CN203482564U - Airborne liquid cooling system for airplane load refrigeration - Google Patents
Airborne liquid cooling system for airplane load refrigeration Download PDFInfo
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- CN203482564U CN203482564U CN201320532305.8U CN201320532305U CN203482564U CN 203482564 U CN203482564 U CN 203482564U CN 201320532305 U CN201320532305 U CN 201320532305U CN 203482564 U CN203482564 U CN 203482564U
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- ice
- storage tank
- heat exchanger
- storage box
- liquid
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Abstract
The utility model provides an airborne liquid cooling system for airplane load refrigeration. The system comprises a liquid storage tank, a water pump and a heat exchanger, wherein the liquid storage tank is connected with the two ends of an airplane load inlet and an airplane load outlet to form a cooling liquid circulation loop; the outlet pipeline of an airplane load respectively communicates with the inlets of an ice storage tank and the heat exchanger which are in parallel arrangement; the outlet of the ice storage tank communicates with the inlet of the liquid storage tank through a second rapid joint; and the inlet of the ice storage tank communicates with the outlet pipeline of the airplane load through a first rapid joint. According to the utility model, a high temperature cooling liquid after airplane load heat exchange respectively enter the ice storage tank and the heat exchanger for cooling so that the refrigerating capacity disadvantage of the heat exchanger is made up through the refrigeration of the ice storage tank, thus the requirement for quite large refrigerating capacity is satisfied under the condition that quite small airborne electric power is consumed during an airplane flying process.
Description
Technical field
The utility model relates to aircraft airborne refrigeration technology field, is specifically related to a kind of airborne liquid cooling system for aircraft load refrigeration.
Background technology
Along with a large amount of utilizations of air environment, the heat load of electronic equipment also improves constantly, and the operating ambient temperature of electronic equipment also has influence on its reliability and life-span.So air environment is more and more higher to the requirement of the refrigerating capacity of cooling system on the one hand; On the other hand, due to the particularity of airborne equipment, also very strict to the restriction of the volume of cooling system, weight, electrical power.So airborne liquid cooling system should meet the requirement that refrigerating capacity is large, meet again the requirement that volume is little, lightweight, consumption of electric power is little.
Because electronic equipment on aircraft is many, produce heat awing large, by air and cooling fluid, the heat exchange in heat exchanger is transferred to ambient atmosphere by the thermal force of electronic equipment to airborne liquid cooling system.In current airborne liquid cooling system, for the air general using aircraft ram-air of heat exchange, and the air inflow of ram-air is often subject to the restriction of aircraft flight speed, aircraft altitude and air intake duct, generally can not meet the requirement of large heat exchange amount.
Utility model content
In order to overcome existing issue, the utility model provides a kind of airborne liquid cooling system for aircraft load refrigeration, is not subject to aircraft ram-air air inlet quantitative limitation, and reaches the requirement of larger refrigerating capacity.
For achieving the above object, the utility model has adopted following technical scheme: a kind of airborne liquid cooling system for aircraft load refrigeration, comprise the liquid reserve tank, water pump and the heat exchanger that are connected to aircraft load import and export two ends and form liquid circulation loop, the export pipeline of described aircraft load is communicated with the entrance of the ice-storage box being arranged in parallel, heat exchanger respectively; The outlet of described ice-storage box is communicated with the entrance of liquid reserve tank by the second snap joint, and the entrance of ice-storage box is communicated with the export pipeline of described aircraft load by the first snap joint.
For can according to the variation of aircraft load request refrigerating capacity regulate the ice-storage box of flowing through cooling fluid flow, the entrance pipe of described ice-storage box is provided with flow control valve.
Further, the top of described liquid reserve tank be provided with expansion drum with for the automatic exhaust steam valve of air-discharging.
The utility model is at the two ends of the heat exchanger in liquid circulation loop and connect an ice-storage box, water pump imports the cooling fluid meeting the demands in liquid reserve tank in aircraft load, cooling fluid temperature after aircraft load heat exchange raises, from its outlet, enter respectively heat exchanger in parallel and ice-storage box, after making the temperature of cooling fluid reduce after heat exchange, return in liquid reserve tank, reach aircraft load is carried out to cooling object.
The top of liquid reserve tank and the filling of expanding are communicated with, and can maintain the constant pressure of liquid reserve tank inside, and the automatic exhaust steam valve that top arranges is for getting rid of the air in airborne liquid cooling system, improves refrigeration.For monitoring machine carrier fluid cooling system better, can be on the entrance pipe of aircraft load set temperature transducer and pressure sensor, simultaneously at the inner set temperature transducer of liquid reserve tank, thus can be when airborne liquid cooling system operation real-time monitoring system temperature and pressure value.
In liquid reserve tank, can be provided with electric heating, when coolant temperature is too low, heated cooling fluid is to the temperature requiring.The top of liquid reserve tank and bottom are respectively arranged with liquid injection port and leakage fluid dram, are used for supplementing cooling fluid and get rid of cooling fluid.
The two ends that enter, export of ice-storage box are connected with the outlet of aircraft load, the entrance of liquid reserve tank by the first snap joint, the second snap joint respectively.When ice-storage box carries out ice-reserving, first snap joint of outwarding winding, the second snap joint, disconnect itself and liquid circulation loop, and be connected with ground ice storage unit by the first snap joint, the second snap joint; After ice-storage box ice-reserving finishes, outward winding the first snap joint and the second snap joint, disconnect itself and ground ice storage unit.And by the first snap joint, the second snap joint and liquid circulation circuit communication, aircraft load is carried out comparatively fast cooling, according to the size of ice-reserving amount, can meet the cold requirement of aircraft in certain flight time.By regulate flow control valve on the entrance pipe of ice-storage box realize according to the variation of aircraft load request refrigerating capacity regulate the ice-storage box of flowing through cooling fluid flow, can bring into play to greatest extent the ability of ice cold-storage, thereby reach the object of accurate refrigeration.
So this is implemented novel ice-storage box and has realized the quick switching of interface by snap joint, has facilitated the ice-reserving of aircraft when ground, and carry out cooling object after taking off.
The beneficial effects of the utility model are embodied in:
1) due to the two ends of the heat exchanger in liquid circulation loop and connect an ice-storage box, high temperature coolant after aircraft load heat exchange is carried out respectively carrying out in ice-storage box and heat exchanger cooling, by ice-storage box, freeze and made up the deficiency of heat exchanger refrigerating capacity, can in aircraft flight process, consume under the condition of less airborne electrical power, meet the requirement of larger refrigerating capacity.
2) this airborne liquid cooling system is restricted in aircraft ram-air air inflow, and then in the situation of restriction heat exchanger heat exchange amount, has met the requirement of larger refrigerating capacity by the ice-storage box increasing.
3) ice-storage box of this airborne liquid cooling system can complete ice-reserving on ground, in aircraft flight process, provides refrigeration, returns to ground and again carry out ice-reserving after aircraft flight finishes.This mode takes full advantage of the feature of aircraft flight, and can, according to the size of aircraft non-stop flight time match design ice-storage box, realize the optimization of system effectiveness.
4) this system is provided with flow control valve in ice-storage box import department, can regulate according to the variation of load in aircraft flight process the flow of the ice-storage box cooling fluid of flowing through, when load less, when heat exchanger can meet the demands by ram-air heat exchange, can close adjuster valve completely, save the cold of ice-storage box, can bring into play to greatest extent the ability of the cold-storage of ice-storage box.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
In figure: 1-liquid reserve tank, 2-water pump, the load of 3-aircraft, 4-flow control valve, 5-heat exchanger, 6-ice-storage box, 7-1-the first snap joint, 7-2-the second snap joint, 8-expansion drum, 9-automatic exhaust steam valve.
Embodiment
As shown in Figure 1, a kind of airborne liquid cooling system for aircraft load refrigeration, comprise the liquid reserve tank 1, the water pump 2 and heat exchanger 5 that are connected to aircraft load 3 import and export two ends and form liquid circulation loop, the export pipeline of described aircraft load 3 is communicated with the entrance of the ice-storage box 6 being arranged in parallel, heat exchanger 5 respectively; Described outlet is communicated with the entrance of liquid reserve tank 1 by the second snap joint 7-2, and the entrance of ice-storage box 6 is communicated with the export pipeline of aircraft load 3 by the first snap joint 7-1, and the entrance pipe of ice-storage box 6 is provided with flow control valve 4; The top of liquid reserve tank 1 is provided with expansion drum 8 and automatic exhaust steam valve 9 for air-discharging.
The two ends of the heat exchanger in liquid circulation loop also connect an ice-storage box, high temperature coolant after aircraft load heat exchange is carried out respectively carrying out in ice-storage box and heat exchanger cooling, after cooling, converge to together and in liquid reserve tank, carry out cool cycles next time, by ice-storage box, freeze and made up the deficiency of heat exchanger refrigerating capacity, can in aircraft flight process, consume under the condition of less airborne electrical power, meet the requirement of larger refrigerating capacity.And take full advantage of the feature of aircraft flight, ice-storage box can complete ice-reserving on ground, in aircraft flight process, provide refrigeration, can according to the variation of load in aircraft flight process, regulate the flow of the ice-storage box cooling fluid of flowing through, realized the optimization of system effectiveness.
Above embodiment is not limited only to protection range of the present utility model, all based on basic thought of the present utility model, modify or change all belong to protection range of the present utility model.
Claims (3)
1. the airborne liquid cooling system for aircraft load refrigeration, comprise the liquid reserve tank, water pump and the heat exchanger that are connected to aircraft load import and export two ends and form liquid circulation loop, it is characterized in that: the export pipeline of described aircraft load is communicated with the entrance of the ice-storage box being arranged in parallel, heat exchanger respectively; The outlet of described ice-storage box is communicated with the entrance of liquid reserve tank by the second snap joint, and the entrance of ice-storage box is communicated with the export pipeline of described aircraft load by the first snap joint.
2. the airborne liquid cooling system for aircraft load refrigeration according to claim 1, is characterized in that: the entrance pipe of described ice-storage box is provided with flow control valve.
3. the airborne liquid cooling system for aircraft load refrigeration according to claim 1, is characterized in that: the top of described liquid reserve tank is provided with expansion drum and automatic exhaust steam valve for air-discharging.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320532305.8U CN203482564U (en) | 2013-08-29 | 2013-08-29 | Airborne liquid cooling system for airplane load refrigeration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320532305.8U CN203482564U (en) | 2013-08-29 | 2013-08-29 | Airborne liquid cooling system for airplane load refrigeration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203482564U true CN203482564U (en) | 2014-03-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320532305.8U Withdrawn - After Issue CN203482564U (en) | 2013-08-29 | 2013-08-29 | Airborne liquid cooling system for airplane load refrigeration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203482564U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103458660A (en) * | 2013-08-29 | 2013-12-18 | 合肥天鹅制冷科技有限公司 | Airborne liquid cooling system used for airplane load refrigeration |
| CN104144596A (en) * | 2014-07-17 | 2014-11-12 | 合肥天鹅制冷科技有限公司 | Airborne liquid cooling system |
| CN104703444A (en) * | 2015-03-19 | 2015-06-10 | 合肥天鹅制冷科技有限公司 | Pressure-stabilizing, liquid-supplementing and gas-exhausting device of closed liquid cooling system |
| CN108458537A (en) * | 2018-06-04 | 2018-08-28 | 东莞市昭鼎环保科技有限公司 | A kind of radiator under low temperature environment |
-
2013
- 2013-08-29 CN CN201320532305.8U patent/CN203482564U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103458660A (en) * | 2013-08-29 | 2013-12-18 | 合肥天鹅制冷科技有限公司 | Airborne liquid cooling system used for airplane load refrigeration |
| CN103458660B (en) * | 2013-08-29 | 2016-06-08 | 合肥天鹅制冷科技有限公司 | A kind of machine carrier fluid cooling system for airplane load refrigeration |
| CN104144596A (en) * | 2014-07-17 | 2014-11-12 | 合肥天鹅制冷科技有限公司 | Airborne liquid cooling system |
| CN104144596B (en) * | 2014-07-17 | 2017-10-03 | 合肥天鹅制冷科技有限公司 | A kind of airborne liquid cooling system |
| CN104703444A (en) * | 2015-03-19 | 2015-06-10 | 合肥天鹅制冷科技有限公司 | Pressure-stabilizing, liquid-supplementing and gas-exhausting device of closed liquid cooling system |
| CN108458537A (en) * | 2018-06-04 | 2018-08-28 | 东莞市昭鼎环保科技有限公司 | A kind of radiator under low temperature environment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140312 Effective date of abandoning: 20160608 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20140312 Effective date of abandoning: 20160608 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |