Diversion cooling device and rocket engine ignition test system

Abstract

The invention discloses a diversion cooling device and a rocket engine ignition test system, and belongs to the technical field of rocket launching tests. The flow guide cooling device comprises a spraying piece, a flow guide mechanism and a water supply mechanism. The spraying piece is arranged at the initial section of the tail flame of the rocket engine, a water curtain barrier can be arranged through spraying from top to bottom, cooling and noise reduction are achieved, fuel gas of the tail flame is prevented from burning other devices, and the temperature of the cooled tail flame cannot be too high when the cooled tail flame makes contact with the flow guide mechanism, and the flow guide mechanism cannot be damaged; in the flow guide mechanism, a flow guide groove water spraying panel which is in an arc shape and protrudes downwards in an inclined mode and flow guide groove bodies located on the two sides of the flow guide groove water spraying panel are used for conducting comprehensive spraying and flow guide on the high-impact-force and high-temperature tail flame, cooling and noise reduction are achieved, and water spraying areas with different spraying densities can conduct targeted spraying according to the temperature of the inner flame and the outer flame of the tail flame. And the arc plate and the second nozzle are detachable, so that the arc plate and the second nozzle are convenient to replace, assemble and disassemble after a certain part is damaged by high temperature, the cost is reduced, and the use economy is improved.

Description

Technical Field

[0001] The present application relates to the field of rocket launch test technology, and in particular to a flow guide cooling device and a rocket engine ignition test system. Background Art

[0002] During a rocket engine ignition test, the nozzle ejects a high-temperature, high-velocity gas stream. To ensure the gas is safely discharged after cooling and reducing noise, the design of a flow-guiding cooling device is crucial.

[0003] In the Chinese patent document with application number CN202210525986.9 and invention name "A cooling device and rocket engine test bench cooling system", a cooling device including a guide groove, a cooling box and a cooler is disclosed. The inclined surface of the cooling box is flush with the surface of the guide groove, and together they guide and spray water to cool the wake of the rocket engine. The cooling water can be discharged in time along the guide groove, which can effectively prevent the device from being damaged by high temperature.

[0004] However, the temperature of the gas flow at different positions of the rocket engine tail flame is different. The cooling box of the above-mentioned cooling device has a uniform water pressure, and the spray density of the guide groove is the same, which lacks targeted spraying, resulting in untimely and insufficient cooling; the guide groove and the water outlet nozzle are integrally formed. After a part of the water outlet nozzle is damaged by high temperature, it can only be replaced as a whole, which lacks economy and is not conducive to loading and unloading. Summary of the Invention

[0005] In view of this, the present application provides a diversion cooling device and a rocket engine ignition test system, which can fully and specifically cool and divert the temperature distribution of the rocket engine tail flame during the ignition test. The injection density and water pressure are adjustable, so that the cooling and noise reduction are more sufficient. The diversion device is detachable, which facilitates loading and unloading and replacement, reduces maintenance costs, and improves economic efficiency.

[0006] Specifically, the following technical solutions are included: In a first aspect, the present application provides a flow-guiding cooling device suitable for cooling the tail flame of a rocket engine during an ignition test, the flow-guiding cooling device comprising: A spraying member located at the initial section of the rocket engine tail flame, the spraying member comprising a plurality of evenly distributed and detachable first nozzles; The guide mechanism is located below the tail flame of the rocket engine. The guide mechanism includes a guide trough water spray panel that protrudes obliquely downward in an arc shape and a guide trough body located on both sides of the guide trough water spray panel. The guide trough water spray panel is hollow inside, and its upper surface is composed of multiple detachable arc plates. Each arc plate includes a water spray area with different spray densities, and multiple detachable second nozzles are set in the water spray area. The water supply mechanism includes a water supply pipeline, which is connected to the spray element and the guide groove water spray panel and is used to supply water to the spray element and to supply water to the guide groove water spray panel in different areas.

[0007] In some embodiments, water spray areas with different spray densities are set to correspond to the temperature distribution of the rocket engine tail flame, and the spray density of the water spray area corresponds to the distribution density of the second nozzle set thereon.

[0008] In some embodiments, the diversion mechanism also includes an inverted U-shaped diversion trough side water spray pipe, which is arranged in a circle above the diversion trough body. The diversion trough side water spray pipe includes a plurality of detachable first nozzles on the side close to the diversion trough water spray panel, and the diversion trough side water spray pipe is connected to the water supply pipeline.

[0009] 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 water spray pipe on the side of the guide groove, and the second water supply sub-pipeline is connected to the water spray panel of the guide groove; The second water supply sub-pipeline is arranged below the water spray panel of the guide trough, and includes a first partition sub-pipeline, a second partition sub-pipeline and a third partition sub-pipeline. The water pressure of the first partition sub-pipeline and the third partition sub-pipeline is the same and less than the water pressure of the second partition sub-pipeline. The first partition sub-pipeline and the third partition sub-pipeline are used to supply water to the water spray area with a first injection density, and the second partition sub-pipeline is used to supply water to the water spray area with a second injection density.

[0010] In some embodiments, the first nozzle is a duckbill-shaped nozzle, the second nozzle is a conical nozzle, and the second nozzle has a groove for disassembly.

[0011] In some embodiments, the water supply mechanism includes multiple first water tanks, multiple second water tanks and multiple third water tanks arranged between the guide trough water spray panel and the second water supply sub-pipeline, the first water tank, the second water tank and the third water tank are respectively connected to the first partition sub-pipeline, the second partition sub-pipeline and the third partition sub-pipeline, and are used to provide partitioned water supply to the guide trough water spray panel, and the water pressure of the second water tank and the third water tank is the same and less than the water pressure of the second water tank.

[0012] In some embodiments, the flow guiding mechanism includes a support member, and the support member is used to support the flow guiding mechanism.

[0013] In some embodiments, the diversion cooling device includes a base, which is fixedly connected to the support member and fixedly connected to the ground interface via bolts.

[0014] In some embodiments, the water supply mechanism further includes a motor, a water pump and a valve arranged on the water supply pipeline.

[0015] In a second aspect, the present application provides a rocket engine ignition test system, comprising a flow-guiding cooling device as described in the first aspect.

[0016] The beneficial effects of the technical solutions provided by the embodiments of the present application include at least: The embodiment of the present application provides a diversion cooling device and a rocket engine ignition test system, the diversion cooling device includes a spray part, a diversion mechanism and a water supply mechanism. When cooling the rocket engine tail flame in the ignition test, due to the different temperatures of the gas flow at different positions of the rocket engine tail flame, the temperature of the initial section of the rocket engine tail flame is the highest. The diversion cooling device of the present application sets a spray part at the initial section of the rocket engine tail flame. The top-down spraying can set a water curtain barrier to achieve cooling and noise reduction, and can prevent the gas of the tail flame from splashing around and burning other devices. The tail flame after cooling will not be too hot when it contacts the diversion mechanism, thereby damaging the diversion mechanism. The diversion mechanism below the rocket engine tail flame of the diversion cooling device of the present application, the diversion groove water spray panel that is arc-shaped and protrudes obliquely downward in the diversion mechanism and the diversion groove bodies located on both sides of the diversion groove water spray panel can be used to cool the high-impact and high-temperature tail flame. It performs comprehensive spraying and diversion, and has good cooling and noise reduction effects. The guide trough water spray panel can spray and cool the tail flame from bottom to top. It is arc-shaped, which can increase the number of nozzles installed, and is also beneficial for the coolant after spraying to be diverted downward in time to avoid damage to the diversion mechanism due to accumulation. The multiple detachable arc plates of the guide trough water spray panel include water spray areas with different spray densities, thereby indirectly adjusting the water pressure at various locations corresponding to the tail flame. Multiple detachable second nozzles are arranged in the water spray area. The water spray areas with different spray densities can be targeted according to the temperature of the inner flame and outer flame of the tail flame, so that the cooling is timely and sufficient, and the arc plate and the second nozzle are detachable, which is convenient for replacement and loading and unloading after a part is damaged by high temperature, reducing costs and improving economic efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0018] Figure 1 A schematic structural diagram of a flow-guiding cooling device provided in this application; Figure 2 A schematic diagram of the relative positions of a diversion cooling device and a rocket engine provided in this application; Figure 3 This is a schematic structural diagram of a water supply pipeline in a diversion cooling device provided in this application; Figure 4 This is a schematic structural diagram of a first nozzle in a flow-guiding cooling device provided in this application; Figure 5 This is a schematic structural diagram of the second nozzle in a flow-guiding cooling device provided in this application.

[0019] The reference numerals in the figures represent respectively: 1-spraying part, 12-first nozzle, 2-guiding mechanism, 21-guiding trough water spray panel, 211-arc plate, 2111-second nozzle, 22-guiding trough body, 23-guiding trough side water spray pipe, 24-support part, 311-first water supply sub-pipeline, 312-second water supply sub-pipeline, 3121-first partition sub-pipeline, 3122-second partition sub-pipeline, 3123-third partition sub-pipeline, 32-first water tank, 33-second water tank, 34-third water tank. DETAILED DESCRIPTION

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

[0021] In order to make the technical solutions and advantages of the present application clearer, the implementation methods of the present application will be described in further detail below with reference to the accompanying drawings.

[0022] In the first aspect, the present application provides a flow guide cooling device suitable for cooling the tail flame of a rocket engine during an ignition test. Figure 1 and Figure 2 , the flow-guiding cooling device comprises: A spraying member 1 located at the initial section of the rocket engine tail flame, the spraying member 1 comprising a plurality of evenly distributed and detachable first nozzles 12; The guide mechanism 2 is located below the rocket engine tail flame. The guide mechanism 2 includes an arc-shaped guide trough water spray panel 21 that protrudes obliquely downward and a guide trough body 22 located on both sides of the guide trough water spray panel 21. The guide trough water spray panel 21 is hollow inside, and its upper surface is spliced ​​by multiple detachable arc plates 211. Each arc plate 211 includes a water spray area with different spray densities. Multiple detachable second nozzles 2111 are installed in the water spray area. The water supply mechanism includes a water supply pipeline, which is connected to the spray element 1 and the guide groove water spray panel 21 and is used to supply water to the spray element 1 and to supply water to the guide groove water spray panel 21 in different areas.

[0023] See also Figure 2The guide cooling device is located under the test bench, the rocket power unit is located on the test bench, and the rocket power unit (rocket engine) is used Figure 2 When cooling the rocket engine tail flame in the ignition test, the temperature of the rocket engine tail flame is the highest at the initial stage due to the different temperatures of the gas flow at different positions of the rocket engine tail flame. The diversion cooling device of the present application sets a spray part 1 at the initial section of the rocket engine tail flame. The top-down spraying can set up a water curtain barrier to achieve cooling and noise reduction, and can prevent the combustion gas of the tail flame from splashing around and burning other devices. The tail flame after cooling will not be too hot when it contacts the diversion mechanism 2, thereby damaging the diversion mechanism 2; the diversion cooling device of the present application has a diversion mechanism 2 below the tail flame of the rocket engine, a diversion groove water spray panel 21 that is arc-shaped and protrudes obliquely downward in the diversion mechanism 2, and a diversion groove body 22 located on both sides of the diversion groove water spray panel 21. It can fully spray and guide the high-impact and high-temperature tail flame, and has a good cooling and noise reduction effect. The diversion groove water spray panel 21 can spray water from bottom to top The tail flame is sprayed to cool it down, and it is in an arc shape, which can increase the number of nozzles installed, and is also beneficial for the coolant after spraying to be diverted downward in time to avoid damage to the guide mechanism 2 due to accumulation. The multiple detachable arc plates 211 of the guide groove water spray panel 21 include water spray areas with different spray densities, so as to indirectly adjust the water pressure at various locations corresponding to the tail flame. Multiple detachable second nozzles 2111 are set in the water spray area. The water spray areas with different spray densities can be targeted according to the temperature of the inner flame and the outer flame of the tail flame, so that the cooling is timely and sufficient, and the arc plate 211 and the second nozzle 2111 are detachable, which is convenient for replacement and assembly after a part is damaged by high temperature, reducing costs and improving economic efficiency.

[0024] In some embodiments, the spray element 1 may be annular, which is beneficial for wrapping the tail flame therein, and is beneficial for cooling and reducing noise.

[0025] In some embodiments, water spray areas with different spray densities are arranged to correspond to the temperature distribution of the rocket engine exhaust flame, and the spray density of the water spray area corresponds to the distribution density of the second nozzles 2111 arranged thereon. The temperature of the inner flame of the rocket engine exhaust flame is high, so the water spray area with a higher spray density is arranged accordingly. The temperature of the outer flame of the exhaust flame is relatively low, so the water spray area with a higher spray density is arranged accordingly. This achieves targeted spraying of the rocket engine exhaust flame, ensures sufficient cooling, reduces cooling costs, and facilitates the economical production of the number of water spray holes in the guide groove water spray panel 21.

[0026] In some embodiments, the diversion mechanism 2 further includes an inverted U-shaped diversion trough side water spray pipe 23, which is disposed around the diversion trough body 22. The diversion trough side water spray pipe 23 includes a plurality of detachable first nozzles 12 on one side of the diversion trough water spray panel 21. The diversion trough side water spray pipe 23 is connected to the water supply pipeline. The diversion trough side water spray pipe 23 can cool and reduce the noise of the rocket engine exhaust flame from all sides.

[0027] In some embodiments, 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 the spray element 1 and the side water spray pipe 23 of the guide groove, and the second water supply sub-pipeline 312 is connected to the water spray panel 21 of the guide groove; the second water supply sub-pipeline 312 is arranged below the water spray panel 21 of the guide groove, 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 water spray area of ​​the first injection density, and the second partition sub-pipeline 3122 is used to supply water to the water spray area of ​​the second injection density.

[0028] In some embodiments, as Figure 4 As shown, the first nozzle 12 is a duckbill nozzle. The first nozzle 12 is arranged on the water spray hole of the spray part 1 and the side water spray pipe 23 of the guide groove. The duckbill nozzle not only ensures the stability of water pressure but also can make the water spray spread all around. Its advantage is that while cooling, the duckbill nozzle has a wider water spray area, can also play a good noise reduction function, and is easy to disassemble, which is convenient for 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 arranged on the water spray hole of the guide groove water spray panel 21. The conical nozzle not only ensures the stability of water pressure but also can make the water spray spread all around, covering the required cooling area, and a groove required for disassembly is left on the outside. Its advantage is that if a single water spray hole is blocked, only a single nozzle needs to be replaced.

[0029] 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.

[0030] In some embodiments, the water supply mechanism includes multiple first water tanks 32, multiple second water tanks 33 and multiple third water tanks 34 arranged between the guide trough water spray panel 21 and the second water supply sub-pipeline 312. The first water tank 32, the second water tank 33 and the third water tank 34 are respectively connected to the first partition sub-pipeline 3121, the second partition sub-pipeline 3122 and the third partition sub-pipeline 3123, and are used to provide partitioned water supply to the guide trough water spray panel 21. The water pressure of the second water tank 33 and the third water tank 34 is the same and less than the water pressure of the second water tank 33.

[0031] 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 inspection.

[0032] In some embodiments, the guide mechanism 2 includes a support member 24, which is used to support the guide mechanism 2, so that the guide trough water spray panel 21 and the second water supply sub-pipeline 312 can withstand the strong impact force of the rocket engine tail flame.

[0033] In some embodiments, the support member 24 may be a steel plate.

[0034] In some embodiments, the support member 24 may include a plurality of crisscross support portions therein to enhance the support capability of the flow guiding mechanism 2 .

[0035] In some embodiments, the diversion cooling device includes a base, which is fixedly connected to the support member 24 and fixedly connected to the ground interface by bolts, thereby ensuring the stability of the diversion cooling device during use. When in use, after adjusting the flatness and test position, the base is fixedly connected to the ground interface by bolts.

[0036] In some embodiments, the water supply mechanism further includes a motor, a water pump, and a valve disposed on the water supply pipeline.

[0037] In some embodiments, the diversion cooling device is used as follows: (1) After adjusting the flatness and test position, the base is fixed 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) By adjusting the motor, water pump and valve, the water pressure, water supply and the number of water tanks and pipelines that meet the cooling and noise reduction requirements are set; (4) The diversion cooling device is controlled to start and the rocket engine ignition test is carried out.

[0038] In summary, the present application provides a diversion cooling device that can fully and specifically cool and divert the temperature distribution of the rocket engine tail flame during the ignition test. The spray density and water pressure are adjustable, so that the cooling and noise reduction are more sufficient. The diversion device is detachable, which facilitates loading and unloading and replacement, reduces maintenance costs, and improves economic efficiency.

[0039] In a second aspect, the present application provides a rocket engine ignition test system, comprising a flow-guiding cooling device as described in the first aspect.

[0040] In summary, the present application provides a rocket engine ignition test system that can fully and specifically cool and guide the temperature distribution of the rocket engine tail flame during the ignition test. The injection density and water pressure are adjustable, thereby making the cooling and noise reduction more sufficient. The guide device is detachable, thereby facilitating loading and unloading and replacement, reducing maintenance costs, and improving economic efficiency.

[0041] Those skilled in the art will readily appreciate other embodiments of the present invention after considering the specification and practicing the present invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present invention that follow the general principles of the present invention and include common knowledge or customary techniques in the art not disclosed herein. The description and examples are to be considered as exemplary only.

[0042] It should be understood that the present application is not limited to the exact structures described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present application is limited only by the appended claims.

Claims

1. A flow guide cooling device suitable for cooling the tail flame of a rocket engine during an ignition test, characterized in that: The flow-guiding cooling device comprises: A spraying member (1) located at the initial section of the rocket engine tail flame, the spraying member (1) comprising a plurality of evenly distributed and detachable first nozzles (12); A guide mechanism (2) is located below the tail flame of the rocket engine, the guide mechanism (2) comprising an arc-shaped guide trough water spray panel (21) that obliquely protrudes downward and a guide trough body (22) located on both sides of the guide trough water spray panel (21), the guide trough water spray panel (21) is hollow inside, and the upper surface is formed by splicing a plurality of detachable arc plates (211), each arc plate (211) includes a water spray area with different spray densities, and a plurality of detachable second nozzles (2111) are provided in the water spray area; The water supply mechanism comprises a water supply pipeline, which is connected to the spraying member (1) and the guide groove water spray panel (21) and is used to supply water to the spraying member (1) and to supply water to the guide groove water spray panel (21) in a zoned manner.

2. The flow-conducting cooling device according to claim 1, characterized in that: The water spraying areas with different spraying densities are arranged corresponding to the temperature distribution of the rocket engine tail flame, and the spraying density of the water spraying area corresponds to the distribution density of the second nozzle (2111) arranged thereon.

3. The flow-conducting cooling device according to claim 1, characterized in that: The guide mechanism (2) further comprises an inverted U-shaped guide trough side water spray pipe (23), which is arranged in a ring above the guide trough body (22); the guide trough side water spray pipe (23) comprises a plurality of detachable first nozzles (12) on a side close to the guide trough water spray panel (21); and the guide trough side water spray pipe (23) is connected to the water supply pipeline.

4. The flow-conducting cooling device according to claim 3, characterized in that: The water supply pipeline comprises a first water supply sub-pipeline (311) and a second water supply sub-pipeline (312), wherein the first water supply sub-pipeline (311) is connected to both the spray element (1) and the water spray pipe (23) on the side of the guide groove, and the second water supply sub-pipeline (312) is connected to the water spray panel (21) of the guide groove; The second water supply sub-pipeline (312) is arranged below the guide trough water spray panel (21), 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 water spray area of ​​the first injection density, and the second partition sub-pipeline (3122) is used to supply water to the water spray area of ​​the second injection density.

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

6. The flow-conducting cooling device according to claim 1, characterized in that: The water supply mechanism comprises a plurality of first water tanks (32), a plurality of second water tanks (33) and a plurality of third water tanks (34) arranged between the guide trough water 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), and are used for providing partitioned water supply to the guide trough water spray panel (21); the water pressure of the second water tank (33) and the third water tank (34) is the same and less than the water pressure of the second water tank (33).

7. The flow-conducting cooling device according to claim 1, characterized in that: The flow guiding mechanism (2) comprises a support member (24), and the support member (24) is used to support the flow guiding mechanism (2).

8. The flow-conducting cooling device according to claim 1, characterized in that: The diversion cooling device comprises a base, which is fixedly connected to the support member (24) and fixedly connected to the ground interface via bolts.

9. The flow-conducting cooling device according to claim 1, characterized in that: The water supply mechanism also includes a motor, a water pump and a valve arranged on the water supply pipeline.

10. A rocket engine ignition test system, characterized in that: It comprises a flow-conducting cooling device as described in any one of claims 1 to 9.

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