CN113531972A - Device for improving heat sink high temperature uniformity of aerospace annular mold equipment - Google Patents
Device for improving heat sink high temperature uniformity of aerospace annular mold equipment Download PDFInfo
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- CN113531972A CN113531972A CN202110699022.1A CN202110699022A CN113531972A CN 113531972 A CN113531972 A CN 113531972A CN 202110699022 A CN202110699022 A CN 202110699022A CN 113531972 A CN113531972 A CN 113531972A
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- liquid nitrogen
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
- F25D3/00—Devices using other cold materials; Devices using cold-storage bodies
- F25D3/10—Devices using other cold materials; Devices using cold-storage bodies using liquefied gases, e.g. liquid air
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L7/00—Heating or cooling apparatus; Heat insulating devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
- F25D29/00—Arrangement or mounting of control or safety devices
- F25D29/005—Mounting of control devices
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- Combustion & Propulsion (AREA)
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- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
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- Chemical Kinetics & Catalysis (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
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Abstract
The invention provides a device for improving the heat sink high temperature uniformity of an aerospace ring die device, which comprises a liquid nitrogen inlet pipe, a liquid nitrogen running pipe, a nitrogen discharging pipe and a plurality of liquid nitrogen branch pipes, wherein the liquid nitrogen running pipe is communicated with one end of the liquid nitrogen inlet pipe; the nitrogen running pipe is communicated with one end of the nitrogen discharge pipe; one end of the liquid nitrogen branch pipe is communicated with the liquid nitrogen running pipe, and the other end of the liquid nitrogen branch pipe is communicated with the nitrogen running pipe; the liquid nitrogen branch pipes are mutually connected in parallel; the liquid nitrogen inlet pipe is provided with a first pneumatic regulating valve, and the nitrogen gas discharge pipe is provided with a low-temperature ball valve. The invention can automatically eliminate the phenomenon of poor temperature uniformity under the condition of not suspending the aerospace product circular mold test, effectively improve the test efficiency and reduce the test cost; the temperature return and the pressure recovery are not involved, the test is not required to be restored to the initial state, and the reliability of the test is improved; different temperature uniformity difference elimination modes can be started according to actual conditions, and most of conditions can be covered.
Description
Technical Field
The invention relates to the field of aviation equipment, in particular to a device for improving the high temperature uniformity of an aerospace environmental model equipment heat sink, and especially relates to a high temperature uniformity device applied to the aerospace environmental model equipment heat sink.
Background
The aerospace product ring model test mainly aims to verify the reliability of the product by simulating the space black and cold environment, and the aerospace ring model equipment is a main body for bearing the aerospace product ring model test. The aerospace ring mould equipment generally comprises a vacuum system, a vacuum container and a heat sink in the vacuum container, and the space cold black background is simulated by the heat sink generally. The heat sink is composed of an outer inlet and outlet pipeline, a liquid nitrogen branch and the like, and the principle is that liquid nitrogen is introduced into the pipeline to provide a cold background at the temperature of-196 ℃, and a black thermal control coating is sprayed on the surface of the heat sink pipeline to simulate the background similar to a black body in the universe. The liquid nitrogen branches are connected with the liquid nitrogen inlet pipeline and the liquid nitrogen outlet pipeline in parallel, and the number of the branches is dozens to hundreds. The long-term test practice shows that the phenomenon that the uniformity of local temperature is poor easily occurs in the initial stage of introducing liquid nitrogen and the middle stage of introducing liquid nitrogen, specifically, the local branch is filled with liquid nitrogen, so that the local temperature of the heat sink is low, the local branch is filled with the mixture of some gas nitrogen and the liquid nitrogen, so that the local temperature of the heat sink is high, the temperature difference of the heat sink is large, the test requirement cannot be met, and the phenomenon continuously exists under the condition of no effective intervention, so that the test cannot be continued. The reason for causing the poor uniformity of the local temperature of the heat sink is that different branches are different in position and processing technology, after part of branches are introduced with liquid nitrogen, the liquid nitrogen in the pipeline is more and more along with the reduction of the temperature, and after other parts of branches are introduced with liquid nitrogen, the pipeline has not only liquid nitrogen but also some gas nitrogen along with the reduction of the temperature. At present, two methods for solving the problem of poor temperature uniformity are available: and (4) introducing the liquid nitrogen method again and restarting the test process. The method for introducing liquid nitrogen again comprises the following steps: suspending the test and stopping liquid nitrogen supply, re-introducing the liquid nitrogen after the liquid nitrogen in the heat sink is completely vaporized to a certain temperature, wherein the phenomenon of uneven temperature still cannot be eliminated after the liquid nitrogen is re-introduced, and sometimes the repeated implementation is needed until the phenomenon disappears; the restart test process method comprises the following steps: and (3) suspending the test and stopping liquid nitrogen supply, repressing in the tank after the temperature of the heat sink is raised to room temperature, restoring the test to an initial state, and then carrying out the test again. Therefore, the problem of poor heat sink temperature uniformity influences the aerospace product circular mold test at present, the existing processing method not only reduces the efficiency of the aerospace product circular mold test, but also increases the uncertain risk in the test process, and the reliability of the test process is reduced.
Through inquiry, the invention patent with patent number 200810188293.5, namely a liquid nitrogen and alcohol double-medium compatible heat sink system of space environment simulation test equipment, relates to a heat sink temperature equalization processing scheme, but the processing effect is not ideal.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a device for improving the high temperature uniformity of a heat sink of an aerospace annular mold device, and solves one or more of the technical problems.
According to one aspect of the invention, the device for improving the heat sink high temperature uniformity of the aerospace ring die equipment comprises a liquid nitrogen inlet pipe, a liquid nitrogen running pipe, a nitrogen discharge pipe and a plurality of liquid nitrogen branch pipes, wherein the liquid nitrogen running pipe is communicated with one end of the liquid nitrogen inlet pipe; the nitrogen running pipe is communicated with one end of the nitrogen discharge pipe; one end of the liquid nitrogen branch pipe is communicated with the liquid nitrogen running pipe, and the other end of the liquid nitrogen branch pipe is communicated with the nitrogen running pipe; the liquid nitrogen branch pipes are mutually connected in parallel; the liquid nitrogen inlet pipe is provided with a first pneumatic regulating valve, and the nitrogen gas discharge pipe is provided with a low-temperature ball valve.
In some embodiments, a plurality of temperature sensors are arranged on the liquid nitrogen branch pipe.
In some embodiments, the device further comprises a gas transmission branch connected with the liquid nitrogen inlet pipe in parallel, and the gas transmission branch is provided with a heater, a second pneumatic regulating valve and a heat exchanger.
In some embodiments, the system further comprises a discharge branch, one end of the discharge branch is communicated with the liquid nitrogen inlet pipe, the other end of the discharge branch is communicated with the outside, and a third pneumatic regulating valve and a heat exchanger are arranged on the discharge branch.
In some embodiments, the liquid nitrogen run tube is annularly disposed.
In some embodiments, the nitrogen run tube is annularly disposed.
Compared with the prior art, the invention has the following beneficial effects: the invention can automatically eliminate the phenomenon of poor temperature uniformity under the condition of not suspending the aerospace product circular mold test, effectively improve the test efficiency and reduce the test cost; the temperature return and the pressure recovery are not involved, the test is not required to be restored to the initial state, and the reliability of the test is improved; different temperature uniformity difference elimination modes can be started according to actual conditions, and most of conditions can be covered.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural diagram of an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of another embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
With reference to fig. 1 to 2, a device for improving the heat sink high temperature uniformity of an aerospace ring die equipment comprises a liquid nitrogen inlet pipe 11, a liquid nitrogen running pipe 12, a nitrogen running pipe 22, a nitrogen discharge pipe 21 and a plurality of liquid nitrogen branch pipes 30, wherein the liquid nitrogen running pipe 12 is communicated with one end of the liquid nitrogen inlet pipe 11; the nitrogen gas running pipe 22 is communicated with one end of the nitrogen gas discharge pipe 21; one end of the liquid nitrogen branch pipe 30 is communicated with the liquid nitrogen running pipe 12, and the other end thereof is communicated with the nitrogen running pipe 22; the liquid nitrogen branch pipes 30 are connected in parallel; the liquid nitrogen inlet pipe 11 is provided with a first pneumatic regulating valve 111, and the nitrogen outlet pipe 21 is provided with a low-temperature ball valve 211.
The liquid nitrogen branch pipe 30 is provided with a plurality of temperature sensors 40.
The device also comprises a gas transmission branch 13 which is connected with the liquid nitrogen inlet pipe 11 in parallel, and a heater 132, a second pneumatic regulating valve 131 and a heat exchanger 142 are arranged on the gas transmission branch 13.
The device further comprises a discharge branch 14, one end of the discharge branch 14 is communicated with the liquid nitrogen inlet pipe 11, the other end of the discharge branch 14 is communicated with the outside, and a third pneumatic regulating valve 141 and a heat exchanger 142 are arranged on the discharge branch 14.
The liquid nitrogen operation pipe 12 is annularly arranged. The nitrogen running pipe 22 is annularly arranged.
The invention judges whether the phenomenon of uneven temperature control occurs according to a temperature sensor arranged on a liquid nitrogen branch, when 45 min of liquid nitrogen is introduced into a heat sink, the phenomenon of uneven temperature locally occurs on the surface of the heat sink when the local temperature of the heat sink is higher than the average temperature of the heat sink by more than 35 ℃, the phenomenon of uneven temperature locally occurs can be judged, the P I D is used as a target control system to adjust the pneumatic regulating valves and heaters on a liquid nitrogen inlet pipe 11, a gas transmission branch 13 and a discharge branch 14 according to the temperature signal, the phenomenon of uneven temperature can be judged to be eliminated when the temperature difference on the surface of the heat sink is gradually reduced to be within 10 ℃, the condition that the uneven temperature cannot be effectively eliminated after the regulating valves and the heaters are regulated is considered to close the pneumatic regulating valves of the liquid nitrogen inlet pipe 11, the gas transmission branch 13 and the discharge branch 14, and the pneumatic regulating valves are opened to introduce the liquid nitrogen again after the temperature of the surface of the heat sink tends to be consistent.
Compared with the prior art, the invention has the following beneficial effects:
the invention can automatically eliminate the phenomenon of poor temperature uniformity under the condition of not suspending the aerospace product circular mold test, effectively improve the test efficiency and reduce the test cost; the temperature return and the pressure recovery are not involved, the test is not required to be restored to the initial state, and the reliability of the test is improved; different temperature uniformity difference elimination modes can be started according to actual conditions, and most of conditions can be covered.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (6)
1. The device for improving the high temperature uniformity of the heat sink of the aerospace ring die equipment is characterized by comprising a liquid nitrogen inlet pipe (11), a liquid nitrogen running pipe (12), a nitrogen running pipe (22), a nitrogen discharge pipe (21) and a plurality of liquid nitrogen branch pipes (30),
the liquid nitrogen running pipe (12) is communicated with one end of the liquid nitrogen inlet pipe (11); the nitrogen running pipe (22) is communicated with one end of the nitrogen discharge pipe (21); one end of the liquid nitrogen branch pipe (30) is communicated with the liquid nitrogen running pipe (12), and the other end of the liquid nitrogen branch pipe is communicated with the nitrogen running pipe (22); the liquid nitrogen branch pipes (30) are mutually connected in parallel;
the liquid nitrogen inlet pipe (11) is provided with a first pneumatic regulating valve (111), and the nitrogen outlet pipe (21) is provided with a low-temperature ball valve (211).
2. The device for improving the heat sink high temperature uniformity of an aerospace ring die equipment as claimed in claim 1, wherein a plurality of temperature sensors (40) are arranged on the liquid nitrogen branch pipe (30).
3. The device for improving the heat sink high temperature uniformity of an aerospace ring die equipment as claimed in claim 2, further comprising a gas transmission branch (13) connected in parallel with the liquid nitrogen inlet pipe (11), wherein the gas transmission branch (13) is provided with a heater (132), a second pneumatic regulating valve (131) and a heat exchanger (142).
4. The device for improving the heat sink high temperature uniformity of an aerospace ring die equipment as claimed in claim 3, further comprising a discharge branch (14), wherein one end of the discharge branch (14) is communicated with the liquid nitrogen inlet pipe (11), the other end of the discharge branch is communicated with the outside, and the discharge branch (14) is provided with a third pneumatic regulating valve (141) and a heat exchanger (142).
5. The device for improving the heat sink high temperature uniformity of the aerospace ring die equipment as claimed in claim 4, wherein the liquid nitrogen operation pipe (12) is arranged in a ring shape.
6. The device for improving the heat sink high temperature uniformity of an aerospace ring die equipment as claimed in claim 5, wherein the nitrogen running pipe (22) is arranged in a ring shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110699022.1A CN113531972B (en) | 2021-06-23 | 2021-06-23 | Device for improving heat sink high temperature uniformity of aerospace annular mold equipment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110699022.1A CN113531972B (en) | 2021-06-23 | 2021-06-23 | Device for improving heat sink high temperature uniformity of aerospace annular mold equipment |
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| CN113531972A true CN113531972A (en) | 2021-10-22 |
| CN113531972B CN113531972B (en) | 2022-08-16 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5309722A (en) * | 1992-11-06 | 1994-05-10 | Harsco Corporation | Temperature control system for liquid nitrogen refrigerator |
| JP2000186997A (en) * | 1998-12-22 | 2000-07-04 | Bridgestone Corp | Temperature controller for thermostat |
| KR20020029697A (en) * | 2000-10-13 | 2002-04-19 | 윤종용 | Temperature regulating apparatus with automatic control circuit for tester |
| CN102175457A (en) * | 2011-01-28 | 2011-09-07 | 北京航空航天大学 | Flat-shaped liquid-nitrogen and liquid-helium dual-media compatible heat sink device and cooling method thereof |
| CN102175456A (en) * | 2011-01-28 | 2011-09-07 | 北京航空航天大学 | Straight cylindrical liquid-nitrogen liquid-helium double-medium compatible heat sink device and refrigeration method thereof |
| CN110658867A (en) * | 2019-09-05 | 2020-01-07 | 中国航发北京航科发动机控制系统科技有限公司 | Low-temperature test temperature control system and method for jet nozzle oil source pump of aircraft engine |
-
2021
- 2021-06-23 CN CN202110699022.1A patent/CN113531972B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5309722A (en) * | 1992-11-06 | 1994-05-10 | Harsco Corporation | Temperature control system for liquid nitrogen refrigerator |
| JP2000186997A (en) * | 1998-12-22 | 2000-07-04 | Bridgestone Corp | Temperature controller for thermostat |
| KR20020029697A (en) * | 2000-10-13 | 2002-04-19 | 윤종용 | Temperature regulating apparatus with automatic control circuit for tester |
| CN102175457A (en) * | 2011-01-28 | 2011-09-07 | 北京航空航天大学 | Flat-shaped liquid-nitrogen and liquid-helium dual-media compatible heat sink device and cooling method thereof |
| CN102175456A (en) * | 2011-01-28 | 2011-09-07 | 北京航空航天大学 | Straight cylindrical liquid-nitrogen liquid-helium double-medium compatible heat sink device and refrigeration method thereof |
| CN110658867A (en) * | 2019-09-05 | 2020-01-07 | 中国航发北京航科发动机控制系统科技有限公司 | Low-temperature test temperature control system and method for jet nozzle oil source pump of aircraft engine |
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| CN113531972B (en) | 2022-08-16 |
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