A ground experiment gas cooling device for an aerospace engine

Abstract

A gas cooling device for ground experiments on aerospace engines comprises a cooling cylinder + an ice-making device for liquid rocket engines or a cooling cylinder + an ice-making / absorption device for solid rocket engines; specifically, it comprises a gas cooling system and a liquid supply system, a cooling system, and a vacuum pumping system connected thereto; utilizing cold energy provided by low-temperature liquid nitrogen and liquid supplied by a water tank or an alkaline solution tank, ice is made by circulating flow during non-testing hours, and an ice channel is formed by controlling the thickness of the ice layer by radial movement of a nozzle; during testing hours, a low-pressure environment is created by the vacuum pumping system, the ice channel rapidly cools the gas, and the solution after the ice layer melts and absorbs harmful gases is recycled; the present invention has good sealing performance, high cooling efficiency, a simple process, does not require disassembly, requires less supercooling for ice making, avoids structural ablation, has high water resource utilization, has little environmental harm, has a high freezing point for ice-making from the solution, and has high ice-making efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engine fuel gas post-processing, and in particular to a fuel gas cooling device for ground experiments on aerospace engines. Background Art

[0002] During rocket launches and ground experiments on aerospace engines, high temperatures (stagnation temperature exceeding 3000K), high speeds (nozzle exit velocity exceeding 2000m·s) are generated. -1 If left untreated, the fuel gas produced by aerospace engines (such as rocket engines) can cause significant damage to surrounding facilities and the environment. Solid rocket engines, on the other hand, produce large quantities of toxic HCl gas and molten alumina particles exceeding 30% by mass, polluting the surrounding air and water. Furthermore, ground-based experiments on aerospace engines require a low-pressure environment created by the ejection system to simulate the engine's operation at high altitudes. Maintaining this low-pressure environment while performing efficient, environmentally friendly, and cost-effective post-processing of the engine fuel gas is crucial.

[0003] Traditional gas post-processing methods primarily rely on water treatment, using water tanks and sprays to cool, slow, and settle contaminants. However, water treatment systems present numerous challenges, including large flow systems, long processing times, low cooling efficiency, high water consumption, and the need for wastewater treatment. Furthermore, water treatment systems are not enclosed, which can easily affect low-pressure environments. Research has demonstrated that using ice as a gas cooling medium offers high cooling efficiency and low water consumption.

[0004] The conventional method of making ice channels (CN201910101422.0, entitled: An ice core preparation device and method) is to make ice through a mold, put the water used for ice making into the mold, add cold energy to it through a cold head, and then demold after the ice channel is formed. The disadvantage of the conventional method is that different sizes of molds are required for different working conditions of different rocket engines. After the ice channel is installed in the rocket engine nozzle, it needs to be disassembled and remade after use. For rocket engines with larger thrust, the process steps of using the ice channel are too cumbersome. In addition, for solid rocket engines, alkaline solution needs to be sprayed during the cooling process to absorb toxic gases, and high-temperature combustion gas can easily cause ablation of structures such as the nozzle. Summary of the Invention

[0005] In order to overcome the shortcomings of the above-mentioned prior art, the purpose of the present invention is to provide a ground experimental gas cooling device for aerospace engines, which maintains a low-pressure environment while using ice channels to efficiently process the gas; it does not require disassembly, does not require molds, is easy to operate, and requires less supercooling for ice making.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is:

[0007] A gas cooling device for ground experiments on aerospace engines, comprising a cooling cylinder + ice-making device for liquid rocket engines or a cooling cylinder + ice-making / absorption device for solid rocket engines;

[0008] The cooling cylinder + ice making device for liquid rocket engines includes a gas cooling system 1 and a liquid supply system 2, a cooling system 3, and a vacuum system 4 connected thereto;

[0009] The gas cooling system 1 includes a liquid rocket engine 5, which is placed vertically on a horizontal support bracket 6. The horizontal support bracket 6 is connected to the top of the vertical support bracket 7, and a spray device 9 is fixed to the upper part of the vertical support bracket 7; a cooling cylinder 15 is fixed inside the vertical support bracket 7 below the spray device 9, and the top of the cooling cylinder 15 is connected to the engine nozzle of the rocket engine 5 through a metal deflector 8. The wall of the cooling cylinder 15 is provided with a metal interlayer, and the metal interlayer is connected to the cooling system 3; a gas-liquid separator 16 is connected to the bottom of the vertical support bracket 7, and the bottom of the gas-liquid separator 16 is connected to the liquid supply system 2 through a recovery pipeline 17, and the top of the gas-liquid separator 16 is connected to the vacuum system 4;

[0010] The liquid supply system 2 includes a water tank 18, a water valve 19, and a water pump 20. The water tank 18 is connected to the spray device 9 via the water valve 19 and the water pump 20.

[0011] The cooling system 3 includes a cryogenic liquid nitrogen storage tank 21, a liquid nitrogen pump 22, and a cryogenic valve 23. The cryogenic liquid nitrogen storage tank 21 is connected to the metal interlayer of the cooling cylinder wall 15 via the liquid nitrogen pump 22 and the cryogenic valve 23.

[0012] The vacuum system 4 includes a gas generator 24, an ejector 25, and a diffuser 26. The gas generator 24 is connected to the main ejection direction of the ejector 25, the ejector 25 is connected to the diffuser 26, and the ejected direction of the ejector 25 is connected to the top of the gas-liquid separator 16.

[0013] The cooling cylinder + ice-making / absorption device for solid rocket engines has the same structure as the cooling cylinder + ice-making device for liquid rocket engines, except that the bottom of the gas-liquid separator 16 is separated by a filter screen 27 and connected to the liquid supply system 2 through a recovery pipe 17. The inlet of the water pump 20 of the liquid supply system 2 is also connected to the alkaline solution tank 28 via an alkaline solution valve 29.

[0014] The spray device 9 includes a first concentric circular bracket 11 and a second concentric circular bracket 12 . A guide rail 10 is connected between the first concentric circular bracket 11 and the second concentric circular bracket 12 , and a nozzle 13 is provided on the guide rail 10 .

[0015] The guide rail 10, the first concentric circular bracket 11 and the second concentric circular bracket 12 are made of steel, and the nozzle angle of the nozzle 13 is adjustable and inclined toward the wall.

[0016] The liquid rocket engine 5 is connected to a cryogenic fuel pipeline.

[0017] The horizontal support bracket 6 and the vertical support bracket 7 are made of stainless steel, and the length and width of the vertical support bracket 7 can be adjusted as needed.

[0018] The cooling cylinder wall 15 is made of steel, and the side close to the gas adopts coils, corrugations, fins, etc. to enhance heat exchange.

[0019] The bottom filter 27 of the gas-liquid separator for the solid rocket engine is made of fine metal material, and the filter diameter is at the micron level.

[0020] The alkaline solution valve 29 and the water pump 20 are resistant to alkali corrosion, and the working liquid in the alkaline solution tank 28 is an alkaline solution with a concentration of 3-5%.

[0021] The liquid nitrogen pump 22 and cryogenic valve 23 must meet the refrigerant temperature requirements; for the liquid rocket engine 5, the operating temperature range is 77K, and a cryogenic flange is used to connect to the transmission pipeline.

[0022] Beneficial effects of the present invention:

[0023] The present invention uses a metal deflector 8 to connect the ice channel and the engine nozzle to cool the aerospace engine combustion gas. Compared with the water spray solution, it has better sealing performance and is conducive to maintaining a low-pressure environment of the engine nozzle.

[0024] After entering the ice channel, the high-temperature, high-speed combustion gas directly contacts the ice layer 14 on the wall of the cooling tube 15. The ice surface is washed by turbulent pulsation and particles in the solid rocket engine combustion gas, thereby fully contacting the combustion gas. The ice quickly absorbs the heat in the combustion gas, causing the combustion gas temperature to drop rapidly. Using the ice channel as a cooling device has a good cooling effect, low water consumption, and also has a significant deceleration and noise reduction effect.

[0025] Using a flowing water ice-making method, the cooling cylinder is placed vertically. Water flows continuously along the cylinder surface under the action of gravity, eventually increasing the thickness of the ice on the wall. Compared to mold-based ice making, the ice channel effectively processes the gas, effectively simplifies the process, eliminates the need for disassembly, and eliminates the need for molds, making operation simple. At the same time, the ice-making requires a lower degree of subcooling, making it suitable for a variety of working conditions.

[0026] For solid rocket engines, the spray device 9 sprays alkaline solution to make ice during non-testing, while maintaining a high absorption efficiency of harmful gas HCl, avoiding the erosion of high-temperature gas on piping structures such as the spray device 9 and the nozzle 13.

[0027] During the ice-making process outside of test runs, unfrozen water or alkaline solution exits cooling cylinder 15 and is recycled through recovery line 17 into water tank 18 for spraying and circulated ice-making. During test runs, the water produced by melting ice or the salt solution produced by HCl absorption can be collected for subsequent ice-making. Recycling water and solution, filtering and collecting solid particles, conserves resources while reducing environmental pollution. The recycled solution has a higher freezing point than water.

[0028] In summary, the aerospace engine ground experimental gas cooling device proposed by the present invention has good sealing performance, can maintain a low-pressure environment, has high cooling efficiency, simple process, does not require disassembly, requires less supercooling for ice making, can avoid structural ablation, has high water resource utilization rate, has little environmental harm, and has a high freezing point for solution ice making, and has considerable application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of a cooling cylinder + ice-making device for a liquid rocket engine according to Example 1 of the present invention.

[0030] Figure 2 This is a schematic diagram of a cooling cylinder + ice making / absorption device for a solid rocket engine according to Example 2 of the present invention. DETAILED DESCRIPTION

[0031] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0032] Example 1, with reference to Figure 1 , a gas cooling device for ground experiments on aerospace engines, including a cooling cylinder + ice making device for liquid rocket engines or a cooling cylinder + ice making / absorption device for solid rocket engines;

[0033] The cooling cylinder + ice-making device for liquid rocket engines includes a gas cooling system 1 and a liquid supply system 2, a cooling system 3, and a vacuum system 4 connected thereto; the gas cooling system 1 includes a liquid rocket engine 5, a horizontal support bracket 6, a vertical support bracket 7, a metal deflector 8, a spray device 9, a cooling cylinder wall 15, and a gas-liquid separator 16; the rocket engine 5 is vertically placed on the horizontal support bracket 6, the horizontal support bracket 6 is connected to the top of the vertical support bracket 7, and a spray device 9 is fixed to the upper part of the vertical support bracket 7; a cooling cylinder 15 is fixed inside the vertical support bracket 7 below the spray device 9, and the top of the cooling cylinder 15 is connected to the engine nozzle of the rocket engine 5 through the metal deflector 8, and the wall of the cooling cylinder 15 is provided with a metal interlayer, which is connected to the cooling system 3 The bottom of the vertical support bracket 7 is connected to a gas-liquid separator 16, the bottom of the gas-liquid separator 16 is connected to the liquid supply system 2 through a recovery pipeline 17, and the top of the gas-liquid separator 16 is connected to the vacuum system 4; the liquid supply system 2 includes a water tank 18, a water valve 19, and a water pump 20. The water tank 18 is connected to the spray device 9 via the water valve 19 and the water pump 20; the cooling system 3 includes a low-temperature liquid nitrogen storage tank 21, a liquid nitrogen pump 22, and a low-temperature valve 23. The low-temperature liquid nitrogen storage tank 21 is connected to the metal interlayer of the cooling cylinder wall 15 via the liquid nitrogen pump 22 and the low-temperature valve 23; the vacuum system 4 includes a gas generator 24, an ejector 25, and a diffuser 26. The gas generator 24 is connected to the main injection direction of the ejector 25, the ejector 25 is connected to the diffuser 26, and the ejected direction of the ejector 25 is connected to the top of the gas-liquid separator 16.

[0034] The spray device 9 includes a first concentric circular bracket 11 and a second concentric circular bracket 12 . A guide rail 10 is connected between the first concentric circular bracket 11 and the second concentric circular bracket 12 , and a nozzle 13 is provided on the guide rail 10 .

[0035] The guide rail 10, the first concentric circular bracket 11 and the second concentric circular bracket 12 are made of steel, and the nozzle angle of the nozzle 13 is adjustable and inclined toward the wall.

[0036] The liquid rocket engine 5 is connected to a cryogenic fuel pipeline.

[0037] The horizontal support bracket 6 and the vertical support bracket 7 are made of stainless steel, and the length and width of the vertical support bracket 7 can be adjusted as needed.

[0038] The cooling tube 15 is made of steel, and the side close to the gas adopts coils, corrugations, fins, etc. to enhance heat exchange.

[0039] The liquid nitrogen pump 22 and cryogenic valve 23 must meet the refrigerant temperature requirements; for the liquid rocket engine 5, the operating temperature range is 77K, and a cryogenic flange is used to connect to the transmission pipeline.

[0040] The working principle of this embodiment is:

[0041] For the cooling cylinder + ice-making device of the liquid rocket engine, during non-test time, the liquid supply system 2 is driven by a water pump 20, the water valve 19 is opened, and the water in the water tank 18 enters the spray device 9 and is sprayed along the wall of the cooling cylinder 15 through the nozzle 13 on the guide rail 10; the cooling system 3 is driven by a liquid nitrogen pump 22, and the low-temperature valve 23 is opened. The low-temperature liquid nitrogen in the low-temperature liquid nitrogen storage tank 21 can directly enter the metal interlayer of the cooling cylinder 15 and exchange heat with the water provided by the liquid supply system 2, and finally form an ice layer 14 on the wall of the cooling cylinder 15. The thickness of the ice layer 14 is controlled by the radial movement of the nozzle 13 on the guide rail 10, and the unfrozen water is circulated and sprayed through the recovery pipeline 17 for ice making. During the test run, the vacuum system 4 generates a high-speed main jet gas from the gas generator 24, which is ejected into the aerospace engine through the ejector 25, creating a low-pressure environment at the engine nozzle and in the ice channel, and is finally discharged into the atmosphere through the diffuser 26; the ice channel formed by the ice layer 14 has a good cooling effect on the high-temperature gas, and the water vapor generated by the combustion of the fuel and the water generated by the melting of the ice layer 14 can be collected and utilized through the recovery pipeline 17.

[0042] Example 2, reference Figure 2, the cooling cylinder + ice making / absorption device for solid rocket engines includes a gas cooling system 1 and a liquid supply system 2, a cooling system 3, and a vacuum system 4 connected thereto; the gas cooling system 1 includes a solid rocket engine 5, a horizontal support bracket 6, a vertical support bracket 7, a metal deflector 8, a spray device 9, a cooling cylinder 15, a gas-liquid separator 16, and a filter 27; the solid rocket engine 5 is vertically placed on the horizontal support bracket 6, the horizontal support bracket 6 is connected to the top of the vertical support bracket 7, and the spray device 9 is fixed on the upper part of the vertical support bracket 7; a cooling cylinder 15 is fixed inside the vertical support bracket 7 below the spray device 9, and the top of the cooling cylinder 15 is connected to the engine nozzle of the rocket engine 5 through the metal deflector 8, and the wall of the cooling cylinder 15 is provided with a metal interlayer, which is connected to the cooling system 3; the bottom of the vertical support bracket 7 is connected to the gas-liquid separator 16, the gas The bottom of the liquid separator 16 is connected to the liquid supply system 2 through the recovery pipe 17 after the filter screen 27 is separated, and the top of the gas-liquid separator 16 is connected to the vacuum system 4; the liquid supply system 2 includes a water tank 18, a water valve 19, a water pump 20, an alkaline solution tank 28, and an alkaline solution valve 29; the water tank 18 is connected to the inlet of the water pump 20 through the water valve 19, and the inlet of the water pump 20 is also connected to the alkaline solution tank 28 through the alkaline solution valve 29, and the outlet of the water pump 20 is connected to the spray device 9 ; The cooling system 3 includes a low-temperature liquid nitrogen storage tank 21, a liquid nitrogen pump 22, and a low-temperature valve 23. The low-temperature liquid nitrogen storage tank 21 is connected to the metal interlayer of the cooling cylinder wall 15 through the liquid nitrogen pump 22 and the low-temperature valve 23; the vacuum system 4 includes a gas generator 24, an ejector 25, and a diffuser 26. The gas generator 24 is connected to the main injection direction of the ejector 25, the ejector 25 is connected to the diffuser 26, and the ejected direction of the ejector 25 is connected to the top of the gas-liquid separator 16.

[0043] The bottom filter 27 of the gas-liquid separator for the solid rocket engine is made of fine metal material, and the filter diameter is at the micron level.

[0044] The alkaline solution valve 29 and the water pump 20 are resistant to alkali corrosion, and the working liquid in the alkaline solution tank 28 is an alkaline solution with a concentration of 3-5%.

[0045] The working principle of this embodiment is:

[0046] For the cooling cylinder + ice-making device of the solid rocket engine, during non-test time, the liquid supply system 2 is driven by a water pump 20, the water valve 19 and the alkaline solution valve 29 are opened, and the water in the water tank 18 is mixed with the alkaline solution in the alkaline solution tank 28 and enters the spray device 9, and is sprayed along the wall of the cooling cylinder 15 through the nozzle 13 on the guide rail 10; the cooling system 3 is driven by a liquid nitrogen pump 22, and the low-temperature valve 23 is opened. The liquid nitrogen in the low-temperature liquid nitrogen storage tank 21 enters the metal interlayer of the cooling cylinder 15 and exchanges heat with the liquid provided by the liquid supply system 2, and finally forms an ice layer 14 on the wall of the cooling cylinder 15. The thickness of the ice layer is controlled by the radial movement of the nozzle 13 on the guide rail 10, and the unfrozen liquid is circulated and sprayed through the recovery pipeline 17 for ice making. During the test run, the vacuum system generates a high-speed main jet gas from the gas generator 24, which is ejected into the aerospace engine through the ejector 25, creating a low-pressure environment at the engine nozzle and in the channel, and finally discharged into the atmosphere through the diffuser; the ice channel formed by the ice layer 14 has a good cooling effect on the high-temperature combustion gas, and the alkaline solution generated by the melting of the ice layer 14 absorbs harmful gases to form a salt solution, which is mixed with the solid particles generated by the combustion of the fuel and then enters the gas-liquid separator 16. After the solid particles are filtered out by the filter 27, the salt solution can be collected and utilized through the recovery pipeline 17.

[0047] In summary, the method proposed in the present invention can maintain a low-pressure environment while achieving a good gas cooling effect, simplifying the process, eliminating the need for disassembly, achieving higher ice-making efficiency, avoiding structural ablation, achieving high water resource utilization, and minimizing environmental harm.

Claims

1. A gas cooling device for ground experiments on aerospace engines, comprising a cooling cylinder and an ice-making device for liquid rocket engines; characterized by: The cooling cylinder + ice making device for liquid rocket engines comprises a gas cooling system (1) and a liquid supply system (2), a cooling system (3), and a vacuum system (4) connected thereto; The gas cooling system (1) includes a liquid rocket engine (5), which is vertically placed on a horizontal support bracket (6), which is connected to the top of a vertical support bracket (7), and a spray device (9) is fixed on the upper part of the vertical support bracket (7); a cooling cylinder (15) is fixed inside the vertical support bracket (7) below the spray device (9), and the top of the cooling cylinder (15) is connected to the engine nozzle of the rocket engine (5) through a metal deflector (8), and the wall of the cooling cylinder (15) is provided with a metal interlayer, which is connected to the cooling system (3); a gas-liquid separator (16) is connected below the vertical support bracket (7), the bottom of the gas-liquid separator (16) is connected to the liquid supply system (2) through a recovery pipeline (17), and the top of the gas-liquid separator (16) is connected to the vacuum system (4); The liquid supply system (2) includes a water tank (18), which is connected to the spraying device (9) via a water valve (19) and a water pump (20); The cooling system (3) includes a low-temperature liquid nitrogen storage tank (21), which is connected to the metal interlayer of the wall of the cooling cylinder (15) via a liquid nitrogen pump (22) and a low-temperature valve (23); The vacuum system (4) includes a gas generator (24), the gas generator (24) is connected to the main injection direction of the ejector (25), the ejector (25) is connected to the diffuser (26), and the ejected direction of the ejector (25) is connected to the top of the gas-liquid separator (16); The spraying device (9) comprises a first concentric circular bracket (11) and a second concentric circular bracket (12); a guide rail (10) is connected between the first concentric circular bracket (11) and the second concentric circular bracket (12); and a nozzle (13) is provided on the guide rail (10).

2. The aerospace engine ground experiment gas cooling device according to claim 1, characterized in that: The guide rail (10), the first concentric circular bracket (11) and the second concentric circular bracket (12) are made of steel, and the nozzle angle of the nozzle (13) is adjustable and inclined toward the wall.

3. The aerospace engine ground experiment gas cooling device according to claim 1, characterized in that: The liquid rocket engine (5) is connected to a cryogenic fuel pipeline.

4. The aerospace engine ground experiment gas cooling device according to claim 1, characterized in that: The horizontal support bracket (6) and the vertical support bracket (7) are made of stainless steel, and the length and width of the vertical support bracket (7) can be adjusted as needed.

5. The aerospace engine ground experiment gas cooling device according to claim 1, characterized in that: The cooling cylinder (15) is made of steel, and the side close to the gas adopts the form of coils, corrugations, and fins to enhance heat exchange.

6. The aerospace engine ground experiment gas cooling device according to claim 1, characterized in that: The liquid nitrogen pump (22) and cryogenic valve (23) meet the refrigerant temperature requirements; for the liquid rocket engine (5), the operating temperature range is 77K, and a cryogenic flange is used to connect to the transmission pipeline.

7. A gas cooling device for ground experiments on aerospace engines, comprising a cooling cylinder for solid rocket engines and an ice making / absorption device; characterized by: The cooling cylinder + ice making / absorption device for solid rocket engines comprises a gas cooling system (1) and a liquid supply system (2), a cooling system (3), and a vacuum system (4) connected thereto; The gas cooling system (1) includes a liquid rocket engine (5), which is vertically placed on a horizontal support bracket (6), which is connected to the top of a vertical support bracket (7), and a spray device (9) is fixed on the upper part of the vertical support bracket (7); a cooling cylinder (15) is fixed inside the vertical support bracket (7) below the spray device (9), and the top of the cooling cylinder (15) is connected to the engine nozzle of the rocket engine (5) through a metal deflector (8), and the wall of the cooling cylinder (15) is provided with a metal interlayer, which is connected to the cooling system (3); a gas-liquid separator (16) is connected to the bottom of the vertical support bracket (7), and the bottom of the gas-liquid separator (16) is connected to the liquid supply system (2) through a recovery pipeline (17) after being separated by a filter screen (27), and the top of the gas-liquid separator (16) is connected to the vacuum system (4); The liquid supply system (2) includes a water tank (18), which is connected to the spray device (9) via a water valve (19) and a water pump (20), and the inlet of the water pump (20) is connected to the alkaline solution tank (28) via an alkaline solution valve (29); The cooling system (3) includes a low-temperature liquid nitrogen storage tank (21), which is connected to the metal interlayer of the wall of the cooling cylinder (15) via a liquid nitrogen pump (22) and a low-temperature valve (23); The vacuum system (4) includes a gas generator (24), the gas generator (24) is connected to the main injection direction of the ejector (25), the ejector (25) is connected to the diffuser (26), and the ejected direction of the ejector (25) is connected to the top of the gas-liquid separator (16); The spraying device (9) comprises a first concentric circular bracket (11) and a second concentric circular bracket (12); a guide rail (10) is connected between the first concentric circular bracket (11) and the second concentric circular bracket (12); and a nozzle (13) is provided on the guide rail (10).

8. The aerospace engine ground experiment gas cooling device according to claim 7, characterized in that: The bottom spacer filter (27) of the gas-liquid separator for the solid rocket engine is made of fine metal material, and the filter diameter is at the micron level.

9. The aerospace engine ground experiment gas cooling device according to claim 7, characterized in that: The alkaline solution valve (29) and the water pump (20) are resistant to alkali corrosion, and the working liquid in the alkaline solution tank (28) is an alkaline solution with a concentration of 3 to 5%.

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