Self-suction type moisture-proof and waterproof device for inner cavity of low-temperature liquid rocket engine

Abstract

The invention relates to the technical field of spaceflight, in particular to a low-temperature liquid rocket engine inner cavity self-suction type damp-proof and waterproof device. The low-temperature liquid rocket engine inner cavity self-suction type damp-proof and waterproof device comprises a self-suction cavity, an opening communicated with an inner cavity of the self-suction cavity is formed in one end of the self-suction cavity, a one-way water permeable diaphragm is installed in the opening in a sealed mode, and the self-suction cavity is filled with water absorption materials. The device has the advantages that the structural design is simple and reasonable, the dew point value of the inner cavity of the engine can be effectively controlled, the defects that in the preparation process of the engine in the prior art, the blow-off replacement time of the engine is long, and the gas consumption is large are overcome, the test requirement can be met only by conducting simple blow-off replacement on the engine before the test is conducted, and the test efficiency is improved. And after use, the blow-off replacement can be completed within a short time, so that the blow-off replacement time and the gas consumption of the engine are greatly shortened, and the test cost can be indirectly reduced.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a self-priming moisture-proof and waterproof device for an inner cavity of a cryogenic liquid rocket engine. Background Art

[0002] At present, the commonly used drying technologies and maintenance measures for cryogenic liquid rocket engines mainly include moisture-proof sandbags and color-changing silica gel, which not only have poor water absorption but are also difficult to observe.

[0003] Take the liquid oxygen-methane engine as an example. When the liquid oxygen-methane engine is started, liquid oxygen and methane enter the engine combustion chamber through their respective supply systems. In the combustion chamber, liquid oxygen and methane are fully mixed and pre-combusted under appropriate conditions to prepare for formal combustion. The mixed gas is ignited through the ignition system, triggering violent combustion and producing high-temperature and high-pressure combustion gas. These high-temperature and high-pressure combustion gases expand rapidly in the combustion chamber and are discharged through the nozzle at an accelerated speed, thereby generating thrust. The main products of the entire working process are water and carbon dioxide (H2O+CO2). Since the design and use of liquid oxygen-methane engines mainly focus on the purity and treatment of propellants to ensure the efficient operation and safety of the engine, since moisture or water entering the engine system will have an adverse effect on the safe operation of the engine, it is crucial to ensure that the system is dry and clean for the design and maintenance of liquid oxygen-methane engines to avoid any possible adverse effects.

[0004] Based on this, it is necessary to develop a self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine to overcome the above technical problems. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a method which effectively overcomes the defects of the prior art.

[0006] The technical solution of the present invention to solve the above technical problems is as follows:

[0007] A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine comprises a self-priming chamber, one end of the self-priming chamber is provided with an opening connected to the inner cavity, a one-way water-permeable diaphragm is sealed in the opening, and the self-priming chamber is filled with a water-absorbing material.

[0008] Based on the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, the self-priming chamber includes a cylindrical shell, a first end cover and a second end cover, the first end cover and the second end cover are respectively and detachably sealed on the two ends of the shell, the first end cover is provided with an opening, the one-way water-permeable diaphragm is clamped between one end of the shell and the first end cover, and a sealing ring is clamped between the other end of the shell and the second end cover.

[0010] Furthermore, the outer surfaces of both ends of the shell are respectively provided with external threads, the first end cover is a cylindrical component with one end open, and its inner wall is provided with internal threads, the first end cover is threadedly screwed on one end of the shell, and the other end of the first end cover is provided with a circular opening, the second end cover is a cylindrical component with one end open, and its inner wall is provided with internal threads, and the second end cover is threadedly screwed on the other end of the shell.

[0011] Furthermore, the shell is a transparent shell, and a hook is provided on one end or the first end cover of the shell.

[0012] Furthermore, the one-way water-permeable membrane comprises multiple layers of DuPont water-locking paper.

[0013] Furthermore, the water absorbing material is calcium chloride particles.

[0014] Furthermore, a water filter baffle is provided in the middle of the self-priming chamber, the water filter baffle is covered with a plurality of water permeable holes, and the water absorbing material is filled in the cavity between the water filter baffle and one end of the self-priming chamber.

[0015] Furthermore, the water filtering partition is a spherical panel or a conical panel, and is protruded toward one end of the self-priming chamber.

[0016] Furthermore, a non-return structure capable of passing water is provided at one end of the water filter baffle away from the opening.

[0017] Furthermore, the anti-return structure is a funnel-shaped component, the tip of which faces the other end of the self-priming chamber, and a water hole is formed at the tip.

[0018] The beneficial effects of the present invention are: the structural design is simple and reasonable, and the dew point value of the engine inner cavity can be effectively controlled, which improves the disadvantages of the prior art that the blowing and replacement time of the engine is long and the gas consumption is large during the engine preparation process. By using the present device, only a simple blowing and replacement of the engine is required before the test to meet the test requirements, and the blowing and replacement can be completed in a short time after use, which not only greatly shortens the blowing and replacement time and gas consumption of the engine, but also can indirectly reduce the test cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic structural diagram of the self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine of the present invention;

[0020] Figure 2 It is an exploded view of the self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine of the present invention;

[0021] Figure 3 It is a structural cross-sectional view of the self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine of the present invention.

[0022] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0023] 1. Self-priming chamber; 2. One-way water-permeable diaphragm; 3. Water-absorbing material; 11. Shell; 12. First end cover; 13. Second end cover; 14. Sealing ring; 15. Water filter baffle; 16. Check structure; 151. Water permeable hole. DETAILED DESCRIPTION

[0024] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0025] Example: Figure 1 , 2 As shown in Figure 3, the self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine of this embodiment includes a self-priming chamber 1, one end of the self-priming chamber 1 is provided with an opening connected to its inner cavity, a one-way water-permeable diaphragm 2 is sealed in the opening, and the self-priming chamber 1 is filled with a water-absorbing material 3.

[0026] Before the use of the self-priming moisture-proof and waterproof device for the inner cavity of the cryogenic liquid rocket engine of this embodiment, the engine will be purged and replaced before the ground test to ensure safety and performance, which usually consumes a large amount of dry inert gas, time and personnel to meet the control of the dew point value of the engine cavity. Through the purging and replacement operations, the impurities, residues and moisture inside the engine are effectively removed to ensure that the engine can run stably and safely during the test, so as to obtain accurate test data. The purge and replacement time of an engine after it is put on the stage takes more than two hours. Sometimes, when the dew point value measured after the purge and replacement cannot meet the test requirements, the engine must be purged and replaced twice or more times, which not only consumes a lot of time, but also increases the gas consumption, thereby indirectly increasing the test cost. By using the device of this embodiment, not only the dew point value of the engine cavity can be effectively controlled, but also the disadvantages of the prior art in that the blowing and replacement time of the engine is long and the gas consumption is large during the preparation of the engine are improved. During the preparation of the engine, the device starts working. By using this device, only a simple blowing and replacement of the engine is required before the test to meet the test requirements. After use, the blowing and replacement can be completed in a short time, which not only greatly shortens the blowing and replacement time and gas consumption of the engine, but also can indirectly reduce the test cost.

[0027] It should be noted that the dew point refers to the temperature at which the water vapor in the air reaches saturation. When the humidity in the air is too high, it will cause corrosion and damage to the internal parts of the engine. For liquid oxygen-methane engines, if the humidity inside the engine is not properly controlled, it may cause the metal parts inside the engine to rust or corrode, thereby affecting the performance and life of the engine. In addition, a high humidity environment may also cause the insulating materials inside the engine to get damp, thereby affecting the normal operation of the electrical system and even causing safety problems such as short circuits. The height of the dew point will also affect the cooling system of the engine. Liquid oxygen-methane engines usually use regenerative cooling technology, and a high humidity environment may affect the efficiency of the cooling system because moisture may interfere with the normal operation of the cooling system, causing the engine to overheat, thereby affecting its performance and safety. Therefore, for liquid oxygen-methane engines, it is very important to control the dew point. By adopting appropriate drying technology and maintenance measures, the humidity inside the engine can be effectively reduced, thereby ensuring the performance and safety of the engine. The self-priming moisture-proof and waterproof device for the inner cavity of the cryogenic liquid rocket engine of this embodiment can well control the dew point value of the inner cavity of the engine. By using this moisture-proof measure, the adverse effects of the dew point on the liquid oxygen-methane engine can be effectively reduced.

[0028] In this embodiment, the self-priming chamber 1 comprises a cylindrical shell 11, a first end cover 12 and a second end cover 13. The first end cover 12 and the second end cover 13 are respectively and detachably sealed at the two ends of the shell 11. The first end cover 12 is provided with an opening. The one-way water-permeable diaphragm 2 is sandwiched between one end of the shell 11 and the first end cover 12. A sealing ring 14 is sandwiched between the other end of the shell 11 and the second end cover 13. The self-priming chamber 1 adopts a split-type combined structural part, which is easy to disassemble and assemble, and easy to fill and replace the internal filler. The specific use process of the entire device is as follows:

[0029] Step 1: Equipment Inspection

[0030] First, remove the first end cover 12 and the second end cover 13, and check whether the water-proof sealing ring 14 is intact;

[0031] Check whether there is any residual water-absorbing material 3 in the shell 11, and clean it in time; check whether there is any residual water in the second end cover 13, and use the purge gas to blow the water away in time;

[0032] Check the device for any damage to prevent water leakage.

[0033] Step 2: Reinstall the first end cap 12 and the second end cap 13 and fill with water-absorbing material 3

[0034] Specifically, first install the second end cover 13;

[0035] The water-absorbing material 3 is loaded through one end of the housing 11, and then the one-way water-permeable membrane 2 is installed and pressed using the first end cover 12;

[0036] Step 3: Get started

[0037] The device is placed in the inner cavity of the rocket engine thrust chamber or turbo pump exhaust pipe that needs to be dewatered;

[0038] Step 4: Recycling

[0039] After a period of time, the device is removed and the equipment is inspected;

[0040] If water is found in the second end cover 13, it indicates that there is water in the inner cavity of the engine and the water in the inner cavity can be sucked out by the device, and a new one can be replaced for continued use;

[0041] If it is found that the device has no visible moisture or very little moisture, it indicates that the dew point in the engine cavity is qualified.

[0042] It should be noted that the working time of the device and the amount of water-absorbing particles used will vary depending on the water content in the engine cavity.

[0043] As a preferred embodiment, the outer surfaces of both ends of the shell 11 are respectively provided with external threads, the first end cover 12 is a cylindrical component with one end open, and its inner wall is provided with internal threads, the first end cover 12 is threadedly screwed on one end of the shell 11, and the other end of the first end cover 12 is provided with a circular opening, the second end cover 13 is a cylindrical component with one end open, and its inner wall is provided with internal threads, and the second end cover 13 is threadedly screwed on the other end of the shell 11.

[0044] In the above embodiment, the first end cover 12 and the second end cover 13 are assembled with both ends of the housing 11 by threaded connection, and assembly and disassembly are very quick and simple.

[0045] In this embodiment, the housing 11 is a transparent housing, which is easy to observe. At the same time, a hook is provided on one end of the housing 11 or the first end cap 12. The device can be used by being hung on the inner cavity catheter in conjunction with the hook.

[0046] In this embodiment, the one-way water-permeable membrane 2 comprises multiple layers of DuPont water-locking paper.

[0047] In this embodiment, the water-absorbing material 3 is calcium chloride particles. Specifically, the principle of calcium chloride absorbing water is that calcium chloride has a strong hydrophilicity and can absorb moisture in the air. The chemical formula of calcium chloride is CaCl2. When calcium chloride is exposed to the air, it absorbs the surrounding water vapor. This is because calcium chloride has a high relative humidity hygroscopicity and can quickly absorb moisture in the air. Calcium chloride is a salt compound and its crystal structure has a strong polarity. Polarity means that there is a charge difference between the chloride ions (CI-) and calcium ions (Ca2+) in the calcium chloride molecules. This polarity makes calcium chloride have the ability to absorb moisture. When green calcium is exposed to the air, the chloride ions and calcium ions attract the oxygen ions (O2-) and hydrogen ions (H+) in the surrounding water molecules. This attraction causes the water molecules to combine with the calcium chloride molecules to form hydrates. The formation of hydrates causes the water molecules to be fixed on the surface of the calcium chloride crystals. Since calcium chloride has a strong hydrophilicity, it can adsorb and fix the surrounding water molecules on its own surface. In this way, calcium chloride can continuously absorb moisture in the air, making it moist. In summary, the principle of calcium chloride absorbing water is to use its polar molecular structure and hydrophilic properties to absorb and fix water molecules in the air, thereby forming a moist state. This makes calcium chloride a commonly used desiccant and humidity control agent.

[0048] As a preferred embodiment, a water filter baffle 15 is provided in the middle of the self-priming chamber 1 , and the water filter baffle 15 is covered with a plurality of water-permeable holes 151 , and the water-absorbing material 3 is filled in the cavity between the water filter baffle 15 and one end of the self-priming chamber 1 .

[0049] In the above implementation scheme, the water absorbed by the water-absorbing material 3 will penetrate into the cavity formed between the water filtering baffle 15 and the other end of the self-priming chamber 1 through the water-permeable holes 151 on the water filtering baffle 15, and be stored and collected. The dew point of the engine cavity is judged to be qualified based on the amount of water in the cavity (how to judge is defined according to the actual situation, and how to judge has no direct relationship with the device of this embodiment, so it will not be elaborated here).

[0050] In this embodiment, the water filter baffle 15 is a spherical panel or a cone panel, and is protruding toward one end of the self-priming chamber 1. This design ensures that the water absorbed by the water absorbing material 3 will not accumulate on the surface of the water filter baffle 15 when passing through the water filter baffle 15, but will diffuse along the surface of the water filter baffle 15 to the surrounding low position, and enter another cavity through the water permeable holes 151 on the surface during the diffusion process.

[0051] As a preferred embodiment, the end of the water filter baffle 15 away from the opening is provided with a non-return structure 16 that can pass water.

[0052] In the above embodiment, the anti-return structure 16 can prevent the water in the cavity between the water filtering baffle 15 and the other end of the self-priming chamber 1 from reversely passing through the water filtering baffle 15 .

[0053] As a preferred embodiment, the anti-return structure 16 is a funnel-shaped component, the tip of which faces the other end of the self-priming chamber 1 and has a water hole.

[0054] In the above-mentioned implementation scheme, the water that passes through the water filter baffle 15 passes through the water hole at the tip of the anti-return structure 16 and accumulates in the cavity between the outer surface of the anti-return structure 16 and the self-priming chamber 1. Since the size of the water hole is small, it is difficult for the water in the cavity to flow back and it will be well stored in the cavity. The design of this structure has a better anti-return effect.

[0055] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0056] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying 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 the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0057] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it 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.

[0058] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0059] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0060] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine, characterized in that: It comprises a self-priming chamber (1), one end of which is provided with an opening communicating with its inner cavity, a one-way water-permeable diaphragm (2) being sealed in the opening, and the self-priming chamber (1) is filled with a water-absorbing material (3).

2. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 1, characterized in that: The self-priming chamber (1) comprises a cylindrical shell (11), a first end cover (12) and a second end cover (13); the first end cover (12) and the second end cover (13) are respectively and detachably sealed at the two ends of the shell (11); the first end cover (12) is provided with an opening; the one-way water-permeable diaphragm (2) is sandwiched between one end of the shell (11) and the first end cover (12); and a sealing ring (14) is sandwiched between the other end of the shell (11) and the second end cover (13).

3. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 2, characterized in that: The outer surfaces of both ends of the shell (11) are respectively provided with external threads. The first end cover (12) is a cylindrical component with one end open and an inner wall provided with internal threads. The first end cover (12) is threadedly screwed onto one end of the shell (11). The other end of the first end cover (12) is provided with a circular opening. The second end cover (13) is a cylindrical component with one end open and an inner wall provided with internal threads. The second end cover (13) is threadedly screwed onto the other end of the shell (11).

4. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 2, characterized in that: The shell (11) is a transparent shell, and a hook is provided on one end of the shell (11) or on the first end cover (12).

5. The self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 1, characterized in that: The one-way water-permeable diaphragm (2) comprises multiple layers of laminated DuPont water-locking paper.

6. The self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 1, characterized in that: The water absorbing material (3) is calcium chloride particles.

7. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to any one of claims 1 to 6, characterized in that: A water filter baffle (15) is provided in the middle of the self-priming chamber (1), and the water filter baffle (15) is covered with a plurality of water permeable holes (151). The water absorbing material (3) is filled in a cavity between the water filter baffle (15) and one end of the self-priming chamber (1).

8. The self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 7, characterized in that: The water filtering partition plate (15) is a spherical panel or a conical panel and is arranged to protrude toward one end of the self-priming chamber (1).

9. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 8, characterized in that: The end of the water filtering baffle (15) away from the opening is provided with a non-return structure (16) capable of passing water.

10. A self-priming moisture-proof and waterproof device for the inner cavity of a cryogenic liquid rocket engine according to claim 9, characterized in that: The anti-return structure (16) is a funnel-shaped component, the tip of which faces the other end of the self-priming chamber (1), and a water hole is formed at the tip.

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