CN102179140B - Drying system used in airplane - Google Patents
Drying system used in airplaneDownload PDFInfo
- Publication number
- CN102179140B CN102179140BCN2011100300252ACN201110030025ACN102179140BCN 102179140 BCN102179140 BCN 102179140BCN 2011100300252 ACN2011100300252 ACN 2011100300252ACN 201110030025 ACN201110030025 ACN 201110030025ACN 102179140 BCN102179140 BCN 102179140B
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- Prior art keywords
- air
- dehumidification
- aircraft
- exhaust gas
- drying system
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
- B01D53/26—Drying gases or vapours
- B01D53/265—Drying gases or vapours by refrigeration (condensation)
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D2259/00—Type of treatment
- B01D2259/45—Gas separation or purification devices adapted for specific applications
- B01D2259/4566—Gas separation or purification devices adapted for specific applications for use in transportation means
- B01D2259/4575—Gas separation or purification devices adapted for specific applications for use in transportation means in aeroplanes or space ships
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0662—Environmental Control Systems with humidity control
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Thermal Sciences (AREA)
- Pulmonology (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Analytical Chemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Central Air Conditioning (AREA)
- Drying Of Gases (AREA)
Abstract
Translated fromChinese
Description
Technical field
The present invention relates to a kind of for the drying system in the aircraft.More particularly, the present invention relates to a kind of drying system in the aircraft of being used for that reduces energy consumption.
Background technology
Aircraft in flight course, per hour approximately breathe out steam of 100 grams of every passenger, and these steam run into after the cold mechanism of aircraft rapidly cooling and form condensed water, therefore, are very surprising in long-term in-flight formed condensed water quantity.The result, after condensed water is absorbed by the heat insulation layer in the fuselage and miscellaneous equipment, the weight that makes aircraft is increased more than half ton (condensation water quantity is mainly relevant with passengers quantity, the aircraft method of operation, regional climate), and the weight that increases will cause higher fuel consume, and environment is caused negative influence.Worse, a large amount of condensed waters can cause heat insulation layer damage and then etching machine body structure and damage electrical equipment that reduced the service life of aircraft.In addition, liquid water droplets flows into main cabin or driving cabin, also is that the passenger and crew is undesirable.
Apparently, or the generation of control condensed water, or the condensed water that forms is processed is the method that solves the problems of the technologies described above.In the prior art, some aircrafts are controlled the generation of condensed water by installing drying system additional, but mostly be special drying system, to the heat treatment that dehumidifies of air in the cabin, this will cause the increase of airplane equipment weight, can strengthen the power consumption of aircraft simultaneously, thereby cause the increase of aircraft energy consumption, namely this dehumidification mode is to be based upon on the basis that makes the increase of aircraft energy consumption.
Summary of the invention
In order to reduce aircraft energy consumption, a kind of new drying system that the present invention proposes on the basis that takes full advantage of the aircraft existing equipment as much as possible.Electronic equipment on the aircraft needs cooling-air to cool off to keep its normal operation, and the generation used heat that will heat up behind the air-cooling electronic apparatus, in the prior art, basically, the air that all these is had used heat is directly discharged aircraft.Yet in the present invention, these used heat heat the fresh air that cooling assembly generates by heat exchanger, thereby reduce the relative humidity of fresh air.Because existing cooling assembly equipment itself just has except water function, the humidity of the fresh air of cooling assembly outlet is very low, and behind the heat temperature raising of over-heat-exchanger, humidity will be lower again, drying capacity is enhanced, and has improved simultaneously the utilization rate of the energy on the aircraft.
Particularly, the invention discloses a kind ofly for the drying system in the aircraft, it comprises: cooling assembly, heat exchanger, distribution circuit and Control Component.Wherein, cooling assembly has the air upstream end of for the first time dehumidifying and the Bas Discharged end that dehumidifies for the first time, reduces its absolute humidity thereby described cooling assembly is used for that the fresh air that the air upstream end from the described dehumidifying first time enters is carried out the dehumidifying first time; Heat exchanger, has the waste gas upstream end, the waste gas outlet side, for the second time the air upstream end of dehumidifying and for the second time the Bas Discharged end of dehumidifying, described waste gas upstream end is communicated with electronics bay, described waste gas outlet side is communicated with the outside of aircraft, the air upstream end of described second time of dehumidifying is communicated with the Bas Discharged end of the described dehumidifying first time, thereby described heat exchanger is used for the waste gas of the heat that will enter and be discharged by described waste gas outlet side from described waste gas upstream end and enters and carry out heat exchange by the fresh air of the Bas Discharged end discharge of the described dehumidifying second time and carry out dehumidifying the second time and obtain dry air to reduce its relative humidity from the air upstream end of the described dehumidifying second time; Distribution circuit is used for the dry air that the Bas Discharged end of the described dehumidifying second time is discharged is transported in the fuselage interlayer; Control Component is used for controlling at least according to different operating modes one of them person of the efficient of the flow of described dry air and described heat exchanger.
Preferably, described Control Component is for the exhaust gas flow of the waste gas upstream end of controlling described heat exchanger.
Preferably, described Control Component is used for controlling the flow of described dry air.
More preferably, arbitrary place in position between the air upstream end of the Bas Discharged end of the position of the air upstream end of described first time of dehumidifying, the position on the described distribution circuit, the described first time of dehumidifying and the described second time of dehumidifying and the position of described waste gas upstream end is provided with flow control valve, and described Control Component is realized flow-control to described dry air via described flow control valve.
Particularly, described distribution circuit is arranged in lateral region and/or the top area of aircraft.
Particularly, described aircraft has bilge section, and air bleeding valve is located at described bilge section, and the dry air that is used for being transported in the fuselage interlayer is discharged.
By described drying system, the present invention can reach following useful technique effect: reduce or eliminate the accumulation of the interior condensed water of the adiabatic sound insulating layer of aircraft or ice; Utilize the used heat in the electronic equipment exhaust, improve the aircraft energy utilization rate, strengthen the aircraft economy; Reduce the fuselage corrosion, reduce electric fault and the short circuit phenomenon of aircraft, improve aircraft safety; Strengthen the adiabatic heat-insulation effect of aircraft interlayer, reduce the aircraft air-conditioning system thermal force, reduce the aircraft energy consumption, improve economy and the comfortableness of aircraft.
Description of drawings
Fig. 1 is the schematic diagram of drying system of the present invention;
Fig. 2 is airframe interlayer gap schematic diagram.
The specific embodiment
As shown in Figure 1, it shows the schematic diagram of drying system of the present invention, and wherein, described drying system 10 is comprised of cooling assembly 1, heat exchanger 2, distribution circuit 3 and Control Component 4.Described cooling assembly 1 has the air upstream end 11 of for the first time dehumidifying and the Bas Discharged end 12 of dehumidifying for the first time, thereby it is used for the fresh air that the air upstream end 11 from the described dehumidifying first time enters carried out dehumidifying first time reducing its absolute humidity.Described heat exchanger 2 has the air upstream end 23 of waste gas upstream end 21, waste gas outlet side 22, for the second time dehumidifying and the Bas Discharged end 24 that dehumidifies for the second time.Wherein, described waste gas upstream end 21 is connected with electronics bay 5, described waste gas outlet side 22 communicates with the aircraft external world, the air upstream end 23 of the described dehumidifying second time communicates with the Bas Discharged end 12 of the dehumidifying first time of cooling assembly 1, and the Bas Discharged end 24 of the described dehumidifying second time is communicated with distribution circuit 3.Described distribution circuit 3 has an end 31 of the dry air of Bas Discharged end 24 discharges that receive the described dehumidifying second time, and described dry air is transported to the other end 32 in the fuselage interlayer, the described other end 32 arranges near the fuselage interlayer of aircraft, and described distribution circuit 3 is used for dry gas is assigned to the preposition place and forms air-flow in the airframe interlayer.Described Control Component 4, be used for according to different operating conditions cooling assemblies 1 and heat exchanger 2, more preferably, control at least one of them person of the efficient of the flow of described dry air and described heat exchanger 2, more preferably, can control simultaneously the efficient of flow and the heat exchanger 2 of dry air.More specifically, described Control Component 4 is single-chip microcomputer (SCM) or any controllers that can realize data operation and disposal ability such as CPU (CPU) or programmable logic controller (PLC) (PLC), it can control the flow of dry air to satisfy need of work via flow control valve, the exhaust gas flow that can control also that waste gas upstream end 21 via heat exchanger 2 enters and be discharged by waste gas outlet side 22 is controlling the efficient of described heat exchanger 2, thereby the power that also can control in addition described cooling assembly 1 and described heat exchanger 2 reaches the parameters such as temperature and humidity of regulating the final dry air that flows out.Preferably, position between the air upstream end 23 of the Bas Discharged end 12 of the position of the air upstream end 11 of dehumidifying first time of described cooling assembly 1, the position on the described distribution circuit 3, the described first time of dehumidifying and the described second time of dehumidifying (namely, position between cooling assembly 1 and the heat exchanger 2), in the position of described waste gas upstream end 21 (being the position between heat exchanger 2 and the described electronics bay 5), a flow control valve can be set respectively also can only in some or certain several position flow control valve be set.Described flow control valve also can be manually operated, is preferably automatically controlled by above-mentioned Control Component 4.
As everyone knows, cooling assembly 1 in the aircraft is interior all to have de-watering apparatus, therefore, when entering cooling assembly 1 by the absolute humidity that can be reduced widely fresh air by the de-watering apparatus of described cooling assembly 1 from the fresh air of engine from the air upstream end 11 of for the first time dehumidifying.What like this, the Bas Discharged end 12 of the dehumidifying first time of cooling assembly 1 was discharged is exactly the lower fresh air of humidity.In the present invention, described heat exchanger 2 is used for and will will discharge and enter the relatively cold fresh air of heat exchanger 2 and carry out exchange heat from the waste gas of the relatively hot of heat exchanger 2 that electronics bay 5 is discharged and entered from waste gas upstream end 21 from the air upstream end 23 that dehumidifies for the second time from the Bas Discharged end 12 of the dehumidifying first time of cooling assembly 1.From the cold fresh air of cooling assembly 1 behind over-heat-exchanger 2, because temperature raises after the heat exchange, thereby the relative water capacity of fresh air will decrease, what therefore, discharge from the Bas Discharged end 24 of dehumidifying second time of heat exchanger 2 is exactly all lower dry airs of absolute humidity and relative humidity.Described dry air is transported to those by distribution circuit 3 needs dry aircraft passenger compartment zone such as zones such as top, main cabin, main cabin sidewall spacers.Simultaneously, discharge aircraft through the waste gas after the heat exchange via waste gas outlet side 22.
More preferably, can control by the extraction flow from electronics bay 5 oncontrol heat exchanger 2 hot limits the efficient ofheat exchanger 2, obtain the temperature dry air different with relative humidity.Simultaneously also can be according to temperature, damp condition in external condition and the cabin different, the flow of control dry air.
More preferably, in order to alleviate the weight of aircraft, distribution circuit 3 can be comprised of the pipeline of lighter weight, and is arranged in from front to back the top area of aircraft, and the central authorities of the as far as possible close aircraft in its position are with the uniformity of guaranteeing that control air distributes.
Below, describe how forming shielding gas flow in conjunction with Fig. 2.
Fuselage outer side structure and inside sidewalls structure have formed fuselage sandwich, as shown in Figure 2, it shows a kind of fuselage sandwich that is made ofairframe structure 6,trim panel 7, adiabatic sound insulating layer 8 substantially, wherein, is formed withgap 9 betweentrim panel 7 and the adiabatic sound insulating layer 8.
In the prior art, the passenger and crew is in the main cabin behind the exhalation humid air, this humid air can enter by the slit top area and the sidewall areas in main cabin, and from the top orlateral region 9 flow to the gap, the adiabatic sound insulating layer 8 that humid air and temperature are lower contacts withairframe structure 6 and forms condensed water.
In the present invention, after all comparatively suitable dry air is delivered to top, main cabin or lateral region equably with temperature and humidity by distribution circuit 3, because air bleeding valve is located at the bilge section of aircraft usually, like this, the pressure of aircraft cabin bottom can be a little less than the top area in main cabin, therefore, the gap 9 of dry air between trim panel 7 and adiabatic sound insulating layer 8 flows into the trigonum, participate in the recirculation except a part of dry air enters recirculation regions, all the other dry airs are finally discharged out of my cabin by the air bleeding valve of bilge section.The dry air that temperature is higher, humidity is lower in the gap of fuselage interlayer, formed one deck play " heat-insulation layer " effect shielding gas flow fuselage outer side structure and the higher inside sidewalls structure of temperature that temperature is lower keep apart; thereby; avoided humid air directly directly to contact with fuselage outer side structure (such as covering, long purlin etc.); therefore, effectively prevent the drop in temperature of humid air and produce condensed water.As previously mentioned, the top, main cabin that distribution circuit 3 is arranged in aircraft only is more excellent scheme, and in fact, distribution circuit 3 also can be arranged in the both sides, main cabin of aircraft, and more preferably, distribution circuit 3 can also be arranged in both sides, main cabin and the main cabin top area of aircraft simultaneously.
Principle of the present invention is as follows: utilize the higher characteristics heating of electronics bay delivery temperature from the fresh air of cooling assembly, reduction is from the relative humidity of the fresh air of cooling assembly, make this part fresh air drier and obtain dry air, again this part dry air is passed in the gap of the lower fuselage interlayer of temperature, prevent the generation of condensed water.At this, need to prove, in the prior art, itself just has the cooling assembly of aircraft except water function, and the present invention has utilized this function of cooling assembly just, does not need special dehydrating unit.Simultaneously, utilized used heat in the electronics bay exhaust to heat fresh air from cooling assembly.Like this, not only obtain dry air, also improved capacity usage ratio.The dry air that temperature is higher enters in the aircraft interlayer, can improve the heat-insulating property of aircraft interlayer, reduces the thermal force of aircraft air-conditioning system.
The present invention can be achieved as follows technique effect: keep the aircraft cabin inner drying, alleviate aircraft weight, prolong heat-insulating material life-span, reduce airplane fault and reduce aircraft maintenance work.Simultaneously, also effectively utilized the high-temp waste gas that cooling electronic apparatus produces.
Technology contents of the present invention and technical characterstic disclose as above, yet are appreciated that under creative ideas of the present invention, and those skilled in the art can make various changes and improve said structure, but all belongs to protection scope of the present invention.The description of above-mentioned embodiment is exemplary rather than restrictive, and protection scope of the present invention is determined by claim.
Claims (6)
Translated fromChinesePriority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100300252ACN102179140B (en) | 2011-01-27 | 2011-01-27 | Drying system used in airplane |
| PCT/CN2011/079648WO2012100542A1 (en) | 2011-01-27 | 2011-09-14 | Dehumidification system for use in airplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100300252ACN102179140B (en) | 2011-01-27 | 2011-01-27 | Drying system used in airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102179140A CN102179140A (en) | 2011-09-14 |
| CN102179140Btrue CN102179140B (en) | 2013-05-01 |
Family
ID=44565542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100300252AActiveCN102179140B (en) | 2011-01-27 | 2011-01-27 | Drying system used in airplane |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN102179140B (en) |
| WO (1) | WO2012100542A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103204242B (en)* | 2013-03-25 | 2015-07-22 | 大连理工大学 | Double air channel wall for airplane |
| EP2799343B1 (en) | 2013-04-03 | 2017-02-15 | Airbus Operations GmbH | Aircraft air-conditioining system |
| US9988151B2 (en) | 2014-01-24 | 2018-06-05 | The Boeing Company | Dehumidification system for use in a vehicle and method of assembling thereof |
| CN104071327B (en)* | 2014-06-05 | 2016-03-30 | 江苏科技大学 | Stratospheric Airship Parallel Temperature Control System and Control Method |
| CN104260891B (en)* | 2014-09-23 | 2016-08-24 | 中国商用飞机有限责任公司 | Method and system for ventilating and heating aircraft cargo compartment |
| CN105984305A (en)* | 2015-01-30 | 2016-10-05 | 观致汽车有限公司 | Drying and ventilating device and system for high-pressure system of vehicle |
| US11459110B2 (en)* | 2016-04-22 | 2022-10-04 | Hamilton Sunstrand Corporation | Environmental control system utilizing two pass secondary heat exchanger and cabin pressure assist |
| CN110960964A (en)* | 2019-12-21 | 2020-04-07 | 铜陵万华禾香板业有限公司 | Method and device for dehumidifying compressed air of glue applying system |
| CN113955123A (en)* | 2021-12-09 | 2022-01-21 | 中国商用飞机有限责任公司 | Aircraft dehumidification system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1060270A (en)* | 1990-08-17 | 1992-04-15 | 联合技术股份有限公司 | The environmental control system condensing circulation |
| CA2753109A1 (en)* | 2009-02-23 | 2010-08-26 | Airbus Operations Gmbh | Air conditioner having an air dehumidifying device and method for operating such an air conditioner |
| DE102009018401A1 (en)* | 2009-04-22 | 2010-10-28 | Airbus Deutschland Gmbh | System and method for cooling a room in a vehicle |
| CN101881490A (en)* | 2009-05-05 | 2010-11-10 | 北京航空航天大学 | High pressure dehumidification aircraft new environmental control system using membrane modules |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE465772B (en)* | 1990-03-06 | 1991-10-28 | Ctt Systems Hb | PROCEDURE AND DEVICE TO PREVENT THE CONDUCT OF SCALE CONSTRUCTIONS |
| DE102004038860A1 (en)* | 2004-08-10 | 2006-02-23 | Airbus Deutschland Gmbh | Process air production system for aircraft has existing cooling system whose heat exchanger is arranged in ram-air cooling channel serving as cooling sink |
- 2011
- 2011-01-27CNCN2011100300252Apatent/CN102179140B/enactiveActive
- 2011-09-14WOPCT/CN2011/079648patent/WO2012100542A1/enactiveApplication Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1060270A (en)* | 1990-08-17 | 1992-04-15 | 联合技术股份有限公司 | The environmental control system condensing circulation |
| CA2753109A1 (en)* | 2009-02-23 | 2010-08-26 | Airbus Operations Gmbh | Air conditioner having an air dehumidifying device and method for operating such an air conditioner |
| DE102009018401A1 (en)* | 2009-04-22 | 2010-10-28 | Airbus Deutschland Gmbh | System and method for cooling a room in a vehicle |
| CN101881490A (en)* | 2009-05-05 | 2010-11-10 | 北京航空航天大学 | High pressure dehumidification aircraft new environmental control system using membrane modules |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2012100542A1 (en) | 2012-08-02 |
| CN102179140A (en) | 2011-09-14 |
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