Waste gas treatment device suitable for rocket launching site station

Abstract

The invention discloses a waste gas treatment device suitable for a rocket launching site station, and belongs to the technical field of waste gas treatment, the waste gas treatment device is connected with a waste gas pipeline, the waste gas treatment device comprises a combustion furnace heat preservation piece and a combustor, and a combustion furnace is provided with a first section, a second section and a third section which are sequentially connected in the first direction; a first air distribution opening is formed in the periphery of the second section, and a second air distribution opening is formed in the periphery of the third section; the heat-insulating part is connected to the inner circumference of one end of the first section away from the second section; the combustor penetrates through the heat preservation part and is connected with the waste gas pipeline. The waste gas is fully treated through three-stage combustion, the combustion state during treatment is optimized, the generation amount of nitric oxide in the incineration process can be reduced, the treatment efficiency of the propellant waste gas is improved, and the treated waste gas reaches the standard and is discharged.

Description

Technical Field

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

[0002] As propellants for rocket engines, UDMH and nitrogen tetroxide are widely used in national defense and aerospace, where UDMH is a combustion agent and nitrogen tetroxide is an oxidant. UDMH and nitrogen tetroxide are often used as propellants at rocket launch sites. During the filling, transfer, gas inspection and tank pressure relief processes of the rocket filling system, a large amount of UDMH and nitrogen tetroxide waste gas is easily generated. Under normal temperature and reduced pressure, nitrogen tetroxide is easily decomposed into nitrogen dioxide, and mainly exists in the form of nitrogen dioxide in the oxidant waste gas.

[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 contacting air containing high concentrations of oxidant waste gas can also cause poisoning or skin damage to humans.

[0004] Therefore, a treatment device capable of effectively treating the waste gas of propellants such as unsymmetrical dimethylhydrazine and nitrogen tetroxide is needed. Summary of the invention

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

[0006] To achieve the above-mentioned objectives, 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, a thermal 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. A first air distribution port is arranged on the periphery of the second section, and a second air distribution port is arranged on the periphery of the third section. The thermal insulation component is connected to the inner periphery of an end of the first section away from the second section. The burner passes through the thermal 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 which 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 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 the exhaust gas is connected to the exhaust gas pipeline.

[0008] Optionally, the burner further includes swirl blades, and the swirl blades are arranged in a one-to-one correspondence with the channels for letting in 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 disposed at one end of the passage through which the exhaust gas is introduced 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 is introduced.

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

[0012] Optionally, the combustion furnace further comprises a connecting section, which connects 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 circumferentially arranged air inlets are provided between the thermal insulation component and the inner periphery of 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 and they 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 which 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 a waste gas treatment device suitable for a rocket launch site. The inner circumference of the first section is a primary combustion chamber, the inner circumference of the second section is a secondary combustion chamber, and the inner circumference of the third section is a tertiary combustion chamber. The hydrazine waste gas or nitrogen tetroxide waste 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 of the secondary combustion chamber is introduced by the first air distribution port, and the air distribution of 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, creates 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, part of the fuel leaving the primary combustion chamber is not completely burned, so the secondary combustion chamber must be introduced through the first air distribution port. The appropriate amount of oxygen and control the temperature in the appropriate range, so that the organic matter is fully burned in the secondary combustion chamber and avoids the generation of thermal nitrogen oxides. Finally, the second air distribution port introduces air into the three-stage combustion chamber to cool the high-temperature gas, increase the saturation of the flue gas, fully treat the exhaust gas through the three-stage combustion, optimize the combustion state during treatment, reduce the amount of nitrogen oxides produced during the incineration process, and improve the treatment efficiency of the propellant exhaust gas, so 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; Figure 2 This is a schematic diagram of the internal structure of the combustion furnace in the embodiment of the present application; Figure 3 This is a schematic diagram of ventilation at the second section in the embodiment of the present application; Figure 4 This is a schematic diagram of ventilation at the third section in the embodiment of the present application; Figure 5 The burner structure of the embodiment of the present application is shown in FIG. Figure 1 ; Figure 6 The burner structure of the embodiment of the present application is shown in FIG. Figure 2 .

[0018] 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, thermal insulation component; 3, burner; 31, swirl blade; 32, ring; 321, micropore; 4, igniter; 5, air inlet.

[0019] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] 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 components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0022] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0023] 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 used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. 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 the field to implement. When the combination of technical solutions is 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.

[0024] refer to Figure 1 to Figure 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. 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; 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.

[0025] 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 primary combustion chamber, the inner periphery of the second section 12 is a secondary combustion chamber, and the inner periphery of the third section 13 is a tertiary combustion chamber. The hydrazine waste gas or the nitrogen tetroxide waste gas is introduced into the combustion furnace 1 through the burner 3 for combustion, the air supply in the primary combustion chamber is introduced by the burner 3, the air supply to the secondary combustion chamber is introduced by the first air supply port 121, and the air supply to the tertiary combustion chamber is introduced by the second air supply port 131. Firstly, the primary 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 first combustion chamber controls the amount of oxygen according to laboratory data, some of the fuel leaving the first combustion chamber is not completely burned, so the second combustion chamber must be introduced into the second combustion chamber through the first air distribution port 121 and the temperature must be controlled in a suitable range, so that the organic matter is fully burned in the second combustion chamber and the generation of thermal nitrogen oxides is avoided. Finally, the second air distribution port 131 introduces air distribution into the third combustion chamber to cool the high-temperature gas, increase the saturation of the flue gas, fully treat the exhaust gas through the third combustion, optimize the combustion state during the treatment, reduce the amount of nitrogen oxides generated during the incineration process, and improve the treatment efficiency of the propellant exhaust gas, so that the treated exhaust gas meets the emission standards.

[0026] It should be noted that if Figure 1 and Figure 2 As shown, one 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.

[0027] 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.

[0028] 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 primary combustion chamber, the inner periphery of the second section 12 is the secondary combustion chamber, and the inner periphery of the third section 13 is the tertiary 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, so that the flame burning in the primary combustion chamber is concentrated in the central area, and the combustion process is more reasonable.

[0029] It should be understood that the purpose of the airflow introduced into the first air distribution port 121 is to fully react the unburned combustibles with the oxygen in the airflow introduced into the secondary combustion chamber, thereby achieving full combustion of the combustibles and controlling the temperature in the furnace body to remain within the optimal temperature preset range. The purpose of the airflow introduced into the second air distribution port 131 is to reduce the flue gas temperature in the third combustion chamber, increase the flue gas saturation, and prevent the flue gas from condensing when it is discharged.

[0030] in, Figure 6 N 2 O 4 That is nitrogen tetroxide waste gas.

[0031] 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 pipelines that are sequentially connected, the inner periphery of the pipeline located in the center is a channel, and the gap between adjacent pipelines 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.

[0032] 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 and 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 continuous.

[0033] It should be noted that if the exhaust gas is pre-mixed with the wind flow and injected into the primary combustion chamber, the combustion flame is relatively 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, the flame state is better, and the concentration of the exhaust gas injected alone is higher, which can ensure that the exhaust gas and the fuel react well and fully while maintaining a good flame state, increase the reaction rate, and further improve the exhaust gas treatment efficiency.

[0034] 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, and 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 are gradually reduced, so that corresponding gas pipelines can be connected to the peripheries of the corresponding channels for ventilation.

[0035] Furthermore, a flame detection device is provided at one end of the passage for introducing 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, so as to further ensure the normal progress of the exhaust gas treatment process.

[0036] refer to Figure 5 and Figure 6 In an exemplary embodiment, the burner 3 may further include swirl blades 31, and the swirl blades 31 are arranged in a one-to-one correspondence with the channels for introducing the external primary air and the internal primary air, and the swirl blades 31 are arranged in a surrounding manner in the corresponding channels.

[0037] Specifically, the swirl blades 31 can be arranged in the annular channel similar to the auger blades, so that the wind can only pass through the channel in a swirl manner, so that the inner primary air and the outer primary air can enter the primary combustion chamber in a swirl manner, so that the fuel and the exhaust gas can be more fully mixed with the oxygen in the inner primary air and the outer primary air, the combustion is more complete, the generation rate of nitrogen oxides is lower, that is, the exhaust gas treatment effect is better.

[0038] Furthermore, the rotation angle of the swirl blade 31 is a, 0°<a<90°. In a preferred embodiment, a is 45°. In this way, the swirl angle is larger, which can make the gases mix more fully.

[0039] 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 .

[0040] refer to Figure 6In 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 achieving a better treatment effect on the nitrogen tetroxide.

[0041] refer to Figure 5 In the exemplary embodiment, the exhaust gas is UDMH, and the burner 3 may further include a ring 32, which is disposed at one end of the exhaust gas passage close to the first section 11, and a plurality of micropores 321 are disposed on the ring 32, which are surrounded by the ring 32.

[0042] Specifically, the low calorific value of unsymmetrical dimethyl hydrazine is relatively high, the energy density is large, and it is easy to cause deflagration when sprayed with a large diameter; based on this, after the ring 32 and the micropore 321 are set, the unsymmetrical dimethyl hydrazine needs to be injected into the primary combustion chamber through the micropore 321, which effectively increases the flow rate of the unsymmetrical dimethyl hydrazine exhaust gas, prevents the burner 3 from backfired, and improves the combustion stability and ignition success rate.

[0043] It is worth mentioning that as an oxidant, nitrogen tetroxide has a relatively low energy density and a relatively high ignition point, so there is no need to set the micropores 321, and the solution of setting the swirl blades 31 can be adopted.

[0044] refer to Figure 2 In the exemplary embodiment, the cross-sectional area of ​​the inner circumference of the third section 13 perpendicular to the first direction is smaller than the cross-sectional area of ​​the inner circumference 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, which connects 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.

[0045] Specifically, 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 complete.

[0046] refer to Figure 2 In an exemplary embodiment, a plurality of surrounding air inlets 5 are provided between the thermal insulation component 2 and the inner periphery of 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.

[0047] 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 inlet 5 can enter the airflow close to the inner periphery of the first section 11, which is recorded as wall-adhering wind; the purpose of the wall-adhering 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 from the combustion furnace 1 to the outside world.

[0048] refer to Figure 3 In an exemplary embodiment, on a cross section perpendicular to the first direction, the flame in the second section 12 is concentrated and burns in a 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 tangent to the first circle.

[0049] Specifically, in the combustion furnace 1, the burner 3 sprays fuel and exhaust gas 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 airflow introduced into the first air distribution port 121 is secondary air, and the secondary air 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.

[0050] 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 directions in the multiple second air distribution ports 131 are tangent to the second circle.

[0051] 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 wind flow introduced into the second air distribution port 131 is tertiary wind, and the tertiary wind is tangent to the second circle. In this way, the tertiary wind is mixed with the flue gas generated after combustion more evenly, 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.

[0052] Further, such as Figure 3 or Figure 4 As shown, there may be four first air distribution openings 121 and four second air distribution openings 131 .

[0053] Furthermore, since the second section 12 and the third section 13 have a certain length in the first direction, taking the first air distribution port 121 as an example, the multiple first air distribution ports 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 port 131 is similar to that of the first air distribution port 121, and will not be described in detail here.

[0054] On the basis of the above embodiments, the present application may 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 for use in conjunction with the above waste gas emission device to form a waste gas treatment system for unsymmetrical dimethylhydrazine and nitrogen tetroxide.

[0055] The waste gas storage and transportation system is mainly composed of a gas storage tank, an automatic control valve, a flow meter, a pressure sensor, etc. The waste gas transportation system is connected to the waste gas channel on the burner 3 through a pipeline. The propellant waste gas is transported to the gas storage tank by the upstream filling system of the upper rocket. When the pressure of the gas storage tank reaches the set value, the automatic control valve opens and adjusts the waste gas flow entering the burner 3 according to the flow rate set by the flow meter. After the waste gas enters the combustion furnace 1 through the burner 3, it is ignited by the fuel flame and incinerated in the combustion chamber.

[0056] 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 automatic control valves and flow meters to control the combustion process.

[0057] The fuel delivery system is mainly composed of an oil pump, a fuel storage tank, an intermediate fuel tank, a pressure sensor, an automatic control valve, and a flow meter. The fuel delivery system is connected to the fuel channel on the burner 3 and the igniter 4. The fuel is delivered to the fuel channel and the igniter 4 at the burner 3 through the oil pump to maintain the flame and temperature of the main combustion zone of the combustion chamber. According to the exhaust gas treatment volume in the exhaust gas storage and delivery system, the flow meter and the automatic control valve cooperate with each other to adjust the amount of fuel entering the combustion chamber and control the combustion state.

[0058] The smoke emission system is mainly composed of a chimney, a smoke emission detection sensor, etc. After the propellant exhaust gas is burned in the combustion chamber, smoke is formed and discharged from the chimney. A smoke emission detection sensor is installed in the chimney and the emission data is detected by the smoke emission detection sensor to facilitate the adjustment of the exhaust gas flow rate of the exhaust gas storage and transportation system to achieve closed-loop control of the system.

[0059] In addition, considering the particularity of propellant exhaust gas, the system exhaust gas pipeline and exhaust gas treatment device will be automatically purged with protective gas (such as nitrogen, etc.) before and after exhaust gas treatment. And accidental purge is set for sudden equipment failure to prevent toxic gas leakage or residual exhaust gas explosion in the system (especially unsymmetrical dimethylhydrazine vapor).

[0060] 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 shut down due to lack of fuel during the treatment stage, causing a safety accident.

[0061] In addition, the exhaust gas treatment system can monitor the temperature in the three-stage combustion chamber in real time, and automatically adjust the values ​​of relevant parameters such as air distribution and oil distribution to maintain continuous and stable operation of the system. It also monitors the smoke emission from the chimney in real time, and adjusts the exhaust gas flow of the exhaust gas storage and transportation system according to the monitoring data to achieve closed-loop control of the system.

[0062] The above are only preferred embodiments of the present application, and are not intended to 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) comprising a first section (11), a second section (12) and a third section (13) which are sequentially connected in a first direction, the outer periphery of the second section (12) being provided with a first air distribution port (121), and the outer periphery of the third section (13) being provided with a second air distribution port (131); A heat-insulating component (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 component (2) and is connected to the exhaust gas pipeline.

2. The exhaust gas treatment device suitable for a rocket launch site as claimed in claim 1, characterized in that: 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 which are sleeved in sequence, the inner periphery of the pipe located at 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 thermal insulation component (2) in the first direction; Among them, 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 introducing the exhaust gas is connected to the exhaust gas pipeline.

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

4. The exhaust gas treatment device suitable for a rocket launch site as claimed in claim 2, characterized in that: The exhaust gas is unsymmetrical dimethylhydrazine, and the burner (3) further comprises: The circular ring (32) is arranged at one end of the passage for introducing the exhaust gas close to the first section (11), and the circular ring (32) is provided with a plurality of micropores (321), and the plurality of micropores (321) are arranged in a surrounding manner.

5. The exhaust gas treatment device suitable for a rocket launch site as claimed in claim 3, characterized in that: The exhaust gas is nitrogen tetroxide, and the swirl blades (31) are also arranged in the channel through which the nitrogen tetroxide is introduced.

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

7. The exhaust gas treatment device suitable for a rocket launch site as claimed in 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.

8. The exhaust gas treatment device suitable for a rocket launch site as claimed in claim 1, characterized in that: A plurality of air inlets (5) are arranged around the inner periphery of the heat-insulating component (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.

9. The exhaust gas treatment device suitable for a rocket launch site as claimed in claim 1, characterized in that: In 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 first air distribution openings (121) which are arranged in a circumferential manner, and the plurality of first air distribution openings (121) are evenly spaced; Wherein, the airflow directions in the plurality of first air distribution ports (121) are all tangent to the first circle.

10. The exhaust gas treatment device suitable for a rocket launch station 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; Wherein, the airflow directions in the plurality of second air distribution ports (131) are all tangent to the second circle.

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