multiple first air distribution outlets are evenly spaced; wherein, the airflow directions in the multiple first air distribution outlets are tangent to the first circle.

[0015] Optionally, on a cross section perpendicular to the first direction, the flame in the third section burns concentratedly in a second circle; there are multiple second air distribution outlets that are arranged in a surrounding manner, and the multiple second air distribution outlets are evenly spaced; wherein the airflow directions in the multiple second air distribution outlets are tangent to the second circle.

[0016] The embodiment of the present application proposes an exhaust gas treatment device suitable for a rocket launch site. The inner periphery of the first section is a primary combustion chamber, the inner periphery of the second section is a secondary combustion chamber, and the inner periphery of the third section is a tertiary combustion chamber. The unilateral dimethylhydrazine exhaust gas or nitrogen tetroxide exhaust gas is introduced into the combustion furnace through a burner for combustion. The air distribution in the primary combustion chamber is introduced by the burner, the air distribution in the secondary combustion chamber is introduced by the first air distribution port, and the air distribution in the tertiary combustion chamber is introduced by the second air distribution port. First, the primary combustion chamber controls the reaction temperature and gas equivalence ratio to create a constant temperature oxygen-deficient combustion environment, inhibits the generation of fuel-type and thermal nitrogen oxides, and reduces nitrogen oxides to nitrogen, optimizes the reaction state, and improves the treatment efficiency. Secondly, because the primary combustion chamber controls the oxygen content according to laboratory data, some of the fuel leaving the primary combustion chamber is not completely burned. Therefore, the secondary combustion chamber must introduce an appropriate amount of oxygen through the first air distribution port and control the temperature to be in a suitable range, so that the organic matter is fully burned in the secondary combustion chamber and the generation of thermal nitrogen oxides is avoided. Finally, the second air distribution port introduces air into the three-stage combustion chamber to cool the high-temperature gas and increase the saturation of the flue gas. The exhaust gas is fully treated through the three-stage combustion, and the combustion state during treatment is optimized. This can reduce the amount of nitrogen oxides produced during the incineration process, improve the treatment efficiency of the propellant exhaust gas, and ensure that the treated exhaust gas meets the emission standards. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the structure of a combustion furnace of an exhaust gas treatment device suitable for a rocket launch station provided in an embodiment of the present application;

[0018] Figure 2 This is a schematic diagram of the internal structure of the combustion furnace in the embodiment of the present application;

[0019] Figure 3 This is a schematic diagram of ventilation at the second section in the embodiment of the present application;

[0020] Figure 4 This is a schematic diagram of ventilation at the third section in the embodiment of the present application;

[0021] Figure 5 The burner structure of the embodiment of the present application is shown in FIG. Figure 1 ;

[0022] Figure 6 The burner structure of the embodiment of the present application is shown in FIG. Figure 2 .

[0023] In the figure: 1. Combustion furnace; 11. First section; 12. Second section; 121. First air distribution port; 13. Third section; 131. Second air distribution port; 14. Connecting section; 2. Insulation component; 3. Burner; 31. Swirl blade; 32. Ring; 321. Micropore; 4. Igniter; 5. Air inlet.

[0024] The realization of the objectives, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0025] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0026] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0027] In the present invention, unless otherwise specified or limited, the terms "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can mean fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will be able to understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0028] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or suggesting their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of such features. In addition, the meaning of "and / or" appearing throughout the text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme in which A and B are satisfied at the same time. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0029] refer to Figures 1 to 6An embodiment of the present application provides an exhaust gas treatment device suitable for a rocket launch site, which is connected to an exhaust gas pipeline. The exhaust gas treatment device may include a combustion furnace 1, a thermal insulation component 2 and a burner 3. The combustion furnace 1 has a first section 11, a second section 12 and a third section 13 connected in sequence in a first direction. A first air distribution port 121 is provided on the periphery of the second section 12, and a second air distribution port 131 is provided on the periphery of the third section 13; the thermal insulation component 2 is connected to the inner periphery of one end of the first section 11 away from the second section 12; the burner 3 passes through the thermal insulation component 2 and is connected to the exhaust gas pipeline.

[0030] The embodiment of the present application proposes an exhaust gas treatment device suitable for a rocket launch site, wherein the inner periphery of the first section 11 is a first-stage combustion chamber, the inner periphery of the second section 12 is a second-stage combustion chamber, and the inner periphery of the third section 13 is a third-stage combustion chamber. The unilateral dimethylhydrazine exhaust gas or the dinitrogen tetroxide exhaust gas is introduced into the combustion furnace 1 through the burner 3 for combustion, the air supply in the first-stage combustion chamber is introduced by the burner 3, the air supply for the second-stage combustion chamber is introduced by the first air supply port 121, and the air supply for the third-stage combustion chamber is introduced by the second air supply port 131. First, the first-stage combustion chamber controls the reaction temperature and the gas equivalence ratio, creates a constant-temperature oxygen-deficient combustion environment, suppresses the generation of fuel-type and thermal-type nitrogen oxides, and reduces the nitrogen oxides to nitrogen, thereby optimizing the reaction state and improving the treatment efficiency. Secondly, because the oxygen level in the first combustion chamber is controlled based on laboratory data, some fuel exiting the first combustion chamber remains unburned. Therefore, the second combustion chamber must be fed with an appropriate amount of oxygen through first air distribution port 121 and its temperature controlled within a suitable range to fully burn organic matter within the second combustion chamber and prevent the production of thermal nitrogen oxides. Finally, second air distribution port 131 introduces air into the third combustion chamber, cooling the high-temperature gases and increasing the flue gas saturation. This third-stage combustion fully treats the exhaust gas, optimizing the combustion state during treatment, reducing the amount of nitrogen oxides produced during the incineration process, improving the treatment efficiency of the propellant exhaust, and ensuring that the treated exhaust gas meets emission standards.

[0031] It should be noted that if Figure 1 and Figure 2 As shown, the end of the third section 13 away from the second section 12 is connected to a chimney to discharge the treated exhaust gas; the first direction is the same as the axial direction of the combustion furnace 1.

[0032] Among them, the exhaust gas pipeline can be a hydrazine exhaust gas pipeline, or a nitrogen tetroxide exhaust gas pipeline, or other nitrogen oxide exhaust gas pipeline. In the embodiment of the present application, the device is mainly used to treat hydrazine and nitrogen tetroxide, so as to be suitable for the exhaust gas treatment of the rocket filling system in the rocket launch station.

[0033] In addition, the first section 11, the second section 12 and the third section 13 are all hollow cylindrical. The inner periphery of the first section 11 is the first-stage combustion chamber, the inner periphery of the second section 12 is the second-stage combustion chamber, and the inner periphery of the third section 13 is the third-stage combustion chamber. The thermal insulation part 2 arranged on the inner periphery of one end of the first section 11 can be in the shape of a pancake, and the burner 3 passes through the center position of the thermal insulation part 2. In this way, the flame burning in the first-stage combustion chamber is concentrated in the central area, and the combustion process is more reasonable.

[0034] It should be understood that the purpose of the airflow introduced through the first air distribution port 121 is to fully react unburned combustibles with the oxygen in the airflow introduced into the secondary combustion chamber, thereby achieving complete combustion of the combustibles and controlling the temperature within the furnace to remain within the preset optimal temperature range. The purpose of the airflow introduced through the second air distribution port 131 is to lower the flue gas temperature in the tertiary combustion chamber, increase the flue gas saturation, and prevent condensation of the flue gas upon exhaust.

[0035] in, Figure 6 The N2O4 in it is nitrogen tetroxide waste gas.

[0036] refer to Figure 5 and Figure 6 In an exemplary embodiment, the exhaust gas treatment device may further include an igniter 4, which is arranged throughout the outer periphery of the first section 11; the burner 3 may include five pipes that are sequentially connected, the inner periphery of the pipe located in the center is a channel, and the gap between adjacent pipes is a channel, and both ends of each channel are located on both sides of the insulation component 2 in the first direction; wherein, from the center to the periphery, fuel oil, central air, inner primary air, exhaust gas, and outer primary air are sequentially introduced into each channel, and the channel for introducing exhaust gas is connected to the exhaust gas pipeline.

[0037] Specifically, the burner 3 adopts a layered structure, and the fuel enters the first-stage combustion chamber and is ignited by the igniter 4, and the central wind provides oxygen for igniting the fuel; in addition, the inner primary wind and the outer primary wind both provide oxygen for the combustion of the exhaust gas, play a combustion-supporting role, and can both be called combustion-supporting wind. The exhaust gas is sandwiched between the inner primary wind and the outer primary wind, which can increase the contact area between the exhaust gas and the combustion-supporting wind, so that the exhaust gas and the fuel are fully mixed with the oxygen in the central wind, the inner primary wind, and the outer primary wind, which can not only achieve the reduction reaction between the propellant exhaust gas and kerosene to inhibit the production of nitrogen oxides, but also can undergo a continuous oxidation reaction with the oxygen in the primary wind to keep the flame from going out.

[0038] It should be noted that if the exhaust gas is pre-mixed with the airflow and injected into the primary combustion chamber, the combustion flame will be more divergent. In the embodiment of the present application, the exhaust gas is sandwiched between the inner primary air and the outer primary air and injected into the primary combustion chamber in layers, which improves the flame state. The concentration of the exhaust gas injected separately is higher. While maintaining a good flame state, it can ensure that the exhaust gas and fuel react well and fully, increase the reaction rate, and further improve the exhaust gas treatment efficiency.

[0039] It should be understood that, from the center to the periphery of the burner 3, the channels are sequentially recorded as the first channel to the fifth channel. The first channel is fed with fuel and connected to an external fuel pipeline. The fuel may be aviation kerosene. In the second channel to the fifth channel, one end of each channel away from the first section 11 is closed, such as Figure 5 or Figure 6 As shown, the lengths of the second to fifth channels extending out of the combustion furnace 1 gradually decrease, so that corresponding gas pipelines can be connected to the periphery of the corresponding channels for ventilation.

[0040] Furthermore, a flame detection device is provided at one end of the passage for the internal primary air outside the combustion furnace 1 to detect whether there is a flame in the combustion furnace 1 and whether the flame is normal, thereby further ensuring that the exhaust gas treatment process proceeds normally.

[0041] refer to Figure 5 and Figure 6 In an exemplary embodiment, the burner 3 may further include swirl blades 31. The swirl blades 31 are arranged in a one-to-one correspondence with the channels for the external primary air and the internal primary air, and the swirl blades 31 are arranged in a surrounding manner in the corresponding channels.

[0042] Specifically, the swirl blades 31 can be similar to the auger blades and are arranged in the annular channel so that the airflow can only pass through the channel in a swirl manner. In this way, the inner primary air and the outer primary air can enter the first-stage combustion chamber in a swirl manner. This allows the fuel and exhaust gas to be more fully mixed with the oxygen in the inner primary air and the outer primary air, resulting in more complete combustion and a lower generation rate of nitrogen oxides, that is, a better exhaust gas treatment effect.

[0043] Furthermore, the rotation angle of the swirl blade 31 is a, 0°<a<90°. In a preferred embodiment, a is 45°. Such a large swirl angle can make the gases mix more fully.

[0044] It should be noted that the rotation angle of the swirl blade 31 refers to the angle between the axes of the swirl blade 31 and the swirl blade 31 .

[0045] refer to Figure 6 In the exemplary embodiment, the exhaust gas is nitrogen tetroxide, and a swirl blade 31 is also provided in the channel for introducing the nitrogen tetroxide, that is, a swirl blade 31 is also provided in the fourth channel, so that the nitrogen tetroxide is injected into the primary combustion chamber in a swirl manner, and is more fully mixed with the fuel and oxygen, thereby having a better treatment effect on the nitrogen tetroxide.

[0046] refer to Figure 5In the exemplary embodiment, the exhaust gas is UDMH, and the burner 3 may further include a ring 32, which is arranged at one end of the exhaust gas inlet channel close to the first section 11, and a plurality of micropores 321 are provided on the ring 32, which are surrounded by the plurality of micropores 321.

[0047] Specifically, UDMH has a high low calorific value and a high energy density, and is prone to deflagration when injected with a large aperture. Based on this, after the ring 32 and the micropore 321 are provided, UDMH needs to be injected into the primary combustion chamber through the micropore 321, effectively increasing the flow rate of the UDMH exhaust gas, preventing the burner 3 from backfiring, and improving the combustion stability and ignition success rate.

[0048] It is worth mentioning that nitrogen tetroxide, as an oxidant, has a low energy density and a relatively high ignition point, so there is no need to set the microholes 321, and the solution of setting the swirl blades 31 can be adopted.

[0049] refer to Figure 2 In the exemplary embodiment, the cross-sectional area of the inner periphery of the third section 13 perpendicular to the first direction is smaller than the cross-sectional area of the inner periphery of the second section 12 perpendicular to the first direction. In the exemplary embodiment, the combustion furnace 1 may further include a connecting section 14 connecting the second section 12 and the third section 13; wherein the connecting section 14 gradually contracts from the second section 12 to the third section 13 in the first direction.

[0050] Specifically, such as Figure 2 As shown, in the first direction, from the second section 12 to the third section 13, the connecting section 14 contracts in a trumpet shape, which can effectively increase the flue gas flow rate at the outlet of the secondary combustion chamber, and the connecting section 14 that contracts in a trumpet shape can promote the mixing of exhaust gas and oxygen, making the exhaust gas oxidation reaction more complete; at the same time, the connecting section 14 that contracts in a trumpet shape can improve the uniformity of the flow field in the primary combustion chamber and the secondary combustion chamber, making the temperature field in the combustion furnace 1 more uniform and the reaction more sufficient.

[0051] refer to Figure 2 In an exemplary embodiment, a plurality of air inlets 5 are arranged around the inner periphery of the thermal insulation component 2 and the first section 11; wherein the air inlets 5 are connected to two opposite sides of the thermal insulation component 2 in the first direction.

[0052] It should be noted that the air inlet 5 can be formed by surrounding the insulation part 2 and the first section 11, so that the air flow can enter the air inlet 5 along the inner periphery of the first section 11, which is recorded as wall-adjacent wind; the purpose of the wall-adjacent wind is to maintain the temperature of the outer wall of the high-temperature zone of the combustion chamber at a lower state during the combustion of the exhaust gas, so as to cool the inner wall of the combustion furnace 1 and reduce the heat energy radiated by the combustion furnace 1 to the outside world.

[0053] refer to Figure 3In an exemplary embodiment, on a cross section perpendicular to the first direction, the flame in the second section 12 is concentrated and burns in the first circle; there are multiple first air distribution ports 121 and they are arranged in a surrounding manner, and the multiple first air distribution ports 121 are evenly spaced; wherein, the airflow directions in the multiple first air distribution ports 121 are all tangent to the first circle.

[0054] Specifically, in the combustion furnace 1, fuel and exhaust gas are sprayed by the burner 3 for combustion, and the flame should be sprayed in a columnar shape. Therefore, on the cross section perpendicular to the first direction, the flame in the second section 12 is concentrated in the first circle for combustion, and the air flow introduced into the first air distribution port 121 is secondary air, which is tangent to the first circle. In this way, the secondary air allows the unburned combustibles to fully mix and react with the oxygen in the secondary air, thereby achieving full combustion of the combustibles and controlling the temperature in the furnace body to remain within the optimal temperature preset range.

[0055] refer to Figure 4 In an exemplary embodiment, on a cross section perpendicular to the first direction, the flame in the third section 13 is concentrated and burns in the second circle; there are multiple second air distribution ports 131 and they are arranged in a surrounding manner, and the multiple second air distribution ports 131 are evenly spaced; wherein, the airflow direction in the multiple second air distribution ports 131 is tangent to the second circle.

[0056] Specifically, on the cross section perpendicular to the first direction, the flame in the third section 13 is concentrated in the second circle to burn, and the airflow entering the second air distribution port 131 is tertiary wind, which is tangent to the second circle. In this way, the tertiary wind is mixed more evenly with the flue gas generated after combustion, which is convenient for cooling the high-temperature flue gas after combustion, improving the saturation of the flue gas, and facilitating the discharge of the flue gas.

[0057] Further, such as Figure 3 or Figure 4 As shown, there can be four first air distribution openings 121 and four second air distribution openings 131 .

[0058] Furthermore, since the second section 12 and the third section 13 have a certain length in the first direction, taking the first air distribution outlet 121 as an example, the multiple first air distribution outlets 121 arranged in a surrounding manner can be recorded as a group of first air distribution structures, and multiple groups of first air distribution structures can be arranged at intervals in the first direction to ensure sufficient ventilation in the second section 12. In the embodiment of the present application, two groups of first air distribution structures are set; in addition, the setting of the second air distribution outlet 131 is similar to that of the first air distribution outlet 121, and will not be described in detail here.

[0059] Based on the above embodiments, the present application can also be provided with a waste gas storage and transportation system, an air distribution system, a fuel delivery system and a flue gas emission system to be used in conjunction with the above waste gas emission device to form a waste gas treatment system for unsymmetrical dimethylhydrazine and nitrogen tetroxide.

[0060] The exhaust gas storage and transportation system primarily consists of a gas storage tank, an automatic valve, a flow meter, and a pressure sensor. The exhaust gas delivery system is connected to the exhaust gas channel on burner 3 via piping. Propellant exhaust gas is delivered to the gas storage tank by the upstream filling system of the upper rocket. When the tank pressure reaches the set value, the automatic valve opens and adjusts the exhaust gas flow rate entering burner 3 according to the flow meter setting. After passing through burner 3 and into combustion furnace 1, the exhaust gas is ignited by the fuel flame and incinerated within the combustion chamber.

[0061] The air distribution system is mainly composed of a fan, an automatic control valve, and a flow meter. The air distribution system is connected to the first air distribution port 121, the second air distribution port 131, and the central air channel, the inner primary air channel, and the outer primary air channel on the burner 3 through pipelines, and controls the air flow through the automatic control valve and the flow meter to control the combustion process.

[0062] The fuel delivery system primarily consists of an oil pump, fuel storage tank, intermediate fuel tank, pressure sensor, automatic valve, and flow meter. The system is connected to the fuel channel on burner 3 and igniter 4. Fuel is pumped to the fuel channel and igniter 4 on burner 3 to maintain the flame and temperature in the main combustion zone of the combustion chamber. The flow meter and automatic valve coordinate with each other to adjust the amount of fuel entering the combustion chamber based on the exhaust gas treatment volume in the exhaust gas storage and delivery system, thereby controlling the combustion state.

[0063] The flue gas emission system is mainly composed of a chimney, a flue gas emission detection sensor, etc. After the propellant exhaust gas is burned in the combustion chamber, the flue gas is formed and discharged from the chimney. A flue gas emission detection sensor is installed in the chimney and the emission data is detected by the flue gas emission detection sensor to facilitate the adjustment of the exhaust gas flow of the exhaust gas storage and transportation system to achieve closed-loop control of the system.

[0064] Furthermore, considering the unique characteristics of propellant exhaust, the system's exhaust pipes and exhaust treatment devices are automatically purged with protective gas (such as nitrogen) before and after exhaust treatment. An emergency purge is also implemented to prevent toxic gas leaks or explosions from residual exhaust (especially UDMH vapor) in the system in the event of a sudden equipment failure.

[0065] Among them, the exhaust gas treatment system can also monitor the liquid level of the fuel tank in real time, and provide low liquid level reminders or automatically add fuel to the fuel tank to prevent the burner 3 from being extinguished due to lack of fuel during the treatment stage, causing a safety accident.

[0066] In addition, the exhaust gas treatment system monitors the temperature inside the three-stage combustion chamber in real time and automatically adjusts relevant parameters such as air and oil distribution to maintain continuous and stable system operation. It also monitors chimney flue gas emissions in real time and adjusts the exhaust gas flow rate of the exhaust gas storage and transportation system based on the monitoring data, achieving closed-loop control of the system.

[0067] The above are only preferred embodiments of the present application and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. An exhaust gas treatment device suitable for a rocket launch site, characterized in that: Connected to the exhaust gas pipeline, the exhaust gas treatment device includes: A combustion furnace (1) comprises a first section (11), a second section (12), and a third section (13) connected in sequence in a first direction, wherein the outer periphery of the second section (12) is provided with a first air distribution port (121), and the outer periphery of the third section (13) is provided with a second air distribution port (131); A heat-insulating element (2) connected to the inner periphery of an end of the first section (11) away from the second section (12); A burner (3) passes through the heat-insulating member (2) and is connected to the exhaust gas pipeline; The exhaust gas treatment device further comprises an igniter (4), wherein the igniter (4) is arranged through the outer periphery of the first section (11); The burner (3) comprises five pipes that are sleeved in sequence, the inner periphery of the pipe located in the center is a channel, the gap between adjacent pipes is a channel, and both ends of each channel are located on both sides of the insulation component (2) in the first direction; Among them, from the center to the periphery, each channel is sequentially fed with fuel, central air, inner primary air, exhaust gas, and outer primary air, and the channel for the exhaust gas is connected to the exhaust gas pipeline; The exhaust gas is unsymmetrical dimethylhydrazine, and the burner (3) further comprises: A circular ring (32) is arranged at one end of the passage for introducing the exhaust gas close to the first section (11), and a plurality of micropores (321) are arranged on the circular ring (32), and the plurality of micropores (321) are arranged in a surrounding manner.

2. The exhaust gas treatment device suitable for a rocket launch site according to claim 1, characterized in that: The burner (3) further comprises: The swirl blades (31) are arranged in a one-to-one correspondence with the channels for the external primary air and the internal primary air, and the swirl blades (31) are arranged in a surrounding manner in the corresponding channels.

3. The exhaust gas treatment device suitable for a rocket launch site according to claim 2, characterized in that: The exhaust gas is nitrogen tetroxide, and the swirl blade (31) is provided in the channel for introducing the nitrogen tetroxide instead of the ring (32).

4. The exhaust gas treatment device suitable for a rocket launch site according to claim 1, characterized in that: The cross-sectional area of the inner periphery of the third section (13) perpendicular to the first direction is smaller than the cross-sectional area of the inner periphery of the second section (12) perpendicular to the first direction.

5. The exhaust gas treatment device suitable for a rocket launch site according to claim 1, characterized in that: The combustion furnace (1) further comprises: a connecting section (14), connecting the second section (12) and the third section (13); Wherein, in the first direction, from the second section (12) to the third section (13), the connecting section (14) gradually shrinks.

6. The exhaust gas treatment device suitable for a rocket launch site according to claim 1, characterized in that: A plurality of air inlets (5) are arranged around the inner periphery of the heat-insulating element (2) and the first section (11); Wherein, the air inlet (5) is connected to two opposite sides of the thermal insulation component (2) in the first direction.

7. The exhaust gas treatment device suitable for a rocket launch site according to claim 1, characterized in that: On a cross section perpendicular to the first direction, the flame in the second section (12) burns concentratedly in a first circle; There are a plurality of the first air distribution openings (121) which are arranged in a surrounding manner, and the plurality of the first air distribution openings (121) are evenly spaced; The directions of the airflow in the plurality of first air distribution ports (121) are all tangent to the first circle.

8. The exhaust gas treatment device suitable for a rocket launch site according to claim 1, characterized in that: On a cross section perpendicular to the first direction, the flame in the third section (13) burns concentratedly in a second circle; There are a plurality of the second air distribution openings (131) which are arranged in a circumferential manner, and the plurality of the second air distribution openings (131) are evenly spaced; The directions of the airflow in the plurality of second air distribution ports (131) are all tangent to the second circle.

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