CN115610696B - Airplane ground air conditioner and control method thereof - Google Patents
Airplane ground air conditioner and control method thereof Download PDFInfo
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- CN115610696B CN115610696B CN202211447654.XA CN202211447654A CN115610696B CN 115610696 B CN115610696 B CN 115610696B CN 202211447654 A CN202211447654 A CN 202211447654A CN 115610696 B CN115610696 B CN 115610696B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/36—Other airport installations
- B64F1/362—Installations for supplying conditioned air to parked aircraft
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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
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Abstract
The application relates to the technical field of airplane ground air conditioners, in particular to an airplane ground air conditioner and a control method thereof. The aircraft ground air conditioner comprises a first-stage refrigeration system and a cold quantity distribution system, wherein the first-stage refrigeration system comprises a first-stage compressor, a front-stage evaporator and a rear-stage evaporator, the first-stage compressor is communicated with the front-stage evaporator, an inlet of the rear-stage evaporator is communicated with the front-stage evaporator, and an outlet of the rear-stage evaporator is communicated with the first-stage compressor; the cold energy distribution system comprises a cold storage tank, a circulating pump and a cold release device, wherein the cold storage tank is used for containing a heat exchange medium, and the circulating pump can enable the heat exchange medium in the cold storage tank to exchange heat with the rear-stage evaporator so as to absorb surplus cold energy, avoid over-low air outlet temperature and slow down frosting speed; the circulating pump can also make the heat transfer medium in the cold storage tank flow to the cold release device to make the cold release device cool the wind of air inlet, improve the unit refrigeration effect.
Description
Technical Field
The application relates to the technical field of airplane ground air conditioners, in particular to an airplane ground air conditioner and a control method thereof.
Background
The airplane ground air conditioning unit can supply low-temperature fresh air to the airplane, generally comprises a plurality of independent refrigerating systems provided with fixed-frequency compressors, generally requires that the air supply temperature is lower than 2 ℃, the evaporating temperature of the refrigerating systems is lower than 0 ℃, an evaporator inevitably frosts, and when the fresh air load is reduced to cause surplus of the cold capacity of the unit, the air outlet temperature is lower, and the frosting of the unit is accelerated. Under the high-temperature working condition, the temperature of an internal pipeline of the air conditioning unit and an evaporator of a refrigerating system is close to the ambient temperature, and when the air conditioning unit is started, the air supply temperature is higher, the load of the unit is overlarge, and the cooling time of the interior of an airplane is longer.
Disclosure of Invention
The application aims to provide an aircraft ground air conditioner and a control method thereof, and aims to solve the technical problems that in the prior art, when the fresh air load is reduced to cause surplus of unit cold capacity, the air outlet temperature is lower, the unit frosting is accelerated, the air supply temperature is higher when the aircraft is just started under a high-temperature working condition, the unit load is overlarge, and the cooling time in the aircraft is longer.
Based on the purpose, the application provides an aircraft ground air conditioner, which comprises a first-stage refrigerating system and a cold quantity distribution system, wherein the first-stage refrigerating system comprises a first-stage compressor, a preceding-stage evaporator and a rear-stage evaporator, the first-stage compressor is communicated with the preceding-stage evaporator, an inlet of the rear-stage evaporator is communicated with the preceding-stage evaporator, and an outlet of the rear-stage evaporator is communicated with the first-stage compressor;
the cold energy distribution system comprises a cold storage tank, a circulating pump and a cold releasing device, wherein the cold storage tank is used for containing heat exchange media, the circulating pump can enable the heat exchange media in the cold storage tank to exchange heat with the rear-stage evaporator, and the circulating pump can also enable the heat exchange media in the cold storage tank to flow to the cold releasing device.
In one embodiment of the present application, the cold rejector is located on a side of the pre-evaporator proximate to an air intake of the aircraft ground air conditioner.
In one embodiment of the application, the cold energy distribution system further comprises a first valve and a second valve, the first outlet of the cold storage tank is communicated with the inlet of the circulating pump, the outlet of the circulating pump is communicated with the inlet of the cold releaser, and the outlet of the cold releaser is communicated with the return port of the cold storage tank;
the first valve is positioned between the first outlet of the cold storage tank and the inlet of the circulation pump, and the second valve is positioned between the outlet of the circulation pump and the inlet of the cold release device.
In one embodiment of the present application, the cold energy distribution system further includes a first cold storage pipeline and a third valve, one end of the first cold storage pipeline is communicated with the second outlet of the cold storage tank, and the other end of the first cold storage pipeline is located between the first valve and the inlet of the circulating pump; the third valve is positioned on the first cold accumulation pipeline.
In one embodiment of the present application, the cold energy distribution system further includes a second cold accumulation pipeline and a fourth valve, one end of the second cold accumulation pipeline is located between the outlet of the circulating pump and the second valve, and the other end of the second cold accumulation pipeline is communicated with the return port of the cold accumulation tank; the fourth valve is positioned on the second cold accumulation pipeline.
In one embodiment of the present application, the rear stage evaporator is located in the regenerator at a position near the second outlet of the regenerator;
or, the cold storage tank is provided with a partition plate, the first outlet and the second outlet of the cold storage tank are respectively located on two sides of the partition plate, the rear-stage evaporator is located in the cold storage tank, and the rear-stage evaporator is located on one side, close to the partition plate, of the second outlet of the cold storage tank.
In one embodiment of the application, the aircraft ground air conditioner further comprises a second-stage refrigeration system, wherein the second-stage refrigeration system comprises a second-stage compressor and a second-stage evaporator, the second-stage compressor is communicated with the second-stage evaporator, and the second-stage evaporator is located on one side, far away from the air inlet of the aircraft ground air conditioner, of the air cooler.
In one embodiment of the application, the number of the second-stage refrigeration systems is multiple, the number of the cold releases is multiple, and the cold releases are communicated in parallel.
In an embodiment of the present application, the aircraft ground air conditioner further includes an air supply passage and an air blower, the cold releaser, the front stage evaporator and the rear stage evaporator are all located in the air supply passage, and the front stage evaporator is close to an air outlet of the air supply passage.
In an embodiment of the present application, the aircraft ground air conditioner further includes an outlet air temperature sensor, and the outlet air temperature sensor is used for detecting an outlet air temperature of the outlet.
Based on the above object, the present application also provides an aircraft ground air-conditioning control method, which is applied to the aircraft ground air-conditioning, and includes the following steps:
when the outlet air temperature is lower than the set temperature, controlling the heat exchange medium in the cold storage tank to exchange heat with the rear-stage evaporator so that the heat exchange medium in the cold storage tank absorbs surplus cold energy to carry out cold storage;
when the outlet air temperature is higher than the set temperature, the heat exchange medium in the cold storage tank is controlled to flow to the cold release device through the first outlet of the cold storage tank, so that the air at the air inlet is cooled through the cold release device, and the cold release is carried out.
In one embodiment of the present application, before the aircraft is picked up, the controlling the aircraft ground air conditioner to pre-cool includes: starting the first-stage refrigeration system to enable the heat exchange medium in the cold storage tank to exchange heat with the rear-stage evaporator, controlling the heat exchange medium in the cold storage tank to flow to the cold releaser through a second outlet of the cold storage tank, and cooling the air in the air supply channel through the cold releaser to realize precooling; and when the temperature in the cold storage tank reaches a preset temperature or the precooling time reaches a preset time, ending precooling.
The beneficial effect of this application mainly lies in:
the application provides an aircraft ground air conditioner, under the high temperature operating mode, before the aircraft is connected, start first stage compressor of first stage refrigerating system, the refrigerant circulates in first stage compressor, preceding stage evaporator and back stage evaporator, reduce the temperature of preceding stage evaporator and back stage evaporator, the circulating pump makes the heat transfer medium in the cold-storage tank and the heat transfer of back stage evaporator simultaneously, make the temperature of heat transfer medium reduce, the circulating pump carries the heat transfer medium in the cold-storage tank to the cold releaser, the cold releaser can cool down the wind that gets into aircraft ground air conditioner, in order to reduce the refrigerant in the preceding stage evaporator and the difference in temperature of the wind before this preceding stage evaporator, the cooling time that the temperature of having shortened the unit air supply reaches the settlement temperature, quick invariable air-out temperature improves the refrigeration effect of unit, effectively avoid the unit high load. When the aircraft ground air conditioner supplies cold for the aircraft under the partial load working condition, the unit air-out temperature can be lower, and the circulating pump can make the heat transfer medium and the back stage evaporator heat transfer in the cold storage tank to absorb the abundant cold volume that first order refrigerating system produced, avoid the air-out temperature to hang down excessively, thereby slow down the evaporimeter speed of frosting.
Drawings
In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of an aircraft ground air conditioner provided in an embodiment of the present application;
FIG. 2 is a schematic view of an aircraft ground air conditioner provided in an embodiment of the present application in a cold storage mode;
fig. 3 is a schematic structural diagram of a cold storage tank in an aircraft ground air conditioner according to an embodiment of the present application;
fig. 4 is a schematic structural diagram of a modification of the aircraft ground air conditioner according to the embodiment of the present application;
fig. 5 is a schematic structural diagram of another modification of the aircraft ground air conditioner according to the embodiment of the present application;
fig. 6 is a schematic view of another modification of the aircraft ground air conditioner provided in the embodiment of the present application in a cold storage mode.
Icon: 1-a first stage refrigeration system; 2-a second stage refrigeration system; 3-a second stage compressor; 4-a second stage evaporator; 5-a first stage compressor; 6-a pre-evaporator; 7-a rear-stage evaporator; 8-a cold storage tank; 9-a circulating pump; 10-a cooling releasing device; 11-a first valve; 12-a second valve; 13-a third valve; 14-a fourth valve; 15-a first cold storage pipeline; 16-a second cold storage pipeline; 17-a separator; 18-a first outlet; 19-a second outlet; 20-a blower; 21-an air supply channel; 22-an air outlet temperature sensor; 23-ambient temperature sensor; 24-a second stage condenser; 25-first stage condenser; 26-a pressure transmitter; 27-an expansion valve; 28-Return port.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the following embodiments, and it should be apparent that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it should be noted that, as the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. appear, their indicated orientations or positional relationships are based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" as appearing herein are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" should be interpreted broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Referring to fig. 1 to 6, the present embodiment provides an aircraft ground air conditioner, including a first-stage refrigeration system 1, a second-stage refrigeration system 2 and a refrigeration capacity distribution system, where the second-stage refrigeration system 2 includes a second-stage compressor 3 and a second-stage evaporator 4, the second-stage compressor 3 is communicated with the second-stage evaporator 4, the first-stage refrigeration system 1 includes a first-stage compressor 5, a preceding-stage evaporator 6 and a subsequent-stage evaporator 7, the first-stage compressor 5 is communicated with the preceding-stage evaporator 6, an inlet of the subsequent-stage evaporator 7 is communicated with the preceding-stage evaporator 6, and an outlet of the subsequent-stage evaporator 7 is communicated with the first-stage compressor 5; the cold quantity distribution system comprises a cold storage tank 8, a circulating pump 9 and a cold releaser 10, wherein the cold storage tank 8 is used for containing heat exchange media, the circulating pump 9 can enable the heat exchange media in the cold storage tank 8 to exchange heat with the rear-stage evaporator 7, and the circulating pump 9 can also enable the heat exchange media in the cold storage tank 8 to flow to the cold releaser 10.
In the aircraft ground air conditioner provided by this embodiment, under a high-temperature working condition, before the aircraft is connected, the air duct and the evaporator inside the aircraft unit need to be precooled, the first-stage compressor 5 of the first-stage refrigeration system 1 is started, the refrigerant circulates in the first-stage compressor 5, the preceding-stage evaporator 6 and the subsequent-stage evaporator 7, the temperatures of the preceding-stage evaporator 6 and the subsequent-stage evaporator 7 are reduced, meanwhile, the heat exchange medium in the cold storage tank 8 exchanges heat with the subsequent-stage evaporator 7 by the circulating pump 9, the temperature of the heat exchange medium is reduced, the heat exchange medium in the cold storage tank 8 is conveyed to the cold releaser 10 by the circulating pump 9 from the second outlet 19, the cold releaser 10 can cool the air in the air supply channel 21, so as to achieve precooling, shorten the cooling time for the air supply temperature of the aircraft unit to reach a set temperature, quickly maintain the air outlet temperature constant, improve the refrigeration effect of the aircraft unit, and effectively avoid the overload of the aircraft unit. When the ground air conditioner of the airplane supplies cold to the airplane under the partial load working condition, the air outlet temperature of a unit may be lower than a set temperature (the set temperature range is minus 5 to 2 ℃), and at the moment, the heat exchange medium in the cold storage tank 8 can exchange heat with the rear-stage evaporator 7 through the circulating pump 9, so that surplus cold generated by the first-stage refrigerating system 1 is absorbed, namely the surplus cold is stored in the cold storage tank 8, the air outlet temperature is prevented from being too low, and the frosting speed of the evaporator is reduced. After the cold storage tank 8 stores cold, the heat exchange medium can enter the cold release device 10 through the first outlet 18 and the circulating pump 9 to cool the fresh air, so that the second-stage compressor 3 and/or the first-stage compressor 5 can not be started under partial working conditions, and the refrigerating efficiency of the unit can be improved on the premise of not improving the operating power of the unit.
In one embodiment, the aircraft ground air conditioner further comprises an air supply passage 21 and an air blower 20, wherein the air blower 20, the second stage evaporator 4, the air cooler 10, the front stage evaporator 6 and the rear stage evaporator 7 are all positioned in the air supply passage 21, the second stage evaporator 4 is close to an air inlet of the air supply passage 21, and the front stage evaporator 6 is close to an air outlet of the air supply passage 21.
For example, referring to fig. 1, under the action of the blower 20, air in the external environment enters the air supply passage 21 along the arrow direction a, and after being cooled by the air cooler 10, the second stage evaporator 4 and the front stage evaporator 6, enters the aircraft from the air outlet of the air supply passage 21 to cool the interior of the aircraft.
In one embodiment, as shown in fig. 1 and 3, the regenerator 8 has a first outlet port 18, a second outlet port 19, and a return port 28. The partition plate 17 is provided in the cool storage tank 8, the first outlet 18 and the second outlet 19 of the cool storage tank 8 are respectively located at both sides of the partition plate 17, the first outlet 18 is located at a side wall of the cool storage tank 8, and the second outlet 19 is located at a bottom plate of the cool storage tank 8. The rear stage evaporator 7 is located in the cool storage tank 8, and the rear stage evaporator 7 is located in the cool storage tank at a position close to the second outlet 19, and the second outlet 19 is located below the rear stage evaporator 7.
In some embodiments, the partition plate 17 is fixedly connected to the bottom plate of the cool storage tank 8, and a gap is formed between the upper edge of the partition plate 17 and the top plate of the cool storage tank 8, so as to ensure that the heat exchange medium in the entire cool storage tank can exchange heat, and thus the overall temperature is consistent.
The partition 17 may not be provided inside the cool storage tank 8.
In one embodiment, referring to FIG. 1, the air cooler 10 is located on the side of the backing evaporator near the air intake of the aircraft ground air conditioner.
In one embodiment, the cold rejector 10 is located on the side of the second stage evaporator 4 near the intake. In such a way, the air can exchange heat with the cold releaser 10 before passing through the second-stage evaporator 4, that is, the cold releaser 10 precools the air in the air supply channel, so that the temperature difference between the refrigerant in the second-stage evaporator 4 and the air before passing through the second-stage evaporator 4 is reduced, the cooling time is shortened, and the working efficiency is improved.
In one embodiment, referring to fig. 1, the aircraft ground air conditioner further includes an outlet air temperature sensor 22, and the outlet air temperature sensor 22 is configured to detect an outlet air temperature of the air outlet.
In one embodiment, the aircraft ground air conditioner further comprises a control system, wherein the control system is used for comparing the outlet air temperature with a set temperature, and the set temperature can be set according to actual needs.
Illustratively, the control system may be a PLC control system, e.g., S7-200.
In one embodiment, referring to fig. 1, the aircraft ground air conditioner further comprises an ambient temperature sensor 23, the ambient temperature sensor 23 being configured to detect an ambient temperature.
The solid arrows in fig. 1 indicate the flow direction of the heat exchange medium, and the hollow arrows indicate the flow direction of the refrigerant in each of the first-stage refrigeration system 1 and the second-stage refrigeration system 2.
In one embodiment, the second stage refrigeration system 2 further comprises a second stage condenser 24, the outlet of the second stage compressor 3 is in communication with an inlet of the second stage condenser 24, an outlet of the second stage condenser 24 is in communication with an inlet of the second stage evaporator 4, and an outlet of the second stage evaporator 4 is in communication with a return air port of the second stage compressor 3. Similarly, the first-stage refrigeration system 1 further includes a first-stage condenser 25, and the connection relationship between the first-stage condenser 25 and the first-stage compressor 5, the preceding-stage evaporator 6, and the following-stage evaporator 7 is not described in detail herein.
It should be noted that the second stage refrigeration system 2 further includes a pressure transmitter 26 and an expansion valve 27, and the pressure transmitter 26 and the expansion valve 27 are both in the prior art and will not be described in detail herein.
Illustratively, the front-stage evaporator 6 is of a copper tube-aluminum fin structure, is positioned in the air supply channel 21 and exchanges heat with fresh air processed by the ground air conditioner of the airplane, the rear-stage evaporator 7 is a shell-and-tube heat exchanger, and the rear-stage evaporator 7 is placed in the cold storage tank 8 and exchanges heat with a heat exchange medium. For example, the heat exchange medium may be ethylene glycol, or may be other phase change materials, as long as the heat exchange function can be achieved.
In one embodiment, referring to fig. 1 and 2, the refrigeration capacity distribution system further comprises a first valve 11 and a second valve 12, the first outlet 18 of the cold storage tank 8 is communicated with the inlet of the circulating pump 9, the outlet of the circulating pump 9 is communicated with the inlet of the cold releaser 10, and the outlet of the cold releaser 10 is communicated with the return port 28 of the cold storage tank 8; the first valve 11 is located between the first outlet 18 of the cold storage tank 8 and the inlet of the circulation pump 9, and the second valve 12 is located between the outlet of the circulation pump 9 and the inlet of the air cooler 10.
When the machine is connected, when the outlet air temperature is higher than the set temperature, the circulating pump 9, the first valve 11 and the second valve 12 are opened, the cold energy stored in the cold storage tank 8 is released, specifically, the circulating pump 9 conveys the heat exchange medium in the cold storage tank 8 to the cold release device 10 through the first outlet 18, and the air in the air supply channel 21 is cooled, so that the temperature difference between the refrigerant in the second-stage evaporator 4 and the air before passing through the second-stage evaporator is reduced. The heat exchange medium flows back to the cold storage tank 8 through the outlet of the cold releaser 10 and the return port 28 of the cold storage tank 8, so that the circulating heat exchange is realized.
In one embodiment, the cold energy distribution system further comprises a first cold accumulation line 15 and a third valve 13, one end of the first cold accumulation line 15 is communicated with the second outlet 19 of the cold accumulation tank 8, and the other end of the first cold accumulation line 15 is located between the first valve 11 and the inlet of the circulation pump 9; the third valve 13 is located on the first cold accumulation line 15.
Under a high-temperature working condition, wind needs to be precooled before the aircraft is connected, specifically, the circulation pump 9, the second valve 12 and the third valve 13 are started, the first-stage compressor 5 of the first-stage refrigeration system 1 is started, the refrigerant circulates in the first-stage compressor 5, the preceding-stage evaporator 6 and the subsequent-stage evaporator 7, the temperatures of the preceding-stage evaporator 6 and the subsequent-stage evaporator 7 are reduced, meanwhile, the circulation pump 9 conveys the heat exchange medium in the cold storage tank 8 to the cold release device 10 through the second outlet 19 and the first cold storage pipeline 15, the heat exchange medium flows back to the cold storage tank 8 through the outlet of the cold release device 10 and the return opening 28 of the cold storage tank 8, when the temperature in the cold storage tank 8 reaches a preset temperature (for example, the preset temperature range is-5 ℃ to 2 ℃) or when the precooling time reaches a preset time (for example, the preset time range is 5 ℃ to 40min), the first-stage compressor 5 of the first-stage refrigeration system 1 stops working, and the second valve 12 and the third valve 13 are closed, namely, the precooling mode exits. The precooling mode is started, so that the cooling time of the unit air supply temperature reaching the set temperature can be shortened, the air outlet temperature is quickly kept constant, the refrigerating effect of the unit is improved, and the unit overload is effectively avoided.
In one embodiment, the refrigeration capacity distribution system further comprises a second cold storage pipeline 16 and a fourth valve 14, one end of the second cold storage pipeline 16 is positioned between the outlet of the circulating pump 9 and the second valve 12, and the other end of the second cold storage pipeline 16 is communicated with the return port 28 of the cold storage tank 8; the fourth valve 14 is located on the second cold storage conduit 16.
When the aircraft is connected, under the working condition of partial load, the air conditioning unit supplies cold to the aircraft, the cold energy of the unit is larger, and when the control system detects that the air outlet temperature of the unit is lower than the set temperature, the cold accumulation mode is started. Specifically, the third valve 13, the fourth valve 14 and the circulation pump 9 are opened. Because the refrigerant circulates in the first-stage compressor 5, the preceding-stage evaporator 6 and the subsequent-stage evaporator 7, the temperature of the preceding-stage evaporator 6 and the subsequent-stage evaporator 7 is reduced, then the heat exchange medium of the cold storage tank 8 is conveyed to the second cold storage pipeline 16 through the second outlet 19 and the first cold storage pipeline 15 by the circulating pump 9, the heat exchange medium flows back into the cold storage tank 8 through the second cold storage pipeline 16 and the return port 28, the heat exchange medium on one side of the subsequent-stage evaporator 7 in the cold storage tank is cooled by exchanging heat with the subsequent-stage evaporator 7, and the cooled heat exchange medium is circularly conveyed to the other side of the cold storage tank, so that cold storage is realized, and when the control system detects that the air outlet temperature of the air conditioning unit is equal to or higher than the set temperature, the third valve 13 and the fourth valve 14 are closed, namely the cold storage mode exits. Through the cold-storage mode, absorb the abundant cold volume that first order refrigerating system produced, avoid the air-out temperature to hang down excessively to slow down the evaporimeter speed of frosting.
For example, the first valve 11, the second valve 12, the third valve 13, and the fourth valve 14 may all be solenoid valves.
The flow of circulating pump 9 can be adjusted, and exemplarily, the flow of circulating pump 9 can infinitely variable control, and control system adjusts the flow of circulating pump 9, maintains the air-out temperature constant.
In one embodiment, the number of the second-stage refrigeration systems 2 is multiple, the number of the cold releases 10 is multiple, the multiple cold releases 10 are connected in parallel, and the multiple cold releases and the multiple second-stage refrigeration systems may be in a one-to-one correspondence relationship, for example. It should be noted that the number of the coolers and the number of the second stage refrigeration systems may not be equal.
In this embodiment, the first-stage refrigeration system 1 and the plurality of second-stage refrigeration systems 2 are independent refrigeration systems.
Illustratively, referring to fig. 4, the number of the second-stage refrigeration systems 2 is two, each second-stage refrigeration system 2 comprises a second-stage evaporator 4, one side of each second-stage evaporator 4 close to the air inlet is provided with a cold releaser 10, illustratively, referring to fig. 4, the number of the cold releasers 10 is two, the two cold releasers 10 are connected in parallel, specifically, the outlet of the circulating pump 9 is simultaneously communicated with the inlets of the two cold releasers 10, and the outlets of the two cold releasers 10 are both communicated with the return port 28 of the cold storage tank 8.
When the cold release device 10 cools the fresh air, the second-stage compressor 3 is not started, or the second-stage compressor 3 in one of the second-stage refrigeration systems 2 is started, so that the refrigerating capacity of the unit can be improved on the premise of not improving the running power of the unit.
In summary, the aircraft ground air conditioner provided by this embodiment has the advantages of preventing hot air from being supplied to an aircraft when the aircraft is started under a high-load working condition, quickly keeping the outlet air temperature constant to reach a set temperature, and increasing the refrigerating capacity of the unit on the premise of not increasing the power of the unit; under the partial load operating mode, have and absorb unnecessary cold volume to feedback back to unit refrigerating system's function, not only can avoid the air-out temperature to hang down excessively, slow down the evaporimeter speed of frosting, can also avoid cold and hot offsetting each other, delay the effect of compressor start-stop time.
The aircraft ground air conditioner provided by this embodiment may not include the second-stage refrigeration system 2, and as an example, referring to fig. 5 and fig. 6, the aircraft ground air conditioner provided by this embodiment includes a first-stage refrigeration system 1 and a refrigeration capacity distribution system, where the first-stage refrigeration system 1 includes a first-stage compressor 5, a preceding-stage evaporator 6 and a subsequent-stage evaporator 7, the first-stage compressor 5 is communicated with the preceding-stage evaporator 6, an inlet of the subsequent-stage evaporator 7 is communicated with the preceding-stage evaporator 6, and an outlet of the subsequent-stage evaporator 7 is communicated with the first-stage compressor 5; the cold quantity distribution system comprises a cold storage tank 8, a circulating pump 9 and a cold releaser 10, wherein the cold storage tank 8 is used for containing heat exchange media, the circulating pump 9 can enable the heat exchange media in the cold storage tank 8 to exchange heat with the rear-stage evaporator 7, and the circulating pump 9 can also enable the heat exchange media in the cold storage tank 8 to flow to the cold releaser 10.
In the aircraft ground air conditioner provided by this embodiment, under a high-temperature working condition, before the aircraft is connected, the first-stage compressor 5 of the first-stage refrigeration system 1 is started, a refrigerant circulates in the first-stage compressor 5, the preceding-stage evaporator 6 and the subsequent-stage evaporator 7, the temperatures of the preceding-stage evaporator 6 and the subsequent-stage evaporator 7 are reduced, meanwhile, the circulating pump 9 makes a heat exchange medium in the cold storage tank 8 exchange heat with the subsequent-stage evaporator 7, so that the temperature of the heat exchange medium is reduced, the circulating pump 9 conveys the heat exchange medium in the cold storage tank 8 to the cold releaser 10, the cold releaser 10 can cool air entering the aircraft ground air conditioner, so as to reduce the temperature difference between the refrigerant in the preceding-stage evaporator 6 and air before the preceding-stage evaporator 6, shorten the cooling time for the air supply temperature of the aircraft unit to reach a set temperature, quickly maintain the air outlet temperature constant, improve the refrigeration effect of the aircraft ground air conditioner, and effectively avoid the over-load of the aircraft. When the aircraft ground air conditioner supplies cold to the aircraft under the partial load operating mode, the unit air-out temperature can be lower, and circulating pump 9 can make the heat transfer medium in the cold storage tank 8 and the heat transfer of back stage evaporator 7 to absorb the abundant cold volume that first order refrigerating system 1 produced, avoid the air-out temperature to hang down excessively, thereby slow down the evaporimeter and frosted speed.
Referring to fig. 5, the cold rejector 10 is located on the side of the backing evaporator 6 adjacent the air intake of the aircraft floor air conditioner. Under the action of the blower 20, air in the external environment enters the air supply channel 21 along the arrow direction a, is cooled by the air cooler 10 and the front-stage evaporator 6, and then enters the airplane from the air outlet of the air supply channel 21 to cool the interior of the airplane.
Illustratively, when the ground air conditioner of the aircraft supplies cold to the aircraft under the partial load working condition, that is, when the rated cold capacity of the ground air conditioner of the aircraft is greater than the cold capacity required by the aircraft, if the control system detects that the outlet air temperature is lower than the set temperature, the cold storage mode can be started, as shown in fig. 6, the third valve 13 and the fourth valve 14 are opened, under the action of the circulating pump 9, the heat exchange medium enters the first cold storage pipeline 15 from the second outlet 19 of the cold storage tank 8, and flows back into the cold storage tank 8 from the return port 28 through the second cold storage pipeline 16, so as to absorb the surplus cold capacity generated by the first-stage refrigeration system, avoid the outlet air temperature being too low, and thus slow down the frosting speed of the evaporator.
The embodiment also provides an aircraft ground air-conditioning control method, which is applied to the aircraft ground air-conditioning provided by the embodiment, and the aircraft ground air-conditioning control method comprises the following steps:
when the outlet air temperature is lower than the set temperature, controlling the heat exchange medium in the cold storage tank 8 to exchange heat with the rear-stage evaporator 7 so that the heat exchange medium in the cold storage tank 8 absorbs surplus cold energy to carry out cold storage;
when the outlet air temperature is higher than the set temperature, the heat exchange medium in the cold storage tank is controlled to flow to the cold releaser 10 through the first outlet 18 of the cold storage tank to release the cold so as to cool the air in the air inlet through the cold releaser.
In some embodiments, when the aircraft is on the aircraft, and the outlet air temperature is detected to be lower than the set temperature, and the first-stage refrigeration system 1 is in the start state at this time, the third valve 13, the circulating pump 9, and the fourth valve 14 are controlled to be opened, so that the heat exchange medium in the cool storage tank 8 circulates between the second outlet 19 and the return port 28, thereby performing cool storage; and when the outlet air temperature reaches the set temperature, controlling the third valve 13, the circulating pump 9 and the fourth valve 14 to be closed, and finishing cold accumulation.
Illustratively, when the ground air conditioner of the aircraft supplies cold to the aircraft under the partial load working condition, that is, when the rated cold capacity of the ground air conditioner of the aircraft is greater than the cold capacity required by the aircraft, if the control system detects that the outlet air temperature is lower than the set temperature, the cold storage mode can be started, as shown in fig. 2 and fig. 6, the third valve 13 and the fourth valve 14 are opened, under the action of the circulating pump 9, the heat exchange medium enters the first cold storage pipeline 15 from the second outlet 19 of the cold storage tank 8, and flows back into the cold storage tank 8 from the return port 28 through the second cold storage pipeline 16, so as to absorb the surplus cold capacity generated by the first stage refrigeration system, avoid the outlet air temperature being too low, and thus slow down the frosting speed of the evaporator.
In other embodiments, when the aircraft is on, and the outlet air temperature is detected to be greater than the set temperature, the first valve 11, the circulating pump 9 and the second valve 12 are controlled to be opened, so that the heat exchange medium in the cold storage tank 8 circulates among the first outlet 18, the cold releaser 10 and the return opening 28, and the cold release is performed; and when the outlet air temperature reaches the set temperature, controlling the first valve 11, the circulating pump 9 and the second valve 12 to be closed, and ending the cooling.
Illustratively, when the cold quantity generated by starting the compressors of the two refrigeration systems is larger than the cold quantity required in the engine room, and the cold quantity generated by starting the compressor of one refrigeration system is not enough to cool the engine room, the cold release mode can be started under the condition of starting the compressor of one refrigeration system, so that the cooling can be assisted, the environment of the engine room is comfortable, the running power of the unit can be reduced, and the energy can be saved.
Before the aircraft is connected, the ground air conditioner of the aircraft is controlled to pre-cool, and the method specifically comprises the following steps: starting the first-stage refrigeration system 1 to enable the heat exchange medium in the cold storage tank 8 to exchange heat with the rear-stage evaporator 7, controlling the heat exchange medium in the cold storage tank 8 to flow to the cold releaser through a second outlet 19 of the cold storage tank 8, and cooling the air in the air supply channel through the cold releaser to realize precooling; and when the temperature in the cold storage tank 8 reaches the preset temperature or the precooling time reaches the preset time, ending precooling.
When precooling is needed, the first-stage refrigeration system 1 is controlled to be started so that the heat exchange medium in the cold storage tank 8 exchanges heat with the rear-stage evaporator 7; controlling the third valve 13, the circulating pump 9 and the second valve 12 to be opened so as to enable the heat exchange medium in the cold storage tank 8 to circulate in the cold release device 10 and the cold storage tank 8, thereby cooling the air in the air supply channel 21 to realize precooling; and when the temperature in the cold accumulation tank 8 reaches the preset temperature or the precooling time reaches the preset time, controlling the third valve 13, the circulating pump 9 and the second valve 12 to be closed, and finishing precooling.
It is emphasized that precooling is generally required before the aircraft is connected, i.e., in preparation for the aircraft being connected.
In one embodiment, in a high-temperature weather, before supplying cold to the aircraft (i.e., before landing), the pre-cooling mode may be started, the second valve 12 and the third valve 13 are opened, the first-stage compressor 5 of the first-stage refrigeration system 1 is started, refrigerant circulates in the first-stage compressor 5, the preceding-stage evaporator 6, and the subsequent-stage evaporator 7, so as to reduce the temperature of the evaporators in the refrigeration systems, and at the same time, the circulation pump 9 delivers the heat exchange medium in the cold storage tank 8 to the cold release device 10 through the first cold storage pipeline 15, and the cold release device 10 cools the air in the air supply channel, so as to reduce the temperature difference between the refrigerant in the second-stage evaporator 4 and the air before passing through the second-stage evaporator, and when the temperature in the cold storage tank 8 reaches a preset temperature or the pre-cooling time reaches a preset time, the pre-cooling mode may be exited, at this time, the second valve 12 and the third valve 13 are closed, and the first-stage compressor 5 stops operating.
Through the cold quantity distribution system, precooling is carried out before the aircraft is connected, and cold is released when the aircraft is connected, which is equivalent to improving the refrigerating capacity of the unit, quickly keeping the air outlet temperature constant, improving the refrigerating effect of the unit, effectively avoiding the over-high load of the unit, reducing the overload probability of the unit and improving the comfort level of the engine room on the premise of not improving the running power of the unit.
It should be noted that the control system of the aircraft ground air conditioner is used for executing the control method of the aircraft ground air conditioner in the above embodiment.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.
Claims (12)
1. An aircraft ground air conditioner is characterized by comprising a first-stage refrigeration system and a cold quantity distribution system, wherein the first-stage refrigeration system comprises a first-stage compressor, a preceding-stage evaporator and a rear-stage evaporator, the first-stage compressor is communicated with the preceding-stage evaporator, an inlet of the rear-stage evaporator is communicated with the preceding-stage evaporator, and an outlet of the rear-stage evaporator is communicated with the first-stage compressor;
the cold energy distribution system comprises a cold storage tank, a circulating pump and a cold release device, wherein the cold storage tank is used for containing a heat exchange medium, the circulating pump can enable the heat exchange medium in the cold storage tank to exchange heat with the rear-stage evaporator, and the circulating pump can enable the heat exchange medium in the cold storage tank to flow to the cold release device.
2. An aircraft floor air conditioner according to claim 1, wherein the air rejector is located on a side of the pre-evaporator proximate an air intake of the aircraft floor air conditioner.
3. An aircraft floor air conditioner as claimed in claim 1, wherein the refrigeration distribution system further comprises a first valve and a second valve, the first outlet of the cold storage tank is in communication with the inlet of the circulation pump, the outlet of the circulation pump is in communication with the inlet of the cold releaser, and the outlet of the cold releaser is in communication with the return port of the cold storage tank;
the first valve is positioned between the first outlet of the cold storage tank and the inlet of the circulation pump, and the second valve is positioned between the outlet of the circulation pump and the inlet of the cold release device.
4. An aircraft floor air conditioner according to claim 3, wherein the refrigeration capacity distribution system further comprises a first cold storage pipeline and a third valve, one end of the first cold storage pipeline is communicated with the second outlet of the cold storage tank, and the other end of the first cold storage pipeline is located between the first valve and the inlet of the circulating pump; the third valve is positioned on the first cold accumulation pipeline.
5. An aircraft floor air conditioner according to claim 3, wherein the refrigeration capacity distribution system further comprises a second cold storage pipeline and a fourth valve, one end of the second cold storage pipeline is located between the outlet of the circulation pump and the second valve, and the other end of the second cold storage pipeline is communicated with the return port of the cold storage tank; the fourth valve is positioned on the second cold accumulation pipeline.
6. An aircraft ground air conditioner according to claim 4, wherein the rear stage evaporator is located within the regenerator adjacent the second outlet of the regenerator;
or, the cold storage tank is provided with a partition plate, the first outlet and the second outlet of the cold storage tank are respectively located on two sides of the partition plate, the rear-stage evaporator is located in the cold storage tank, and the rear-stage evaporator is located on one side, close to the partition plate, of the second outlet of the cold storage tank.
7. An aircraft floor air conditioner according to claim 1, further comprising a second stage refrigeration system including a second stage compressor and a second stage evaporator, the second stage compressor being in communication with the second stage evaporator, the second stage evaporator being located on a side of the air rejector remote from the air intake of the aircraft floor air conditioner.
8. An aircraft floor air conditioner as claimed in claim 7, wherein the number of the second stage refrigeration system is plural, the number of the air coolers is plural, and the plural air coolers are connected in parallel.
9. An aircraft floor air conditioner according to any one of claims 1 to 8, further comprising a supply air duct and a supply air blower, the cold release device, the pre-evaporator and the post-evaporator all being located within the supply air duct, the pre-evaporator being proximate an air outlet of the supply air duct.
10. An aircraft floor air conditioner according to claim 7, further comprising an outlet air temperature sensor for detecting the outlet air temperature of the outlet air outlet.
11. An aircraft ground air conditioning control method, characterized in that it is applied to an aircraft ground air conditioning system according to any one of claims 1 to 10, comprising the steps of:
when the outlet air temperature is lower than the set temperature, controlling the heat exchange medium in the cold storage tank to exchange heat with the rear-stage evaporator so that the heat exchange medium in the cold storage tank absorbs surplus cold energy to carry out cold storage;
when the outlet air temperature is higher than the set temperature, the heat exchange medium in the cold storage tank is controlled to flow to the cold release device through the first outlet of the cold storage tank, so that the air at the air inlet is cooled through the cold release device, and the cold release is carried out.
12. The aircraft ground air conditioning control method of claim 11, wherein controlling the aircraft ground air conditioning to pre-cool before the aircraft is picked up comprises: starting the first-stage refrigeration system to enable the heat exchange medium in the cold storage tank to exchange heat with the rear-stage evaporator, controlling the heat exchange medium in the cold storage tank to flow to the cold releaser through a second outlet of the cold storage tank, and cooling the air in the air supply channel through the cold releaser to realize precooling; and when the temperature in the cold storage tank reaches a preset temperature or the precooling time reaches a preset time, ending precooling.
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| JP2004276870A (en) * | 2003-03-18 | 2004-10-07 | Agp Corp | Cooling-medium distributed type air-conditioner for air craft and mobile air-conditioner |
| CN100470152C (en) * | 2006-10-12 | 2009-03-18 | 广东省吉荣空调设备公司 | Dynamic high temperature cool accumulation air conditioner system |
| CN110371315B (en) * | 2019-08-20 | 2024-03-05 | 无锡雪鸥移动空调有限公司 | Cold-storage low-energy-consumption aircraft ground air conditioner |
| CN112178843A (en) * | 2020-09-21 | 2021-01-05 | 广东申菱环境系统股份有限公司 | Air conditioning unit with heat storage function and control method thereof |
| CN112856551B (en) * | 2021-01-18 | 2022-04-12 | 北京理工大学 | Solar energy step phase change heat storage coupling air source heat pump heating system and method |
| CN215808967U (en) * | 2021-06-25 | 2022-02-11 | 无锡雪鸥移动空调有限公司 | Cold and hot common storage aircraft ground air conditioning unit |
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