High-temperature fuel gas active cooling device for attitude control engine high-altitude simulation test

Abstract

The invention relates to a high-temperature fuel gas active cooling device for a high-altitude simulation test of an attitude control engine, and mainly solves the technical problem that an existing cooling device is poor in cooling effect. The cooling device comprises a shell and a plurality of cooling units arranged in the shell. The shell is of a cylindrical structure, the multiple cooling units are arranged side by side in the axial direction of the shell, and each cooling unit comprises a fixing ring and multiple spraying pipes evenly distributed in the circumferential direction of the fixing ring; the spraying pipe is of a hollow structure with one end open and the other end closed, the open end of the spraying pipe is fixed to the shell and extends out of the shell, and the closed end of the spraying pipe is fixed to the fixing ring in the radial direction and extends into the fixing ring. The spraying pipes in every two adjacent cooling units are sequentially arranged in a staggered mode in the radial direction. A plurality of first spraying holes are formed in the side wall of each spraying pipe, and the first spraying holes in all the spraying pipes in each cooling unit face the same direction; and the first spraying holes in the first cooling unit close to the combustion chamber face the combustion chamber.

Description

Technical Field

[0001] The invention relates to a liquid rocket engine environment simulation test device, in particular to a high-temperature combustion gas active cooling device for an attitude control engine high-altitude simulation test. Background Art

[0002] The attitude control engine high-altitude simulation test is to build an environment with high-altitude conditions, make the engine work in this environment, and conduct various tests on its performance, reliability and service life, so as to determine the thrust, specific impulse and aftereffect impulse of the engine when working at high altitude, thereby verifying the feasibility of the rocket engine design, the reliability of the process and the methods of assessment, inspection and debugging, and making a comprehensive evaluation of the quality and performance of the engine.

[0003] In the existing attitude control engine ground high-altitude simulated ignition test equipment, the temperature of the high-temperature combustion gas generated in the combustion chamber can usually reach above 3400K, which is quite different from the temperature requirement of less than 300℃ at the inlet of the ejection system, so the ejection performance cannot be guaranteed, which in turn affects the ejection suction performance and high-altitude simulation capability, and ultimately leads to the inability to achieve the attitude control engine ground ignition test requirements. At the same time, the temperature of the high-temperature combustion gas exceeds the heat resistance limit of the ground equipment material, which will also cause serious ablation to the ground equipment, and even failure and damage. In addition, the high-temperature combustion gas speed of the attitude control engine reaches 6-7Ma, and the mass of the combustion gas is large, which is easy to cause instantaneous scouring and impact on the inside of the high-altitude simulated ground equipment, further causing equipment failure and fatigue damage.

[0004] To this end, the prior art uses a cooler set at the outlet of the combustion chamber to cool the high-temperature gas. The cooler is equipped with a water-cooled cooling device, which can achieve a certain degree of cooling effect. However, the water-cooling area of ​​the existing cooling device is small, and it is directly facing the flow direction of the high-temperature gas. The high-speed high-temperature gas is very likely to cause high-temperature impact on it, stagnate on its surface and form an instantaneous high-temperature area, causing the cooling device to be ablated or damaged, thereby reducing the cooling effect or even failing the cooling ability, and ultimately failing to ensure the smooth implementation of the attitude control engine high-altitude simulation test. Summary of the invention

[0005] In order to solve the technical problem that the existing cooling device is easily impacted by high-temperature combustion gas, resulting in reduced cooling effect or even failure of cooling capacity, the present invention provides a high-temperature combustion gas active cooling device for attitude control engine high-altitude simulation test.

[0006] To achieve the above objectives, the technical solutions provided by the present invention are:

[0007] A high-temperature combustion gas active cooling device for an attitude control engine high-altitude simulation test, which is special in that it comprises a shell and a plurality of cooling units arranged in the shell;

[0008] The shell is a cylindrical structure, one end of which is used to connect to the outlet end of the combustion chamber, and the other end is used to connect to the inlet end of the injection system;

[0009] A plurality of cooling units are arranged along the axial direction of the shell, and each cooling unit is arranged along the radial direction of the shell; each cooling unit comprises a fixing ring and a plurality of spray pipes uniformly distributed around the fixing ring; the fixing ring is coaxial with the central axis of the shell; the spray pipe is a hollow structure with one end open and the other end closed, and the open end is fixed to the shell and extends out of the shell for connecting to an external cooling water source; the closed end of the spray pipe is fixed to the fixing ring along the radial direction and extends into the fixing ring; the spray pipes in two adjacent cooling units are sequentially staggered in the radial direction in space;

[0010] A plurality of first spray holes are respectively provided on the side wall of each spray pipe, and the first spray holes on all the spray pipes in each cooling unit are facing the same direction; among them, in the first cooling unit close to the combustion chamber, the first spray holes on all the spray pipes are arranged toward the combustion chamber.

[0011] Furthermore, the first spray hole is a circular hole structure, and the central axes of two adjacent first spray holes on each spray pipe form an angle of 90°.

[0012] Furthermore, the distance between two adjacent first spray holes on the spray pipe increases from inside to outside.

[0013] Furthermore, each of the spray pipes in the first cooling unit close to the combustion chamber is provided with two groups of flow-guiding counter-punching holes, the two groups of flow-guiding counter-punching holes are respectively located on both sides of the connection between the spray pipe and the fixing ring, and are symmetrically arranged; the two groups of flow-guiding counter-punching holes are both located on the side of the spray pipe where the first spray hole is provided;

[0014] Each group of diversion counter-punching holes includes a plurality of counter-punching holes arranged in an array on the surface of the spray pipe, and the angle between each counter-punching hole and the central axis of the spray pipe decreases successively as the distance between the counter-punching hole and the fixing ring increases.

[0015] Furthermore, the fixed ring is a hollow cooling ring, and the cooling ring is respectively connected to a water inlet pipe and a water outlet pipe, one end of the water inlet pipe and the water outlet pipe are respectively connected to the cooling ring, and the other end is respectively connected to the shell and extends out of the shell to connect to an external cooling water source.

[0016] Furthermore, a plurality of second spray holes are axially arranged at the closed end of the spray pipe.

[0017] Furthermore, the diameters of the first spray hole and the second spray hole are 0.8-1.2 mm.

[0018] Furthermore, there is one fixing ring in each of the cooling units, and all the spray pipes are welded to the side of the corresponding fixing ring away from the combustion chamber; or, there are two fixing rings in each of the cooling units, the two fixing rings are placed side by side, and all the spray pipes are welded between the sides of the corresponding two fixing rings close to each other.

[0019] Furthermore, the length of the spray pipe extending into the corresponding fixing ring is 10mm-100mm; the spray pipe is a stainless steel pipe that has been subjected to fire-resistant treatment or coating treatment.

[0020] Furthermore, in the remaining cooling units, the first spray holes on all the spray pipes are arranged toward the inlet end of the injection system.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The present invention comprises a shell and a plurality of parallel cooling units arranged in the shell, each cooling unit comprises a fixed ring and a plurality of spray pipes uniformly distributed around the fixed ring, each spray pipe is provided with a plurality of first spray holes facing the same side, cooling water is introduced from one end of the spray pipe, and then sprayed out through each first spray hole, and the spray pipes in two adjacent cooling units are staggered in radial order, thereby achieving uniform cooling of high-temperature combustion gas; at the same time, in the first cooling unit close to the combustion chamber, the first spray holes on all the spray pipes are arranged toward the combustion chamber, thereby avoiding high-temperature scouring of the cooling unit by the high-temperature combustion gas, which not only ensures the cooling effect, but also achieves the protection of the cooling unit itself.

[0023] 2. The central axes of two adjacent first spray holes on each spray pipe of the present invention form an angle of 90°, thereby realizing a counter-attack mode and ensuring the effect of atomization and cooling.

[0024] 3. The distance between two adjacent first spray holes on the spray pipe of the present invention increases from the inside to the outside (ie, from the center of the shell to the inner wall of the shell), thereby matching the flow distribution of the high-temperature gas and improving the uniformity of cooling.

[0025] 4. The present invention provides two groups of flow-guiding counter-punching holes on each spray pipe in the first cooling unit close to the combustion chamber, thereby protecting the fixed ring and reducing the rapid scouring of the fixed ring by the high-temperature gas.

[0026] 5. The present invention designs the fixing ring as a hollow cooling ring, and passes cooling water into the ring to achieve self-cooling during the temperature reduction process. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the structure in which two cooling units are arranged in parallel in an embodiment of the present invention.

[0028] Figure 2 Schematic diagram of the structure of a cooling unit in an embodiment of the present invention.

[0029] Figure 3 It is a structural schematic diagram of a cooling unit on the side where the first spray hole is not provided in an embodiment of the present invention.

[0030] Figure 4 Schematic diagram of the structure of the spray pipe in the embodiment of the present invention.

[0031] Figure 5 Schematic diagram of the connection structure between the spray pipe and the fixing ring in the cooling unit close to the combustion chamber in an embodiment of the present invention.

[0032] Figure 6 Schematic diagram of the structure of two groups of diversion punching holes in an embodiment of the present invention.

[0033] Figure 7 Schematic diagram of the structure of the second spray hole in an embodiment of the present invention.

[0034] The reference numerals are as follows:

[0035] 1-fixing ring, 2-spray pipe, 3-first spray hole, 4-counter-punch hole, 5-water inlet pipe, 6-water outlet pipe, 7-second spray hole. DETAILED DESCRIPTION

[0036] In order to make the purpose, advantages and features of the present invention clearer, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0037] The present embodiment provides a high-temperature combustion gas active cooling device for an attitude control engine high-altitude simulation test, comprising a shell (not shown in the figure) and a plurality of cooling units arranged in the shell.

[0038] The shell is a cylindrical structure, one end of which is used to connect to the outlet of the combustion chamber, and the other end is used to connect to the inlet of the injection system. Multiple cooling units are arranged in sequence along the axial direction of the shell, and each cooling unit is arranged along the radial direction of the shell, such as Figure 1 As shown. This embodiment adopts a multi-section cooling method, i.e., a multi-row cooling method, for cooling and flushing high-temperature and high-speed combustion gases in high-altitude simulation tests of attitude control engines. The specific number of rows is determined according to the amount of combustion gases and the cooling temperature requirements. The high-temperature combustion gases formed by the combustion chamber enter the housing of the present invention, and then enter the ejection system after being cooled by each cooling unit in turn, thereby meeting the temperature requirements of the ejection system inlet.

[0039] like Figure 2 and Figure 3As shown, to ensure uniformity, each cooling unit includes a fixed ring 1 and a plurality of spray pipes 2 evenly distributed around the fixed ring 1, wherein the fixed ring 1 is coaxial with the central axis of the shell. The spray pipe 2 is a hollow structure with one end open and the other end closed. Its open end is fixed to the shell and extends out of the shell to connect to an external cooling water source; the closed end of the spray pipe 2 is radially fixed to the fixed ring 1 and extends into the fixed ring 1, and the length of the spray pipe 2 extending into the fixed ring 1 varies from 10mm to 100mm. The spray pipes 2 in two adjacent cooling units are radially staggered in space to achieve consistency in high-temperature gas cooling.

[0040] The spray pipe 2 is made of a stainless steel pipe that has been refractory treated or coated to ensure its working reliability. The length and inner and outer diameters of all spray pipes 2 are consistent, and cooling water with a certain pressure and flow rate can be introduced into the interior.

[0041] This embodiment adopts the form of water spray cooling. A plurality of first spray holes 3 are respectively opened on the side wall of each spray pipe 2, and the first spray holes 3 on all the spray pipes 2 in each cooling unit are facing the same direction. The cooling water is discharged quickly on one side through the first spray holes 3, thereby achieving the effect of slowing down the temperature of the high-temperature fuel gas.

[0042] After the high-temperature gas is ejected from the combustion chamber, it reaches the first cooling unit, where it is fully mixed with the cooling water ejected from the spray pipe 2. The momentum exchange and heat exchange between the droplets and the continuous phase reduce the speed and temperature of the high-temperature gas. The subsequent multi-section water spraying further reduces the speed and temperature of the high-temperature gas, thereby achieving a cooling effect.

[0043] In order to prevent the cooling device from being impacted and ablated by high-temperature gas, in this embodiment, the first spray holes 3 on all the spray pipes 2 in the first cooling unit close to the combustion chamber are all set toward the combustion chamber to realize the windward water spraying mode, that is, the spraying direction is opposite to the impact direction of the high-temperature gas, while ensuring the water spraying, the scouring force of the high-temperature gas on it is reduced, thereby ensuring the stability of the device's own structure and avoiding ablation damage. The other cooling units are in the downwind direction, that is, the same as the gas impact direction, or partly spray water downwind and partly against the wind, thereby ensuring that the cooling effect is improved while spraying water.

[0044] like Figure 4As shown, the first spray hole 3 is a circular hole structure, and its aperture is generally 0.8-1.2 mm, so as to ensure the atomization effect. This embodiment adopts a two-by-two hedge mode, and the angle between the central axes of two adjacent first spray holes 3 on each spray pipe 2 is designed to be 90°, that is, each first spray hole 3 is obliquely arranged, and the angle between its central axis and the central axis of the spray pipe 2 where it is located is 45°. The inclination directions of the two adjacent first spray holes 3 are opposite, so that the angle between the central axes of the two is 90°. The equivalent area and isentropic principle are used to perform hedge atomization impact and heat exchange analysis to achieve the atomization cooling effect.

[0045] Since the temperature of the central area of ​​the high-temperature gas is relatively high, the first spray holes 3 on the spray pipe 2 are arranged in a descending manner from the center of the shell to the side wall of the shell. The descending manner can be achieved through spacing, number, number of holes, aperture, etc., to achieve gradient water spray cooling. For example, the spacing between the first spray holes 3 in the central area of ​​the shell is smaller, and the spacing between the first spray holes 3 in the side wall area of ​​the shell is larger; or, the number of the first spray holes 3 in the central area of ​​the shell may be larger or more densely distributed, and the number of the first spray holes 3 in the side wall area of ​​the shell may be smaller or more sparsely distributed. This embodiment realizes zoned spraying by increasing the spacing between two adjacent first spray holes 3 on the spray pipe 2 from the inside to the outside.

[0046] There can be one fixed ring 1 in each cooling unit, and all the spray pipes 2 are welded to the side of the corresponding fixed ring 1 away from the combustion chamber. Alternatively, there can be two fixed rings 1 in each cooling unit, and the two fixed rings 1 are placed side by side, and all the spray pipes 2 are welded between the sides of the two corresponding fixed rings 1 close to each other, thereby improving the fixing effect, enhancing the integrity of the high-temperature gas active cooling device, and effectively reducing the scouring and impact of the high-temperature gas.

[0047] like Figure 2 As shown, the fixed ring 1 is a hollow cooling ring, and a water inlet pipe 5 and a water outlet pipe 6 are respectively connected to the cooling ring. One end of the water inlet pipe 5 and the water outlet pipe 6 are respectively connected to the cooling ring, and the other end is respectively connected to the shell, and extends out of the shell to connect to an external cooling water source, thereby enhancing the temperature reduction protection of the cooling ring itself.

[0048] Combination Figure 4 , Figure 5 , Figure 6 As shown, in order to further protect the fixed ring 1, in this embodiment, two groups of flow-guiding counter-punching holes are respectively arranged on each spray pipe 2 in the cooling unit closest to the combustion chamber. The two groups of flow-guiding counter-punching holes are symmetrically arranged on both sides of the connection between the spray pipe 2 and the fixed ring 1, and are located on the same side as the first spray hole 3 on the corresponding spray pipe 2, that is, the two groups of flow-guiding counter-punching holes are also arranged toward the incoming flow direction of the high-temperature fuel gas.

[0049] Each group of diversion counter-punching holes includes a plurality of counter-punching holes 4 arranged in a matrix on the surface of the spray pipe 2, that is, the plurality of counter-punching holes 4 are arranged in a plurality of rows and columns, and the angle of each row is opposite to the flow direction of the high-temperature gas, and the angle between each counter-punching hole 4 and the central axis of the spray pipe 2 decreases with the increase of the distance between the location of the counter-punching hole 4 and the fixing ring 1. Figure 4 As shown, when there are three rows of punching holes 4, the angle between the central axis of the row of punching holes 4 closest to the fixing ring 1 and the central axis of the spray pipe 2 can be designed to be 60°, and the angle between the central axis of the second row of punching holes 4 adjacent to it and the central axis of the spray pipe 2 can be designed to be 45°, and the third row can be designed to be 30°, and so on.

[0050] Since the first fixed ring 1 near the combustion chamber is the first windward surface in contact with the high-temperature gas, the high-temperature gas will form a rapid high-temperature scouring guide on both sides of the fixed ring 1. Therefore, in this embodiment, the guide counter-punching holes are symmetrically set on both sides of the fixed ring 1. The high-temperature and high-speed gas is sucked into the cooling water of the cooling system to mix, which will gradually reduce the total temperature. The momentum exchange and heat exchange between the droplets and the continuous phase further reduce the temperature of the gas velocity on both sides of the cooling ring. The spray characteristics of the counter-punching holes 3 are used to reduce the rapid scouring effect of the gas on the spray pipe 2 on both sides of the fixed ring 1, and at the same time form a low-temperature area in this area, reduce high-temperature heating and protect the device body.

[0051] like Figure 7 As shown, preferably, in this embodiment, a plurality of second spray holes 7 are also axially provided at the closed end of the spray pipe 2, and the aperture of the second spray hole 7 is 0.8-1.2 mm, thereby achieving cooling of the high-temperature combustion gas flowing through the central area of ​​the fixing ring 1, and further improving the uniformity of cooling.

[0052] The present invention adopts the method of water spray cooling to realize the cooling of high-temperature gas, and realizes the self-protection of the cooling device by increasing the volume and flow resistance of the exhaust system, thereby ensuring the cooling effect and cooling capacity. In addition, based on the active cooling device, the ablation effect of high-temperature gas on ground equipment can be effectively reduced, the low temperature requirements of the ejection system can be ensured, and the heat resistance, working stability and reliability of ground equipment can be protected, thereby meeting the ejection suction performance and high-altitude simulation capability requirements, and completing the ground ignition test of the attitude control engine.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

Claims

1. A high-temperature combustion gas active cooling device for an attitude control engine high-altitude simulation test, characterized in that: It comprises a shell and a plurality of cooling units arranged in the shell; The shell is a cylindrical structure, one end of which is used to connect to the outlet end of the combustion chamber, and the other end is used to connect to the inlet end of the injection system; A plurality of cooling units are arranged along the axial direction of the shell, and each cooling unit is arranged along the radial direction of the shell; each cooling unit comprises a fixing ring (1) and a plurality of spray pipes (2) uniformly distributed around the fixing ring (1); the fixing ring (1) is coaxial with the central axis of the shell; the spray pipe (2) is a hollow structure with one end open and the other end closed, the open end of which is fixed to the shell and extends out of the shell for connecting to an external cooling water source; the closed end of the spray pipe (2) is fixed to the fixing ring (1) along the radial direction and extends into the fixing ring (1); the spray pipes (2) in two adjacent cooling units are arranged in a radially staggered manner in sequence in space; A plurality of first spray holes (3) are respectively provided on the side wall of each spray pipe (2), and the first spray holes (3) on all the spray pipes (2) in each cooling unit are oriented in the same direction; wherein, in the first cooling unit close to the combustion chamber, the first spray holes (3) on all the spray pipes (2) are oriented toward the combustion chamber.

2. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 1 is characterized by: The first spray hole (3) is a circular hole structure, and the central axes of two adjacent first spray holes (3) on each spray pipe (2) form an angle of 90°.

3. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 2 is characterized by: The distance between two adjacent first spray holes (3) on the spray pipe (2) increases from the inside to the outside.

4. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 1, 2 or 3, characterized in that: Each of the spray pipes (2) in the first cooling unit close to the combustion chamber is provided with two groups of flow-guiding counter-punching holes, the two groups of flow-guiding counter-punching holes are respectively located on both sides of the connection between the spray pipe (2) and the fixing ring (1), and are symmetrically arranged; the two groups of flow-guiding counter-punching holes are both located on the side of the spray pipe (2) where the first spray hole (3) is provided; Each group of flow-guiding counter-punching holes comprises a plurality of counter-punching holes (4) arranged in an array on the surface of the spray pipe (2), and the angle between each counter-punching hole (4) and the central axis of the spray pipe (2) decreases successively as the distance between the counter-punching hole (4) and the fixing ring (1) increases.

5. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 4 is characterized by: The fixed ring (1) is a hollow cooling ring, and is respectively connected to a water inlet pipe (5) and a water outlet pipe (6); one end of the water inlet pipe (5) and the water outlet pipe (6) are respectively connected to the cooling ring, and the other end is respectively connected to the shell and extends out of the shell to connect to an external cooling water source.

6. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 5 is characterized by: The closed end of the spray pipe (2) is provided with a plurality of second spray holes (7) along the axial direction.

7. The high temperature combustion gas active cooling device for the attitude control engine high altitude simulation test according to claim 6 is characterized by: The apertures of the first spray hole (3) and the second spray hole (7) are 0.8 to 1.2 mm.

8. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 1 is characterized by: There is one fixing ring (1) in each cooling unit, and all the spray pipes (2) are welded to the side of the corresponding fixing ring (1) away from the combustion chamber; Alternatively, there are two fixing rings (1) in each of the cooling units, the two fixing rings (1) are placed side by side, and all the spray pipes (2) are welded between the sides of the two corresponding fixing rings (1) that are close to each other.

9. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 8, characterized in that: The length of the spray pipe (2) extending into the corresponding fixing ring (1) is 10 mm to 100 mm; The spray pipe (2) is a stainless steel pipe that has been subjected to fire-resistant treatment or coating treatment.

10. The high temperature combustion gas active cooling device for attitude control engine high altitude simulation test according to claim 1, characterized in that: In the remaining cooling units, the first spray holes (3) on all the spray pipes (2) are arranged toward the inlet end of the injection system.

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