Axially distributed surface tension storage tank for gas trap compartments

Abstract

The invention relates to the technical field of energy storage, in particular to a gas trap bulkhead axially-distributed surface tension storage box which comprises an upper seal head section, a first cylinder section, a second cylinder section and a lower seal head section, and a first gas trap is arranged at the joint of the upper seal head section and the first cylinder section; a second gas trap is arranged at the joint of the first cylinder section and the second cylinder section; a T-shaped ring is arranged at the joint of the second cylinder section and the lower sealing head section; and a third gas trap is arranged at the bottom end in the lower sealing head section. The surface tension storage tank is applied to the field of carrier rockets, according to the flight time sequence of the carrier rockets, the propellant remaining amounts of different stages are calculated, a plurality of closed traps composed of capillary screens and shells are sequentially arranged from an air port to a liquid port, and it is guaranteed that the propellant with the flow meeting the requirement and not carrying bubbles is supplied under the flight working condition.

Description

Technical Field

[0001] The present application relates to the technical field of energy storage, and in particular to an axially distributed surface tension storage tank with a gas trap compartment. Background Art

[0002] In order to ensure the safe and reliable operation of launch vehicles and spacecraft, propellant must be accurately injected into the engine for combustion when needed. If the propellant tank is discharged and gas is entrained, the rocket engine will stall or even explode, with extremely serious consequences. Therefore, liquid propellant tanks require a management device that can store liquid and discharge the liquid without entrained gas when needed.

[0003] At present, the tanks of launch vehicles and spacecraft all solve the problem of non-air-entrained discharge based on the idea of ​​making the liquid cover the discharge port. According to the constraints of operating conditions, space, weight, cost, etc., a variety of specific methods have been developed. Among them, the surface tension tank is widely used in spacecraft due to its light weight, simple structure and no moving parts. This type of tank utilizes the characteristic that surface tension plays a dominant role in a micro-low gravity environment. When the screen is wetted, a liquid film is formed on the mesh. Under the support of capillary pressure difference, the liquid film can withstand a certain pressure without being damaged. In this way, the liquid in the tank can enter the channel through the screen and be discharged, while the gas is blocked outside the channel, thereby achieving the purpose of gas-liquid separation. By reasonably designing the internal structure of the tank and utilizing surface tension to store part or all of the propellant and cover the tank discharge port, the normal supply of propellant in a microgravity environment can be achieved.

[0004] However, the traditional surface tension tanks (such as plate type and mesh type surface tension tanks) have harsh application conditions and can only adapt to accelerations not exceeding 10 -3 g working condition, so it is only used in outer space, that is, the activity area of ​​​​spacecraft. Summary of the invention

[0005] The present application provides a gas trap compartment axially distributed surface tension tank, which is used to store and supply non-gas-entrained liquid propellant for the attitude control power system of a launch vehicle and has a certain overload resistance and discharge capability.

[0006] In order to achieve the above-mentioned purpose, the present application provides a gas trap compartment axially distributed surface tension storage tank, comprising an upper head section, a first cylindrical section, a second cylindrical section and a lower head section, wherein: a first gas trap is arranged at the connection between the upper head section and the first cylindrical section; a second gas trap is arranged at the connection between the first cylindrical section and the second cylindrical section; a T-ring is arranged at the connection between the second cylindrical section and the lower head section; and a third gas trap is arranged at the bottom end inside the lower head section.

[0007] Furthermore, both the upper head section and the lower head section are semicircular air cavity sealing structures.

[0008] Furthermore, the first gas trap includes a first top plate, a first trap seat, a first cover plate and a screen assembly, wherein: the first top plate is buckled on the first trap seat, and an inlet is provided on the first top plate; the first cover plate is arranged at the center of the first trap seat, and forms a first chamber with the middle area of ​​the first trap seat; the interior of the first chamber is an annular maze structure, and screen assemblies are provided on the top and bottom of the first chamber.

[0009] Furthermore, the second gas trap includes a second top plate, a second trap seat, a second cover plate and a screen assembly, wherein: the second top plate is buckled on the second trap seat; the second cover plate is arranged at the center of the second trap seat and forms a second chamber with the middle area of ​​the second trap seat; a plurality of screen assemblies are arranged on the top and bottom of the second chamber; and a plurality of inlets corresponding to the plurality of screen assemblies are arranged on the second top plate.

[0010] Furthermore, the third gas trap includes a third cover plate, a fourth cover plate and multiple screen assemblies, wherein: the third cover plate is arranged above the fourth cover plate, and the third cover plate and the third cover plate are both welded to the inner wall of the shell of the lower head section; multiple screen assemblies are evenly distributed on the surface of the third cover plate and the fourth cover plate; a third chamber is formed between the third cover plate and the fourth cover plate.

[0011] Furthermore, a first anti-sway grid is welded below the first gas trap via a T-shaped bracket; a second anti-sway grid is welded above the third gas trap via a T-shaped bracket; and an anti-slump grid is welded below the third gas trap via a T-shaped bracket.

[0012] Furthermore, the first anti-sway grille and the second anti-sway grille are both welded by anti-sway plates and anti-sway rings.

[0013] Furthermore, the anti-swirl collapse grille is welded by an anti-swirl collapse plate and an anti-swirl collapse ring.

[0014] Furthermore, the materials of the first anti-sway grille, the second anti-sway grille and the anti-collapse grille are all TC4, with a thickness of 1-2 mm.

[0015] Furthermore, the screen assembly is composed of a pressing plate and a mesh, the mesh is fixed to the cover plate through the pressing plate, and the mesh is a 00Cr18Ni13 or 316L twill weave mesh.

[0016] The present application provides a gas trap compartment axially distributed surface tension storage tank, which has the following beneficial effects:

[0017] The present application applies a surface tension tank to the field of launch vehicles. According to the flight sequence of the launch vehicle, by calculating the propellant surplus at different stages, a number of closed traps consisting of a capillary screen and a shell are sequentially arranged from the gas port to the liquid port to ensure that the propellant supply meets the flow requirements and does not carry bubbles under flight conditions; and in order to prevent the problem of air inclusion caused by liquid collapse and vortexes at the end of the tank discharge, a baffle + cross grid integrated anti-collapse vortex device is also arranged to prevent liquid surface collapse and vortex formation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings constituting a part of this application are used to provide a further understanding of this application, so that other features, purposes and advantages of this application become more obvious. The schematic embodiment drawings and their descriptions of this application are used to explain this application and do not constitute an improper limitation on this application. In the drawings:

[0019] Figure 1 It is a structural schematic diagram of an axially distributed surface tension tank of a gas trap compartment provided in an embodiment of the present application;

[0020] Figure 2 is a schematic diagram of a first gas trap provided according to an embodiment of the present application;

[0021] Figure 3 is a schematic diagram of a second gas trap provided according to an embodiment of the present application;

[0022] Figure 4 is a schematic diagram of a third gas trap provided according to an embodiment of the present application;

[0023] Figure 5 is a schematic diagram of a first anti-sway grille (a second anti-sway grille) provided according to an embodiment of the present application;

[0024] Figure 6 is a schematic diagram of an anti-slump vortex grille provided according to an embodiment of the present application;

[0025] Figure 7 It is a schematic diagram of liquid distribution during positive axial overload flight of an axially distributed surface tension tank of a gas trap compartment provided in an embodiment of the present application;

[0026] Figure 8 It is a schematic diagram of liquid distribution during the first "gliding-working" period of the axially distributed surface tension tank of the gas trap compartment provided in an embodiment of the present application;

[0027] Fig. 9 It is a schematic diagram of liquid distribution during the second "gliding-working" period of the gas trap compartment axially distributed surface tension tank provided in an embodiment of the present application;

[0028] Fig.10It is a schematic diagram of liquid distribution during the third "glide-work" period of the axially distributed surface tension tank of the gas trap compartment provided by the embodiment of the present application;

[0029] In the figure: 1-upper head section, 2-first cylindrical section, 3-second cylindrical section, 4-lower head section, 5-first gas trap, 51-first trap seat, 52-first cover plate, 53-first top plate, 6-second gas trap, 61-second trap seat, 62-second cover plate, 63-second top plate, 7-T-ring, 8-third gas trap, 81-third cover plate, 82-fourth cover plate, 9-T-shaped bracket, 10-first anti-sway grille, 11-second anti-sway grille, 12-anti-collapse vortex grille, 13-anti-sway plate, 14-anti-sway ring, 15-anti-collapse vortex plate, 16-anti-collapse vortex ring, 17-screen assembly, 18-inlet. DETAILED DESCRIPTION

[0030] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0031] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0032] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0033] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0034] In addition, the term "plurality" shall mean two or more.

[0035] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0036] like Figure 1 As shown, the present application provides a gas trap compartment axially distributed surface tension storage tank, comprising an upper head section 1, a first cylindrical section 2, a second cylindrical section 3 and a lower head section 4, wherein: a first gas trap 5 is provided at the connection between the upper head section 1 and the first cylindrical section 2; a second gas trap 6 is provided at the connection between the first cylindrical section 2 and the second cylindrical section 3; a T-ring 7 is provided at the connection between the second cylindrical section 3 and the lower head section 4; and a third gas trap 8 is provided at the bottom end inside the lower head section 4.

[0037] Specifically, the gas trap compartment axially distributed surface tension tank provided in the embodiment of the present application stores and manages propellant based on the surface tension principle, and is mainly used to store and supply non-gas-entrained liquid propellant to the attitude control power system of the launch vehicle. It has a certain overload discharge resistance capability, and a plurality of position-adjustable gas trap compartments are arranged according to the profiles of different missions of the rocket, thereby being able to meet the propellant management requirements under all working conditions. The tank is composed of four sections as a whole, of which the upper and lower sections are head structures, and the middle two sections are cylindrical tank bodies. The materials for making the head section and the cylinder section are preferably TC4; the first gas trap 5 is arranged at the connection between the upper head section 1 and the first cylinder section 2, the second gas trap 6 is arranged at the connection between the first cylinder section 2 and the second cylinder section 3, and the T-ring 7 is arranged at the connection between the second cylinder section 3 and the lower head section 4, which is used to provide a lock bottom for vacuum electron beam welding to prevent welding through, and the third gas trap 8 is arranged at the bottom end inside the lower head section 4; the rocket engine does not work during the gliding stage, and it flies by inertia. At this time, the liquid in the tank is in a weightless state. The three gas traps are mainly used to manage the liquid inside the tank during the gliding stage to ensure that no gas passes through the trap outlet during this "gliding" period, so that the downstream cabin is filled with liquid, so that it is ready for liquid supply to the subsequent "working" section.

[0038] Furthermore, the upper head section 1 and the lower head section 4 are both semicircular air cavity sealing structures. The upper head and the lower head are semicircular structures as a whole, which are connected with the cylindrical structure of the tank body to achieve the sealing inside the tank and the storage and management of the internal propellant.

[0039] Further, such as Figure 2 As shown, the first gas trap 5 includes a first top plate 53, a first trap seat 51, a first cover plate 52 and a screen assembly 17, wherein: the first top plate 53 is buckled on the first trap seat 51, and an inlet 18 is provided on the first top plate 53; the first cover plate 52 is arranged at the center of the first trap seat 51, and forms a first chamber with the middle area of ​​the first trap seat 51; the interior of the first chamber is an annular maze structure, and the top and bottom of the first chamber are provided with a screen assembly 17.

[0040] Specifically, the first gas trap 5 is a round box-shaped cavity structure composed of a first trap seat 51 and a first cover plate 52. An inlet 17 is provided on one side of the top, and an outlet is provided in the middle of the bottom. A labyrinth-like flow channel structure is provided inside the cavity. The communicating vessel principle is used to realize the function that no gas passes through the trap during transportation when the tank is filled. The mesh is pressed and welded to the first cover plate 52 by a pressing plate, so as to form a screen structure at the top and bottom outlets of the first chamber for the flow of liquid. During the implementation of the flattening, erecting and road transportation operations, the first gas trap 5 can also prevent the gas from entering the trap through the trap entrance due to impact and vibration.

[0041] Further, such as Figure 3 As shown, the second gas trap 6 includes a second top plate 63, a second trap seat 61, a second cover plate 62 and a screen assembly 17, wherein: the second top plate 63 is buckled on the second trap seat 61; the second cover plate 62 is arranged at the center of the second trap seat 61, and forms a second chamber with the middle area of ​​the second trap seat 61; a plurality of screen assemblies 17 are arranged at the top and bottom of the second chamber; a plurality of inlets 18 corresponding to the plurality of screen assemblies 17 are arranged on the second top plate 63. The second gas trap 6 is used to manage the flow of liquid during the rocket's glide, and its structure is similar to the first gas trap 5, except that a maze structure is not arranged inside, and a plurality of screen assemblies 17 are arranged at the inlet and outlet to ensure the discharge of the liquid.

[0042] Further, such as Figure 4As shown, the third gas trap 8 includes a third cover plate 81, a fourth cover plate 82 and a plurality of screen assemblies 17, wherein: the third cover plate 81 is arranged above the fourth cover plate 82, and the third cover plate 81 and the third cover plate 82 are both welded to the inner wall of the shell of the lower head section 4; a plurality of screen assemblies 17 are evenly distributed on the surfaces of the third cover plate 81 and the fourth cover plate 82; a third chamber is formed between the third cover plate 81 and the fourth cover plate 82. The third gas trap 8 is also used to manage the flow of liquid during the rocket's glide, and is mainly formed by the space between the upper and lower partitions and the inner wall of the shell, the third cover plate 81 and the fourth cover plate 82 are directly welded to the inner wall of the shell, and the space between the cover plate and the shell forms the third chamber; a plurality of screen assemblies 17 are arranged on each cover plate.

[0043] Specifically, the main body of the gas trap is a closed structure consisting of a trap seat and a cover plate, and a capillary screen is arranged on it; under microgravity conditions, the residual liquid in the trap tends to gather at the large curvature portion, and the liquid is distributed at the edge of the chamber. By setting the screen assembly 17, it is beneficial to drain the trap and minimize the amount of residual liquid in the trap; in extreme microgravity conditions, when only one mesh is passed through the liquid, it can also ensure that the pressure difference on both sides of the wetted screen is less than the screen bubble breaking point, and the gas will not pass through the screen; in addition, the position and number of gas traps are determined by the flight conditions of the rocket's gliding and operation. In the embodiment of the present application, the first gas trap 5 preferably has a chamber structure with a single mesh outlet; the second gas trap 6 preferably has a chamber structure with multiple mesh outlets; the third gas trap 8 preferably has a double-layer partition structure with multiple meshes.

[0044] More specifically, during tank draining, when the propellant sinks to the bottom under the positive axial overload (about 6g-9g) generated by the operation of the rocket engine, no propellant management is required, such as Figure 7 As shown; when the rocket is in the "gliding" state, the orbit control thrusters do not work (no axial overload is generated), and the attitude control thrusters work in a pulsed mode, generating a small instantaneous lateral overload (about 0.03g). The tank is in a microgravity state, and the liquid propellant will be distributed in the unique morphology of liquid under microgravity. In the most extreme case, the air pillow floats to the liquid port; therefore, when the rocket switches from the "gliding" state to the "working" state, the tank may supply air-entrained propellant to the orbit control thrusters, and the propellant needs to be managed at this time.

[0045] Furthermore, a first anti-sway grid 10 is welded below the first gas trap 5 through a T-shaped bracket 9; a second anti-sway grid 11 is welded above the third gas trap 8 through a T-shaped bracket 9; and an anti-slump grid 12 is welded below the third gas trap 8 through a T-shaped bracket 9.

[0046] Further, such as Figure 5As shown, the first anti-sway grille 10 and the second anti-sway grille 11 are both welded by an anti-sway plate 13 and an anti-sway ring 14. The anti-sway grille is welded by an anti-sway plate 13 and an anti-sway ring 14 of a cross structure, through holes are evenly distributed on the anti-sway plate 13 and the anti-sway ring 14, and the whole is supported and fixed by a T-shaped bracket 9 to reduce the influence of liquid sway and ensure the stability of the gas trap.

[0047] Further, such as Figure 6 As shown, the anti-swirl grid 12 is welded by the anti-swirl plate 15 and the anti-swirl ring 16. The anti-swirl grid 12 is also welded by the anti-swirl plate 15 and the anti-swirl ring 16 of the cross structure. The anti-swirl plate 15 and the anti-swirl ring 16 are evenly distributed with through holes. The whole is supported and fixed by the T-shaped bracket 9, which can suppress the collapse and vortex phenomenon at the end of the discharge, and prevent the collapse of the liquid surface at the center line of the outlet and the through-gas column generated by the vortex.

[0048] Furthermore, the first anti-sway grille 10, the second anti-sway grille 11 and the anti-slump grille 12 are all made of TC4 with a thickness of 1-2 mm. The anti-sway grille and the anti-slump grille 12 are made of TC4 material to ensure the strength of the overall support.

[0049] Further, the screen assembly 17 is composed of a pressing plate and a mesh, the mesh is fixed to the cover plate by the pressing plate, and the mesh is a 00Cr18Ni13 or 316L twill weave mesh. In the embodiment of the present application, the mesh is preferably processed with 00Cr18Ni13 or 316L twill weave mesh, and is fixed to each cover plate by a pressing plate in a roll welding manner to form a screen assembly 17 for the flow of liquid in and out.

[0050] Specifically, the gas trap compartment axially distributed surface tension tank provided in the embodiment of the present application is used in the attitude control power system of a launch vehicle. From the gas port to the liquid port, a trap with a capacity that meets the liquid supply demand of this "glide" is set in sequence for each "glide", and liquid is supplied to the rocket's "glide" section respectively, and it is ensured that no gas passes through the trap outlet during this "glide", so that the downstream compartment is filled with liquid, so that it is ready for the liquid supply of the subsequent "working" section; each trap has completed its main mission after the corresponding "glide" action, but the trap will become a barrier to limit the distribution of the remaining liquid, thereby improving the working environment of subsequent traps and reducing the amplitude of the change in the center of mass of the tank; therefore, the position of each trap is below the liquid level at the beginning of each "glide" and above the liquid level at the end of each "work".

[0051] More specifically, during the first “glide”, the propellant in the first gas trap 5 is consumed, but the tank space below the outlet of the first gas trap 5 is still filled with propellant; at the beginning of the first “work”, the propellant below the outlet of the first gas trap 5 is consumed, and after the orbital control thruster is ignited, the propellant in the tank sinks to the bottom, and as the drainage continues, the residual propellant above and in the first gas trap 5 is successively drained, and then the propellant between the first gas trap 5 and the second gas trap 6 continues to be consumed. Due to the existence of a positive axial overload of 1.3g, the liquid in the chamber is in a sinking state; this is equivalent to the first “glide-work” section, inlet of the second gas trap 6 is always covered by liquid, such as Figure 8 As shown. Similar to the first "glide-work" section, during the second "glide", the propellant between the first gas trap 5 and the second gas trap 6 is in a weightless state. At this time, the propellant in the second gas trap 6 is consumed, but the tank space below the outlet of the second gas trap 6 is still full of propellant; at the beginning of the second "work", the propellant below the outlet of the second gas trap 6 is consumed, and the propellant in the tank sinks to the bottom after the orbit control thruster is ignited. As the drainage continues, the residual propellant above and in the second gas trap 6 is successively drained, and then the propellant between the second gas trap 6 and the third gas trap 8 continues to be consumed. Due to the existence of a positive axial overload of 1.3g, the liquid in the chamber is in a sinking state. During the entire second "glide-work" section, the entrance of the third gas trap 8 is always covered by liquid, as shown in FIG. Fig. 9 Similarly, the third “sliding-working” is similar to the first and second times, as shown in Fig.10 In general, the present application calculates the propellant surplus at different stages and sequentially sets a number of closed traps consisting of capillary screens and shells from the gas port to the liquid port to ensure that the propellant with a flow rate that meets the requirements and does not carry bubbles is supplied under flight conditions, thereby meeting the requirements of propellant management under all conditions.

[0052] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A gas trap compartment axially distributed surface tension tank, characterized in that: It includes an upper head section, a first cylinder section, a second cylinder section and a lower head section, wherein: A first gas trap is provided at the connection between the upper head section and the first cylindrical section; A second gas trap is provided at the connection between the first cylindrical section and the second cylindrical section; A T-ring is provided at the connection between the second cylindrical section and the lower head section; A third gas trap is arranged at the bottom end of the lower head section.

2. The gas trap compartment axially distributed surface tension tank according to claim 1, characterized in that: The upper head section and the lower head section are both semicircular air cavity sealing structures.

3. The gas trap compartment axially distributed surface tension tank according to claim 2, characterized in that: The first gas trap comprises a first top plate, a first trap seat, a first cover plate and a screen assembly, wherein: The first top plate is buckled on the first trap seat, and the first top plate is provided with an inlet; The first cover plate is arranged at the center of the first trap seat and forms a first chamber with the middle area of ​​the first trap seat; The interior of the first chamber is an annular maze structure, and screen assemblies are arranged on the top and bottom of the first chamber.

4. The gas trap compartment axially distributed surface tension tank according to claim 3, characterized in that: The second gas trap comprises a second top plate, a second trap seat, a second cover plate and a screen assembly, wherein: The second top plate is buckled onto the second trap seat; The second cover plate is arranged at the center of the second trap seat and forms a second chamber with the middle area of ​​the second trap seat; A plurality of screen assemblies are disposed at the top and bottom of the second chamber; The second top plate is provided with a plurality of inlets corresponding to the plurality of screen assemblies.

5. The gas trap compartment axially distributed surface tension tank according to claim 4, characterized in that: The third gas trap comprises a third cover plate, a fourth cover plate and a plurality of screen assemblies, wherein: The third cover plate is arranged above the fourth cover plate, and the third cover plate and the fourth cover plate are both welded to the inner wall of the shell of the lower head section; A plurality of screen mesh components are evenly distributed on the surfaces of the third cover plate and the fourth cover plate; A third chamber is formed between the third cover plate and the fourth cover plate.

6. The gas trap compartment axially distributed surface tension tank according to claim 5, characterized in that: A first anti-sway grid is welded below the first gas trap via a T-shaped bracket; a second anti-sway grid is welded above the third gas trap via a T-shaped bracket; and an anti-slump grid is welded below the third gas trap via a T-shaped bracket.

7. The gas trap compartment axially distributed surface tension tank according to claim 6, characterized in that: The first anti-sway grille and the second anti-sway grille are both formed by welding an anti-sway plate and an anti-sway ring.

8. The gas trap compartment axially distributed surface tension tank according to claim 7, characterized in that: The anti-swirl collapse grille is formed by welding an anti-swirl collapse plate and an anti-swirl collapse ring.

9. The gas trap compartment axially distributed surface tension tank according to claim 8, characterized in that: The first anti-sway grille, the second anti-sway grille and the anti-collapse grille are all made of TC4 with a thickness of 1-2 mm.

10. The gas trap compartment axially distributed surface tension tank according to claim 5, characterized in that: The screen assembly consists of a pressing plate and a mesh, the mesh is fixed on the cover plate through the pressing plate, and the mesh is a 00Cr18Ni13 or 316L twill woven mesh.

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