Tilted rocket engine test bench with thermal protection device and thermal protection method

Abstract

The present invention relates to a thermal protection device and a thermal protection method. In order to solve the problem that the high-temperature and high-speed combustion gas generated by the existing rocket engine during operation causes serious damage to the ground and the surrounding environment, an inclined rocket engine test bench with a thermal protection device and a thermal protection method are provided. The present invention includes a test bench for tilting the rocket engine, a radiation zone ground arranged on the side of the rocket engine away from the test bench, an impact zone ground connected to the radiation zone ground away from the test bench, a pool for collecting cooling water connected to the impact zone ground away from the test bench, and a diversion zone ground connected to the pool away from the test bench; the radiation zone ground is provided with a plurality of semi-circular columnar arc cofferdams with the convex surface of the arc facing the test bench, the impact zone ground is provided with a plurality of groups of water spraying devices, and the diversion zone ground is provided with a plurality of regular tetrahedral pyramid-shaped silencer cones. The present invention has the advantages of thermal protection, noise reduction and diversion.

Description

Technical Field

[0001] The invention relates to a thermal protection device and a thermal protection method, and in particular to a tilted rocket engine test bench with a thermal protection device and a thermal protection method. Background Art

[0002] With the rapid development of rocket engine test technology, the safety of rocket engine test benches has received more and more attention. The high-temperature and high-speed gas ejected by rocket engines during hot tests has great destructive power and produces a lot of noise. Therefore, how to guide the high-temperature and high-speed gas generated by rocket engines during hot tests, the safety of the guide structure, and the noise reduction are very important issues, which will directly affect the stability and safety of rocket engine test benches.

[0003] Existing rocket engines do not use thermal protection measures for the ground during test runs and are not equipped with noise reduction and flow diversion devices. Therefore, the high-temperature and high-speed combustion gases generated when the rocket engines are working will cause serious damage to the ground and the surrounding environment. Summary of the invention

[0004] The purpose of the present invention is to solve the problem that the existing rocket engines do not adopt thermal protection measures for the ground during testing and are not equipped with noise reduction and diversion devices, which leads to the high-temperature and high-speed combustion gas generated by the rocket engine when it is working causing serious damage to the ground and the surrounding environment, and to provide an inclined rocket engine test bench with a thermal protection device and a thermal protection method.

[0005] The design idea of ​​the present invention is: to divide the contact part of the high-temperature and high-speed combustion gas generated by the rocket engine when it is working with the ground into four parts: the radiation zone ground, the impact zone ground, the water pool and the diversion zone ground. Different thermal protection measures are established according to different heated areas, thereby reducing the impact of the high-temperature and high-speed combustion gas on the ground and the surrounding environment.

[0006] To achieve the above purpose, the technical solution provided by the present invention is:

[0007] A tilted rocket engine test bench with a thermal protection device, which is special in that:

[0008] It includes a test bench for tilting a rocket engine, a radiation zone ground arranged on a side of the rocket engine away from the test bench, an impact zone ground connected to the radiation zone ground on a side away from the test bench, a pool for collecting cooling water connected to the impact zone ground on a side away from the test bench, and a diversion zone ground connected to the pool on a side away from the test bench; a plurality of arc-shaped cofferdams are arranged on the radiation zone ground, a plurality of groups of water spraying devices are arranged on the impact zone ground, and a plurality of silencer cones are arranged on the diversion zone ground; each group of the water spraying devices includes a cast iron plate with a water spraying hole and a cooling water supply branch pipe connected to the water spraying hole; each of the cooling water supply branch pipes is connected to a cooling water supply main pipe arranged in the foundation, the cooling water supply main pipe is connected to a water source, and a valve is arranged on the cooling water supply main pipe; two adjacent cast iron plates are laid in layers in a stepped manner, and the position of the cast iron plate closer to the test bench is higher.

[0009] Furthermore, the arc-shaped cofferdams are staggered along the axial direction of the ground of the radiation zone; and the silencer cones are staggered along the axial direction of the ground of the diversion zone.

[0010] Furthermore, the shapes of the radiation zone ground, impact zone ground, pool and diversion zone ground are trapezoid, rectangle, rectangle and trapezoid respectively, which can provide the largest possible range of protection for the ground; the large end of the radiation zone ground is connected to the impact zone ground, and the small end of the diversion zone ground is connected to the pool; the arc cofferdam is semi-circular columnar and the convex direction of the arc faces the test bench; the silencer cone is a regular tetrahedron.

[0011] Furthermore, the inclination angle between the nozzle of the rocket engine and the ground is 5° to 23°, and the distance between the nozzle of the rocket engine and the ground is 0.3 to 0.7 m. The purpose of such arrangement is to facilitate cooling of the high-temperature combustion gas generated when the rocket engine is working.

[0012] Furthermore, the cooling water flow rate of each cooling water supply branch pipe is 300 kg / s, which can meet the cooling demand for high-temperature combustion gas. The angle between the plane where the ground of the diversion area is located and the plane where the ground of the impact area is located is 135°, which has a good noise reduction effect on the airflow generated when the rocket engine is working.

[0013] Furthermore, each of the arc-shaped cofferdams and the muffler cone is made of refractory concrete, which has the advantages of high temperature resistance and high strength. The water pool is a dustpan pool.

[0014] Furthermore, the valve comprises a main valve and a bypass valve connected in parallel with the main valve, and both the main valve and the bypass valve are pneumatic remote-controlled ball valves, which can remotely control the cooling water flow with high precision.

[0015] Furthermore, each cast iron plate has a thickness of 30 mm, a length of 700 mm, a width of 500 mm, and an overlap width of 200 mm between two adjacent cast iron plates; each water spray hole has a diameter of 5 mm, and the angle between the direction of each water spray hole and the ground is 45°, and the specification of each cooling water supply branch pipe is DN300PN1.6MPa. The purpose of such a setting is to improve the cooling efficiency of cooling water.

[0016] Furthermore, the thickness of each arc cofferdam is 70mm, and the radius of curvature of the concave side is 150mm; the height of the arc cofferdam located on the outermost side of the radiation zone ground is 350mm, and the height of the remaining arc cofferdams is 320mm; along the symmetry axis of the radiation zone ground, the distance between two adjacent arc cofferdams is 150mm; perpendicular to the symmetry axis of the radiation zone ground, the distance between two adjacent arc cofferdams is 100mm. The height of each silencer cone is 1500mm, the size of the lower bottom surface is 500mm×500mm, the size of the upper bottom surface is 100mm×100mm, and the angle between the busbar and the lower bottom surface is 60°; along the axial direction of the diversion zone ground or perpendicular to the axial direction, the distance between two adjacent silencer cones is 300mm.

[0017] At the same time, the present invention also provides a thermal protection method for the above-mentioned inclined rocket engine test bench with a thermal protection device, which is special in that it includes the following steps:

[0018] Step 1, assembling a tilted rocket engine test bench with a thermal protection device;

[0019] Step 2, open and adjust the valve so that the cooling water forms a stable flowing water film on the ground of the radiation area;

[0020] Step 3, ignite the rocket engine and start the test run;

[0021] Step 4: The high-temperature and high-speed combustion gas ejected from the rocket engine first exchanges heat with the water film on the ground of the radiation zone, and then passes through the silencer cone on the ground of the diversion zone for diversion to form harmless combustion gas;

[0022] Step 5: After the test run, turn off the rocket engine first, and then close the valve after the high-temperature gas generated by the rocket engine has completed the heat exchange with the water film;

[0023] Step 6: Clean the remaining cooling water in the pool and finish using it.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The inclined rocket engine test bench with a thermal protection device provided by the present invention has multiple groups of water spraying devices facing the rocket engine on the ground of the impact zone, which can spray cooling water on the ground of the radiation zone; multiple arc cofferdams with convex surfaces facing the test bench are arranged on the ground of the radiation zone, which have the function of reducing the flow rate of cooling water and preventing the accumulation of cooling water, and can ensure that the cooling water on the ground of the radiation zone forms a stable flowing water film, and ensure that the high-temperature combustion gas generated when the rocket engine is working exchanges heat with the water film, so that the ground is not damaged by thermal radiation; multiple cast iron plates are laid on the ground of the impact zone to reduce the scouring of the ground by the high-temperature combustion gas generated when the rocket engine is working; a water pool is provided to facilitate the collection of residual cooling water; multiple staggered silencer cones are arranged on the ground of the diversion zone, which can quickly guide the high-speed combustion gas to an area away from the test bench, prevent the flame, smoke and debris from reflecting back to impact the test bench, and at the same time, the airflow generated when the rocket engine is working can form a turbulent flow at the silencer cone, reducing the speed and noise of the high-speed combustion gas;

[0026] 2. The inclined rocket engine test bench with a thermal protection device provided by the present invention has an inclination angle of 5° to 23° between the nozzle of the rocket engine and the ground, and a distance between the nozzle of the rocket engine and the ground of 0.3 to 0.7 m, which is convenient for cooling the high-temperature combustion gas generated when the rocket engine is working;

[0027] 3. The inclined rocket engine test bench with a thermal protection device provided by the present invention has the shapes of the radiation area ground, impact area ground, pool and diversion area ground in trapezoidal, rectangular, rectangular and trapezoidal shapes respectively, which can provide the largest possible range of protection for the ground; the angle between the diversion area ground and the impact area ground is 135°, which has a good noise reduction effect on the airflow generated when the rocket engine is working;

[0028] 4. The thermal protection method of the tilted rocket engine test bench with a thermal protection device provided by the present invention has the advantages of simple principle and easy operation;

[0029] 5. The inclined rocket engine test bench with a thermal protection device provided by the present invention has the advantages of good process reliability, low construction cost, strong adaptability, and convenience for conducting various large-scale engine tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic structural diagram of an embodiment of a tilted rocket engine test bench with a thermal protection device according to the present invention;

[0031] Figure 2 for Figure 1 A top view of

[0032] Figure 3Schematic diagram of the structure of the cast iron plate and cooling water supply pipeline in the embodiment of the tilted rocket engine test bench with thermal protection device of the present invention; (a) is a top view, and (b) is a front view;

[0033] Figure 4 Schematic diagram of the structure of the arc cofferdam in the embodiment of the tilted rocket engine test bench with a thermal protection device of the present invention; (a) is a top view, and (b) is a front view;

[0034] Figure 5 It is a layout diagram of the arc-shaped cofferdam in the embodiment of the tilted rocket engine test bench with a thermal protection device of the present invention;

[0035] Figure 6 Schematic diagram of the structure of the silencer cone in the embodiment of the tilted rocket engine test bench with a thermal protection device of the present invention; (a) is a top view, and (b) is a front view;

[0036] Figure 7 It is a layout diagram of the silencer cone in the embodiment of the tilted rocket engine test bench with a thermal protection device of the present invention;

[0037] Explanation of the reference numerals: 1-test bench; 2-rocket engine; 3-ground of the radiation zone, 301-arc cofferdam; 4-ground of the impact zone, 401-water spraying device, 4011-cast iron plate, 40111-water spraying hole, 4012-cooling water supply branch pipe, 4013-cooling water supply main pipe, 40131-main valve, 40132-bypass valve; 5-water tank; 6-ground of the diversion zone, 601-silencer cone. DETAILED DESCRIPTION

[0038] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0039] A tilted rocket engine test stand with thermal protection, see Figures 1 to 7, comprising a test bench 1 for tilting a rocket engine 2, a radiation zone ground 3 arranged on the side of the rocket engine 2 away from the test bench 1, an impact zone ground 4 connected to the radiation zone ground 3 away from the test bench 1, a pool 5 connected to the impact zone ground away from the test bench 1 for collecting cooling water, and a diversion zone ground 6 connected to the pool 5 away from the test bench 1; the radiation zone ground 3 is provided with a plurality of semi-circular columnar arc cofferdams 301 with the convex surface of the arc facing the test bench 1, the impact zone ground 4 is provided with a plurality of groups of water spray devices 401, and the diversion zone ground 6 is provided with a plurality of muffler cones 601 in the shape of regular quadrangular pyramids; each group of the water spray devices 401 includes a water spray hole 401 11 and a cooling water supply branch pipe 4012 connected to the water spray hole 40111; each of the cooling water supply branch pipes 4012 is connected to a cooling water supply main pipe 4013 arranged in the foundation, the cooling water supply main pipe 4013 is connected to a water source, and a main valve 40131 and a bypass valve 40132 connected in parallel with the main valve 40131 are arranged on the cooling water supply main pipe 4013; the arc cofferdams 301 are staggered along the axial direction of the radiation zone ground 3; the silencer cones 601 are staggered along the axial direction of the diversion zone ground 6; two adjacent cast iron plates 4011 are laid in layers in a stepped manner, and the closer the cast iron plate 4011 is to the test bench 1, the higher the position of the cast iron plate 4011 is.

[0040] The inclination angle between the rocket engine 2 and the ground is 10°, and the distance between the nozzle of the rocket engine 2 and the ground is 0.3-0.7m. The purpose of such arrangement is to facilitate cooling of the high-temperature combustion gas generated when the rocket engine 2 is working. Depending on different engines, the inclination angle can be adjusted between 5° and 23°.

[0041] The shapes of the radiation zone ground 3, the impact zone ground 4, the pool 5 and the diversion zone ground 6 are trapezoid, rectangle, rectangle and trapezoid respectively, which can provide the largest possible range of protection for the ground; the large end of the radiation zone ground 3 is connected to the impact zone ground 4, and the small end of the diversion zone ground 6 is connected to the pool 5.

[0042] Each of the arc-shaped cofferdams 301 and the muffler cone 601 is made of refractory concrete, which has the advantages of high temperature resistance and high strength. The water pool 5 is a dustpan pool.

[0043] The cooling water flow rate of each cooling water supply branch pipe 4012 is 300 kg / s, which can meet the cooling demand of high-temperature combustion gas. The angle between the plane where the ground 6 of the guide area is located and the plane where the ground 4 of the impact area is located is 135°, which has a good noise reduction effect on the airflow generated by the rocket engine 2 when it is working.

[0044] The valve includes a main valve 40131 and a bypass valve 40132 connected in parallel with the main valve 40131. The main valve 40131 and the bypass valve 40132 are both pneumatic remote-controlled ball valves, which can remotely control the cooling water flow with high precision.

[0045] Each cast iron plate 4011 has a thickness of 30 mm, a length of 700 mm, a width of 500 mm, and an overlap width of 200 mm between two adjacent cast iron plates 4011; each water spray hole 40111 has a diameter of 5 mm, and the angle between the direction of each water spray hole 40111 and the ground is 45°, and the specification of each cooling water supply branch pipe 4012 is DN300PN1.6MPa. The purpose of such a setting is to improve the cooling efficiency of cooling water.

[0046] The thickness of each of the arc cofferdams 301 is 70 mm, and the radius of curvature of the concave side is 150 mm; the height of the arc cofferdam 301 located at the outermost side of the radiation zone ground 3 is 350 mm, and the heights of the remaining arc cofferdams 301 are 320 mm; along the symmetry axis of the radiation zone ground 3, the distance between two adjacent arc cofferdams 301 is 150 mm; perpendicular to the symmetry axis of the radiation zone ground 3, the distance between two adjacent arc cofferdams 301 is 100 mm.

[0047] The height of each silencer cone 601 is 1500mm, the size of the lower bottom surface is 500mm×500mm, the size of the upper bottom surface is 100mm×100mm, and the angle between the busbar and the lower bottom surface is 60°; along the axial direction of the ground 6 of the guide area or in a direction perpendicular to the axial direction, the distance between two adjacent silencer cones 601 is 300mm.

[0048] At the same time, the embodiment of the present invention also provides a thermal protection method for the above-mentioned tilted rocket engine test bench with a thermal protection device, comprising the following steps:

[0049] Step 1, assembling a tilted rocket engine test bench with a thermal protection device;

[0050] Step 2, open and adjust the main valve 40131 and the bypass valve 40132 to ensure that the cooling water flow rate of each cooling water supply branch pipe 4012 is 300 kg / s, so that the cooling water forms a stable flowing water film on the ground 3 of the radiation area, the flow rate of the water film is 500 kg / s, and the water pressure is 0.85 MPa;

[0051] Step 3, ignite the rocket engine 2 and start the test run;

[0052] Step 4, the high-temperature and high-speed combustion gas ejected from the rocket engine 2 first exchanges heat with the water film on the ground 3 of the radiation zone, and then passes through the silencer cone 601 on the ground 6 of the diversion zone for diversion to form harmless combustion gas;

[0053] Step 5, after the test run is completed, the rocket engine 2 is turned off first, and after the high-temperature combustion gas generated by the rocket engine 2 is completely heat-exchanged with the water film, the main valve 40131 and the bypass valve 40132 are closed;

[0054] Step 6, clean the remaining cooling water in the pool 5 and finish using it.

[0055] The inclined rocket engine test bench with a thermal protection device provided by the embodiment of the present invention has multiple groups of water spraying devices 401 facing the rocket engine 2 on the impact zone ground 4, which can spray cooling water on the radiation zone ground 3; multiple staggered arc cofferdams 301 with convex surfaces facing the test bench 1 are arranged on the radiation zone ground 3, which have the function of reducing the cooling water flow rate and preventing the cooling water from accumulating, and can ensure that the cooling water on the radiation zone ground 3 forms a stable flowing water film, ensuring that the high-temperature combustion gas generated by the rocket engine 2 when working exchanges heat with the water film, so that the ground is not damaged by thermal radiation; the impact zone ground 4 is paved with A plurality of cast iron plates 4011 are used to reduce the scouring of the ground by the high-temperature combustion gas generated when the rocket engine 2 is working; a water pool 5 is provided to collect residual cooling water; a plurality of staggered silencer cones 601 are provided on the ground 6 of the guide area to quickly guide the high-speed combustion gas to an area away from the test bench 1, to prevent the flame, smoke and debris from reflecting back and impacting the test bench 1, and at the same time to make the airflow generated by the rocket engine 2 when it is working to form a turbulent flow at the silencer cone 601, to reduce the speed and noise of the high-speed combustion gas; the device also has the advantages of good process reliability, low construction cost, strong adaptability, and is convenient for conducting various large-scale engine tests.

Claims

1. A tilted rocket engine test bench with a thermal protection device, characterized in that: The invention comprises a test bench (1) for tilting a rocket engine (2), a radiation zone floor (3) arranged on a side of the rocket engine (2) away from the test bench (1), an impact zone floor (4) connected to a side of the radiation zone floor (3) away from the test bench (1), a water pool (5) connected to a side of the impact zone floor away from the test bench (1) for collecting cooling water, and a diversion zone floor (6) connected to a side of the water pool (5) away from the test bench (1); A plurality of arc-shaped cofferdams (301) are arranged on the ground (3) of the radiation zone, a plurality of groups of water spray devices (401) are arranged on the ground (4) of the impact zone, and a plurality of silencer cones (601) are arranged on the ground (6) of the diversion zone; Each group of the water spray devices (401) comprises a cast iron plate (4011) with a water spray hole (40111) and a cooling water supply branch pipe (4012) connected to the water spray hole (40111); each cooling water supply branch pipe (4012) is connected to a cooling water supply main pipe (4013) arranged in the foundation, the cooling water supply main pipe (4013) is connected to a water source, and a valve is arranged on the cooling water supply main pipe (4013); Two adjacent cast iron plates (4011) are laid in layers in a stepped manner, and the closer the cast iron plate (4011) is to the test bench (1), the higher its position is.

2. The tilted rocket engine test bench with a thermal protection device according to claim 1, characterized in that: The arc-shaped cofferdams (301) are arranged in a staggered manner along the axial direction of the ground surface (3) of the radiation zone; and the silencer cones (601) are arranged in a staggered manner along the axial direction of the ground surface (6) of the diversion zone.

3. The tilted rocket engine test bench with a thermal protection device according to claim 1 or 2, characterized in that: The shapes of the radiation zone ground (3), the impact zone ground (4), the pool (5) and the diversion zone ground (6) are respectively trapezoidal, rectangular, rectangular and trapezoidal; the large end of the radiation zone ground (3) is connected to the impact zone ground (4), and the small end of the diversion zone ground (6) is connected to the pool (5); the arc-shaped cofferdam (301) is semi-circular columnar and the convex surface of the arc faces the test bench (1); the silencer cone (601) is a regular quadrangular pyramid.

4. The inclined rocket engine test bench with a thermal protection device according to claim 3 is characterized in that: The inclination angle between the nozzle of the rocket engine (2) and the ground is 5° to 23°, and the distance between the nozzle of the rocket engine (2) and the ground is 0.3 to 0.7 m.

5. The tilted rocket engine test bench with a thermal protection device according to claim 4, characterized in that: The cooling water flow rate flowing into each cooling water supply branch pipe (4012) is 300 kg / s; the angle formed by the plane where the ground (6) of the diversion area is located and the plane where the ground (4) of the impact area is located is 135°.

6. The tilted rocket engine test bench with a thermal protection device according to claim 5, characterized in that: The material of each of the arc-shaped cofferdams (301) and the silencer cone (601) is refractory concrete; and the water pool (5) is a dustpan pool.

7. The tilted rocket engine test bench with a thermal protection device according to claim 1, characterized in that: Features: The valve comprises a main valve (40131) and a bypass valve (40132) connected in parallel with the main valve (40131), and both the main valve (40131) and the bypass valve (40132) are pneumatic remote-controlled ball valves.

8. The tilted rocket engine test bench with a thermal protection device according to claim 1, characterized in that: The thickness of each cast iron plate (4011) is 30 mm, the length is 700 mm, the width is 500 mm, and the width of the overlapping area of ​​two adjacent cast iron plates (4011) is 200 mm; the diameter of each water spray hole (40111) is 5 mm, all face the rocket engine (2) and form an angle of 45° with the ground, and the specifications of each cooling water supply branch pipe (4012) are DN300PN1.6MPa.

9. The tilted rocket engine test bench with a thermal protection device according to claim 6, characterized in that: The thickness of each arc-shaped cofferdam (301) is 70 mm, and the radius of curvature of the concave side is 150 mm; the height of the arc-shaped cofferdam (301) located at the outermost side of the radiation zone ground (3) is 350 mm, and the heights of the remaining arc-shaped cofferdams (301) are 320 mm; along the symmetry axis direction of the radiation zone ground (3), the distance between two adjacent arc-shaped cofferdams (301) is 150 mm; perpendicular to the symmetry axis direction of the radiation zone ground (3), the distance between two adjacent arc-shaped cofferdams (301) is 100 mm; The height of each silencer cone (601) is 1500 mm, the size of the lower bottom surface is 500 mm×500 mm, the size of the upper bottom surface is 100 mm×100 mm, and the angle between the busbar and the lower bottom surface is 60°; along the axial direction of the ground surface (6) of the guide area or in a direction perpendicular to the axial direction, the distance between two adjacent silencer cones (601) is 300 mm.

10. A thermal protection method for a tilted rocket engine test bench with a thermal protection device as claimed in any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1, assembling a tilted rocket engine test bench with a thermal protection device; Step 2, opening and adjusting the valve so that the cooling water forms a stable flowing water film on the ground (3) of the radiation zone; Step 3, igniting the rocket engine (2) and starting a test run; Step 4, the high-temperature and high-speed combustion gas ejected from the rocket engine (2) first exchanges heat with the water film on the ground (3) of the radiation zone, and then passes through the silencer cone (601) on the ground (6) of the diversion zone to be diverted to form harmless combustion gas; Step 5, after the test run is completed, the rocket engine (2) is turned off first, and the valve is closed after the high-temperature combustion gas generated by the rocket engine (2) has completed the heat exchange with the water film; Step 6, clean the remaining cooling water in the pool (5) and complete the use.

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