Anti-condensation design method for low-temperature pipeline system in sealed cabin of manned spacecraft

Abstract

The invention discloses an anti-condensation design method for a low-temperature pipeline system in a sealed cabin of a manned spacecraft, and the method comprises the steps: dividing the working temperature range of temperature control equipment of the low-temperature pipeline system into two types according to a range higher than and lower than a dew point, and carrying out the centralized arrangement of the equipment with the working temperature lower than the dew point; the length of the low-temperature pipeline between equipment is reduced, meanwhile, the low-temperature pipeline layout is visible and reachable, and temperature measuring points and inspection openings are formed in the pipeline, so that on-orbit inspection is facilitated. A pipeline bypass and a flow adjusting valve are arranged for equipment with the working temperature higher than the dew point, secondary adjustment of the working temperature is achieved, and the working temperature of the pipeline and the equipment is increased as much as possible on the premise that the working temperature does not exceed the limit. Through the measures, on the premise that the scale of the low-temperature pipeline system is not obviously increased, the pipeline length, lower than the dew point temperature, of the low-temperature pipeline system is obviously shortened, the dew formation risk of the low-temperature pipeline system is effectively reduced, the safety problem caused by dew formation is avoided, and the dew formation condition checking and handling operation of the on-orbit low-temperature pipeline system is optimized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft overall design, and particularly relates to a low-temperature pipeline system anti-condensation design method in a manned spacecraft sealed cabin. BACKGROUND

[0002] The low-temperature pipeline system in the manned spacecraft sealed cabin is usually equipped with a low-temperature pipeline system, which is used to provide a cold source for a condensing dryer, an out-of-cabin suit, and part of platform equipment and load equipment requiring low temperature. The existing design of the low-temperature pipeline system is to sort the devices according to the working temperature range from upstream to downstream, the devices with low working temperature are upstream of the low-temperature pipeline, and the devices with relatively high working temperature are downstream of the low-temperature pipeline. The liquid working medium is driven to flow by a circulating pump, flows through each device, collects the heat generated by the device, and finally transmits the low-temperature loop heat to the outer loop system through a heat exchanger. The low-temperature pipeline system usually has a temperature control valve at the most upstream, which can adjust the working temperature of the low-temperature loop system. The working temperature of the low-temperature loop system is limited by the lowest working temperature requirement device at the most upstream. The working temperature of the liquid working medium in the low-temperature pipeline is usually lower than the dew point temperature in the sealed cabin. In order to prevent condensation, the pipeline and the device are usually wrapped with thermal insulation materials.

[0003] The existing design of the low-temperature pipeline system of the manned spacecraft has two obvious deficiencies: (1) The low-temperature pipeline system has only one temperature control point, and the anchor is the lowest working temperature requirement device (usually a condensing dryer). Although the lowest working temperature requirement device meets the requirements, most of the pipelines and devices downstream are in an unnecessary supercooling state and cannot be adjusted. (2) The low-temperature pipeline needs to flow through multiple devices, the pipeline length is relatively long, and a large number of pipelines are arranged in hidden areas such as corner partitions with poor visibility and accessibility. The above two deficiencies cause the low-temperature pipeline system to have a wide distribution of easy condensation areas and it is not easy to check and handle. Although the low-temperature pipeline system is wrapped with thermal insulation materials, the thermal insulation effect of the thermal insulation materials is usually closely related to the compression degree. The more serious the compression is, the worse the thermal insulation effect is. The wrapping of the thermal insulation materials is usually implemented by manual operation, and there is a risk of excessive compression in some areas, causing the surface temperature of the wrapping layer to be lower than the dew point, and causing surface condensation. In addition, the low-temperature pipeline is usually formed by splicing several pipelines, and there may be gaps between the wrapping layers. Air contacts the pipeline body through the gaps, and condensation is formed in the wrapping layer, which is not easy to detect.

[0004] The long-term manned spacecraft has a long on-orbit life cycle, supports long-term residence of the crew, and the crew continuously metabolizes and produces moisture. In addition, there are experimental projects such as plant cultivation in the sealed cabin, and the moisture source is more extensive, so the risk of condensation of the low-temperature pipeline system is higher, which may cause the following serious problems: (1) Long-term condensation may cause pitting of the low-temperature pipeline or the device, causing leakage of the liquid working medium of the low-temperature pipeline; (2) If metal fasteners such as screws are soaked in dew for a long time, they may rust, damage the strength of the fasteners, or cause the fasteners to malfunction. (3) If the electrical connectors of low-temperature pipeline equipment are soaked in dew for a long time, condensate may enter the interior of the electrical connectors, causing electrochemical corrosion of the pins and sockets, resulting in short circuits. (4) If non-metallic materials are soaked in dew for a long time, such as coverings and woven fabrics, microorganisms will grow and multiply, corroding the non-metallic materials and entering the human activity area through the ventilation system, endangering the health of passengers.

[0005] Anti-condensation design of cryogenic piping systems is one of the most important safety design requirements for long-term manned spacecraft.

[0006] During the ground development phase of manned spacecraft, implementing more rigorous thermal insulation coverings for cryogenic pipelines can effectively reduce the risk of condensation. However, this method significantly increases the weight and volume of the covering layer, prolongs the project implementation cycle, and incurs substantial costs. Furthermore, once condensation occurs, it hinders the inspection and handling of the situation. Therefore, while utilizing existing pipeline covering methods, the key to anti-condensation design for cryogenic pipeline systems lies in maximizing the operating temperature of the cryogenic pipeline system, minimizing the cryogenic pipeline area, and facilitating the inspection and handling of condensation. Summary of the Invention

[0007] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a design method for preventing condensation in the cryogenic pipeline system inside the sealed cabin of a manned spacecraft. Without affecting the temperature control of the equipment or significantly increasing the weight of the system, this method significantly reduces the risk of condensation in the cryogenic pipeline system, avoids various safety problems caused by condensation, and optimizes the inspection and handling of condensation in the on-orbit cryogenic loop system.

[0008] The technical solution of this invention is: a design method for preventing condensation in a cryogenic piping system inside a sealed cabin of a manned spacecraft, comprising the following steps: Based on the relationship between the operating temperature range and dew point temperature of the temperature-controlled equipment in the cryogenic pipeline system, the equipment is divided into two categories: equipment whose upper limit of operating temperature range is below the dew point temperature is defined as Class I equipment, and equipment whose operating temperature range spans the dew point temperature or whose lower limit of operating temperature range is above the dew point temperature is defined as Class II equipment. Class I equipment is placed upstream of the cryogenic piping system, and Class II equipment is placed downstream of the cryogenic piping system; a temperature regulating component is installed between the output end of the circulating pump and the Class I equipment, and a separate secondary temperature regulating component is installed for the Class II equipment to increase the operating temperature of the Class II equipment without affecting the normal operation of the Class I equipment. In different working modes and different settings of temperature regulating components, the temperature distribution of the low-temperature pipeline system is analyzed, the pipelines with the upper limit of the working temperature range below the dew point temperature, the working temperature range spanning the dew point temperature, and the lower limit of the working temperature range above the dew point temperature are identified, the working temperature range of each device is determined, and the setting strategy of the temperature regulating components at each location is determined. According to the obtained temperature distribution, the devices and pipelines with the upper limit of the working temperature range below the dew point temperature and the devices and pipelines with the working temperature range spanning the dew point temperature are concentratedly laid out, and the concentratedly laid out area is externally visible and accessible.

[0009] Further, the secondary temperature regulating components are separately arranged for the Class II devices, and the specific manner is as follows: A temperature control valve is arranged at the junction of the Class I devices and the Class II devices, and the temperature control valve is connected to the temperature regulating bypass downstream of the Class II devices.

[0010] Further, if the number of the Class II devices and the difference between the working temperature ranges of the devices exceed a preset value, the Class II devices are further split, and the temperature control valve and the temperature regulating bypass are further arranged on the pipeline connected to the Class II devices, and so on.

[0011] Further, the principle of determining the setting strategy of the temperature regulating components at each location is that the working temperature of each device meets the requirements and the overall working temperature of the low-temperature pipeline system is maximized. Further, an air temperature and humidity sensor is arranged in the concentratedly laid out area to detect the dew point temperature.

[0012] Further, an air exchange fan is arranged in the concentratedly laid out area to maintain ventilation with the human activity area.

[0013] Further, the outer cladding layer of the pipeline in the concentratedly laid out area is marked with colors according to the upper limit of the working temperature range below the dew point temperature, the working temperature range spanning the dew point temperature, and the lower limit of the working temperature range above the dew point temperature, so as to facilitate inspection on orbit.

[0014] Further, for the pipeline in the concentratedly laid out area with the upper limit of the working temperature range below the dew point temperature and the working temperature range spanning the dew point temperature, a thermistor is pasted on the surface of the cladding layer to monitor the surface temperature of the cladding layer.

[0015] Further, for the pipeline in the concentratedly laid out area with the upper limit of the working temperature range below the dew point temperature and the working temperature range spanning the dew point temperature, an inspection port is reserved on the cladding layer for astronauts to regularly check whether there is internal condensation caused by loose cladding of the cladding layer.

[0016] The application also relates to a low-temperature pipeline system for preventing dew condensation in a manned spacecraft sealed cabin, which comprises a circulating pump, a heat exchanger, I-type equipment, II-type equipment and connecting pipelines, the I-type equipment is arranged in the upstream of the low-temperature pipeline system, and the II-type equipment is arranged in the downstream of the low-temperature pipeline system, The I-type equipment is defined as equipment with the upper limit of the working temperature range below the dew point temperature, and the II-type equipment is defined as equipment with the working temperature range crossing the dew point temperature or the lower limit of the working temperature range above the dew point temperature; A first temperature adjusting component is arranged between the output end of the circulating pump and the I-type equipment; the II-type equipment is separately provided with a secondary temperature adjusting component, which is used for improving the working temperature of the II-type equipment without affecting the normal working of the I-type equipment; The equipment and pipelines with the upper limit of the working temperature range below the dew point temperature and the equipment and pipelines with the working temperature range crossing the dew point temperature adopt a centralized layout mode, and the centralized layout area is externally visible and accessible.

[0017] Compared with the prior art, the application has the following advantages: The application innovatively provides a low-temperature pipeline system dew condensation prevention design method for a manned spacecraft sealed cabin, the working temperature range of the low-temperature pipeline system temperature control equipment is divided into two types according to being higher and lower than the dew point, the equipment with the working temperature lower than the dew point is centrally arranged, the low-temperature pipeline length between the equipment is reduced, the low-temperature pipeline layout is visible and accessible, temperature measuring points and inspection openings are arranged on the pipelines, and in-orbit inspection is facilitated. The pipelines bypass and flow regulating valves are arranged on the equipment with the working temperature higher than the dew point, the working temperature is secondarily adjusted, the working temperature of the pipelines and the equipment is as high as possible on the premise that the working temperature does not exceed the limit. Through the above measures, the low-temperature pipeline length of the low-temperature pipeline system below the dew point temperature is significantly shortened, the low-temperature pipeline system dew condensation risk is effectively reduced, various safety problems caused by dew condensation are avoided, and in-orbit low-temperature pipeline system dew condensation condition inspection and disposal operation are optimized. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is a schematic diagram of the relationship between the working temperature range of the equipment and the dew point temperature in the application; Figure 2 is a schematic diagram of one independent temperature control point and temperature control valve arranged on the II-type equipment in the application; Figure 3 is a schematic diagram of two independent temperature control points and temperature control valves arranged on the II-type equipment in the application; Figure 4 is a schematic diagram of the centralized layout of the I-type equipment and pipelines in the application; Figure 5 is a schematic diagram of the arrangement of the pipeline temperature measuring points and inspection openings in the centralized layout area in the application. Detailed Implementation

[0019] To better understand the technical solution of the present invention, the specific embodiments of the present invention are described below.

[0020] The present invention proposes a design method for preventing condensation in a cryogenic piping system within a sealed cabin of a manned spacecraft. The main technical concept is as follows: Step 1: Divide the operating temperature range of the temperature control equipment for the low-temperature pipeline system into two categories: above and below the dew point.

[0021] Analyzing the dew point temperature fluctuation range of manned spacecraft, determining the upper and lower limits of the fluctuation, and classifying the operating temperature range of equipment requiring cryogenic loop system temperature control into two categories based on whether it is above or below the dew point temperature, as shown in the appendix. Figure 1 As shown, equipment with an operating temperature range below the dew point temperature fluctuation range is classified as Class I equipment. Equipment with an operating temperature range that spans the dew point temperature fluctuation range or is entirely above the dew point temperature fluctuation range is classified as Class II equipment.

[0022] Step 2: Based on the operating temperature of the equipment, determine the upstream and downstream relationships of each piece of equipment in the low-temperature pipeline system, and set up secondary temperature regulation measures for equipment whose operating temperature is higher than or exceeds the dew point.

[0023] According to one embodiment of the present invention, Class I equipment is arranged upstream of the cryogenic pipeline system and Class II equipment is arranged downstream of the cryogenic pipeline system in order to maximize the operating temperature of the equipment and pipelines and reduce the area where the operating temperature of the cryogenic pipeline system is lower than the dew point temperature.

[0024] Specifically, secondary temperature regulation measures are implemented for Class II equipment. A temperature control valve and bypass are installed on the upstream pipeline of the Class II equipment, and a temperature control point 2 is set. The temperature control valve can be manual or automatic, as shown in the attached diagram. Figure 2 As shown, by adjusting the flow rate of the main bypass, the operating temperature of Class II equipment and pipelines is increased as much as possible, provided that the operating temperature of Class II equipment meets the requirements.

[0025] Furthermore, if there are a large number of Category II devices and their operating temperatures vary significantly, spacecraft resources can be comprehensively considered, and the Category II devices can be further subdivided according to their operating temperature ranges, with additional temperature control points (3) set, as shown in the attached diagram. Figure 3 As shown, more precise temperature control is implemented for Class II equipment. Through these measures, secondary temperature regulation of Class II equipment can be achieved, resolving the overcooling issue of Class II equipment and cryogenic piping systems without affecting the normal operation of upstream Class I equipment, and significantly reducing the cryogenic zone of the cryogenic piping system.

[0026] Step 3: Establish a simulation analysis model of the cryogenic pipeline system, analyze the operating temperature of each piece of equipment and the temperature of each section of the pipeline under different operating modes, and determine the adjustment strategy for secondary temperature regulation. According to one embodiment of the present invention, a thermal simulation analysis model of the cryogenic pipeline system is established for the cryogenic pipeline system structure determined in step two. This model analyzes the operating temperatures of various devices and sections of the cryogenic pipeline under different operating modes of the manned spacecraft. The simulation analysis model should include the following elements: (1) It can reflect the physical properties and flow rate of the working fluid in the cryogenic pipeline system; (2) It can reflect the pipeline connection relationship of the low-temperature pipeline system; (3) It can reflect the heat generated by each piece of equipment and the heat exchange relationship between it and the low-temperature pipeline system; (4) It can reflect the heat transfer relationship between the low-temperature pipeline system and the heat exchanger; (5) It can reflect the flow regulation of the main bypass by each temperature control valve.

[0027] Using a thermal simulation analysis model of a cryogenic piping system, the following results were obtained: (1) Temperature distribution of each section of the cryogenic pipeline system under different operating modes and different opening degrees of the temperature control valve, as shown in the attached figure. Figure 4 As shown, from upstream to downstream, the operating temperature of the low-temperature pipeline gradually increases, identifying pipeline areas with operating temperatures below the dew point, crossing the dew point, and above the dew point. (2) Under different working modes, the working temperature of each device under different opening degrees of the temperature control valve.

[0028] Through the above simulation analysis, the temperature regulation strategies for each temperature control valve in the cryogenic pipeline system were determined. Specifically, this involves defining the setting range of different temperature control points and the corresponding opening range of the temperature control valves for different operating modes of the manned spacecraft. Under the premise that the equipment's operating temperature meets requirements, the goal is to maximize the operating temperature of the cryogenic pipeline system, providing a basis for on-orbit control, avoiding equipment overcooling, and reducing the pipeline area below the dew point temperature. Simultaneously, the operating temperature distribution of each pipeline along the cryogenic pipeline system was determined, laying the foundation for subsequent centralized layout of cryogenic pipelines.

[0029] Step four: Arrange equipment and pipelines with operating temperatures below the dew point in a centralized, visible, and accessible layout.

[0030] According to one embodiment of the present invention, based on the temperature distribution of the cryogenic pipeline system determined by the simulation analysis in step three, equipment and pipelines with operating temperatures below the dew point are centrally located. Where layout conditions permit, equipment and pipelines with operating temperatures exceeding the dew point are also centrally located as much as possible, as shown in the attached figure. Figure 5As shown, for example, they can be centrally arranged in one or several instrument areas, rather than scattered in multiple instrument areas or corner areas. Centralized layout can minimize the length of pipelines at risk of condensation and avoid the difficulty of investigation caused by the wide distribution of condensation areas.

[0031] Simultaneously, the pipeline layout in the centralized area will be made visible and accessible to facilitate subsequent on-orbit inspection and handling of condensation. Key points include: (1) Avoid placing cryogenic pipelines close to the cabin walls, instrument panels or equipment, and leave space for observation and operation; (2) The routing of low-temperature pipelines should avoid being too close to each other; (3) Low-temperature pipelines should not be placed too close to cable bundles; (4) The connection between pipelines is a high-risk area for condensation due to the gaps in the coating layer. It must be located in an area that is convenient for observation and operation.

[0032] If, due to layout constraints, some equipment or pipelines operating below the dew point need to be located outside the centralized layout area, the pipeline length should be shortened as much as possible, and they should be located in areas with good visibility and accessibility. For Class II equipment and pipelines operating above the dew point, since the risk of condensation is low, centralized layout is not required, and the pipelines can be hidden in corner partitions or other areas.

[0033] Preferably, air temperature and humidity sensors are arranged in the concentrated layout area of ​​Class I equipment to detect the dew point temperature of the area in real time. This is to avoid poor ventilation in the instrument area, which could lead to water vapor accumulation in local areas, causing the dew point temperature to rise and increasing the risk of condensation in the pipeline.

[0034] Preferably, ventilation fans are installed in areas where Class I equipment is concentrated to maintain ventilation between these areas and areas where people are active.

[0035] Step 5: Add color markings to the surface of the low-temperature pipeline coating according to different operating temperatures, and set temperature measuring points and inspection ports on pipelines with operating temperatures below the dew point to facilitate on-orbit inspection and handling of condensation.

[0036] According to one embodiment of the present invention, after completing the layout design of the cryogenic piping system for a manned spacecraft, the cryogenic piping and equipment are covered according to the existing covering methods in the manned spacecraft field, and the following improvements are made on this basis: (1) Color markings should be added to the covering layers of pipelines within the centralized layout area of ​​Category I equipment according to their operating temperature, and they should be divided into three categories: operating temperature below the dew point temperature, above the dew point temperature, and above the dew point temperature, so that astronauts can easily and accurately identify the operating temperature of each section of cryogenic pipeline and facilitate on-orbit inspection. If equipment or pipelines outside the centralized layout area of ​​Category I equipment have an operating temperature below the dew point, temperature color markings should also be added. (2) For pipelines with operating temperatures below the dew point or crossing the dew point within the centralized layout area of ​​Class I equipment, a thermistor should be attached to the surface of the coating layer to monitor whether there are areas on the surface of the coating layer with temperatures below the dew point. The same setting should also be made for pipelines with operating temperatures below the dew point outside the centralized layout area of ​​Class I equipment; (3) For pipe coverings with operating temperatures below the dew point or crossing the dew point within the centralized layout area of ​​Category I equipment, an inspection port should be reserved on each independent pipe covering. That is, a covering that can be easily disassembled and installed should be provided, so that astronauts can periodically check through the inspection port whether there is internal condensation caused by inadequate covering. The same setting should also be made for pipes with operating temperatures below the dew point outside the centralized layout area of ​​Category I equipment.

[0037] It is understood that this invention has been described through embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of this invention. Furthermore, under the teachings of this invention, these features and embodiments can be modified to adapt to specific circumstances without departing from the spirit and scope of this invention. Therefore, this invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are protected by this invention.

[0038] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for preventing condensation in a cryogenic piping system within a sealed cabin of a manned spacecraft, characterized in that, Includes the following steps: Based on the relationship between the operating temperature range and dew point temperature of the temperature-controlled equipment in the cryogenic pipeline system, the equipment is divided into two categories: equipment whose upper limit of operating temperature range is below the dew point temperature is defined as Class I equipment, and equipment whose operating temperature range spans the dew point temperature or whose lower limit of operating temperature range is above the dew point temperature is defined as Class II equipment. Class I equipment is placed upstream of the cryogenic piping system, and Class II equipment is placed downstream of the cryogenic piping system; a temperature regulating component is installed between the output end of the circulating pump and the Class I equipment, and a separate secondary temperature regulating component is installed for the Class II equipment to increase the operating temperature of the Class II equipment without affecting the normal operation of the Class I equipment. Under different operating modes and different settings of each temperature regulating component, the temperature distribution of the low-temperature pipeline system is analyzed to identify pipelines with an upper limit of operating temperature below the dew point temperature, operating temperature range spanning the dew point temperature, and lower limit of operating temperature range above the dew point temperature, as well as the operating temperature range of each piece of equipment, and to determine the setting strategy of each temperature regulating component. Based on the temperature distribution obtained from the analysis, equipment and pipelines with an upper limit of operating temperature below the dew point temperature, as well as equipment and pipelines with an operating temperature range exceeding the dew point temperature, are centrally located, and the centrally located area is visible and accessible to the outside world.

2. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: The aforementioned secondary temperature regulation component is separately installed for Class II equipment, specifically in the following manner: A temperature control valve is installed at the junction of Class I and Class II equipment, and the output of the temperature control valve is connected to the downstream temperature control bypass of the Class II equipment.

3. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 2, characterized in that: If the number of Class II equipment and the difference in operating temperature range between the equipment exceed the preset value, the Class II equipment will continue to be split up. Temperature control valves and temperature bypasses will be installed on the pipelines connecting the Class II equipment, and so on.

4. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: The principle for determining the setting strategy of each temperature regulation component is: to ensure that the operating temperature of each device meets the requirements and to maximize the overall operating temperature of the cryogenic pipeline system.

5. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: Air temperature and humidity sensors are deployed in the centralized layout area to detect dew point temperature.

6. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: Ventilation fans should be installed in the centrally located area to maintain ventilation between the area and the people's activity area.

7. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: For the outer covering of pipelines in centralized layout areas, color markings are set according to three categories: the upper limit of the working temperature range is below the dew point temperature, the working temperature range crosses the dew point temperature, and the lower limit of the working temperature range is above the dew point temperature, to facilitate on-orbit inspection.

8. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: For pipelines within a centralized layout area whose upper limit of operating temperature range is below the dew point temperature and whose operating temperature range spans the dew point temperature, a thermistor is attached to the surface of the coating layer to monitor the surface temperature of the coating layer.

9. The anti-condensation design method for the cryogenic piping system inside the sealed cabin of a manned spacecraft according to claim 1, characterized in that: For pipelines within a centralized layout area whose operating temperature range is below the dew point temperature or whose operating temperature range crosses the dew point temperature, inspection ports are reserved on the coating layer for astronauts to periodically check for internal condensation caused by inadequate coating.

10. A cryogenic piping system for preventing condensation inside a sealed cabin of a manned spacecraft, comprising a circulating pump, a heat exchanger, Class I equipment, Class II equipment, and connecting pipes, wherein the Class I equipment is arranged upstream of the cryogenic piping system, and the Class II equipment is arranged downstream of the cryogenic piping system, characterized in that: The Class I equipment is defined as equipment whose upper limit of the operating temperature range is below the dew point temperature, and the Class II equipment is defined as equipment whose operating temperature range crosses the dew point temperature or whose lower limit of the operating temperature range is above the dew point temperature range. A first temperature regulating component is installed between the output end of the circulating pump and the Class I equipment; a second temperature regulating component is installed separately for Class II equipment, which is used to increase the operating temperature of Class II equipment without affecting the normal operation of Class I equipment. Equipment and pipelines with an upper limit of operating temperature below the dew point temperature, and equipment and pipelines with an operating temperature range exceeding the dew point temperature, shall be arranged in a centralized layout, and the centralized layout area shall be visible and accessible to the outside.

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