CN108362025B - Airborne spray cooling system using phase change material to cool spray medium and micro-channel heat exchanger to prevent failure - Google Patents
Airborne spray cooling system using phase change material to cool spray medium and micro-channel heat exchanger to prevent failure Download PDFInfo
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- CN108362025B CN108362025B CN201810280693.2A CN201810280693A CN108362025B CN 108362025 B CN108362025 B CN 108362025B CN 201810280693 A CN201810280693 A CN 201810280693A CN 108362025 B CN108362025 B CN 108362025B
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- 238000001816 cooling Methods 0.000 title claims abstract description 79
- 239000012782 phase change material Substances 0.000 title claims abstract description 61
- 239000007921 spray Substances 0.000 title claims abstract description 54
- 239000002826 coolant Substances 0.000 claims abstract description 101
- 238000005057 refrigeration Methods 0.000 claims abstract description 26
- 230000001105 regulatory effect Effects 0.000 claims description 26
- 239000007788 liquid Substances 0.000 claims description 18
- 238000010438 heat treatment Methods 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 9
- 238000005507 spraying Methods 0.000 claims description 9
- 230000008569 process Effects 0.000 claims description 7
- 239000012535 impurity Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 4
- 230000000630 rising effect Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 2
- 239000012188 paraffin wax Substances 0.000 claims description 2
- 229920000642 polymer Polymers 0.000 claims description 2
- 238000005086 pumping Methods 0.000 claims description 2
- 239000003507 refrigerant Substances 0.000 claims description 2
- 150000003839 salts Chemical class 0.000 claims description 2
- 230000004907 flux Effects 0.000 abstract description 5
- 230000017525 heat dissipation Effects 0.000 abstract description 3
- 238000001704 evaporation Methods 0.000 description 5
- 230000008020 evaporation Effects 0.000 description 5
- 238000000889 atomisation Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000007123 defense Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B9/00—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
- F25B9/02—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using Joule-Thompson effect; using vortex effect
- F25B9/04—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using Joule-Thompson effect; using vortex effect using vortex effect
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D20/00—Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups F28D17/00 or F28D19/00
- F28D20/02—Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups F28D17/00 or F28D19/00 using latent heat
- F28D20/028—Control arrangements therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D5/00—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, using the cooling effect of natural or forced evaporation
- F28D5/02—Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, using the cooling effect of natural or forced evaporation in which the evaporating medium flows in a continuous film or trickles freely over the conduits
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F27/00—Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus
- F28F27/02—Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus for controlling the distribution of heat-exchange media between different channels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F2260/00—Heat exchangers or heat exchange elements having special size, e.g. microstructures
- F28F2260/02—Heat exchangers or heat exchange elements having special size, e.g. microstructures having microchannels
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- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/14—Thermal energy storage
Abstract
An airborne spray cooling system using phase change material to cool spray medium and using micro-channel heat exchanger to prevent failure belongs to the field of airborne equipment cooling. The invention can solve the problem of continuous heat dissipation of high heat flux surfaces of airborne laser weapons and high-power electronic equipment. The main components comprise a cooling medium storage tank, a circulating pump, a phase change material storage tank, a filter, a spray chamber, a first nozzle, a second nozzle, a micro-channel heat exchanger, a surface to be cooled, an engine air-entraining port, a vortex tube refrigeration box and an airfoil anti-icing port. The invention uses a plurality of vortex tubes to build the refrigeration box, introduces external air to provide a cold source for the phase change material through the vortex tubes, uses the phase change material to cool the spray medium, uses the micro-channel heat exchanger to cover the cooling surface in order to prevent spray cooling failure, ensures safe system operation, has good sustainability and meets the cooling requirement under the complex airborne environment.
Description
Technical Field
The invention relates to an airborne spray cooling system for cooling a spray medium by using a phase change material and preventing failure by using a microchannel heat exchanger, belonging to the field of airborne equipment cooling.
Background
With the continuous improvement of the requirements of the maneuverability, stealth performance and defending performance of the aircraft, the high-power laser technology, the high-integration and microminiaturization of electronic components and other technologies are rapidly developed. The directional energy weapon is one of the key technical barriers for the next generation of fighter plane. In 2013, the national defense advanced research program agency authorized the roc hadamard company to install a prototype laser defense weapon onto the validator. 9 months 2015, U.S. air force announced that the air force will be at AC-13And a laser weapon is additionally arranged on the 0 armed conveyor. Such weapons, after firing, produce extremely high heat flux densities at the surface, which can be on the order of thousands of W/cm 2 . In addition, the heat flux density of the military electronic equipment also reaches hundreds of W/cm 2 . If no effective measures are taken to reduce the surface temperature of the electronic equipment, the working efficiency of the electronic equipment is greatly reduced if the electronic equipment is light, and the device is burnt if the electronic equipment is heavy, so that the flight safety is affected. Therefore, how to efficiently and safely solve the problem of rapid heat dissipation of the onboard equipment is of great importance. The heat exchange capacity of the conventional air cooling and water cooling modes reaches the limit, and the heat dissipation requirements of electronic equipment and lasers which are increasingly increased cannot be met.
Spray cooling is a novel cooling mode of decomposing a cooling medium into innumerable discrete droplets through atomization, spraying the cooling medium onto a heating surface and taking away heat through single-phase heat exchange and two-phase heat exchange, and has the advantages that: a small surface temperature difference; no boiling hysteresis; good heat exchange performance; the cooling surface temperature is uniform. The spray cooling technology has a strong application prospect in the field of airborne equipment cooling.
However, spray cooling is subject to heat transfer failure and heat sink selection when applied to the field of airborne applications. When the heating quantity of the airborne device fluctuates, and the heat flux density of the cooling surface is larger than the critical heat flux density of spray cooling, the heat transfer coefficient of the surface is rapidly reduced, and the temperature is rapidly increased, so that the safety of airborne equipment is affected. The patent 201710429948.2 proposes a microchannel surface type spray cooling enhanced heat exchange device, which is mainly characterized in that the surface is covered with a porous heat conducting material and a microchannel, and partial medium is sucked into the microchannel to complete heat exchange between the microchannel and the surface of a heat sink while spray cooling is considered. The method enhances the heat exchange capacity of spray cooling, but the surface of the spray cooling failure is covered by the air film, no liquid cooling medium exists, and even if the liquid cooling medium is sucked into the micro-channel, the heat exchange capacity of the gaseous cooling medium is poor, so the surface temperature rise of the spray cooling failure still cannot be restrained.
Regarding the selection of an airborne cold source, partial schemes are also proposed, as in patent 201510072716.7, a cooling system of an airborne heating element based on air expansion refrigeration is proposed, and is mainly characterized in that a turbine is used as a refrigerating device and a power source, and when the scheme is put into use, the turbine cold storage can be used for spray cooling at first, the cold storage time is long, and the energy consumption in the cold storage process is large; the structure is complicated and the equipment space is great, can't satisfy the quick refrigerated requirement of airborne equipment. The patent 2015174027. X proposes a cooling system and a method of an onboard heating element based on evaporation refrigeration, which are mainly characterized in that an indirect cold source is provided for a system by using an evaporation refrigeration cycle, the evaporation refrigeration cycle mainly acts on a regenerator, and the cold source is not directly connected with a spraying system, so that the cooling effect of a cooling medium is weakened; the volume and the energy consumption are very large after the evaporation refrigeration cycle is added, and the invention does not provide a cold source for the evaporation refrigeration cycle, and if the volume is larger in practical use, the invention cannot meet the requirement of an airborne space.
The invention takes the engine bleed air as an air source, uses a plurality of vortex tubes to be connected in parallel, uses cold air flowing out of the vortex tubes to cool the phase change material, and provides a stable cold source for a spray cooling system; the phase change material is used for cooling the cooling medium, so that the system is simple and reliable; the hot gas flowing out of the vortex tube can be directly used for anti-icing and deicing the wing, so that the energy of an anti-icing system is saved, and the flight safety of an aircraft is improved. In addition, a micro-channel heat exchanger is paved on the surface to be cooled, and part of liquid cooling medium is introduced into the micro-channel heat exchanger, so that the heat exchange performance can be improved, and when the heating quantity suddenly increases to cause the critical failure of spray cooling, the surface temperature can be still controlled through the micro-channel heat exchanger, so that the device is ensured not to be burnt.
Disclosure of Invention
It is an object of the present invention to provide an on-board spray cooling system that uses phase change material to cool the spray medium and a microchannel heat exchanger to prevent failure.
The system mainly comprises a cooling medium storage tank (1), a first stop valve (2), a circulating pump (3), a second stop valve (4), a phase change material storage tank (5), a filter (6), a third stop valve (7), a first flow regulating valve (8), a first flow meter (9), a second flow regulating valve (10), a second flow meter (11), a spray chamber (12), a first nozzle (13), a second nozzle (14), a micro-channel heat exchanger (15), a cooling medium flow channel (16), a surface to be cooled (17), a fourth stop valve (18), an engine air-entraining port (19), a fifth stop valve (20), a vortex tube cooling box (21), a sixth stop valve (22) and a wing anti-icing port (23).
An on-board spray cooling system using phase change material to cool spray media and a microchannel heat exchanger to prevent failure consists of a surface cooling system and a vortex tube cooling system.
The surface cooling system consists of a cooling medium storage tank (1), a first stop valve (2), a circulating pump (3), a second stop valve (4), a phase change material storage tank (5), a filter (6), a third stop valve (7), a first flow regulating valve (8), a first flowmeter (9), a second flow regulating valve (10), a second flowmeter (11), a spraying chamber (12), a first nozzle (13), a second nozzle (14), a micro-channel heat exchanger (15), a cooling medium flow channel (16), a surface to be cooled (17) and a fourth stop valve (18);
the phase change material storage tank (5) is provided with two inlets and two outlets, wherein the first inlet is a cooling medium inlet, the first outlet is a cooling medium outlet, the second inlet is a cold air inlet, and the second outlet is a cold air outlet;
the third shut-off valve (7) has one inlet and two outlets, the first flowmeter (9) has one inlet and two outlets, the second flowmeter (11) has one inlet and two outlets, and the fourth shut-off valve (18) has three inlets and one outlet;
the cooling medium storage tank (1) is connected with the inlet of a first stop valve (2), the outlet of the first stop valve (2) is connected with the inlet of a circulating pump (3) and the outlet of a fourth stop valve (18), the outlet of the circulating pump (3) is connected with the inlet of a second stop valve (4), the outlet of the second stop valve (4) is connected with the first inlet of a phase change material storage tank (5), the first outlet of the phase change material storage tank (5) is connected with the inlet of a filter (6), the outlet of the filter (6) is connected with the inlet of a third stop valve (7), the first outlet of the third stop valve (7) is connected with the inlet of a first flow regulating valve (8), the outlet of the first flow regulating valve (8) is connected with the inlet of a first flow meter (9), the first outlet of the first flow meter (9) is connected with the inlet of a first nozzle (13), and the second outlet of the first flow meter (9) is connected with the inlet of a second nozzle (14);
the second outlet of the third stop valve (7) is connected with the inlet of the second flow regulating valve (10), the outlet of the second flow regulating valve (10) is connected with the inlet of the second flowmeter (11), the first outlet and the second outlet of the second flowmeter (11) are connected with the inlet of the cooling medium flow passage (16), and the outlet of the cooling medium flow passage (16) is connected with the first inlet and the second inlet of the fourth stop valve (18);
the outlets of the first nozzle (13) and the second nozzle (14) spray atomized cooling medium to the surface of the micro-channel heat exchanger (15), the micro-channel heat exchanger (15) is arranged above the surface (17) to be cooled and clings to the surface (17) to be cooled, and the cooling medium flow channel (16) is a component part of the micro-channel heat exchanger (15);
the first nozzle (13), the second nozzle (14), the microchannel heat exchanger (15) and the surface to be cooled (17) are all positioned in the spraying chamber (12), the outlet of the spraying chamber (12) is connected with the third inlet of the fourth stop valve (18), and the outlet of the fourth stop valve (18) is connected with the inlet of the circulating pump (3);
the vortex tube cooling system consists of a phase change material storage tank (5), an engine air-entraining port (19), a fifth stop valve (20), a vortex tube cooling box (21), a sixth stop valve (22) and a wing anti-icing port (23);
the vortex tube refrigeration box (21) is provided with an inlet and two outlets, the inlet is an engine bleed air inlet, the first outlet is a cold air outlet, and the second outlet is a hot air outlet;
the engine bleed port (19) is connected with an inlet of a fifth stop valve (20), an outlet of the fifth stop valve (20) is connected with an inlet of a vortex tube refrigeration box (21), a first outlet of the vortex tube refrigeration box (21) is connected with a second inlet of a phase change material storage tank (5), a second outlet of the vortex tube refrigeration box (21) is connected with an airfoil anti-icing port (23), a second outlet of the phase change material storage tank (5) is connected with an inlet of a sixth stop valve (22), and an outlet of the sixth stop valve (22) is connected with the airfoil anti-icing port (23).
An on-board spray cooling system for cooling a spray medium using a phase change material and for preventing failure using a microchannel heat exchanger, comprising the steps of:
when the system operates, air is introduced from the external environment through an engine air-entraining port (19), cold air and hot air are obtained through a vortex tube refrigeration box (21), the cold air flows into a phase change material storage tank (5) to absorb heat in the phase change material and then flows into a wing anti-icing port (23) through a sixth stop valve (22), and the hot air directly flows into the wing anti-icing port (23) to provide heat for the wing to prevent the wing from icing;
the circulating pump (3) is started, cooling medium in the cooling medium storage tank (1) flows into the phase change material storage tank (5) after passing through the first stop valve (2), the circulating pump (3) and the second stop valve (4), and the phase change material in the phase change material storage tank (5) absorbs heat to reduce the temperature of the cooling medium; the liquid cooling medium flowing out of the phase change material storage tank (5) is filtered by a filter (6) to remove impurities, and the impurities are divided into two paths after flowing through a third stop valve (7);
after the flow of the first path of liquid cooling medium is regulated by a first flow regulating valve (8), the first path of liquid cooling medium flows into a first nozzle (13) and a second nozzle (14) respectively by a first flow meter (9) for atomization, the atomized cooling medium is sprayed onto a micro-channel heat exchanger (15), and the cooling capacity is transferred by the micro-channel heat exchanger (15) to finish the cooling process of a surface (17) to be cooled; after that, the cooling medium flows into the circulating pump (3) through the fourth stop valve (18) to continue circulating;
after the second path of liquid cooling medium flows into the second flow regulating valve (10) to regulate the flow, the second flow meter (11) flows into the cooling medium flow channel (16), and the cooling capacity is transferred in the cooling medium flow channel (16) through the micro-channel heat exchanger (15) to complete the cooling process of the surface (17) to be cooled; after that, the cooling medium flows into the circulating pump (3) through the fourth stop valve (18) to continue circulating;
when the system is stopped, the second stop valve (4) is closed, the first stop valve (2), the third stop valve (7) and the fourth stop valve (18) are opened, and the circulating pump (3) is used for pumping the cooling medium in the pipeline into the cooling medium storage tank (1) for storage.
The first nozzle (13), the second nozzle (14), the micro-channel heat exchanger (15) and the surface (17) to be cooled are sealed in the spray chamber (12), so that cooling medium after spray heat exchange and heat exchange in the micro-channel can flow into the circulating pump (3) along the fourth stop valve (18), and the effects of saving the cooling medium and saving energy are achieved.
The microchannel heat exchanger (15) comprises a plurality of cooling medium flow channels (16), and the specific number of the cooling medium flow channels (16) is determined according to the area of the surface (17) to be cooled.
When the heating quantity of the surface (17) to be cooled is larger than the rated cooling quantity of spray cooling, the temperature of the surface (17) to be cooled is rapidly increased, the cooling medium sprayed by the first nozzle (13) and the second nozzle (14) is directly vaporized on the surface of the micro-channel heat exchanger (15), at the moment, the liquid cooling medium still flows in the cooling medium flow channel (16), and the temperature rising rate of the surface (17) to be cooled is restrained by the micro-channel heat exchanger (15).
The vortex tube cooling box (21) comprises a plurality of vortex tubes, and the number of the vortex tubes is designed according to the actual required cold of the aircraft.
The cooling medium storage tank (1) can store water, alcohol solution or refrigerant mediums.
The phase change material storage tank (5) can store paraffin, salt or polymer.
Drawings
Fig. 1 is a schematic diagram of the present invention.
Reference numerals in fig. 1: 1. the system comprises a cooling medium storage tank, a first stop valve, a circulating pump, a second stop valve, a phase change material storage tank, a filter, a third stop valve, a first flow regulating valve, a first flow meter, a second flow regulating valve, a second flow meter, a spray chamber, a first nozzle, a second nozzle, a micro-channel heat exchanger, a cooling medium flow channel, a cooling medium surface, a cooling surface, a fourth stop valve, an engine bleed port, a fifth stop valve, a vortex tube cooling box, a sixth stop valve and an airfoil anti-icing port.
Fig. 2 is a side view of a nozzle, a microchannel heat exchanger and a surface to be cooled.
Reference numerals in fig. 2: 13. first nozzles, 15, microchannel heat exchangers, 16, cooling medium flow channels, 17, surfaces to be cooled.
Fig. 3 is a structural view of the vortex tube refrigeration case (21).
Reference numerals in fig. 3: 24. bleed air inlet 25. Cool air outlet 26. Hot air outlet.
Detailed Description
As shown in fig. 1, an on-board spray cooling system using a phase change material to cool a spray medium and using a microchannel heat exchanger to prevent failure mainly includes a cooling medium tank 1, a first shut-off valve 2, a circulation pump 3, a second shut-off valve 4, a phase change material tank 5, a filter 6, a third shut-off valve 7, a first flow regulating valve 8, a first flow meter 9, a second flow regulating valve 10, a second flow meter 11, a spray chamber 12, a first nozzle 13, a second nozzle 14, a microchannel heat exchanger 15, a cooling medium flow passage 16, a surface to be cooled 17, a fourth shut-off valve 18, an engine bleed port 19, a fifth shut-off valve 20, a vortex tube cooling box 21, a sixth shut-off valve 22, and a wing anti-icing port 23.
The micro-channel heat exchanger 15 includes a plurality of cooling medium flow channels 16 therein, and the specific number of the cooling medium flow channels 16 is determined according to the area of the surface 17 to be cooled.
The first nozzle 13, the second nozzle 14, the micro-channel heat exchanger 15 and the surface to be cooled 17 are sealed in the spray chamber 12, so that the cooling medium after spray heat exchange and micro-channel internal heat exchange can flow into the circulating pump 3 along the fourth stop valve 18, and the effects of saving the cooling medium and saving energy are achieved.
As shown in fig. 3, the vortex tube refrigeration box 21 includes a bleed air inlet 24, a cold air outlet 25 and a hot air outlet 26.
The number of vortex tubes in vortex tube refrigeration case 21 is determined based on the amount of refrigeration required by the aircraft to store the phase change material.
When the system is in operation, air is introduced from the external environment through the engine bleed port 14 and cooled and heated air is obtained through the vortex tube refrigeration box 21. The cool air flows into the phase change material storage tank 5 to absorb heat in the phase change material and then flows into the wing anti-icing port 23 through the sixth stop valve 22, and the hot air directly flows into the wing anti-icing port 23 to provide heat for the wing, so that the wing is prevented from icing;
the circulating pump 3 is started, the cooling medium in the cooling medium storage tank 1 flows into the phase change material storage tank 5 after passing through the first stop valve 2, the circulating pump 3 and the second stop valve 4, and the phase change material in the phase change material storage tank 5 absorbs heat to reduce the temperature of the cooling medium; at this time, the phase change material in the phase change material storage tank 5 gradually changes from solid state to liquid state; the liquid cooling medium flowing out of the phase change material storage tank 5 is filtered by a filter 6 to remove impurities, and is divided into two paths after flowing through a third stop valve 7;
after the flow of the first path of liquid cooling medium is regulated by a first flow regulating valve 8, the first path of liquid cooling medium flows into a first nozzle 13 and a second nozzle 14 respectively by a first flow meter 9 for atomization, the atomized cooling medium is sprayed onto a micro-channel heat exchanger 15, and the cooling capacity is transferred through the micro-channel heat exchanger 15 to finish the cooling process of the surface 17 to be cooled; after that, the cooling medium flows into the circulating pump 3 through the fourth stop valve 18 to continue circulating;
after the second path of liquid cooling medium flows into the second flow regulating valve 10 to regulate the flow, the second flow meter 11 flows into the cooling medium flow channel 16, and the cooling capacity in the cooling medium flow channel 16 is transferred through the micro-channel heat exchanger 15 to complete the cooling process of the surface 17 to be cooled; after that, the cooling medium flows into the circulating pump 3 through the fourth stop valve 18 to continue circulating;
when the heating amount of the surface to be cooled 17 fluctuates and is suddenly larger than the rated cooling amount of spray cooling, the temperature of the surface to be cooled 17 is suddenly increased, the cooling medium sprayed by the first nozzle 13 and the second nozzle 14 is directly vaporized on the surface of the micro-channel heat exchanger 15, at the moment, the liquid cooling medium still flows in the cooling medium flow channel 16, and the temperature rising rate of the surface to be cooled 17 is restrained through the micro-channel heat exchanger 15 until the heating amount is recovered to be normal.
When the system is stopped, the second stop valve 4 is closed, the first stop valve 2, the third stop valve 7 and the fourth stop valve 18 are opened, and the cooling medium in the pipeline is pumped into the cooling medium storage tank 1 by using the circulating pump 3 for storage. Simultaneously, air is led from the engine air-leading port 19 to the vortex tube refrigeration box 21, and the phase-change material is cooled by using cold air flowing out of the vortex tube refrigeration box 21, so that the phase-change material is changed from a liquid state to a solid state.
When the equipment needs cooling again, the circulation pump 3 is opened again, the second stop valve 4 is opened, and the medium in the cooling medium storage tank 1 is used again for spray cooling.
The airborne spray cooling system which uses the phase change material to cool the spray medium and uses the micro-channel heat exchanger to prevent failure has reliable performance, and the occurrence of burning devices with overhigh surface temperature when the heating quantity fluctuates is effectively prevented; and by continuously introducing air into the vortex tube refrigeration box, the cooling medium and the phase change material can be continuously cooled, and the cooling medium and the phase change material can be recycled, so that the continuous and safe operation of the system is ensured.
Claims (3)
1. An on-board spray cooling system for cooling a spray medium using a phase change material and for preventing failure using a microchannel heat exchanger, characterized by: the system consists of a surface cooling system and a vortex tube cooling system;
the surface cooling system consists of a cooling medium storage tank (1), a first stop valve (2), a circulating pump (3), a second stop valve (4), a phase change material storage tank (5), a filter (6), a third stop valve (7), a first flow regulating valve (8), a first flowmeter (9), a second flow regulating valve (10), a second flowmeter (11), a spraying chamber (12), a first nozzle (13), a second nozzle (14), a micro-channel heat exchanger (15), a cooling medium flow channel (16), a surface to be cooled (17) and a fourth stop valve (18);
the phase change material storage tank (5) is provided with two inlets and two outlets, wherein the first inlet is a cooling medium inlet, the first outlet is a cooling medium outlet, the second inlet is a cold air inlet, and the second outlet is a cold air outlet;
the third shut-off valve (7) has one inlet and two outlets, the first flowmeter (9) has one inlet and two outlets, the second flowmeter (11) has one inlet and two outlets, and the fourth shut-off valve (18) has three inlets and one outlet;
the cooling medium storage tank (1) is connected with the inlet of a first stop valve (2), the outlet of the first stop valve (2) is connected with the inlet of a circulating pump (3) and the outlet of a fourth stop valve (18), the outlet of the circulating pump (3) is connected with the inlet of a second stop valve (4), the outlet of the second stop valve (4) is connected with the first inlet of a phase change material storage tank (5), the first outlet of the phase change material storage tank (5) is connected with the inlet of a filter (6), the outlet of the filter (6) is connected with the inlet of a third stop valve (7), the first outlet of the third stop valve (7) is connected with the inlet of a first flow regulating valve (8), the outlet of the first flow regulating valve (8) is connected with the inlet of a first flow meter (9), the first outlet of the first flow meter (9) is connected with the inlet of a first nozzle (13), and the second outlet of the first flow meter (9) is connected with the inlet of a second nozzle (14);
the second outlet of the third stop valve (7) is connected with the inlet of the second flow regulating valve (10), the outlet of the second flow regulating valve (10) is connected with the inlet of the second flowmeter (11), the first outlet and the second outlet of the second flowmeter (11) are connected with the inlet of the cooling medium flow passage (16), and the outlet of the cooling medium flow passage (16) is connected with the first inlet and the second inlet of the fourth stop valve (18);
the outlets of the first nozzle (13) and the second nozzle (14) spray atomized cooling medium to the surface of the micro-channel heat exchanger (15), the micro-channel heat exchanger (15) is arranged above the surface (17) to be cooled and clings to the surface (17) to be cooled, and the cooling medium flow channel (16) is a component part of the micro-channel heat exchanger (15);
the first nozzle (13), the second nozzle (14), the microchannel heat exchanger (15) and the surface to be cooled (17) are all positioned in the spraying chamber (12), the outlet of the spraying chamber (12) is connected with the third inlet of the fourth stop valve (18), and the outlet of the fourth stop valve (18) is connected with the inlet of the circulating pump (3);
the vortex tube cooling system consists of a phase change material storage tank (5), an engine air-entraining port (19), a fifth stop valve (20), a vortex tube cooling box (21), a sixth stop valve (22) and a wing anti-icing port (23);
the vortex tube refrigeration box (21) is provided with an inlet and two outlets, the inlet is an engine bleed air inlet, the first outlet is a cold air outlet, and the second outlet is a hot air outlet;
the engine bleed port (19) is connected with an inlet of a fifth stop valve (20), an outlet of the fifth stop valve (20) is connected with an inlet of a vortex tube refrigeration box (21), a first outlet of the vortex tube refrigeration box (21) is connected with a second inlet of a phase change material storage tank (5), a second outlet of the vortex tube refrigeration box (21) is connected with an airfoil anti-icing port (23), a second outlet of the phase change material storage tank (5) is connected with an inlet of a sixth stop valve (22), and an outlet of the sixth stop valve (22) is connected with the airfoil anti-icing port (23);
the first nozzle (13), the second nozzle (14), the micro-channel heat exchanger (15) and the surface (17) to be cooled are sealed in the spray chamber (12), so that cooling medium after spray heat exchange and micro-channel heat exchange can flow into the circulating pump (3) along the fourth stop valve (18), and the effects of saving the cooling medium and saving energy are achieved;
the micro-channel heat exchanger (15) comprises a plurality of cooling medium flow channels (16), and the specific number of the cooling medium flow channels (16) is determined according to the area of the surface (17) to be cooled;
the vortex tube cooling box (21) comprises a plurality of vortex tubes, and the number of the vortex tubes is designed according to the actual required cold of the aircraft; the cooling medium storage tank (1) can store water, alcohol solution or refrigerant mediums; the phase change material storage tank (5) can store paraffin, salt or polymer.
2. An on-board spray cooling system for cooling a spray medium using a phase change material and preventing failure using a microchannel heat exchanger as claimed in claim 1, comprising the steps of:
when the system operates, air is introduced from the external environment through an engine air-entraining port (19), cold air and hot air are obtained through a vortex tube refrigeration box (21), the cold air flows into a phase change material storage tank (5) to absorb heat in the phase change material and then flows into a wing anti-icing port (23) through a sixth stop valve (22), and the hot air directly flows into the wing anti-icing port (23) to provide heat for the wing to prevent the wing from icing;
the circulating pump (3) is started, cooling medium in the cooling medium storage tank (1) flows into the phase change material storage tank (5) after passing through the first stop valve (2), the circulating pump (3) and the second stop valve (4), and the phase change material in the phase change material storage tank (5) absorbs heat to reduce the temperature of the cooling medium; the liquid cooling medium flowing out of the phase change material storage tank (5) is filtered by a filter (6) to remove impurities, and the impurities are divided into two paths after flowing through a third stop valve (7);
after flowing into a first flow regulating valve (8) to regulate flow, flowing into a first nozzle (13) and a second nozzle (14) respectively through a first flow meter (9) to be atomized, spraying the atomized cooling medium onto a micro-channel heat exchanger (15), and transmitting cold energy through the micro-channel heat exchanger (15) to finish the cooling process of a surface (17) to be cooled; after that, the cooling medium flows into the circulating pump (3) through the fourth stop valve (18) to continue circulating;
after the second path of liquid cooling medium flows into the second flow regulating valve (10) to regulate the flow, the second flow meter (11) flows into the cooling medium flow channel (16), and the cooling capacity is transferred in the cooling medium flow channel (16) through the micro-channel heat exchanger (15) to complete the cooling process of the surface (17) to be cooled; after that, the cooling medium flows into the circulating pump (3) through the fourth stop valve (18) to continue circulating;
when the system is stopped, the second stop valve (4) is closed, the first stop valve (2), the third stop valve (7) and the fourth stop valve (18) are opened, and the circulating pump (3) is used for pumping the cooling medium in the pipeline into the cooling medium storage tank (1) for storage.
3. An on-board spray cooling system for cooling a spray medium using a phase change material and preventing failure using a microchannel heat exchanger as set forth in claim 1, wherein: when the heating quantity of the surface (17) to be cooled is larger than the rated cooling quantity of spray cooling, the temperature of the surface (17) to be cooled is rapidly increased, the cooling medium sprayed by the first nozzle (13) and the second nozzle (14) is directly vaporized on the surface of the micro-channel heat exchanger (15), at the moment, the liquid cooling medium still flows in the cooling medium flow channel (16), and the temperature rising rate of the surface (17) to be cooled is restrained by the micro-channel heat exchanger (15).
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109246991B (en) * | 2018-10-12 | 2020-02-14 | 北京航空航天大学 | Spray cooling system for periodic high-power density heat load of airplane |
| CN109119873B (en) * | 2018-10-30 | 2024-02-09 | 中国工程物理研究院激光聚变研究中心 | Multi-working-medium combined spray cooling device |
| CN111511164B (en) * | 2020-03-30 | 2023-05-05 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Spray cooling phase-change heat sink integrated evaporative cooling device |
| US11453504B2 (en) | 2020-05-29 | 2022-09-27 | Northrop Grumman Systems Corporation | Passive heater for aircraft de-icing and method |
| CN115230969B (en) * | 2022-07-29 | 2024-04-09 | 南京师范大学 | Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101283231A (en) * | 2005-10-10 | 2008-10-08 | Mg创新公司 | Phase change material heat exchanger |
| JP3160814U (en) * | 2010-04-26 | 2010-07-08 | 株式会社Ｍｉｙａｓａ | Cooling system |
| CN203618277U (en) * | 2013-12-14 | 2014-05-28 | 中国航空工业集团公司第六三一研究所 | Jet cooling system for airborne electronic equipment |
| CN104697236A (en) * | 2015-02-11 | 2015-06-10 | 南京航空航天大学 | Cooling system and method of airborne heating elements based on evaporative refrigeration |
| CN106642855A (en) * | 2016-11-16 | 2017-05-10 | 南京航空航天大学 | Airborne evaporation cycle refrigeration comprehensive heat management system and method and application thereof |
| KR20170097417A (en) * | 2016-02-18 | 2017-08-28 | 엘에스산전 주식회사 | Cooling system for power converter |
| CN107223004A (en) * | 2017-06-09 | 2017-09-29 | 苏州科技大学 | A kind of device and method of microchannel surface formula misting cooling augmentation of heat transfer |
| CN107621200A (en) * | 2017-08-24 | 2018-01-23 | 南京航空航天大学 | The cold storage laser weapon spray cooling system of airborne turbine interval and method |
| CN206963258U (en) * | 2017-06-21 | 2018-02-02 | 广东合一新材料研究院有限公司 | A kind of cooling system |
| CN208205489U (en) * | 2018-03-27 | 2018-12-07 | 南京工业大学 | A kind of airborne spray cooling system preventing failure using phase-change material cooling spray medium and using micro-channel heat exchanger |
-
2018
- 2018-03-27 CN CN201810280693.2A patent/CN108362025B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101283231A (en) * | 2005-10-10 | 2008-10-08 | Mg创新公司 | Phase change material heat exchanger |
| JP3160814U (en) * | 2010-04-26 | 2010-07-08 | 株式会社Ｍｉｙａｓａ | Cooling system |
| CN203618277U (en) * | 2013-12-14 | 2014-05-28 | 中国航空工业集团公司第六三一研究所 | Jet cooling system for airborne electronic equipment |
| CN104697236A (en) * | 2015-02-11 | 2015-06-10 | 南京航空航天大学 | Cooling system and method of airborne heating elements based on evaporative refrigeration |
| KR20170097417A (en) * | 2016-02-18 | 2017-08-28 | 엘에스산전 주식회사 | Cooling system for power converter |
| CN106642855A (en) * | 2016-11-16 | 2017-05-10 | 南京航空航天大学 | Airborne evaporation cycle refrigeration comprehensive heat management system and method and application thereof |
| CN107223004A (en) * | 2017-06-09 | 2017-09-29 | 苏州科技大学 | A kind of device and method of microchannel surface formula misting cooling augmentation of heat transfer |
| CN206963258U (en) * | 2017-06-21 | 2018-02-02 | 广东合一新材料研究院有限公司 | A kind of cooling system |
| CN107621200A (en) * | 2017-08-24 | 2018-01-23 | 南京航空航天大学 | The cold storage laser weapon spray cooling system of airborne turbine interval and method |
| CN208205489U (en) * | 2018-03-27 | 2018-12-07 | 南京工业大学 | A kind of airborne spray cooling system preventing failure using phase-change material cooling spray medium and using micro-channel heat exchanger |
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