CN114364232A - Aircraft distributed pump-drive two-phase cooling system - Google Patents
Aircraft distributed pump-drive two-phase cooling systemDownload PDFInfo
- Publication number
- CN114364232A CN114364232ACN202210097756.7ACN202210097756ACN114364232ACN 114364232 ACN114364232 ACN 114364232ACN 202210097756 ACN202210097756 ACN 202210097756ACN 114364232 ACN114364232 ACN 114364232A
- Authority
- CN
- China
- Prior art keywords
- group
- valve
- heat source
- sensor
- inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Landscapes
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
Translated fromChinese
Description
Translated fromChinese技术领域technical field
本发明涉及飞行器环境控制技术领域，特别是涉及一种飞行器分布式泵驱两相冷却系统。The invention relates to the technical field of aircraft environmental control, in particular to a distributed pump-driven two-phase cooling system for aircraft.
背景技术Background technique
随着飞行器性能的不断提升，机载电子设备和高能设备的热负荷急速飞升，采用冲压空气冷却(风冷)和防冻液冷却(液冷)的单相冷却技术潜力已开发殆尽，难以满足飞行器机载设备的冷却需求。因此，亟需发展可匹配机载设备超高热载荷的新型散热技术——泵驱两相冷却技术，该技术利用流动工质的相变吸收和释放大量潜热，换热量和换热系数比当前的风冷和液冷技术高出一个量级，可以满足机载设备的散热需求。然而，飞行器除了不断增大的热负荷之外，还存在机载发热设备多、不同飞行任务下设备热载荷和飞行器热沉不断变化等情况，导致“大热量、多热源、变负荷、变热沉”的协同散热十分困难，所以采用现在的泵驱两相系统无法解决机载设备协同散热的难题，因此，亟需研究布局合理的泵驱两相系统。With the continuous improvement of aircraft performance, the thermal load of airborne electronic equipment and high-energy equipment has skyrocketed. Cooling requirements for aircraft onboard equipment. Therefore, it is urgent to develop a new heat dissipation technology that can match the ultra-high thermal load of airborne equipment—pump-driven two-phase cooling technology. The air-cooled and liquid-cooled technologies of the Jet are an order of magnitude higher, which can meet the cooling needs of airborne equipment. However, in addition to the ever-increasing heat load of the aircraft, there are also many onboard heating devices, and the heat load of the equipment and the heat sink of the aircraft are constantly changing under different flight missions, resulting in "large heat, multiple heat sources, variable loads, and heat." It is very difficult to coordinate heat dissipation of "Shen", so the current pump-driven two-phase system cannot solve the problem of coordinated heat dissipation of airborne equipment. Therefore, it is urgent to study a pump-driven two-phase system with a reasonable layout.
发明内容SUMMARY OF THE INVENTION
本发明的目的是提供一种飞行器分布式泵驱两相冷却系统，可解决机载设备协同散热的难题。The purpose of the present invention is to provide a distributed pump-driven two-phase cooling system for an aircraft, which can solve the problem of coordinated heat dissipation of airborne equipment.
为实现上述目的，本发明提供了如下方案：For achieving the above object, the present invention provides the following scheme:
一种飞行器分布式泵驱两相冷却系统，包括：A distributed pump-driven two-phase cooling system for an aircraft, comprising:
控制器、泵驱模块、工质冷却模块、补偿模块和热源冷却模块；Controller, pump drive module, working fluid cooling module, compensation module and heat source cooling module;
所述泵驱模块包括：第一传感器组、第二传感器组、储液罐、流量计和泵；所述补偿模块包括：第三传感器组、第四传感器组、预热器和再热器；所述热源冷却模块包括：第五传感器组、第六传感器组、第七传感器组、第一阀门组和热源组；所述工质冷却模块包括：冷凝装置和预冷装置；The pump drive module includes: a first sensor group, a second sensor group, a liquid storage tank, a flow meter and a pump; the compensation module includes: a third sensor group, a fourth sensor group, a preheater and a reheater; The heat source cooling module includes: a fifth sensor group, a sixth sensor group, a seventh sensor group, a first valve group and a heat source group; the working fluid cooling module includes: a condensing device and a pre-cooling device;
所述储液罐、所述预冷装置、所述泵、所述流量计、所述预热器、所述第一阀门组、所述热源组、所述冷凝装置、所述再热器和所述储液罐依次连接，所述第一传感器组设置在所述储液罐上；所述第二传感器组设置在所述预冷装置与所述泵之间，所述第三传感器组设置在所述预热器与所述第一阀门组之间；所述第五传感器组设置所述热源组上；所述第六传感器组和所述第七传感器组均设置在所述热源组与所述冷凝装置之间；所述第四传感器组设置在所述再热器和所述储液罐之间，所述控制器分别与所述第一传感器组、所述第二传感器组、所述第三传感器组、所述第四传感器组、所述第五传感器组、所述第六传感器组、所述第七传感器组、所述预冷装置、所述泵、所述预热器、所述再热器、所述第一阀门组和所述冷凝装置连接，所述控制器用于根据所述第一传感器组、所述第二传感器组、所述第三传感器组、所述第四传感器组、所述第五传感器组、所述第六传感器组、所述第七传感器组获得的数据控制所述预冷装置、所述泵、所述预热器、所述再热器、所述第一阀门组和所述冷凝装置工作。the liquid storage tank, the pre-cooling device, the pump, the flow meter, the preheater, the first valve group, the heat source group, the condensing device, the reheater and The liquid storage tanks are connected in sequence, the first sensor group is arranged on the liquid storage tank; the second sensor group is arranged between the pre-cooling device and the pump, and the third sensor group is arranged between the preheater and the first valve group; the fifth sensor group is arranged on the heat source group; the sixth sensor group and the seventh sensor group are both arranged between the heat source group and the heat source group between the condensing devices; the fourth sensor group is arranged between the reheater and the liquid storage tank, and the controller is respectively connected with the first sensor group, the second sensor group, the the third sensor group, the fourth sensor group, the fifth sensor group, the sixth sensor group, the seventh sensor group, the pre-cooling device, the pump, the preheater, The reheater, the first valve group and the condensing device are connected, and the controller is configured to The data obtained by the sensor group, the fifth sensor group, the sixth sensor group, and the seventh sensor group control the precooling device, the pump, the preheater, the reheater, the The first valve group and the condensing device work.
可选的，所述预冷装置包括：预冷器和预冷冷源；所述预冷器的第一入口与所述储液罐的出口连通，所述预冷器的第一出口通过第一管道与所述泵的入口连通；所述预冷器的第二出口与所述预冷冷源的入口连通；所述预冷器的第二入口与所述预冷冷源的出口连通。Optionally, the pre-cooling device includes: a pre-cooler and a pre-cooling cold source; the first inlet of the pre-cooler is communicated with the outlet of the liquid storage tank, and the first outlet of the pre-cooler passes through the first outlet of the pre-cooler. A pipeline is communicated with the inlet of the pump; the second outlet of the precooler is communicated with the inlet of the precooling cold source; the second inlet of the precooler is communicated with the outlet of the precooling cold source.
可选的，所述冷凝装置包括冷凝器和冷凝冷源；所述热源组的出口通过第三管道与所述冷凝器的第一入口连通；所述冷凝器的第一出口与所述再热器的入口连通；所述冷凝器的第二入口与所述冷凝冷源的出口连通，所述冷凝器的第二出口与所述冷凝冷源的入口连通。Optionally, the condensing device includes a condenser and a condensing cold source; the outlet of the heat source group is communicated with the first inlet of the condenser through a third pipe; the first outlet of the condenser is connected to the reheating The inlet of the condenser is communicated with the inlet of the condenser; the second inlet of the condenser is communicated with the outlet of the condensation cooling source, and the second outlet of the condenser is communicated with the inlet of the cooling cooling source.
可选的，所述热源冷却模块还包括：第二阀门组；所述第二阀门组设置在所述第三管道上。Optionally, the heat source cooling module further includes: a second valve group; the second valve group is arranged on the third pipeline.
可选的，所述第一传感器组包括：第一压力传感器和第一温度传感器；所述第二传感器组包括：第二压力传感器和第二温度传感器；所述第三传感器组包括第三压力传感器和第三温度传感器；所述第四传感器组包括第十温度传感器和第五压力传感器。Optionally, the first sensor group includes: a first pressure sensor and a first temperature sensor; the second sensor group includes: a second pressure sensor and a second temperature sensor; the third sensor group includes a third pressure sensor sensor and a third temperature sensor; the fourth sensor group includes a tenth temperature sensor and a fifth pressure sensor.
可选的，所述第一阀门组包括第一阀门、第二阀门和第三阀门；所述热源组包括第一热源、第二热源和第三热源；所述第二阀门组包括第一单向阀、第二单向阀和第三单向阀；Optionally, the first valve group includes a first valve, a second valve and a third valve; the heat source group includes a first heat source, a second heat source and a third heat source; the second valve group includes a first single A check valve, a second check valve and a third check valve;
所述第一阀门的入口、所述第二阀门的入口和所述第三阀门的入口均与所述预热器的出口连通；所述第一阀门的出口与所述第一热源的入口连通；所述第一热源的出口与所述第一单向阀的入口连通；所述第二阀门的出口与所述第二热源的入口连通，所述第二热源的出口与所述第二单向阀的入口连通；所述第三阀门的出口与所述第三热源的入口连通，所述第三热源的出口与所述第三单向阀的入口连通；所述第一单向阀的出口、所述第二单向阀的出口和所述第三单向阀的出口均与所述冷凝装置的入口连通。The inlet of the first valve, the inlet of the second valve and the inlet of the third valve are all communicated with the outlet of the preheater; the outlet of the first valve is communicated with the inlet of the first heat source ; The outlet of the first heat source is communicated with the inlet of the first one-way valve; the outlet of the second valve is communicated with the inlet of the second heat source, and the outlet of the second heat source is communicated with the second one-way valve The inlet of the valve is communicated with the inlet of the valve; the outlet of the third valve is communicated with the inlet of the third heat source, and the outlet of the third heat source is communicated with the inlet of the third one-way valve; The outlet, the outlet of the second check valve and the outlet of the third check valve are all communicated with the inlet of the condensing device.
可选的，所述第五传感器组包括：第四温度传感器、第五温度传感器和第六温度传感器；所述第四温度传感器设置在所述第一热源上，所述第五温度传感器设置在所述第二热源上；所述第六温度传感器设置在所述第三热源上。Optionally, the fifth sensor group includes: a fourth temperature sensor, a fifth temperature sensor and a sixth temperature sensor; the fourth temperature sensor is arranged on the first heat source, and the fifth temperature sensor is arranged on the on the second heat source; the sixth temperature sensor is arranged on the third heat source.
可选的，所述第六传感器组包括：第七温度传感器、第八温度传感器和第九温度传感器；所述第七温度传感器设置在所述第一热源与所述第一单向阀之间，所述第八温度传感器设置在所述第二热源与所述第二单向阀之间；所述第九温度传感器设置在所述第三热源与所述第三单向阀之间。Optionally, the sixth sensor group includes: a seventh temperature sensor, an eighth temperature sensor and a ninth temperature sensor; the seventh temperature sensor is arranged between the first heat source and the first one-way valve , the eighth temperature sensor is arranged between the second heat source and the second one-way valve; the ninth temperature sensor is arranged between the third heat source and the third one-way valve.
可选的，所述第七传感器组为：第四压力传感器；所述第四压力传感器设置在所述第一单向阀的出口、所述第二单向阀的出口和所述第三单向阀的出口与所述冷凝装置的入口之间。Optionally, the seventh sensor group is: a fourth pressure sensor; the fourth pressure sensor is arranged at the outlet of the first check valve, the outlet of the second check valve and the third check valve between the outlet of the valve and the inlet of the condensing device.
根据本发明提供的具体实施例，本发明公开了以下技术效果：本发明储液罐、预冷装置、泵、流量计、预热器、第一阀门组、热源组、冷凝装置、再热器和储液罐依次连接，第一传感器组设置在储液罐上；第二传感器组设置在预冷装置与泵之间，第三传感器组设置在预热器与第一阀门组之间；第五传感器组设置热源组上；第六传感器组和第七传感器组均设置在热源组与冷凝装置之间；第四传感器组设置在再热器和储液罐之间，控制器分别与传感器组、预冷装置、泵、预热器、再热器、第一阀门组和冷凝装置连接，控制器根据传感器的数据控制预冷装置、泵、预热器、再热器、第一阀门组和冷凝装置工作，可以解决机载设备协同散热的难题。According to the specific embodiments provided by the present invention, the present invention discloses the following technical effects: the liquid storage tank, the precooling device, the pump, the flow meter, the preheater, the first valve group, the heat source group, the condensing device, the reheater of the present invention connected to the liquid storage tank in sequence, the first sensor group is arranged on the liquid storage tank; the second sensor group is arranged between the pre-cooling device and the pump, and the third sensor group is arranged between the preheater and the first valve group; The five sensor groups are arranged on the heat source group; the sixth sensor group and the seventh sensor group are both arranged between the heat source group and the condensing device; the fourth sensor group is arranged between the reheater and the liquid storage tank, and the controller is connected to the sensor group respectively. , the pre-cooling device, the pump, the pre-heater, the reheater, the first valve group and the condensing device are connected, and the controller controls the pre-cooling device, the pump, the pre-heater, the reheater, the first valve group and the condensing device according to the data of the sensor. The condensing device works, which can solve the problem of coordinated heat dissipation of airborne equipment.
附图说明Description of drawings
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings required in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some of the present invention. In the embodiments, for those of ordinary skill in the art, other drawings can also be obtained according to these drawings without creative labor.
图1为本发明实施例提供的飞行器分布式泵驱两相冷却系统的结构示意图。FIG. 1 is a schematic structural diagram of a distributed pump-driven two-phase cooling system for an aircraft according to an embodiment of the present invention.
符号说明：Symbol Description:
1-飞行器，2-预冷器，3-泵，4-预热器，5-第一热源，6-第二热源，7-第三热源，8-冷凝器，9-再热器，10-储液罐，11-第一阀门，12-第二阀门，13-第三阀门，14-第一单向阀，15-第二单向阀，16-第三单向阀，17-冷凝冷源，18-预冷冷源，19-流量计，20-第一压力传感器，21-第二压力传感器，22-第三压力传感器，23-第四压力传感器，24-第一温度传感器，25-第二温度传感器，26-第三温度传感器，27-第四温度传感器，28-第七温度传感器，29-第五温度传感器，30-第八温度传感器，31-第六温度传感器，32-第九温度传感器，33-第十温度传感器，34-第五压力传感器，35-控制器。1-aircraft, 2-precooler, 3-pump, 4-preheater, 5-first heat source, 6-second heat source, 7-third heat source, 8-condenser, 9-reheater, 10 -Liquid reservoir, 11-First valve, 12-Second valve, 13-Third valve, 14-First check valve, 15-Second check valve, 16-Third check valve, 17-Condensation Cold source, 18-precooling cold source, 19-flow meter, 20-first pressure sensor, 21-second pressure sensor, 22-third pressure sensor, 23-fourth pressure sensor, 24-first temperature sensor, 25-second temperature sensor, 26-third temperature sensor, 27-fourth temperature sensor, 28-seventh temperature sensor, 29-fifth temperature sensor, 30-eighth temperature sensor, 31-sixth temperature sensor, 32 - ninth temperature sensor, 33 - tenth temperature sensor, 34 - fifth pressure sensor, 35 - controller.
具体实施方式Detailed ways
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
为使本发明的上述目的、特征和优点能够更加明显易懂，下面结合附图和具体实施方式对本发明作进一步详细的说明。In order to make the above objects, features and advantages of the present invention more clearly understood, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.
本发明公开了一种飞行器分布式泵驱两相冷却系统，包括泵驱模块、热源冷却模块、工质冷却模块、补偿模块和控制模块；泵驱模块为系统提供动力使工质循环流动；热源冷却模块通过流动沸腾吸收热源热量；工质冷却模块利用冷凝装置通过流动冷凝排出系统热量并利用预冷装置通过过冷措施(降温)保证进入泵3的工质为过冷液态；补偿模块利用预热器4、第三温度传感器26、第三压力传感器22，通过热量补偿的方式调节进入热源冷却模块的工质的干度利用再热器9、第十温度传感器33、第五压力传感器34，以热量补偿的方式调节系统压力，继而调节进入热源冷却模块的工质饱和压力等状态参数；控制模块依据采集到的温度、压力和流量信号，调节泵驱模块中泵3的转速、补偿模块的加热量、工质冷却模块的冷量输入、热源冷却模块的阀门开度等，确保各工况下系统均可及时调整至合理状态，从而使热源温度始终保持在设定范围内，具体如图1所示，飞行器分布式泵驱两相冷却系统，包括：控制器35、泵驱模块、工质冷却模块、补偿模块和热源冷却模块；所述泵驱模块包括：第一传感器组、第二传感器组、储液罐10、流量计19和泵3；所述补偿模块包括：第三传感器组、第四传感器组、预热器4和再热器9；所述热源冷却模块包括：第五传感器组、第六传感器组、第七传感器组、第一阀门组和热源组；所述工质冷却模块包括：冷凝装置和预冷装置；所述储液罐10、所述预冷装置、所述泵3、所述流量计19、所述预热器4、所述第一阀门组、所述热源组、所述冷凝装置、所述再热器9和所述储液罐10依次连接，所述第一传感器组设置在所述储液罐10上；所述第二传感器组设置在所述预冷装置与所述泵3之间，所述第三传感器组设置在所述预热器4与所述第一阀门组之间；所述第五传感器组设置所述热源组上；所述第六传感器组和所述第七传感器组均设置在所述热源组与所述冷凝装置之间；所述第四传感器组设置在所述再热器9和所述储液罐10之间，所述控制器35分别与所述第一传感器组、所述第二传感器组、所述第三传感器组、所述第四传感器组、所述第五传感器组、所述第六传感器组、所述第七传感器组、所述预冷装置、所述泵3、所述预热器4、所述再热器9、所述第一阀门组和所述冷凝装置连接，所述控制器35用于根据所述第一传感器组、所述第二传感器组、所述第三传感器组、所述第四传感器组、所述第五传感器组、所述第六传感器组、所述第七传感器组获得的数据控制所述预冷装置、所述泵3、所述预热器4、所述再热器9、所述第一阀门组和所述冷凝装置工作，具体的所述储液罐10的出口与所述预冷装置的入口连通，所述预冷装置的出口通过第一管道与所述泵3的入口连通；所述泵3的出口与所述流量计19的入口连通，所述流量计19的出口与所述预热器4的入口连通，所述预热器4的出口通过第二管道与所述第一阀门组的入口连通；所述第一阀门组的出口与所述热源组的入口连通，所述热源组的出口通过第三管道与所述冷凝装置的入口连通；所述冷凝装置的出口与所述再热器9的入口连通；所述再热器9的出口与所述储液罐10的入口通过第四管道连通，所述第一传感器组设置在所述储液罐10上；所述第二传感器组设置在所述第一管道上，所述第三传感器组设置在所述第二管道上；所述第五传感器组设置所述热源组上；所述第六传感器组和所述第七传感器组均设置在所述第三管道上；所述第四传感器组设置在所述第四管道上。The invention discloses a distributed pump-driven two-phase cooling system for an aircraft, comprising a pump-driven module, a heat source cooling module, a working medium cooling module, a compensation module and a control module; the pump-driven module provides power for the system to make the working medium circulate; a heat source The cooling module absorbs the heat of the heat source through flow boiling; the working fluid cooling module uses the condensing device to discharge the heat of the system through flow condensation, and uses the pre-cooling device to ensure that the working fluid entering the pump 3 is sub-cooled liquid through sub-cooling measures (cooling); the compensation module uses pre-cooling. The heater 4, the third temperature sensor 26, and the third pressure sensor 22 adjust the dryness of the working medium entering the heat source cooling module by means of heat compensation, using the reheater 9, the
作为一种可选的实施方式，所述预冷装置包括：预冷器2和预冷冷源18；所述预冷器2的第一入口与所述储液罐10的出口连通，所述预冷器2的第一出口通过第一管道与所述泵3的入口连通；所述预冷器2的第二出口与所述预冷冷源18的入口连通；所述预冷器2的第二入口与所述预冷冷源18的出口连通。As an optional embodiment, the pre-cooling device includes: a pre-cooler 2 and a pre-cooling
作为一种可选的实施方式，所述冷凝装置包括冷凝器8和冷凝冷源17；所述热源组的出口通过第三管道与所述冷凝器8的第一入口连通；所述冷凝器8的第一出口与所述再热器9的入口连通；所述冷凝器8的第二入口与所述冷凝冷源17的出口连通，所述冷凝器8的第二出口与所述冷凝冷源17的入口连通。As an optional embodiment, the condensing device includes a
作为一种可选的实施方式，所述热源冷却模块还包括：第二阀门组；所述第二阀门组设置在所述第三管道上。As an optional implementation manner, the heat source cooling module further includes: a second valve group; the second valve group is arranged on the third pipeline.
作为一种可选的实施方式，所述第一传感器组包括：第一压力传感器20和第一温度传感器24；所述第二传感器组包括：第二压力传感器21和第二温度传感器25；所述第三传感器组包括第三压力传感器22和第三温度传感器26；所述第四传感器组包括第十温度传感器33和第五压力传感器34。As an optional implementation manner, the first sensor group includes: a first pressure sensor 20 and a
作为一种可选的实施方式，所述第一阀门组包括第一阀门11、第二阀门12和第三阀门13；所述热源组包括第一热源5、第二热源6和第三热源7；所述第二阀门组包括第一单向阀14、第二单向阀15和第三单向阀16；所述第一阀门11的入口、所述第二阀门12的入口和所述第三阀门13的入口均与所述预热器4的出口连通；所述第一阀门11的出口与所述第一热源5的入口连通；所述第一热源5的出口与所述第一单向阀14的入口连通；所述第二阀门12的出口与所述第二热源6的入口连通，所述第二热源6的出口与所述第二单向阀15的入口连通；所述第三阀门13的出口与所述第三热源7的入口连通，所述第三热源7的出口与所述第三单向阀16的入口连通；所述第一单向阀14的出口、所述第二单向阀15的出口和所述第三单向阀16的出口均与所述冷凝装置的入口连通，热源数量更多或更少时，所述泵驱两相冷却系统及其控制方法仍适用。As an optional embodiment, the first valve group includes a first valve 11 , a
作为一种可选的实施方式，所述第五传感器组包括：第四温度传感器27、第五温度传感器29和第六温度传感器31；所述第四温度传感器27设置在所述第一热源5上，所述第五温度传感器29设置在所述第二热源6上；所述第六温度传感器31设置在所述第三热源7上。As an optional implementation manner, the fifth sensor group includes: a fourth temperature sensor 27 , a fifth temperature sensor 29 and a
作为一种可选的实施方式，所述第六传感器组包括：第七温度传感器28、第八温度传感器30和第九温度传感器32；所述第七温度传感器28设置在所述第一热源5与所述第一单向阀14之间，所述第八温度传感器30设置在所述第二热源6与所述第二单向阀15之间；所述第九温度传感器32设置在所述第三热源7与所述第三单向阀16之间。As an optional implementation manner, the sixth sensor group includes: a
作为一种可选的实施方式，所述第七传感器组为：第四压力传感器23；所述第四压力传感器23设置在所述第一单向阀14的出口、所述第二单向阀15的出口和所述第三单向阀16的出口与所述冷凝装置的入口之间。As an optional implementation manner, the seventh sensor group is: a fourth pressure sensor 23; the fourth pressure sensor 23 is disposed at the outlet of the first one-way valve 14 and the second one-way valve Between the outlet of 15 and the outlet of the third one-way valve 16 and the inlet of the condensing device.
作为一种可选的实施方式，所示第三传感器组设置在所述第一阀门11的入口、所述第二阀门12的入口和所述第三阀门13的入口与所述预热器4的出口之间。As an optional implementation manner, the third sensor group shown is disposed at the inlet of the first valve 11 , the inlet of the
作为一种可选的实施方式，所述冷凝冷源17和预冷冷源18，可以是飞行器1上的冲压空气、燃油、防冻液等不同形式的热沉。As an optional embodiment, the
本实施例飞行器分布式泵驱两相冷却系统的工作过程如下：The working process of the distributed pump-driven two-phase cooling system for the aircraft of the present embodiment is as follows:
泵驱模块中的泵将工质从储液罐中抽取，工质经过工质冷却模块的预冷器被冷却至过冷状态进入泵，随后进入补偿模块的预热器被加热至饱和状态和设定干度，然后进入热源冷却模块，通过第一阀门、第二阀门、第三阀门分别进入第一热源、第二热源、第三热源，通过流动沸腾将热源热量带走，再通过第一单向阀、第二单向阀、第三单向阀进入工质冷却模块的冷凝器，通过流动冷凝将热量传递给冷凝冷源，随后工质进入补偿模块的再热器被加热，最后流回储液罐。当热源负荷变化时，控制器调节泵的转速，改变系统流量，调节第一阀门、第二阀门、第三阀门的开度，使流过热源的流量与其热负荷相匹配，改变补偿模块中预热器的加热量使工质重新达到饱和状态和设定干度，改变工质冷却模块中预冷冷源和冷凝冷源的冷量输入以及补偿模块中再热器的加热量使系统重新达到热量输入和冷量输入的平衡，从而实现系统的稳定运行。The pump in the pump drive module extracts the working medium from the liquid storage tank, and the working medium is cooled to a subcooled state through the pre-cooler of the working medium cooling module, and then enters the pre-heater of the compensation module to be heated to a saturated state and Set the dryness, and then enter the heat source cooling module, enter the first heat source, the second heat source, and the third heat source through the first valve, the second valve, and the third valve, respectively. The one-way valve, the second one-way valve and the third one-way valve enter the condenser of the working fluid cooling module, and transfer heat to the condensing cold source through flow condensation, and then the working fluid enters the reheater of the compensation module to be heated, and finally flows into the condenser. back to the reservoir. When the heat source load changes, the controller adjusts the speed of the pump, changes the system flow, adjusts the opening of the first valve, the second valve, and the third valve, so that the flow through the heat source matches its heat load, and changes the preset in the compensation module. The heating capacity of the heater makes the working fluid reach the saturation state and set dryness again, change the cooling capacity input of the pre-cooling cold source and the condensing cold source in the working fluid cooling module and the heating capacity of the reheater in the compensation module to make the system reach a new level. The balance of heat input and cooling input, so as to achieve stable operation of the system.
本发明相对于现有技术取得了以下技术效果：The present invention has achieved the following technical effects with respect to the prior art:
1、本发明的飞行器分布式泵驱两相冷却系统解决了飞行器“大热量、多热源、变负荷、变热沉”协同散热的难题，实现了飞行器环控系统的紧凑高效和技术革新。本发明通过对飞行器泵驱两相冷却系统的构型和控制策略进行设计，利用流动沸腾、流动冷凝、冷热补偿、动态调节等技术，使得机载设备温度始终被控制在合理范围内。1. The aircraft distributed pump-driven two-phase cooling system of the present invention solves the problem of "large heat, multiple heat sources, variable loads, and variable heat sinks" for coordinated heat dissipation of the aircraft, and realizes the compactness, efficiency and technological innovation of the aircraft environmental control system. The invention designs the configuration and control strategy of the aircraft pump-driven two-phase cooling system, and utilizes technologies such as flow boiling, flow condensation, cold and heat compensation, and dynamic adjustment, so that the temperature of the airborne equipment is always controlled within a reasonable range.
2、控制器依据采集到的温度、压力和流量信号，调节泵驱模块中泵的转速、补偿模块的加热量、工质冷却模块的冷量输入、热源冷却模块的阀门开度等，确保热源负荷动态变化时，系统及时调整至合理状态，从而使热源温度始终保持在设定范围内。2. The controller adjusts the speed of the pump in the pump drive module, the heating capacity of the compensation module, the cooling capacity input of the working fluid cooling module, the valve opening of the heat source cooling module, etc., according to the collected temperature, pressure and flow signals to ensure the heat source When the load changes dynamically, the system adjusts to a reasonable state in time, so that the temperature of the heat source is always kept within the set range.
3、控制器通过泵调节系统中工质流量；通过第一阀门、第二阀门、第三阀门调节进入第一热源、第二热源、第三热源的工质流量；通过第一单向阀、第二单向阀、第三单向阀防止工质倒流；通过预热器、再热器补偿系统热量的不足以及提升系统压力；通过冷凝冷源、预冷冷源控制系统冷量输入以及降低系统压力；通过系统热量输入和冷量输入的平衡保证系统的稳定运行。3. The controller adjusts the flow rate of the working medium in the system through the pump; adjusts the flow rate of the working medium entering the first heat source, the second heat source and the third heat source through the first valve, the second valve and the third valve; The second one-way valve and the third one-way valve prevent the backflow of the working medium; compensate for the lack of system heat and increase the system pressure through the preheater and reheater; control the cooling capacity input of the system and reduce System pressure; ensure the stable operation of the system through the balance of heat input and cooling input of the system.
本说明书中各个实施例采用递进的方式描述，每个实施例重点说明的都是与其他实施例的不同之处，各个实施例之间相同相似部分互相参见即可。The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other.
本文中应用了具体个例对本发明的原理及实施方式进行了阐述，以上实施例的说明只是用于帮助理解本发明的方法及其核心思想；同时，对于本领域的一般技术人员，依据本发明的思想，在具体实施方式及应用范围上均会有改变之处。综上所述，本说明书内容不应理解为对本发明的限制。In this paper, specific examples are used to illustrate the principles and implementations of the present invention. The descriptions of the above embodiments are only used to help understand the methods and core ideas of the present invention; meanwhile, for those skilled in the art, according to the present invention There will be changes in the specific implementation and application scope. In conclusion, the contents of this specification should not be construed as limiting the present invention.
Claims (9)
Translated fromChinesePriority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210097756.7ACN114364232B (en) | 2022-01-27 | 2022-01-27 | A Distributed Pump Drive Two-Phase Cooling System for Aircraft |
| PCT/CN2022/093801WO2023142314A1 (en) | 2022-01-27 | 2022-05-19 | Distributed pumped two-phase cooling system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210097756.7ACN114364232B (en) | 2022-01-27 | 2022-01-27 | A Distributed Pump Drive Two-Phase Cooling System for Aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114364232Atrue CN114364232A (en) | 2022-04-15 |
| CN114364232B CN114364232B (en) | 2023-03-03 |
Family
ID=81092373
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210097756.7AActiveCN114364232B (en) | 2022-01-27 | 2022-01-27 | A Distributed Pump Drive Two-Phase Cooling System for Aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN114364232B (en) |
| WO (1) | WO2023142314A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023142314A1 (en)* | 2022-01-27 | 2023-08-03 | 南京航空航天大学 | Distributed pumped two-phase cooling system for aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN208590199U (en)* | 2018-05-21 | 2019-03-08 | 北京空间飞行器总体设计部 | A cooling system based on a compressor and a pump-driven two-phase fluid circuit |
| CN110822961A (en)* | 2019-11-26 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Two-phase fluid cooling system |
| CN112292004A (en)* | 2020-10-27 | 2021-01-29 | 株洲中车时代电气股份有限公司 | Pump-driven two-phase cooling system and working method thereof |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078806B (en)* | 2020-09-25 | 2022-12-30 | 中国直升机设计研究所 | Helicopter liquid cooling integrated control system |
| CN112218497B (en)* | 2020-10-10 | 2021-08-13 | 西安交通大学 | A two-phase cooling loop active control system and method |
| US11273925B1 (en)* | 2020-10-14 | 2022-03-15 | Rolls-Royce North American Technologies Inc. | Thermal management system and method for cooling a hybrid electric aircraft propulsion system |
| CN114364232B (en)* | 2022-01-27 | 2023-03-03 | 南京航空航天大学 | A Distributed Pump Drive Two-Phase Cooling System for Aircraft |
- 2022
- 2022-01-27CNCN202210097756.7Apatent/CN114364232B/enactiveActive
- 2022-05-19WOPCT/CN2022/093801patent/WO2023142314A1/ennot_activeCeased
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN208590199U (en)* | 2018-05-21 | 2019-03-08 | 北京空间飞行器总体设计部 | A cooling system based on a compressor and a pump-driven two-phase fluid circuit |
| CN110822961A (en)* | 2019-11-26 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Two-phase fluid cooling system |
| CN112292004A (en)* | 2020-10-27 | 2021-01-29 | 株洲中车时代电气股份有限公司 | Pump-driven two-phase cooling system and working method thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023142314A1 (en)* | 2022-01-27 | 2023-08-03 | 南京航空航天大学 | Distributed pumped two-phase cooling system for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2023142314A1 (en) | 2023-08-03 |
| CN114364232B (en) | 2023-03-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102954615B (en) | Thermal management system of electric automobile and electric automobile | |
| CN201350573Y (en) | Machine tool spindle cooling device | |
| CN108601314A (en) | A kind of liquid cooling system and flow rate adjusting method | |
| CN102381479B (en) | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct | |
| WO2022048547A1 (en) | Temperature control system, communication device, and temperature control method | |
| CN102390538A (en) | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet | |
| CN112078806B (en) | Helicopter liquid cooling integrated control system | |
| CN108834378A (en) | Airborne spray cooling system using ram air and evaporative refrigeration cycle cooling circulating water | |
| CN109731624A (en) | A high-precision two-stage temperature control system for scientific experiment cabinet based on semiconductor heat pump | |
| CN102390536A (en) | Three-wheel pressure-boosting refrigerating and liquid cooling composite thermal energy managing system | |
| CN112693617B (en) | A fuel heat sink composite mode pump drive two-phase flow cooling system and method | |
| CN105431011A (en) | a liquid cooling system | |
| CN109850168B (en) | Tank Cooling Subsystem for Aircraft Thermal Management System | |
| CN114867293A (en) | A microchannel liquid-cooled coupled air-cooled system | |
| CN114364232B (en) | A Distributed Pump Drive Two-Phase Cooling System for Aircraft | |
| CN104375531A (en) | Combined temperature control system and method adapting to single-phase fluid loop | |
| CN114251889B (en) | A dual-path temperature-controlled circulating fluid supply system and control method for laboratory equipment | |
| CN104680247A (en) | Method for optimizing industrial circulating water system | |
| CN110332762A (en) | Gas and nitrogen cycle temperature adjustment method and system | |
| CN114885569A (en) | Cooling system | |
| CN104296428A (en) | Device for regulating energy of vapor compression cycle refrigeration type cold liquid unit | |
| CN107992127A (en) | High Accuracy Constant Temperature recirculated cooling water device based on Dynamic Thermal capacitor filter | |
| CN105636404A (en) | Liquid cooling system for avionic device | |
| CN117608330A (en) | Constant-temperature water-cooling temperature control system for isolating external environment disturbance | |
| CN207652235U (en) | A kind of power station technical water supply system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |