A flow-guiding cooling device and a rocket engine ignition test system

Abstract

This application discloses a flow-guiding cooling device and a rocket engine ignition test system, belonging to the field of rocket launch test technology. The flow-guiding cooling device includes a spray component, a flow-guiding mechanism, and a water supply mechanism. By setting a spray component in the initial section of the rocket engine's exhaust plume, the top-down spray can create a water curtain barrier, achieving cooling and noise reduction, preventing the exhaust gases from scorching other components. The cooled exhaust plume will not be too hot when it contacts the flow-guiding mechanism, thus preventing damage to the mechanism. The flow-guiding mechanism features an arc-shaped, downward-protruding flow-guiding channel spray panel and flow-guiding channels located on both sides of the panel, providing comprehensive spraying and guidance for the high-impact, high-temperature exhaust plume, thus reducing temperature and noise. Different spray densities can be applied to the inner and outer flames of the exhaust plume for targeted spraying, ensuring timely and sufficient cooling. The arc plate and second nozzle are detachable, facilitating replacement and removal after damage from high temperatures, reducing costs and improving economic efficiency.

Description

Technical Field

[0001] This application relates to the field of rocket launch test technology, and in particular to a flow-guiding cooling device and a rocket engine ignition test system. Background Technology

[0002] During rocket engine ignition tests, the nozzle ejects high-temperature, high-velocity exhaust gases. Designing a flow-guiding cooling device is crucial to ensure the safe exit of these gases after cooling and noise reduction.

[0003] Chinese patent application number CN202210525986.9, entitled "A Cooling Device and Cooling System for Rocket Engine Test Stand", discloses a cooling device including a guide channel, a cooling box, and a cooler. The inclined surface of the cooling box is flush with the surface of the guide channel, which together guides and sprays water to cool the exhaust of the rocket engine. The cooling water can be discharged in time along the guide channel, which can effectively prevent the device from being damaged by high temperature.

[0004] However, the temperature of the exhaust gas flow in the rocket engine varies at different locations. The cooling boxes of the aforementioned cooling devices have uniform water pressure, and the spray density of the guide channels is the same, lacking targeted spraying, resulting in untimely and insufficient cooling. Furthermore, the guide channels and water outlet nozzles are integrally formed, and if some of the water outlet nozzles are damaged by high temperature, the entire assembly must be replaced, which is uneconomical and inconvenient for loading and unloading. Summary of the Invention

[0005] In view of this, this application provides a flow-guiding cooling device and a rocket engine ignition test system, which can provide sufficient and targeted cooling and flow guidance for the temperature distribution of the rocket engine exhaust flame during ignition tests. The spray density and water pressure are adjustable, thereby making the cooling and noise reduction more effective. The flow-guiding device is detachable, which facilitates installation, removal and replacement, reduces maintenance costs and improves the economic efficiency of use.

[0006] Specifically, the following technical solutions are included:

[0007] In a first aspect, this application provides a flow-guiding cooling device suitable for cooling the exhaust plume of a rocket engine during an ignition test, the flow-guiding cooling device comprising:

[0008] The spray component is located in the initial stage of the rocket engine exhaust plume and includes multiple evenly distributed detachable first nozzles.

[0009] The flow guiding mechanism located below the rocket engine exhaust flame includes a flow guiding channel water spray panel that protrudes downward in an arc shape and flow guiding channel bodies located on both sides of the flow guiding channel water spray panel. The flow guiding channel water spray panel is hollow inside, and its upper surface is made up of multiple detachable arc plates spliced ​​together. Each arc plate includes a water spray zone with different spray densities, and multiple detachable second nozzles are set in the water spray zone.

[0010] The water supply system includes a water supply pipeline that is connected to the spray elements and the guide channel spray panel, and is used to supply water to the spray elements and to provide zoned water supply to the guide channel spray panel.

[0011] In some embodiments, water spray zones with different spray densities are set to correspond to the temperature distribution of the rocket engine exhaust flame, and the spray density of the water spray zone corresponds to the distribution density of the second nozzle set thereon.

[0012] In some embodiments, the flow guiding mechanism further includes an inverted U-shaped flow guiding channel side spray pipe, which is arranged around the top of the flow guiding channel body. The side of the flow guiding channel side spray pipe near the flow guiding channel spray panel includes a plurality of detachable first nozzles, and the flow guiding channel side spray pipe is connected to the water supply pipeline.

[0013] In some embodiments, the water supply pipeline includes a first water supply sub-pipeline and a second water supply sub-pipeline. The first water supply sub-pipeline is connected to both the spray element and the side spray pipe of the guide channel, and the second water supply sub-pipeline is connected to the spray panel of the guide channel.

[0014] The second water supply sub-pipeline is located below the water spray panel of the guide channel and includes a first zone sub-pipeline, a second zone sub-pipeline, and a third zone sub-pipeline. The water pressure of the first zone sub-pipeline and the third zone sub-pipeline is the same and less than that of the second zone sub-pipeline. The first zone sub-pipeline and the third zone sub-pipeline are used to supply water to the spray zone with the first spray density, and the second zone sub-pipeline is used to supply water to the spray zone with the second spray density.

[0015] In some embodiments, the first nozzle is a duckbill nozzle, the second nozzle is a conical nozzle, and the second nozzle has a groove for disassembly.

[0016] In some embodiments, the water supply mechanism includes a plurality of first water tanks, a plurality of second water tanks, and a plurality of third water tanks disposed between the guide channel spray panel and the second water supply sub-pipeline. The first water tanks, the second water tanks, and the third water tanks are respectively connected to the first zone sub-pipeline, the second zone sub-pipeline, and the third zone sub-pipeline, for providing zoned water supply to the guide channel spray panel. The water pressure of the first water tanks and the third water tanks is the same and is less than the water pressure of the second water tanks.

[0017] In some embodiments, the flow guiding mechanism includes a support member, and the flow guiding cooling device includes a base, the base being fixedly connected to the support member and to the ground interface by bolts.

[0018] In some embodiments, the water supply mechanism further includes a motor, a water pump, and valves disposed on the water supply pipeline.

[0019] Secondly, this application provides a rocket engine ignition test system, including the flow-guiding cooling device described in the first aspect.

[0020] The beneficial effects of the technical solutions provided in this application include at least the following:

[0021] This application provides a flow-guiding cooling device and a rocket engine ignition test system. The flow-guiding cooling device includes a spray element, a flow-guiding mechanism, and a water supply mechanism. During ignition testing, when cooling the rocket engine exhaust plume, the temperature varies at different locations within the exhaust gas flow, with the initial section of the exhaust plume having the highest temperature. This application's flow-guiding cooling device, by installing a spray element in the initial section of the rocket engine exhaust plume, creates a water curtain barrier through top-down spraying, achieving cooling and noise reduction. It also prevents the exhaust gas from splashing outwards and burning other components. The cooled exhaust plume does not become excessively hot upon contact with the flow-guiding mechanism, thus preventing damage to the mechanism. The flow-guiding mechanism below the rocket engine exhaust plume includes an arc-shaped, downward-protruding flow-guiding channel water spray panel and flow-guiding channels located on both sides of the water spray panel, which can effectively cool the high-impact, high-temperature exhaust plume. The system provides comprehensive spraying and airflow guidance, resulting in effective cooling and noise reduction. The airflow guide channel sprays water onto the tail flame from bottom to top, providing cooling. Its arc shape allows for an increase in the number of nozzles and facilitates the timely flow of coolant after spraying, preventing damage to the airflow guide mechanism due to accumulation. The airflow guide channel spray panel features multiple detachable arc plates with spray zones of varying spray densities, indirectly adjusting the water pressure at different points corresponding to the tail flame. Multiple detachable second nozzles are installed within the spray zones, allowing for targeted spraying based on the temperature of the inner and outer flames of the tail flame, ensuring timely and sufficient cooling. Furthermore, the detachable arc plates and second nozzles facilitate replacement and disassembly after high-temperature damage, reducing costs and improving economic efficiency. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the structure of a flow-guiding cooling device provided in this application;

[0024] Figure 2 A schematic diagram showing the relative position of a flow-guiding cooling device and a rocket engine provided in this application;

[0025] Figure 3This application provides a schematic diagram of the water supply pipeline in a flow-guiding cooling device.

[0026] Figure 4 A schematic diagram of the structure of the first nozzle in a flow-guiding cooling device provided in this application;

[0027] Figure 5 This is a schematic diagram of the structure of the second nozzle in a flow-guiding cooling device provided in this application.

[0028] The reference numerals in the figure are respectively:

[0029] 1-Sprayer component, 12-First nozzle, 2-Flow guiding mechanism, 21-Flow guiding channel spray panel, 211-Arc plate, 2111-Second nozzle, 22-Flow guiding channel body, 23-Flow guiding channel side spray pipe, 24-Support component, 311-First water supply sub-pipeline, 312-Second water supply sub-pipeline, 3121-First zone sub-pipeline, 3122-Second zone sub-pipeline, 3123-Third zone sub-pipeline, 32-First water tank, 33-Second water tank, 34-Third water tank. Detailed Implementation

[0030] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0031] To make the technical solutions and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0032] Firstly, this application provides a flow-guiding cooling device suitable for cooling the exhaust plume of a rocket engine during ignition testing. See [link to relevant documentation]. Figure 1 and Figure 2 The cooling device includes:

[0033] The spray component 1 is located in the initial section of the rocket engine exhaust plume, and the spray component 1 includes multiple evenly distributed detachable first nozzles 12.

[0034] The flow guiding mechanism 2 is located below the exhaust flame of the rocket engine. The flow guiding mechanism 2 includes a flow guiding channel water spray panel 21 that protrudes downward in an arc shape and flow guiding channel bodies 22 located on both sides of the flow guiding channel water spray panel 21. The flow guiding channel water spray panel 21 is hollow inside, and its upper surface is spliced ​​together by multiple detachable arc plates 211. Each arc plate 211 includes a water spray area with different spray densities, and multiple detachable second nozzles 2111 are set in the water spray area.

[0035] The water supply mechanism includes a water supply pipeline that is connected to the spray element 1 and the guide channel spray panel 21, and is used to supply water to the spray element 1 and to provide zoned water supply to the guide channel spray panel 21.

[0036] See Figure 2 The cooling system is located below the test stand, while the rocket propulsion system is located on the test stand. The rocket propulsion system (rocket engine) uses... Figure 2 The cylindrical shape is used instead. During the ignition test, when cooling the rocket engine exhaust plume, the temperature varies at different locations in the exhaust gas flow; the initial section of the exhaust plume has the highest temperature.

[0037] The cooling device of this application uses a spray element 1 installed in the initial section of the rocket engine exhaust plume. The downward spray can create a water curtain barrier, achieving cooling and noise reduction, and preventing the exhaust gas from splashing outwards and burning other components. The cooled exhaust plume will not be too hot when it comes into contact with the cooling mechanism 2, thus preventing damage to the cooling mechanism 2. The cooling device of this application has a cooling mechanism 2 below the rocket engine exhaust plume. The cooling channel water spray panel 21 with an arc shape protruding downwards in the cooling mechanism 2 and the cooling channels 22 located on both sides of the cooling channel water spray panel 21 can spray and guide the high-impact, high-temperature exhaust plume comprehensively, with good cooling and noise reduction effects. The cooling channel water spray panel 21 can spray and guide the high-impact, high-temperature exhaust plume from bottom to top. The upper part sprays water to cool the tail flame, and its arc shape increases the number of nozzles that can be installed. It also helps the coolant to flow down in time after spraying, so as not to damage the guide mechanism 2 due to accumulation. The multiple detachable arc plates 211 of the guide channel spray panel 21 include spray zones with different spray densities, thereby indirectly adjusting the water pressure at various points corresponding to the tail flame. Multiple detachable second nozzles 2111 are set in the spray zone. The spray zones with different spray densities can spray water in a targeted manner according to the temperature of the inner and outer flames of the tail flame, so that the cooling is timely and sufficient. Furthermore, the arc plates 211 and the second nozzles 2111 are detachable, which is convenient for replacement and disassembly after a certain part is damaged by high temperature, reducing costs and improving the economy of use.

[0038] In some embodiments, the spray element 1 can be annular, which helps to envelop the exhaust flame and facilitates cooling and noise reduction.

[0039] In some embodiments, water spray zones with different spray densities are set up to correspond to the temperature distribution of the rocket engine exhaust plume, and the spray density of the water spray zone corresponds to the distribution density of the second nozzle 2111 set thereon. The inner flame of the rocket engine exhaust plume has a high temperature, so a water spray zone with a higher spray density is set up accordingly. The outer flame of the exhaust plume has a relatively low temperature, so a water spray zone with a higher spray density is set up accordingly. This allows for targeted spraying of the rocket engine exhaust plume, ensuring sufficient cooling and reducing cooling costs. It also contributes to the economy of the number of spray holes in the water spray panel 21 of the guide channel.

[0040] In some embodiments, the flow guiding mechanism 2 further includes an inverted U-shaped side spray pipe 23 surrounding the flow guiding channel body 22. The side of the side spray pipe 23 near the water spray panel 21 of the flow guiding channel includes a plurality of detachable first nozzles 12. The side spray pipe 23 is connected to a water supply pipeline. The side spray pipe 23 can cool and reduce noise from the rocket engine exhaust flame from all directions.

[0041] In some embodiments, such as Figure 3 As shown, the water supply pipeline includes a first water supply sub-pipeline 311 and a second water supply sub-pipeline 312. The first water supply sub-pipeline 311 is connected to both the spray component 1 and the side spray pipe 23 of the guide channel. The second water supply sub-pipeline 312 is connected to the guide channel spray panel 21. The second water supply sub-pipeline 312 is located below the guide channel spray panel 21 and includes a first zone sub-pipeline 3121, a second zone sub-pipeline 3122, and a third zone sub-pipeline 3123. The water pressure of the first zone sub-pipeline 3121 and the third zone sub-pipeline 3123 is the same and less than the water pressure of the second zone sub-pipeline 3122. The first zone sub-pipeline 3121 and the third zone sub-pipeline 3123 are used to supply water to the spray area with the first spray density, and the second zone sub-pipeline 3122 is used to supply water to the spray area with the second spray density.

[0042] In some embodiments, such as Figure 4 As shown, the first nozzle 12 is a duckbill-shaped nozzle. The first nozzle 12 is set on the spray hole of the spray component 1 and the side spray pipe 23 of the guide channel. The duckbill-shaped nozzle ensures water pressure stability and allows the spray water to spread in all directions. Its advantage is that while cooling, the spray area of ​​the duckbill-shaped nozzle is relatively large, which can also play a good noise reduction function. It is also easy to disassemble and facilitates later maintenance and replacement. The second nozzle 2111 is a conical nozzle. The second nozzle 2111 has a groove for disassembly. The second nozzle 2111 is set on the spray hole of the spray panel 21 of the guide channel. The conical nozzle ensures water pressure stability and allows the spray water to spread in all directions, covering the required cooling area. The external groove is provided for disassembly. Its advantage is that if a single spray hole is blocked, only the single nozzle needs to be replaced.

[0043] In some embodiments, different models of the first nozzle 12 and the second nozzle 2111 can be replaced according to requirements such as water pressure, water volume and water area.

[0044] In some embodiments, the water supply mechanism includes a plurality of first water tanks 32, a plurality of second water tanks 33, and a plurality of third water tanks 34 disposed between the guide channel spray panel 21 and the second water supply sub-pipeline 312. The first water tanks 32, second water tanks 33, and third water tanks 34 are respectively connected to the first partition sub-pipeline 3121, the second partition sub-pipeline 3122, and the third partition sub-pipeline 3123 for providing partitioned water supply to the guide channel spray panel 21. The water pressure of the first water tanks 32 and the third water tanks 34 is the same and is less than the water pressure of the second water tank 33.

[0045] In some embodiments, each of the first water tank 32, the second water tank 33 and the third water tank 34 is provided with an inspection hole for easy maintenance.

[0046] In some embodiments, the flow guiding mechanism 2 includes a support member 24, thereby enabling the flow guiding channel spray panel 21 and the second water supply sub-pipe 312 to withstand the powerful impact of the rocket engine exhaust flame.

[0047] In some embodiments, the support member 24 may be a steel plate.

[0048] In some embodiments, the support member 24 may include a plurality of crisscrossing support portions to enhance the support capability of the flow guiding mechanism 2.

[0049] In some embodiments, the cooling device includes a base, which is fixedly connected to the support member 24 and to the ground interface by bolts, thereby ensuring the stability of the cooling device during use. During use, after adjusting the flatness and test position, the base is fixedly connected to the ground interface by bolts.

[0050] In some embodiments, the water supply mechanism further includes a motor, a water pump, and valves disposed on the water supply pipeline.

[0051] In some embodiments, the flow-guiding cooling device is used as follows: (1) After adjusting the flatness and test position, the base is fixedly connected to the ground interface by bolts; (2) According to the parameters of the rocket engine and the tail flame temperature, the first nozzle 12 and the second nozzle 2111 that meet the model requirements are selected; (3) The water pressure, water supply and the number of water tanks and pipelines that meet the cooling and noise reduction requirements are set by adjusting the motor, water pump and valve; (4) The flow-guiding cooling device is started to conduct the ignition test of the rocket engine.

[0052] In summary, this application provides a flow-guiding cooling device that can provide sufficient and targeted cooling and flow guidance for the temperature distribution of the rocket engine exhaust flame during ignition tests. The spray density and water pressure are adjustable, thereby making the cooling and noise reduction more effective. The flow-guiding device is detachable, which facilitates installation, removal and replacement, reduces maintenance costs, and improves the economic efficiency of use.

[0053] Secondly, this application provides a rocket engine ignition test system, including the flow-guiding cooling device described in the first aspect.

[0054] In summary, this application provides a rocket engine ignition test system that can provide sufficient and targeted cooling and flow guidance for the temperature distribution of the rocket engine exhaust flame during ignition tests. The injection density and water pressure are adjustable, thereby making the cooling and noise reduction more effective. The flow guidance device is detachable, which facilitates installation, removal and replacement, reduces maintenance costs and improves the economic efficiency of use.

[0055] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the application disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only.

[0056] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this application is limited only by the appended claims.

Claims

1. A flow-guiding cooling device suitable for cooling the exhaust plume of a rocket engine during ignition testing, characterized in that, The flow-guiding cooling device includes: The spray component (1) located in the initial section of the rocket engine exhaust flame includes multiple uniformly distributed detachable first nozzles (12). The guide mechanism (2) located below the tail flame of the rocket engine includes a guide channel water spray panel (21) that protrudes downward in an arc shape and a guide channel body (22) located on both sides of the guide channel water spray panel (21). The guide channel water spray panel (21) is hollow inside, and its upper surface is spliced ​​together by multiple detachable arc plates (211). Each arc plate (211) includes a water spray area with different spray densities, and multiple detachable second nozzles (2111) are set in the water spray area. The water supply mechanism includes a water supply pipeline that is connected to the spray unit (1) and the guide channel spray panel (21) for supplying water to the spray unit (1) and for providing zoned water supply to the guide channel spray panel (21).

2. The flow-guiding cooling device according to claim 1, characterized in that, Different spray densities of water spray zones are set to correspond to the temperature distribution of the rocket engine exhaust flame, and the spray density of the water spray zone corresponds to the distribution density of the second nozzle (2111) set thereon.

3. The flow-guiding cooling device according to claim 1, characterized in that, The flow guiding mechanism (2) also includes a U-shaped flow guiding channel side spray pipe (23) which is arranged around the flow guiding channel body (22). The side of the flow guiding channel side spray pipe (23) near the flow guiding channel spray panel (21) includes a plurality of detachable first nozzles (12). The flow guiding channel side spray pipe (23) is connected to the water supply pipeline.

4. The flow-guiding cooling device according to claim 3, characterized in that, The water supply pipeline includes a first water supply sub-pipeline (311) and a second water supply sub-pipeline (312). The first water supply sub-pipeline (311) is connected to both the spray element (1) and the side spray pipe (23) of the guide channel. The second water supply sub-pipeline (312) is connected to the spray panel (21) of the guide channel. The second water supply sub-pipeline (312) is located below the water spray panel (21) of the guide channel, and includes a first partition sub-pipeline (3121), a second partition sub-pipeline (3122) and a third partition sub-pipeline (3123). The water pressure of the first partition sub-pipeline (3121) and the third partition sub-pipeline (3123) is the same and less than the water pressure of the second partition sub-pipeline (3122). The first partition sub-pipeline (3121) and the third partition sub-pipeline (3123) are used to supply water to the spray area with the first spray density, and the second partition sub-pipeline (3122) is used to supply water to the spray area with the second spray density.

5. The flow-guiding cooling device according to claim 1, characterized in that, The first nozzle (12) is a duckbill-shaped nozzle, and the second nozzle (2111) is a conical nozzle. The second nozzle (2111) has a groove for disassembly.

6. The flow-guiding cooling device according to claim 4, characterized in that, The water supply mechanism includes multiple first water tanks (32), multiple second water tanks (33), and multiple third water tanks (34) disposed between the guide channel spray panel (21) and the second water supply sub-pipeline (312). The first water tanks (32), the second water tanks (33), and the third water tanks (34) are respectively connected to the first partition sub-pipeline (3121), the second partition sub-pipeline (3122), and the third partition sub-pipeline (3123) for partitioned water supply to the guide channel spray panel (21). The water pressure of the first water tanks (32) and the third water tanks (34) is the same and less than the water pressure of the second water tanks (33).

7. The flow-guiding cooling device according to claim 1, characterized in that, The flow guiding mechanism (2) includes a support member (24), and the flow guiding cooling device includes a base. The base is fixedly connected to the support member (24) and fixedly connected to the ground interface by bolts.

8. The flow-guiding cooling device according to claim 1, characterized in that, The water supply mechanism also includes a motor, a water pump, and valves installed on the water supply pipeline.

9. A rocket engine ignition test system, characterized in that, Includes a flow-guiding cooling device as described in any one of claims 1-8.

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