CN116887588A - Aircraft phase transition temperature control system - Google Patents
Aircraft phase transition temperature control system Download PDFInfo
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- CN116887588A CN116887588A CN202311117737.7A CN202311117737A CN116887588A CN 116887588 A CN116887588 A CN 116887588A CN 202311117737 A CN202311117737 A CN 202311117737A CN 116887588 A CN116887588 A CN 116887588A
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- 230000007704 transition Effects 0.000 title description 2
- 239000007788 liquid Substances 0.000 claims abstract description 68
- 238000001816 cooling Methods 0.000 claims abstract description 45
- 238000005507 spraying Methods 0.000 claims abstract description 24
- 238000004891 communication Methods 0.000 claims abstract description 21
- 238000007789 sealing Methods 0.000 claims abstract description 5
- 238000002347 injection Methods 0.000 claims description 25
- 239000007924 injection Substances 0.000 claims description 25
- 230000008859 change Effects 0.000 claims description 16
- 230000002093 peripheral effect Effects 0.000 claims description 15
- 239000003507 refrigerant Substances 0.000 claims description 14
- 230000017525 heat dissipation Effects 0.000 claims description 10
- 238000010438 heat treatment Methods 0.000 abstract description 8
- 210000001503 joint Anatomy 0.000 abstract 2
- 239000002826 coolant Substances 0.000 description 86
- 239000012071 phase Substances 0.000 description 12
- 230000000694 effects Effects 0.000 description 11
- 230000009471 action Effects 0.000 description 10
- 238000005338 heat storage Methods 0.000 description 5
- 230000004308 accommodation Effects 0.000 description 3
- 238000009835 boiling Methods 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000037452 priming Effects 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
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
- H05K7/20845—Modifications to facilitate cooling, ventilating, or heating for automotive electronic casings
- H05K7/20881—Liquid coolant with phase change
-
- 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
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
- H05K7/20327—Accessories for moving fluid, for connecting fluid conduits, for distributing fluid or for preventing leakage, e.g. pumps, tanks or manifolds
-
- 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
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
- H05K7/20336—Heat pipes, e.g. wicks or capillary pumps
-
- 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
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
- H05K7/20381—Thermal management, e.g. evaporation control
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
Abstract
The invention relates to the technical field of aircraft thermal management, in particular to an aircraft phase-change temperature control system. The system comprises a first shell device, a second shell device, a first cooling device and a second cooling device. The first cooling device comprises a circulating pump, a conveying pipeline, a liquid spraying part and a first heat exchanging part. The second housing means accommodates the first heat exchanging portion. The second shell device, the circulating pump and the liquid spraying part are communicated in sequence. The upper end and the lower end of the first heat exchange part are communicated through a large channel. The first heat exchange portion accommodates the second cooling device. The second heat exchange part of the second cooling device comprises a second heat exchange body, a thick channel, a thin channel, a heat exchange base and a communication cavity. The upper end and the lower end of the second heat exchange body are communicated through a thick channel and a thin channel. The heat exchange base is in butt joint with the second heat exchange body to form sealing connection, and a communication cavity is formed at the butt joint. The upper end of the coarse channel is communicated with the upper end of the fine channel through a communication cavity. Thus, the problem of how to improve the heat exchange efficiency with the heating component of the aircraft is solved.
Description
Technical Field
The invention relates to the technical field of aircraft thermal management, in particular to an aircraft phase-change temperature control system.
Background
In recent years, the automation development of aircrafts is rapid, more and more electronic devices are used by aircrafts, a great amount of thermal load is often generated when the electronic devices work under different working conditions, and the electronic devices need to be subjected to effective heat dissipation treatment in time, so that the working faults of the electronic devices in a high-temperature environment are avoided, and the normal flight of the aircrafts is ensured. Aiming at the heat dissipation problem of the aircraft electronic equipment, the traditional single heat dissipation mode often has certain limitation, and the heat exchange efficiency of the aircraft electronic equipment under the high-temperature working condition is low. Therefore, some distributed integrated comprehensive cooling systems are widely applied, various new heat exchange modes and heat exchange systems are invented and utilized, the invention provides a new heat dissipation system, the heat exchange efficiency with the electronic equipment is further improved by adopting a mode of strong coupling of various heat dissipation modes, the operation is convenient, the temperature of the electronic equipment during working can be timely reduced, and a certain guarantee is provided for flight safety.
Disclosure of Invention
In order to solve the problem of how to improve the heat exchange efficiency with the heating component of the aircraft, the invention provides a phase-change temperature control system of the aircraft, which comprises:
a first housing means;
a second housing means disposed within a hollow cavity formed within the first housing means; a hollow accommodating cavity is formed in the second shell device;
a first cooling device disposed in a hollow cavity formed inside the first housing device; the first cooling device comprises a circulating pump, a conveying pipeline, a liquid spraying part and a first heat exchange part; the first heat exchange part is arranged in the accommodating cavity of the second shell device; the liquid spraying part is arranged at the top of the first heat exchange part; the second shell device, the circulating pump and the liquid spraying part are sequentially communicated through the conveying pipeline; a hollow cavity is formed in the first heat exchange part; the first heat exchange part comprises a large channel; the large channel is arranged on the outer peripheral side of the hollow cavity; the upper end and the lower end of the first heat exchange part are communicated through the large channel;
the second cooling device is arranged in the hollow cavity of the first heat exchange part; the second cooling device is positioned below the liquid spraying part; the second cooling device comprises a second heat exchange part; the second heat exchange part comprises a second heat exchange body, a coarse channel, a fine channel, a heat exchange base and a communication cavity; the upper end and the lower end of the second heat exchange body are communicated through the thick channel; the upper end and the lower end of the second heat exchange body are communicated through the fine channel; the thick channel and the thin channel are arranged at intervals in the second heat exchange body; the lower end face of the heat exchange base is abutted with the upper end of the second heat exchange body to form sealing connection; a communication cavity is arranged at the joint of the heat exchange base and the second heat exchange body; the upper end of the thick channel is communicated with the upper end of the thin channel through the communication cavity.
In some embodiments, the second heat exchange portion further comprises a connecting capillary; the connecting capillary is arranged in the communication cavity; the upper end of the thick channel is communicated with the upper end of the thin channel through the connecting capillary.
In some embodiments, the second heat exchange portion further comprises a bottom wick; the bottom capillary is in abutting connection with the lower end face of the second heat exchange body; the lower end of the thick channel is communicated with the accommodating cavity of the second shell device through the bottom capillary; the lower end of the thin channel is communicated with the accommodating cavity of the second shell device through the bottom capillary.
In some embodiments, the second heat exchange portion further comprises a diagonal channel; one end of the inclined channel is communicated with the thick channel at the outer periphery of the second heat exchange body; the other end of the inclined channel obliquely passes through the first heat exchange part downwards and extends to the accommodating cavity of the second shell device; and one end of the inclined channel, which is close to the thick channel, is provided with an upward bent arc section.
In some embodiments, the inclined channel extends to an end of the receiving cavity of the second housing means and is provided with an upwardly curved arcuate segment.
In some embodiments, the second heat exchange portion comprises a plurality of the inclined channels; the height positions of the connecting ports for communicating the inclined channels with the thick channels are different.
In some embodiments, the first heat exchange portion further comprises an inclined enclosure; the inclined surrounding baffle is arranged on the upper end face of the first heat exchange part; the inclined surrounding block is arranged in a ring shape and surrounds the outer peripheral side of the upper port of the large channel; the high side of the inclined enclosure is adjacent to the upper port of the large channel; the lower side of the sloped enclosure extends in a direction away from the upper port of the large channel.
In some embodiments, the first heat exchange portion further comprises a porous cover plate; the porous cover plate is arranged on the upper end face of the first heat exchange part; the porous cover plate is arranged in a ring shape and is arranged on the outer periphery side of the inclined enclosure; the porous cover plate is provided with a plurality of through holes; the through hole communicates the space at the upper part of the porous cover plate with the space of the accommodating cavity of the second shell device.
In some embodiments, the first housing means comprises a vent; the exhaust part comprises an exhaust pipeline and a control valve; the exhaust pipeline communicates the internal cavity of the first shell device with the external space of the first shell device; the control valve is arranged on the exhaust pipeline.
In some embodiments, the first housing means comprises a heat sink; the heat dissipation part comprises a heat exchanger and a refrigerant pipeline; the refrigerant pipeline is communicated with the heat exchanger; the heat exchanger is arranged on the outer periphery side of the second shell device; the heat of the second shell device is transferred to the external space of the first shell device through the refrigerant pipeline.
In some embodiments, the first housing means comprises a liquid injection portion; the liquid injection part comprises a liquid injection pipeline and a liquid injection valve; the liquid injection pipeline is used for communicating the external space of the first shell device with the internal cavity of the second shell device; the liquid injection valve is arranged on the liquid injection pipeline.
In order to solve the problem of how to improve the heat exchange efficiency with the heating component of the aircraft, the invention has the following advantages:
the first heat exchange part of the first cooling device is used for accommodating the second cooling device, so that the first cooling device and the second cooling device can share one conveying pipeline and one circulating pump, pipeline branches are reduced, and the weight of the whole phase-change temperature control system is reduced. The liquid spraying part is arranged at the top of the second heat exchange part to spray the cooling medium to the top of the heating component, and meanwhile, the cooling medium in the accommodating cavity of the second shell device cools the bottom of the heating component through the capillary action of the channel of the second heat exchange part, so that the spray cooling and the gas-liquid phase change cooling are combined in a strong coupling mode, various heat exchange modes are mutually promoted and supplemented, and the heat dissipation effect is enhanced.
Drawings
FIG. 1 illustrates an overall schematic diagram of an aircraft phase change temperature control system of an embodiment;
fig. 2 shows a schematic perspective view of a second housing arrangement of an embodiment in combination with a first heat exchanger and a second cooling arrangement;
FIG. 3 shows a schematic top view of a second housing arrangement of an embodiment in combination with a first heat exchange section and a second cooling arrangement;
FIG. 4 shows a schematic cross-sectional view of a second housing arrangement of an embodiment in combination with a first heat exchanging portion and a second cooling arrangement;
FIG. 5 shows a schematic cross-sectional view of a second housing arrangement of another embodiment in combination with a first heat exchanging portion and a second cooling arrangement;
fig. 6 shows a schematic perspective view of a second housing arrangement of an embodiment;
FIG. 7 shows a schematic perspective view of a first heat exchange portion of an embodiment;
FIG. 8 illustrates a schematic top view of a first heat exchange portion of an embodiment;
FIG. 9 shows a schematic cross-sectional view of a first heat exchange portion of an embodiment;
FIG. 10 shows a schematic perspective view of a second heat exchange portion of an embodiment;
FIG. 11 illustrates a schematic top view of a second heat exchange portion of an embodiment;
FIG. 12 illustrates a schematic cross-sectional view of a second heat exchange portion of an embodiment;
reference numerals:
10 first housing means; 11 an exhaust part; a 111 exhaust duct; 112 control valve; 12 liquid injection parts; 121 fluid injection line; 122 a liquid injection valve; 13 a heat dissipation part; 131 a heat exchanger; 132 refrigerant piping; 20 a first cooling device; a 21-cycle pump; 22 conveying pipelines; 23 a liquid spraying part; 24 a first heat exchange portion; 241 porous cover plate; 242 inclined enclosure; 243 large channels; a second cooling device 30; 31 a second heat exchange part; 311 second heat exchange body; 312 coarse passages; 313 fine channels; 314 diagonal channels; 315 heat exchange base; 316 connected to the cavity; 317 connect capillaries; 318 bottom capillary; a 32 heat storage unit; 40 second housing means; 41 a receiving chamber; 50 heat generating components.
Detailed Description
The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.
As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment".
The embodiment discloses a phase change temperature control system of an aircraft, as shown in fig. 1, fig. 2, fig. 3, fig. 4, fig. 10, fig. 11, fig. 12, may include:
a first housing means 10;
a second housing means 40, the second housing means 40 being disposed within a hollow cavity formed within the first housing means 10; the second housing means 40 is internally provided with a hollow receiving cavity 41;
a first cooling device 20, the first cooling device 20 being disposed in a hollow cavity formed inside the first housing device 10; the first cooling device 20 comprises a circulating pump 21, a conveying pipeline 22, a liquid spraying part 23 and a first heat exchanging part 24; the first heat exchanging portion 24 is disposed in the accommodating chamber 41 of the second housing means 40; the liquid spraying part 23 is arranged at the top of the first heat exchanging part 24; the second housing device 40, the circulating pump 21 and the liquid spraying part 23 are sequentially communicated through the conveying pipeline 22; a hollow cavity is formed inside the first heat exchange part 24; the first heat exchange portion 24 includes a large passage 243; the large passage 243 is provided on the outer peripheral side of the hollow cavity; the upper and lower ends of the first heat exchange part 24 are communicated through a large channel 243;
a second cooling device 30, the second cooling device 30 being disposed in the hollow cavity of the first heat exchanging portion 24; the second cooling device 30 is located below the liquid ejecting section 23; the second cooling device 30 includes a second heat exchanging portion 31; the second heat exchange part 31 comprises a second heat exchange body 311, a thick channel 312, a thin channel 313, a heat exchange base 315 and a communication cavity 316; the upper end and the lower end of the second heat exchange body 311 are communicated through a thick channel 312; the upper end and the lower end of the second heat exchange body 311 are communicated through a thin channel 313; the thick channel 312 and the thin channel 313 are arranged at intervals in the second heat exchange body 311; the lower end surface of the heat exchange base 315 is abutted with the upper end of the second heat exchange body 311 to form a sealed connection; a communication cavity 316 is arranged at the joint of the heat exchange base 315 and the second heat exchange body 311; the upper end of the coarse channel 312 communicates with the upper end of the fine channel 313 through a communication chamber 316.
In this embodiment, various components on the aircraft may generate heat during the flight of the aircraft. To ensure the flight safety of the aircraft, the heat generating component 50 may be heat-dissipated. As shown in fig. 1, an aircraft phase change temperature control system may include a first housing apparatus 10, a second housing apparatus 40, a first cooling apparatus 20, and a second cooling apparatus 30. The first housing device 10 may have a hollow cavity formed therein, and the second housing device 40, the first cooling device 20, and the second cooling device 30 may be disposed in the hollow cavity, so as to exchange heat with the heat generating component 50 in a relatively closed space, thereby enhancing the heat exchange effect with the heat generating component 50, and improving the space utilization. As shown in fig. 6, a hollow receiving space 41 can be provided inside the second housing arrangement 40 for storing a cooling medium and for receiving other components of the aircraft phase change temperature control system. As shown in fig. 2, 3, and 4, the first cooling device 20 may include a circulation pump 21, a delivery pipe 22, a liquid spraying portion 23, and a first heat exchanging portion 24. The input end of the circulation pump 21 may communicate with the accommodation chamber 41 of the second housing device 40 through the delivery pipe 22, and the output end of the circulation pump 21 may communicate with one end of the liquid spraying portion 23 through the delivery pipe 22, so that the circulation pump 21 may pump the cooling medium in the accommodation chamber 41 of the second housing device 40 and deliver the cooling medium to the liquid spraying portion 23 through the delivery pipe 22. The liquid spraying portion 23 is used for spraying the cooling medium to exchange heat with the heat generating component 50, and may be disposed at the top of the first heat exchanging portion 24, so that a part of the gaseous cooling medium phase-changed after the cooling medium sprayed by the liquid spraying portion 23 exchanges heat with the heat generating component 50 flows into the first heat exchanging portion 24 along with the liquid cooling medium. The first heat exchanging portion 24 may be internally formed with a hollow cavity for accommodating other related components. The first heat exchanging portion 24 may be disposed in the receiving chamber 41 of the second housing means 40. The first heat exchanging portion 24 may include a large passage 243. The large passage 243 may be provided on the outer peripheral side of the hollow cavity in the first heat exchanging portion 24. The upper and lower ends of the first heat exchange portion 24 are communicated through the large passage 243, so that the cooling medium flowing into the first heat exchange portion 24 can flow through the large passage 243 to be stored in the accommodating cavity 41, thereby recycling the cooling medium and reducing the consumption of the cooling medium. The second cooling device 30 may be disposed in the hollow cavity of the first heat exchanging portion 24 to improve space utilization. The second cooling device 30 may be located below the liquid spraying portion 23 of the first cooling device 20, the second cooling device 30 may include a second heat exchanging portion 31, and the heat generating component 50 may be placed at an upper end of the second heat exchanging portion 31, so that the liquid spraying portion 23 sprays a cooling medium to a top of the heat generating component 50 to cool, and at the same time, the second heat exchanging portion 31 may exchange heat with a bottom of the heat generating component 50, thereby rapidly reducing a temperature of the heat generating component 50 and improving heat exchange efficiency. As shown in fig. 10, 11 and 12, the second heat exchanging part 31 may include a second heat exchanging body 311, a thick passage 312, a thin passage 313, a heat exchanging base 315, and a communication chamber 316. The inside of the second heat exchange body 311 may be provided with a coarse channel 312 and a fine channel 313, so that the upper end and the lower end of the second heat exchange body 311 may be communicated through the coarse channel 312 and may also be communicated through the fine channel 313, so that the cooling medium in the accommodating cavity 41 may exchange heat with the heat generating component 50 through the coarse channel 312 and the fine channel 313, and the temperature of the heat generating component 50 may be further reduced. The upper end of the heat exchange base 315 may be connected to the heat generating component 50 to transfer heat from the heat generating component 50. The lower end surface of the heat exchange base 315 can be inwards recessed to form a groove, and the peripheral side of the lower end surface of the heat exchange base 315 is in abutting connection with the upper end of the second heat exchange body 311 to form sealing connection, so that an internal cavity is formed after the heat exchange base 315 is in abutting connection with the second heat exchange body 311, and further cooling medium in the second heating part and the heat exchange base 315 are prevented from leaking to the outside when being changed into gas by liquid, and consumption of the cooling medium is reduced. The internal cavity formed at the abutting part of the heat exchange base 315 and the second heat exchange body 311 can be provided with a communication cavity 316, so that the heat exchange uniformity of the cooling medium and the heat exchange base 315 in the space region can be improved, and the heat exchange efficiency is improved. The upper end of the coarse channel 312 and the upper end of the fine channel 313 can be communicated through the communication cavity 316, and the coarse channel 312 and the fine channel 313 can be arranged at intervals in the second heat exchange body 311, so that when the cooling medium with capillary action rising in the fine channel 313 absorbs heat transferred to the heat exchange base 315 by the heat generating component 50 and then undergoes phase change, the gaseous cooling medium can flow into the coarse channel 312 along with part of the liquid cooling medium and finally flow back into the accommodating cavity 41, thereby not only reducing the consumption of the cooling medium, but also enhancing the heat exchange effect.
In other embodiments, the second cooling device 30 may also include a thermal storage 32. As shown in fig. 4, 5, and 12, the heat storage portion 32 may be buried in a thick wall between the thick channel 312 and the thin channel 313 of the second heat exchange portion 31. When the temperature of the heat generating component 50 is too high, the heat exchange efficiency between the cooling medium and the heat generating component 50 is insufficient, and the heat storage portion 32 can absorb part of the heat transferred by the heat generating component 50, so that the heat exchange efficiency is improved. When the heat transferred by the heat generating component 50 is insufficient to cause the cooling medium to reach the boiling point for phase change, the heat storage portion 32 can release the heat absorbed before, so as to improve the phase change rate of the cooling medium and further enhance the heat exchange effect between the cooling medium and the heat generating component 50.
In some embodiments, as shown in fig. 5, the second heat exchange portion 31 further includes a connecting capillary 317; the connection capillary 317 is disposed in the communication chamber 316; the upper end of the coarse channel 312 communicates with the upper end of the fine channel 313 through a connecting capillary 317.
In this embodiment, as shown in fig. 5, the second heat exchanging part 31 may further include a connection capillary 317 for transporting the cooling medium. The connecting capillary 317 can be arranged in the communication cavity 316 above the second heat exchange body 311, the upper end of the thick channel 312 and the upper end of the thin channel 313 can be communicated through the connecting capillary 317, the cooling medium can be conveyed from the lower end of the thin channel 313 to the upper end of the thin channel 313 under the action of capillary action and then enter the connecting capillary 317, and the cooling medium in the connecting capillary 317 can be gradually and uniformly distributed at the lower end of the heat exchange base 315, so that the heat quantity transferred to the lower end of the heat exchange base 315 by the heating component 50 can be better absorbed, and the heat exchange uniformity of the cooling medium in a space area can be improved. When the heat exchange of the cooling medium reaches the self boiling point, the phase change can occur, and the heat of the heat exchange base 315 is further absorbed, so that the heat generating component 50 can be quickly cooled. The gaseous cooling medium can gradually condense back to liquid state when entering the rough channel 312 through the connecting capillary 317 and contacting with the liquid cooling medium in the rough channel 312, thereby recycling the cooling medium and reducing the consumption of the cooling medium.
In some embodiments, as shown in fig. 4 and 5, the second heat exchange portion 31 further includes a bottom capillary 318; the bottom capillary 318 is in abutting connection with the lower end face of the second heat exchange body 311; the lower end of the coarse channel 312 communicates with the receiving cavity 41 of the second housing means 40 via a bottom capillary 318; the lower end of the thin channel 313 communicates with the receiving cavity 41 of the second housing means 40 by means of a bottom capillary 318.
In this embodiment, as shown in fig. 4 and 5, the second heat exchange portion 31 may further include a bottom capillary tube 318, where the bottom capillary tube 318 may be in abutting connection with the lower end surface of the second heat exchange body 311, and the lower end of the coarse channel 312 and the lower end of the fine channel 313 may be communicated with the accommodating cavity 41 of the second housing device 40 through the bottom capillary tube 318, so as to slow down the speed of the cooling medium flowing through the coarse channel 312, the fine channel 313 and the accommodating cavity 41, so as to facilitate the generation of the siphoning action of the cooling medium in the next step.
In other embodiments, the internal structure of the bottom capillary 318 may be a tesla valve structure. The direction from the end of the bottom capillary 318 communicating with the rough channel 312 to the other end of the bottom capillary 318 communicating with the accommodating chamber 41 is the direction in which the tesla valve has a large resistance characteristic, so that the drop of the liquid level of the cooling medium in the rough channel 312 can be better slowed down, and the siphon action is more easily formed.
In some embodiments, as shown in fig. 4 and 5, the second heat exchange portion 31 further includes a diagonal channel 314; one end of the inclined passage 314 is communicated with the thick passage 312 on the outer peripheral side of the second heat exchange body 311; the other end of the inclined passage 314 extends obliquely downward through the first heat exchange portion 24 to the accommodating chamber 41 of the second housing means 40; the angled passages 314 are provided with upwardly curved arcuate segments near one end of the rough passage 312.
In the present embodiment, as shown in fig. 4 and 5, the second heat exchanging part 31 may further include an inclined passage 314, one end of the inclined passage 314 may communicate with the thick passage 312 at the outer circumferential side of the second heat exchanging body 311, and the other end may extend obliquely downward through the large passage 243 of the first heat exchanging part 24 into the accommodating chamber 41 of the second housing means 40. The cooling medium in the thick channel 312 can flow through the inclined channel 314 and be discharged into the accommodating cavity 41, and the cooling medium in the large channel 243 of the first heat exchange part 24 can exchange heat with the cooling medium in the inclined channel 314, so that the heat exchange efficiency is improved. The inclined channel 314 may have an upwardly curved arc section (i.e., an S-channel) near the coarse channel 312, and when the cooling medium flows into the connecting capillary 317 by capillary action of the fine channel 313 and exchanges heat with the heat exchange base 315, the gaseous cooling medium may flow into the coarse channel 312 along with a part of the liquid cooling medium, and the gaseous cooling medium gradually condenses into a liquid state in the course of entering the coarse channel 312. Due to the blocking effect of the bottom capillary 318, the liquid level of the cooling medium in the coarse channel 312 can gradually rise, when the liquid level of the cooling medium reaches the communication port between the inclined channel 314 and the coarse channel 312, the cooling medium can gradually fill the inner cavity of the arc section of the inclined channel 314 and then flow into one end of the inclined channel 314, which is inclined downwards, so that a liquid seal can be formed for the gaseous cooling medium in the coarse channel 312, the gaseous cooling medium in the coarse channel 312 is continuously condensed to form negative pressure in the second heat exchange body 311, and a certain siphon effect can be formed between the outer periphery side coarse channel 312 and the inclined channel 314, so that the heat released by the heat storage part 32 is rapidly taken away, and the heat exchange efficiency is improved.
In other embodiments, the internal structure of the angled passages 314 may be a tesla valve structure. The direction from the input end of the inclined channel 314 communicated with the thick channel 312 to the output end of the inclined channel 314 in the accommodating cavity 41 of the second shell device 40 is the direction of the Tesla valve with small resistance, and the flow resistance of the cooling medium in the opposite direction is large, so that the countercurrent flow of the cooling medium in the inclined channel 314 when the negative pressure is formed in the second heat exchange body 311 can be avoided, the stable existence of liquid seal is promoted, and the siphon effect is easier to form.
In some embodiments, as shown in fig. 4 and 5, the end of the inclined channel 314 extending to the receiving cavity 41 of the second housing means 40 is provided with an upwardly curved arcuate segment.
In this embodiment, as shown in fig. 4 and 5, when the temperature of the heat generating component 50 is high, the cooling medium in the connecting capillary 317 of the second heat exchanging portion 31 can quickly absorb heat to reach the boiling point to generate a phase change, so as to quickly cool the heat generating component 50, and a large amount of gaseous cooling medium generated by the heat exchange phase change can flow into the coarse channel 312 to be split into the inclined channel 314, and the level of the cooling medium in the coarse channel 312 is continuously raised due to the action of the bottom capillary 318 and the gradual condensation of the gaseous cooling medium. The gaseous cooling medium is cooled by the cooling medium in the large channel 243 of the first heat exchange part 24 and can be condensed into the liquid cooling medium again in the process of flowing through the inclined channel 314, one end of the inclined channel 314 extending to the accommodating cavity 41 of the second shell device 40 can be provided with an upward curved arc section, and the liquid cooling medium can gradually fill the arc section of the inclined channel 314, so that part of the liquid cooling medium can block the gaseous cooling medium from being discharged through the inclined channel 314 in advance, the S-shaped channel of the inclined channel 314, which is close to one end of the coarse channel 312, can be accelerated to be filled with the cooling medium, the double liquid sealing effect is further achieved, the siphon effect formed between the coarse channel 312 and the inclined channel 314 is further enhanced, and meanwhile, the heat exchange effect of the cooling medium and the heating component 50 can be enhanced.
In some embodiments, as shown in fig. 4 and 5, the second heat exchange portion 31 includes a plurality of inclined channels 314; the height positions of the connection ports through which the plurality of inclined passages 314 communicate with the thick passage 312 are different.
In the present embodiment, as shown in fig. 4 and 5, the second heat exchanging part 31 may include a plurality of inclined passages 314, the height positions of connection ports at which the plurality of inclined passages 314 communicate with the thick passages 312 on the outer circumferential side of the second heat exchanging body 311 may be different, and the inclined passages 314 on the lower side may more easily form a siphon effect. When the liquid level of the cooling medium in the accommodating cavity 41 passes through the inclined channel 314 on the lower side, the siphoning action of the inclined channel 314 on the lower side is stopped, and the inclined channel 314 on the higher side still can form a certain siphoning action, so that the heat exchange efficiency of the cooling medium with the heat exchange base 315 in the second heat exchange part 31 is enhanced.
In some embodiments, as shown in fig. 7, 8, 9, the first heat exchange portion 24 further includes an inclined enclosure 242; the inclined enclosure 242 is disposed on the upper end surface of the first heat exchange portion 24; the inclined fence 242 is provided in a ring shape surrounding the outer peripheral side of the upper port of the large passage 243; the high side of the angled fence 242 is adjacent to the upper port of the large channel 243; the lower side of the angled fence 242 extends in a direction away from the upper port of the large channel 243.
In this embodiment, as shown in fig. 7, 8 and 9, the first heat exchanging portion 24 may further include an inclined enclosure 242, and the inclined enclosure 242 may be disposed on an upper end surface of the first heat exchanging portion 24, so as to prevent the cooling medium sprayed onto the surface of the heat generating component 50 by the liquid spraying portion 23 from splashing. The inclined peripheral shield 242 may be provided in a ring shape surrounding the outer peripheral side of the upper port of the large passage 243 of the first heat exchanging part 24, so that the cooling medium may be prevented from being sprayed to the surface of the heat generating part 50 to generate splashes in different directions across the large passage 243. The higher side of the inclined enclosure 242 may be adjacent to the upper port of the large passage 243, and the lower side thereof may extend in a direction away from the upper port of the large passage 243, so that splashed cooling medium is collected and flows into the large passage 243, the consumption of the cooling medium is reduced, and the heat exchange efficiency between the cooling medium of the large passage 243 and the cooling medium of the inclined passage 314 is improved.
In some embodiments, as shown in fig. 7, 8, and 9, the first heat exchange portion 24 further includes a porous cover plate 241; the porous cover plate 241 is disposed on the upper end surface of the first heat exchanging portion 24; the porous cover plate 241 is provided in a ring shape and provided on the outer peripheral side of the inclined fence 242; the porous cover plate 241 is provided with a plurality of through holes; the through-holes communicate the space in the upper portion of the porous cover plate 241 with the space of the accommodation chamber 41 of the second housing means 40.
In this embodiment, as shown in fig. 7, 8 and 9, the first heat exchanging portion 24 may further include a porous cover plate 241 for reducing splashing of the cooling medium. The porous cover plate 241 may be disposed on the upper end surface of the first heat exchanging portion 24, may be disposed in a ring shape and disposed on the outer peripheral side of the inclined enclosure 242, and may be provided with a plurality of through holes, so that the space on the upper portion of the porous cover plate 241 is spatially communicated with the accommodating cavity 41 of the second housing device 40, and thus when the cooling medium splashes over the inclined enclosure 242, the cooling medium may still flow into the accommodating cavity 41 through the through holes, so as to reduce the consumption of the cooling medium, and further reduce the oscillation and overflow of the cooling medium stored in the accommodating cavity 41.
In some embodiments, as shown in fig. 1, the first housing means 10 comprises a vent 11; the exhaust portion 11 includes an exhaust duct 111 and a control valve 112; the exhaust duct 111 communicates the internal cavity of the first housing device 10 with the external space of the first housing device 10; a control valve 112 is provided on the exhaust pipe 111.
In the present embodiment, as shown in fig. 1, the first housing device 10 may include an exhaust portion 11, and the exhaust portion 11 may include an exhaust pipe 111 and a control valve 112. The exhaust duct 111 may communicate the internal cavity of the first housing device 10 with the external space of the first housing device 10, and may allow the gaseous cooling medium within the internal cavity of the first housing device 10 to be exhausted. The control valve 112 may be disposed on the exhaust pipe 111, and may control the discharge amount of the gaseous cooling medium, thereby maintaining the air pressure stability of the phase change temperature control system of the aircraft, and further improving the heat exchange effect.
In some embodiments, as shown in fig. 1, the first housing means 10 comprises a heat sink 13; the heat radiating part 13 includes a heat exchanger 131 and a refrigerant pipe 132; the refrigerant pipe 132 communicates with the heat exchanger 131; the heat exchanger 131 is provided on the outer peripheral side of the second casing device 40; the heat of the second housing device 40 is transferred to the external space of the first housing device 10 through the refrigerant pipe 132.
In this embodiment, as shown in fig. 1, the first housing device 10 may include a heat dissipating part 13, and the heat dissipating part 13 may include a heat exchanger 131, a refrigerant pipe 132, and a heat discharging part for discharging heat of the cooling medium. The refrigerant pipe 132 may be in communication with the heat exchanger 131, the heat exchanger 131 may be disposed on an outer peripheral side of the second housing device 40, and heat of the cooling medium in the accommodating chamber 41 of the second housing device 40 may be transferred to the refrigerant pipe 132 through the heat exchanger 131, and then transferred to an external space of the first housing device 10 through the refrigerant pipe 132, so that a temperature of the cooling medium may be reduced, and it is ensured that the cooling medium may continuously perform heat exchange treatment on the heat generating component 50.
In some embodiments, as shown in fig. 1, the first housing means 10 comprises a liquid injection portion 12; the liquid filling part 12 comprises a liquid filling pipeline 121 and a liquid filling valve 122; the liquid injection pipe 121 communicates the outer space of the first housing device 10 with the inner cavity of the second housing device 40; the priming valve 122 is disposed on the priming conduit 121.
In this embodiment, as shown in fig. 1, the first housing device 10 may include a liquid injection portion 12, and the liquid injection portion 12 may include a liquid injection pipe 121 and a liquid injection valve 122 for supplementing the cooling medium. The liquid injection pipe 121 communicates the outer space of the first housing device 10 with the inner cavity of the second housing device 40, and when the cooling medium in the accommodating chamber 41 of the second housing device 40 is consumed to a certain amount, the cooling medium can be supplied from the outer space through the liquid injection pipe 121. A filling valve 122 may be provided on the filling pipe 121 so that the flow rate of the cooling medium replenished to the accommodating chamber 41 may be controlled.
It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples of implementing the disclosure, and that various changes in form and details may be made therein without departing from the spirit and scope of the disclosure.
Claims (11)
1. An aircraft phase change temperature control system, the aircraft phase change temperature control system comprising:
a first housing means;
a second housing means disposed within a hollow cavity formed within the first housing means; a hollow accommodating cavity is formed in the second shell device;
a first cooling device disposed in a hollow cavity formed inside the first housing device; the first cooling device comprises a circulating pump, a conveying pipeline, a liquid spraying part and a first heat exchange part; the first heat exchange part is arranged in the accommodating cavity of the second shell device; the liquid spraying part is arranged at the top of the first heat exchange part; the second shell device, the circulating pump and the liquid spraying part are sequentially communicated through the conveying pipeline; a hollow cavity is formed in the first heat exchange part; the first heat exchange part comprises a large channel; the large channel is arranged on the outer peripheral side of the hollow cavity; the upper end and the lower end of the first heat exchange part are communicated through the large channel;
the second cooling device is arranged in the hollow cavity of the first heat exchange part; the second cooling device is positioned below the liquid spraying part; the second cooling device comprises a second heat exchange part; the second heat exchange part comprises a second heat exchange body, a coarse channel, a fine channel, a heat exchange base and a communication cavity; the upper end and the lower end of the second heat exchange body are communicated through the thick channel; the upper end and the lower end of the second heat exchange body are communicated through the fine channel; the thick channel and the thin channel are arranged at intervals in the second heat exchange body; the lower end face of the heat exchange base is abutted with the upper end of the second heat exchange body to form sealing connection; a communication cavity is arranged at the joint of the heat exchange base and the second heat exchange body; the upper end of the thick channel is communicated with the upper end of the thin channel through the communication cavity.
2. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the second heat exchange part also comprises a connecting capillary; the connecting capillary is arranged in the communication cavity; the upper end of the thick channel is communicated with the upper end of the thin channel through the connecting capillary.
3. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the second heat exchange part also comprises a bottom capillary; the bottom capillary is in abutting connection with the lower end face of the second heat exchange body; the lower end of the thick channel is communicated with the accommodating cavity of the second shell device through the bottom capillary; the lower end of the thin channel is communicated with the accommodating cavity of the second shell device through the bottom capillary.
4. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the second heat exchange part also comprises an inclined channel; one end of the inclined channel is communicated with the thick channel at the outer periphery of the second heat exchange body; the other end of the inclined channel obliquely passes through the first heat exchange part downwards and extends to the accommodating cavity of the second shell device; and one end of the inclined channel, which is close to the thick channel, is provided with an upward bent arc section.
5. The phase-change temperature control system of an aircraft according to claim 4, wherein,
one end of the inclined channel extending to the accommodating cavity of the second shell device is provided with an arc-shaped section which is bent upwards.
6. An aircraft phase change temperature control system as claimed in claim 4, wherein,
the second heat exchange part comprises a plurality of inclined channels; the height positions of the connecting ports for communicating the inclined channels with the thick channels are different.
7. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the first heat exchange part further comprises an inclined enclosing baffle; the inclined surrounding baffle is arranged on the upper end face of the first heat exchange part; the inclined surrounding block is arranged in a ring shape and surrounds the outer peripheral side of the upper port of the large channel; the high side of the inclined enclosure is adjacent to the upper port of the large channel; the lower side of the sloped enclosure extends in a direction away from the upper port of the large channel.
8. The phase change temperature control system of an aircraft according to claim 7,
the first heat exchange part further comprises a porous cover plate; the porous cover plate is arranged on the upper end face of the first heat exchange part; the porous cover plate is arranged in a ring shape and is arranged on the outer periphery side of the inclined enclosure; the porous cover plate is provided with a plurality of through holes; the through hole communicates the space at the upper part of the porous cover plate with the space of the accommodating cavity of the second shell device.
9. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the first housing means includes an exhaust portion; the exhaust part comprises an exhaust pipeline and a control valve; the exhaust pipeline communicates the internal cavity of the first shell device with the external space of the first shell device; the control valve is arranged on the exhaust pipeline.
10. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the first housing device includes a heat dissipation portion; the heat dissipation part comprises a heat exchanger and a refrigerant pipeline; the refrigerant pipeline is communicated with the heat exchanger; the heat exchanger is arranged on the outer periphery side of the second shell device; the heat of the second shell device is transferred to the external space of the first shell device through the refrigerant pipeline.
11. The phase-change temperature control system of an aircraft according to claim 1, wherein,
the first shell device comprises a liquid injection part; the liquid injection part comprises a liquid injection pipeline and a liquid injection valve; the liquid injection pipeline is used for communicating the external space of the first shell device with the internal cavity of the second shell device; the liquid injection valve is arranged on the liquid injection pipeline.
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| CN202311117737.7A CN116887588B (en) | 2023-09-01 | 2023-09-01 | Aircraft phase transition temperature control system |
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| CN202311117737.7A CN116887588B (en) | 2023-09-01 | 2023-09-01 | Aircraft phase transition temperature control system |
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| CN116887588B (en) | 2023-11-21 |
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