High-efficiency rocket engine outer surface temperature recovery system and method

Abstract

The application discloses a high-efficiency rocket engine outer surface temperature recovery system and method, and aims at solving the problems of long assembly preparation time, low work efficiency and long temperature recovery time of the existing assembled closed structure. The system comprises an upper flexible curtain, a lower flexible curtain and a heating mechanism. The upper end of the upper flexible curtain is hung on the nitrogen fire-fighting ring, and the lower end is in contact with the standing platform. The upper flexible curtain is arranged around the periphery of the rocket engine for one round to form an upper temperature recovery space. The upper end of the lower flexible curtain is hung below the standing platform, and the lower end is in contact with the ground. The lower flexible curtain is arranged around the periphery of the rocket engine for one round to form a lower temperature recovery space. The heating end of the heating mechanism is connected with the standing platform and located in the upper temperature recovery space or the lower temperature recovery space to provide hot air. The application not only improves the arrangement efficiency of the upper temperature recovery space and the lower temperature recovery space, but also improves the temperature recovery efficiency by heating the key parts of the rocket engine.

Description

Technical Field

[0001] The present invention relates to a temperature recovery system, and in particular to a high-efficiency rocket engine outer surface temperature recovery system and method. Background Art

[0002] In cryogenic rocket engine tests, the engine's cryogenic pipes and pumps need to be quickly and efficiently warmed up after the engine test to ensure that the engine can quickly enter the next work process. During the warming process, if the temperature is too high, it will cause damage to the non-metallic parts on the engine. If the temperature is too low, the rapid warming cannot be completed.

[0003] Existing regeneration systems typically use enclosed regeneration spaces, such as those in conventional factory buildings or on-site enclosures. These methods offer good regeneration results, but in engine testing, due to the complex on-site environment and the high temperatures, high heat flux, high vibration, and strong airflow intrusion experienced during engine operation, it is difficult to establish a fixed regeneration space. Typically, these systems are assembled, enclosed structures, which require a long preparation time, resulting in low regeneration efficiency and prolonged regeneration times. Summary of the Invention

[0004] The purpose of the present invention is to provide a high-efficiency rocket engine outer surface temperature recovery system and method to solve the technical problems of the existing assembled closed structure with long assembly preparation time, resulting in low work efficiency and long temperature recovery time.

[0005] To achieve the above-mentioned object, the present invention provides a high-efficiency rocket engine outer surface reheating system, wherein a nitrogen fire protection ring and a standing platform are provided around the rocket engine; the nitrogen fire protection ring is located above the standing platform; and the special feature of the system is that it includes an upper flexible curtain, a lower flexible curtain, and a heating mechanism;

[0006] The upper end of the upper flexible curtain is suspended on the nitrogen fire ring, and the lower end is in contact with the standing platform; and the upper flexible curtain is arranged around the periphery of the rocket engine to form an upper temperature recovery space;

[0007] The upper end of the lower flexible curtain is suspended below the standing platform, and the lower end is in contact with the ground; and the lower flexible curtain is arranged around the periphery of the rocket engine to form a lower temperature recovery space;

[0008] The heating end of the heating mechanism is connected to the standing platform and is located in the upper temperature return space or the lower temperature return space, and is used for providing hot air to the upper temperature return space and the lower temperature return space.

[0009] Furthermore, the heating mechanism includes a hot air distribution pipe and an air heater, and the hot air distribution pipe constitutes the heating end;

[0010] The hot gas distribution pipe is installed on the standing platform and is located in the upper temperature recovery space or the lower temperature recovery space; the hot gas distribution pipe is arranged around the periphery of the rocket engine, and a plurality of hot gas outlets are provided on the side close to the rocket engine;

[0011] The air heater is connected to the hot gas distribution pipe through a gas transmission pipeline assembly and is used to fill the upper temperature recovery space and the lower temperature recovery space with hot gas.

[0012] Furthermore, the air heater is located outside the upper temperature recovery space and the lower temperature recovery space;

[0013] The lower flexible curtain or standing platform is provided with two connecting through holes;

[0014] The gas transmission pipeline assembly includes a first pipeline and two second pipelines;

[0015] One end of the first pipeline is connected to the air heater, and the other end is connected to one end of the two second pipelines;

[0016] The other end of the second pipeline passes through the two connecting holes and is communicated with the hot gas distribution pipe.

[0017] Furthermore, the second pipeline is a flexible pipeline.

[0018] Furthermore, the hot gas distribution pipe is C-shaped as a whole.

[0019] Furthermore, a temperature sensor is included;

[0020] The temperature sensor is installed on the air heater to obtain the hot air temperature.

[0021] Furthermore, it also includes an infrared temperature measuring gun;

[0022] The infrared temperature measuring gun is used to obtain the temperature distribution state in the lower temperature recovery space and / or the upper temperature recovery space.

[0023] Furthermore, a mass flow meter is included;

[0024] The mass flow meter is installed on the first pipeline and is used to obtain the hot gas flow.

[0025] Furthermore, the upper flexible curtain and the lower flexible curtain are made of double-sided glued asbestos cloth;

[0026] A plurality of hanging rings are evenly arranged around the periphery of the rocket engine below the standing platform;

[0027] The upper ends of the upper flexible curtain and the lower flexible curtain are evenly provided with a plurality of hooks.

[0028] The upper end of the upper flexible curtain is hung on the nitrogen fire ring through a hook thereon;

[0029] The hook at the upper end of the lower flexible curtain cooperates with the hanging ring for hanging.

[0030] The present invention also provides a method for reheating the outer surface of a high-efficiency rocket engine. The method is based on the above-mentioned system for reheating the outer surface of a high-efficiency rocket engine, and the method comprises the following steps:

[0031] Step 1: After the rocket engine test is completed, quickly push the heating mechanism to the side of the rocket engine;

[0032] Step 2: Hang the upper end of the upper flexible curtain around the periphery of the rocket engine on the nitrogen fire ring to form an upper temperature recovery space; and hang the upper end of the lower flexible curtain around the periphery of the rocket engine on the standing platform to form a lower temperature recovery space;

[0033] Step 3: Connect the heating end of the heating mechanism to the standing platform and place it in the upper temperature recovery space or the lower temperature recovery space;

[0034] Step 4: Start the heating mechanism to provide hot air into the upper temperature recovery space and the lower temperature recovery space to quickly recover the temperature of the outer surface of the rocket engine.

[0035] Beneficial effects of the present invention:

[0036] 1. The present invention adopts an upper flexible curtain and a lower flexible curtain; the upper flexible curtain is hung around the periphery of the rocket engine on the nitrogen fire protection ring existing on site to form an upper temperature recovery space; the lower flexible curtain is hung around the periphery of the rocket engine under the existing standing platform on site to form a lower temperature recovery space; the upper temperature recovery space and the lower temperature recovery space are isolated from the outside air by the upper flexible curtain and the lower flexible curtain to achieve the heat preservation function; at the same time, a heating mechanism is provided to heat the outer surface of the rocket engine; the temperature recovery system provided by the present invention improves the efficiency of the arrangement of the upper temperature recovery space and the lower temperature recovery space, and only the upper ends of the upper flexible curtain and the lower flexible curtain need to be directly hung, which is quick and efficient; on the other hand, the heating mechanism can be used to perform local heating on key parts of the rocket engine, thereby improving the temperature recovery efficiency and reducing the temperature recovery time.

[0037] 2. The present invention transmits hot air to the hot air distribution pipe through an air heater, and a hot air outlet is provided on the hot air distribution pipe; thereby, local heating is performed on key parts of the rocket engine; the heating mechanism is simple and easy to manufacture, and the hot air distribution pipe can be directly manufactured using waste pipes on site to avoid material waste.

[0038] 3. The present invention connects the air heater to the hot air distribution pipe through a flexible pipe, which is convenient for installation and disassembly on the one hand; and convenient for quick storage and saves storage space on the other hand.

[0039] 4. The present invention is provided with an upper flexible screen and a lower flexible screen, and its flexible feature is conducive to storage and saves storage space.

[0040] 5. The present invention arranges the hot gas distribution pipe into a C shape distributed around the rocket engine, further improving its manufacturing convenience.

[0041] 6. The present invention is also equipped with a temperature sensor, an infrared temperature measuring gun and a mass flow meter to facilitate timely adjustment of the heating power of the air heater during the temperature recovery process and real-time monitoring of the hot air distribution and airflow conditions.

[0042] 7. The upper flexible curtain and the lower flexible curtain of the present invention are both made of double-sided glue-coated asbestos cloth, which is both heat-insulating and safe. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 This is a schematic structural diagram of an embodiment of a high-efficiency rocket engine outer surface temperature recovery system according to the present invention;

[0044] Figure 2 This invention Figure 1 A top view of

[0045] Figure 3 Schematic diagram of the installation position of the hot gas distribution pipe in an embodiment of the present invention;

[0046] Figure 4 It is a partial stereoscopic diagram of an embodiment of a high-efficiency rocket engine outer surface temperature recovery system of the present invention.

[0047] Figure Number:

[0048] 1- rocket engine, 2- nitrogen fire ring, 3- standing platform, 4- upper flexible curtain, 5- lower flexible curtain, 6- heating mechanism, 61- hot air distribution pipe, 62- air heater, 63- first pipeline, 64- second pipeline. DETAILED DESCRIPTION

[0049] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0050] A high-efficiency rocket engine outer surface temperature recovery system, a rocket engine 1 is provided with a nitrogen fire ring 2 and a standing platform 3 around its circumference; the nitrogen fire ring 2 is located above the standing platform 3; Figure 1 As shown, the temperature recovery system includes an upper flexible curtain 4, a lower flexible curtain 5, a heating mechanism 6, a temperature sensor, an infrared temperature measuring gun and a mass flow meter;

[0051] The upper end of the upper flexible curtain 4 is uniformly provided with a plurality of hooks, the upper flexible curtain 4 is hung on the nitrogen fire ring 2 outside the periphery of the rocket engine 1 through the hooks thereon, and the lower end is in contact with the standing platform 3; the upper flexible curtain 4 is arranged around the periphery of the rocket engine 1 for one round, thereby surrounding the rocket engine 1 in four directions to form a cylindrical upper temperature recovery space; a plurality of hanging rings are uniformly provided around the periphery of the rocket engine 1 below the standing platform 3; the upper end of the upper flexible curtain 4 is uniformly provided with a plurality of hooks; the hooks on the upper end of the lower flexible curtain 5 are hung in cooperation with the hanging rings, the lower end of the lower flexible curtain 5 is in contact with the ground; and the lower flexible curtain 5 is arranged around the periphery of the rocket engine 1 for one round, thereby surrounding the rocket engine 1 in four directions to form a cylindrical lower temperature recovery space, the diameter of the lower temperature recovery space is about Ф4000mm; the overall height of the upper temperature recovery space and the lower temperature recovery space is about 4000mm; the upper temperature recovery space and the lower temperature recovery space can increase the action time of hot air on the rocket engine; in order to guarantee the temperature recovery efficiency of the surface of the rocket engine, the upper flexible curtain 4 and the lower flexible curtain 5 can be made of double-sided rubberized asbestos cloth.

[0052] The heating mechanism 6 is used for providing hot air into the upper temperature recovery space and the lower temperature recovery space. The heating mechanism 6 comprises a hot air distribution pipe 61, an air heater 62 and a gas transmission pipeline assembly for connecting the hot air distribution pipe 61 and the air heater 62; the hot air distribution pipe 61 is in the shape of C as a whole; the gas transmission pipeline assembly comprises a first pipeline 63 and two second pipelines 64; the two second pipelines 64 are flexible pipelines.

[0053] The hot air distribution pipe 61 is installed on the standing platform 3 and located in the upper temperature recovery space or the lower temperature recovery space, in this embodiment, the hot air distribution pipe 61 is located in the lower temperature recovery space; the hot air distribution pipe 61 is arranged around the periphery of the rocket engine 1, and a plurality of hot air outlets are provided on the side of the hot air distribution pipe 61 close to the rocket engine 1; one end of the first pipeline 63 is in communication with the air heater 62, and the other end is in communication with one end of the two second pipelines 64; two connecting through holes are provided on the lower flexible curtain 5 or the standing platform 3; the other end of the second pipeline 64 respectively passes through the two connecting through holes and is in communication with the hot air distribution pipe 61; the air heater 62 is located outside the upper temperature recovery space and the lower temperature recovery space, and is used for filling hot air into the upper temperature recovery space and the lower temperature recovery space, so that the hot air overflows from each hot air outlet to form a second air isolation in addition to the heat insulation effect of the upper flexible curtain 4 and the lower flexible curtain 5, and large flow heating is performed on the key parts of the rocket engine.

[0054] A temperature sensor is installed on the air heater to obtain the temperature of the hot air. An infrared temperature measuring gun is used to obtain the air temperature distribution state in the lower temperature recovery space or / and the upper temperature recovery space. A mass flow meter is installed on the first pipeline 63 to obtain the flow of the hot air. The three can be combined to optimize the gas distribution ring scheme and maximize the temperature recovery efficiency.

[0055] The above-mentioned high-efficiency rocket engine outer surface temperature recovery system can be arranged quickly and efficiently, and has many advantages such as ease of use, low cost, and easy promotion.

[0056] The method for reheating the outer surface of a high-efficiency rocket engine based on the above-mentioned reheating system comprises the following steps:

[0057] Step 1: After the rocket engine 1 test is completed, the heating mechanism 6 is quickly pushed to one side of the rocket engine 1.

[0058] Step 2: Hang the upper end of the upper flexible curtain 4 around the periphery of the rocket engine 1 on the nitrogen fire protection ring 2 to form an upper temperature recovery space; and hang the upper end of the lower flexible curtain 5 around the periphery of the rocket engine 1 on the standing platform 3 to form a lower temperature recovery space.

[0059] Step 3: Connect one end of the two second pipelines 64 to the hot air distribution pipe 61 , and connect the other end to the air heater 62 through the first pipeline 63 .

[0060] Step 4: Activate the high-power heating mechanism 6 to supply hot air to the upper and lower reheating spaces, heating key areas of the rocket engine 1 to rapidly reheat the outer surface of the rocket engine 1. During this process, the temperatures in the upper and lower reheating spaces can be dynamically adjusted in real time based on data measured by temperature sensors, infrared temperature measuring guns, and mass flow meters.

[0061] Step 5: Turn off the heating mechanism 6, remove the upper flexible screen 4, the lower flexible screen 5 and the second pipeline 64, and complete the entire temperature recovery process.

[0062] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present invention shall be covered by the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope of protection of the claims.

Claims

1. A high-efficiency rocket engine outer surface reheating system, wherein a nitrogen fire ring (2) and a standing platform (3) are provided around the outer periphery of the rocket engine (1); the nitrogen fire ring (2) is located above the standing platform (3); and the system is characterized in that: It comprises an upper flexible curtain (4), a lower flexible curtain (5) and a heating mechanism (6); The upper end of the upper flexible curtain (4) is suspended on the nitrogen fire protection ring (2), and the lower end is in contact with the standing platform (3); and the upper flexible curtain (4) is arranged around the periphery of the rocket engine (1) to form an upper temperature recovery space; The upper end of the lower flexible curtain (5) is suspended below the standing platform (3), and the lower end is in contact with the ground; and the lower flexible curtain (5) is arranged around the periphery of the rocket engine (1) to form a lower temperature recovery space; The heating end of the heating mechanism (6) is connected to the standing platform (3) and is located in the upper temperature return space or the lower temperature return space, and is used to provide hot air to the upper temperature return space and the lower temperature return space.

2. The high-efficiency rocket engine outer surface temperature recovery system according to claim 1, characterized in that: The heating mechanism (6) comprises a hot air distribution pipe (61) and an air heater (62), wherein the hot air distribution pipe (61) constitutes the heating end; The hot gas distribution pipe (61) is installed on the standing platform (3) and is located in the upper temperature recovery space or the lower temperature recovery space; the hot gas distribution pipe (61) is arranged around the periphery of the rocket engine (1), and a plurality of hot gas outlets are provided on a side thereof close to the rocket engine (1); The air heater (62) is connected to the hot air distribution pipe (61) through a gas transmission pipeline assembly and is used to fill the upper temperature recovery space and the lower temperature recovery space with hot air.

3. The high-efficiency rocket engine outer surface temperature recovery system according to claim 2, characterized in that: The air heater (62) is located outside the upper temperature recovery space and the lower temperature recovery space; The lower flexible curtain (5) or the standing platform (3) is provided with two connecting through holes; The gas transmission pipeline assembly includes a first pipeline (63) and two second pipelines (64); One end of the first pipeline (63) is connected to the air heater (62), and the other end is connected to one end of two second pipelines (64); The other ends of the two second pipelines (64) pass through the two connecting through holes respectively and are in communication with the hot gas distribution pipe (61).

4. The high-efficiency rocket engine outer surface temperature recovery system according to claim 3, characterized in that: The second pipeline (64) is a flexible pipeline.

5. The high-efficiency rocket engine outer surface temperature recovery system according to claim 2, 3 or 4, characterized in that: The hot gas distribution pipe (61) is C-shaped as a whole.

6. The high-efficiency rocket engine outer surface temperature recovery system according to claim 5, characterized in that: Also includes a temperature sensor; The temperature sensor is installed on the air heater (62) to obtain the hot air temperature.

7. The high-efficiency rocket engine outer surface temperature recovery system according to claim 6, characterized in that: Also includes an infrared temperature gun; The infrared temperature measuring gun is used to obtain the temperature distribution state in the lower temperature recovery space and / or the upper temperature recovery space.

8. The high-efficiency rocket engine outer surface temperature recovery system according to claim 3, characterized in that: Also included are mass flow meters; The mass flow meter is installed on the first pipeline (63) and is used to obtain the hot gas flow rate.

9. The high-efficiency rocket engine outer surface temperature recovery system according to claim 8, characterized in that: The upper flexible curtain (4) and the lower flexible curtain (5) are made of double-sided glued asbestos cloth; A plurality of hanging rings are evenly arranged around the periphery of the rocket engine (1) below the standing platform (3); The upper ends of the upper flexible curtain (4) and the lower flexible curtain (5) are evenly provided with a plurality of hooks. The upper end of the upper flexible curtain (4) is hung on the nitrogen fire-fighting ring (2) via a hook thereon; The hook at the upper end of the lower flexible curtain (5) cooperates with the hanging ring for hanging.

10. A high-efficiency rocket engine outer surface reheating method, based on the high-efficiency rocket engine outer surface reheating system according to any one of claims 1 to 8, characterized in that: The following steps are involved: Step 1: After the rocket engine (1) is tested, the heating mechanism (6) is quickly pushed to one side of the rocket engine (1); Step 2: Hang the upper end of the upper flexible curtain (4) around the periphery of the rocket engine (1) on the nitrogen fire protection ring (2) to form an upper temperature recovery space; and hang the upper end of the lower flexible curtain (5) around the periphery of the rocket engine (1) on the standing platform (3) to form a lower temperature recovery space; Step 3, connecting the heating end of the heating mechanism (6) to the standing platform (3), and placing it in the upper temperature return space or the lower temperature return space; Step 4: Start the heating mechanism (6) to provide hot air into the upper temperature recovery space and the lower temperature recovery space, so that the outer surface of the rocket engine (1) can be quickly heated up.

Images