CN101148197A - Cabin circumstance control system used for passenger plane - Google Patents
Cabin circumstance control system used for passenger plane Download PDFInfo
- Publication number
- CN101148197A CN101148197A CNA2007101763880A CN200710176388A CN101148197A CN 101148197 A CN101148197 A CN 101148197A CN A2007101763880 A CNA2007101763880 A CN A2007101763880A CN 200710176388 A CN200710176388 A CN 200710176388A CN 101148197 A CN101148197 A CN 101148197A
- Authority
- CN
- China
- Prior art keywords
- pipeline
- heat exchanger
- air
- control system
- gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
Landscapes
- Air-Conditioning For Vehicles (AREA)
Abstract
The cabin environment controlling system for air bus includes the following assemblies: a frequency conversion motor, a supercharger, a reclaiming heat exchanger, an air bleeding unit A, a water spraying pre-cooler, a secondary heat exchanger, an evaporating cycle refrigerating unit, a mixing chamber, a purifying filter, a cabin and an air bleeding unit B. All the assemblies are connected through pipeline for air circulation. The system has motor driven supercharger to compress air for increasing pressure in the cabin, evaporating cycle refrigerating unit to cool air to the cabin, and independent air bleeding fan to ensure high work efficiency and low noise. The present invention provides comfortable cabin environment for air bus in different flying states.
Description
Technical field
The present invention relates to a kind of environmental control system, the particularly a kind of dehumidifying of passenger cabin environment, refrigeration ventilated control system that is applied to passenger plane.
Background technology
There has been various ways so far in traditional trunkliner environmental control system development, but the core coolant part all adopts the air cooling mode of turbine expansion, be that high pressure air does work through turbine expansion, the interior of self can change kinetic energy into, makes drop in temperature to the requirement of satisfying air regulation.Wherein the pressurization air source of Boeing 787 obtains for the ram air that machine is outer carries out supercharging through motor-driven blwr, and all the other are draws from the medium pressure grade of driving engine air compressor or the pressurization air source of high-pressure stage.Owing in compression process, be subjected to the pollution of fuel oil easily from the pressurization air source of engine compressor, so can influence the cabin air quality; Though and the pressurization air source that similar Boeing 787 uses does not influence the cabin air quality, but at first can consumed power ram air be increased to higher pressure and temperature during this type of pressurization air source work, then, therefore very big to the waste of energy again by air heat exchanger cooling, turbine expansion step-down cooling.And in the environmental control system that uses the turbine expansion refrigeration, this can produce bigger noise cold air machine when operation, and the load that increases in order to consume the turbine acting simultaneously also can produce bigger noise.
Summary of the invention
The objective of the invention is that existing passenger plane cockpit environment control system noise is big, expenditure of energy is big and the ropy problem of ventilating gas in order to solve, a kind of cockpit environment control system that is applied to passenger plane is provided, this cockpit environment control system can satisfy passenger plane cabin ventilation refrigeration and supercharging requirement, and can reduce compensatory loss of fuel oil and system noise.
The present invention realizes by following technological means: a kind of cockpit environment control system of passenger plane, has the passenger cabin environment control unit, for the pressurization air source that the supercharging of satisfying passenger cabin requires to use is no longer taken from engine bleed, carry out the supercharging acquisition through the blwr of variable-frequency motor driving and replace the environment ram air; Use the evaporation circulating cooling device to replace traditional turbine expansion refrigeration; Fuel oil is made the part low-temperature receiver on the use machine, improves integrated thermal management efficient; Bleed fan independent operating in the bleed device, not coaxial with the variable-frequency motor of blwr, can the free adjustment rotating speed, the bleed fan is remained under the peak performance operating mode work.
The cockpit environment control system that is applied to passenger plane provided by the invention, have the passenger cabin environment control unit, specifically comprise following assembly: variable-frequency motor, blwr, recovery heat exchanger, bleed device A, water spray fore cooler, secondary heat exchanger, evaporation circulating cooling device, blending box, filtration equipment for clarifying, passenger cabin and bleed device B.
Variable-frequency motor is used to drive blwr work, and ram air enters blwr through pipeline, and the pressurization gas that obtains enters the recovery heat exchanger through pipeline, reclaims heat exchanger and utilizes the passenger cabin exhaust that the blwr air-out is carried out first step cooling; The cooled gas of the first step enters secondary heat exchanger through pipeline and carries out the cooling of second step, cooled gas of second step enters the evaporation circulating cooling device through pipeline and carries out cooling of the 3rd step and dehumidification treatments, enters blending box by pipeline at last so that supply with passenger cabin compression cooling gas; When the thermal load of passenger cabin hour, the gas through reclaiming the cooling of the heat exchanger first step directly enters blending box through pipeline; When not needing the evaporation circulating cooling device to carry out cooling of the 3rd step and dehumidification treatments, the gas that cools off through second step of secondary heat exchanger can directly enter blending box by pipeline, thereby realizes the adjusting to cabin air.
Cooling media in the secondary heat exchanger is a ram air through the cooled gas of water spray fore cooler, and this gas can taking out to draw and enter in the atmosphere by bleed device A.
Cooling media in the water spray fore cooler is a shower water, and described shower water is from the evaporation circulating cooling device.
Described evaporation circulating cooling device comprises compressor, condenser, catcher, evaporator and expansion valve, is connected to form the loop of a closure between compressor-condenser-expansion valve-evaporator-compressor in turn by pipeline; Catcher links to each other with the afterbody of evaporator by pipeline; Described compressor is a frequency-changing cyclone formula refrigerating compressor, can require to regulate evaporating temperature according to passenger cabin, and the refrigerant that uses in the described evaporation circulating cooling device is R134a, also can be the refrigerant that can play refrigeration of other kinds.The low-temperature receiver of condenser is the reserve fuel on the aircraft.
All be by plumbing connection between above-described each assembly, to realize the circulation of gas.
The invention has the advantages that: the design conditions of this system are not subjected to the influence of engine operating condition, can not bring direct influence to the heat power circulation of driving engine; The design of driving engine also can be simpler simultaneously, and performance is higher.For the secondary pollution that can not be subjected to fuel oil on the machine toward the air of passenger cabin, avoid the cabin air quality is damaged.Ram air only is used for satisfying the pressure demand that increases passenger cabin through the boost in pressure of blwr and along the droop loss of journey, compare with the environmental control system that adopts the turbine expansion refrigeration, the pressure of pressurization air source is lower, corresponding temperature is also lower, reduce the heat exchange load of the preceding heat exchanger of refrigerating apparatus, thereby reduced the size of heat exchanger and the consumption of punching press cold air.Independently the bleed device can reduce the noise of fan outlet and the weight of total system.
Description of drawings
Fig. 1 is the principle of work constructional drawing of environmental control system of the present invention;
Fig. 2 is the principle of work constructional drawing of evaporation circulating cooling device among the present invention.
1 variable-frequency motor, 2 blwrs 3 reclaim heat exchanger 301 gas A
302 gas B, 4 bleed device A, 5 water spray fore coolers, 6 secondary heat exchangers
601 gas C, 602 gas D, 501 gas E, 7 evaporation circulating cooling devices
701 evaporators, 702 condensers, 703 compressors, 704 expansion valves
705 catchers, 8 blending boxs, 9 filtration equipment for clarifying, 10 ram airs
11 shower waters, 12 passenger cabins, 13 bleed device B
The specific embodiment
Below in conjunction with accompanying drawing cockpit environment control system of the present invention is described in detail.
As shown in Figure 1, the assembly that environmental control system of the present invention comprises has: variable-frequency motor 1, blwr 2, variable-frequency motor 1 are used for driving blwr 2 work; Reclaim heat exchanger 3, utilize passenger cabin 12 exhausts that blwr 2 air-outs are carried out first step cooling; Bleed device A4 takes out the gas E501 that draws in the secondary heat exchanger 6 and enters in the air environment; Water spray fore cooler 5 is to ram air 10 cooling of lowering the temperature; Secondary heat exchanger 6 carries out the cooling of second step to the gas A301 that reclaims heat exchanger 3 discharges; Evaporation circulating cooling device 7, the gas D602 that secondary heat exchanger 6 is discharged carries out cooling of the 3rd step and dehumidification treatments; Idle call gas blending box 8 is used to mix the compression cooling gas from system; Filtration equipment for clarifying 9 is used for that 12 exhausts purify and filter to passenger cabin; Bleed device B13 extracts and delivers to filtration equipment for clarifying 9 and reclaim heat exchanger 3 by pipeline respectively passenger cabin 12 air.
Ram air 10 is through the ram air inlet duct, and a part enters water spray fore cooler 5, enters secondary heat exchanger 6 after shower water 11 coolings; Another part directly enters blwr 2 by pipeline and compresses, high pressure gas after the compression enter by pipeline and reclaim heat exchanger 3, reclaiming heat exchanger 3 utilizes the exhaust of passenger cabin 12 that high pressure gas are carried out first step cooling, the cooled gas A301 of the first step enters secondary heat exchanger 6 by pipeline and advances the cooling of second step, cooled gas D602 of second step enters evaporation circulating cooling device 7 by pipeline and carries out cooling of the 3rd step and dehumidification treatments, enters blending box 8 so that supply with the compression cooling gas of passenger cabin 12 dryings through pipeline more at last; When the thermal load of passenger cabin 12 hour, the gas B302 through reclaiming the cooling of heat exchanger 3 first steps directly enters blending box 8 through pipeline; When not needing evaporation circulating cooling device 7 to cool off with dehumidification treatments, the gas that cools off through 6 second steps of secondary heat exchanger can directly enter blending box 8 by pipeline, thereby realizes the adjusting to passenger cabin 12 air.
Environmental control system of the present invention has three functions, promptly compresses, dehumidifies and ventilate refrigeration.Pressure gas is realized in blwr 2; Dehumidification process is finished in evaporation circulating cooling device 7; The ventilation process of refrigerastion is applied in the whole cockpit environment control system.
The cooling media that carries out the cooling of second step in the secondary heat exchanger 6 comes from the refrigerating gas E501 of the fore cooler 5 of spraying water, ram air 10 enters water spray fore cooler 5 backs by pipeline and is formed refrigerating gas E501 by shower water 11 coolings, gas E501 passes through secondary heat exchanger 6 through pipeline, and is entered in the air environment by bleed device A4 suction.Bleed device A4 is made up of a bleed fan and an electrical motor, electrical motor is used for separately driving the bleed fan work, so the bleed fan is not coaxial with the variable-frequency motor 1 that increases device 2, thereby can work alone, the free adjustment rotating speed, and can reduce noise; Enter evaporation circulating cooling device 7 from the gas D602 in the secondary heat exchanger 6 through pipeline and carry out the cooling of the 3rd step, after cooling of the 3rd step and dehumidifying, enter blending box 8 again through the cooling of second step.
According to air ambient and passenger traffic condition, when entering the blwr 2 that is driven by variable-frequency motor 1, ram air 10 compresses, and blwr 2 increases the pressure of ram air 10, with the pressure that satisfies passenger cabin 12 needs and overcome along the energy of journey droop loss.The pressurized air of coming out from blwr 2 enters the recovery heat exchanger 3 through pipeline, and a part of passenger cabin 12 exhausts cooling by colder realizes first step cooling.Use colder passenger cabin 12 exhausts to cool off the cooling load that can unload secondary heat exchanger 6, reduce the requirement of ram air 10, reduce the aircraft flight resistance, alleviate the total weight that reclaims heat exchanger 3.The pressure gas A301 of the part cooling of coming out from reclaim heat exchanger 3 enters through pipeline and removes the part heat in the secondary heat exchanger 6 again, realizes the cooling of second step.The cooling media of secondary heat exchanger 6 be from ram air mouth pipeline enter and the water spray fore cooler 5 in by the refrigerating gas E501 of shower water 11 precoolings, gas E501 flows through and does not mix with pressure gas A301 in the process of secondary heat exchanger 6, but directly aspirated the back exhaust to atmosphere by bleed device A4 by pipeline, realize the cooling second time to pressure gas A301.Because bleed device A4 is not coaxial with blwr 2, but by self motor independent drive, this makes the rotating speed of bleed device A4 to regulate separately, keeps state work efficiently all the time, provides energy to make it to discharge to the refrigerating gas E501 by secondary heat exchanger 6 and enters air environment.When the thermal load of passenger cabin 12 hour, another part pressure gas B302 that comes out from reclaim heat exchanger 3 directly entered blending box 8 by a pipeline before entering secondary heat exchanger 6, offer cabin air cycle subsystem and air distribution system and be used for adjustment.
As shown in Figure 2, evaporation circulating cooling device 7 comprises evaporator 701, condenser 702, compressor 703, expansion valve 704, catcher 705, is connected to form the loop of a closure between the compressor 703-condenser 702-expansion valve 704-evaporator 701-compressor 703 in turn by pipeline; Catcher 705 links to each other by the afterbody of pipeline with evaporator 701.In described C/LOOP, the steam of refrigerant at first is compressed in compressor 703, enter in the condenser 702 by pipeline then and cool off, until becoming supercooled liquid, supercooled liquid enters expansion valve 704 by pipeline reduces steam pressure, steam after pressure reduces enters evaporator 701 again by pipeline and is evaporated under evaporating temperature, compresses the circularly cooling process of finishing thereby the gas after the evaporation returns compressor 703.Wherein condenser 702 be one can the use machine on fuel oil make the H Exch of cooling media, evaporator 701 coolings be gas D602 from secondary heat exchanger 6.
Compare with traditional water separator assemblies, it is simple a lot of that the dehumidification process of evaporation circulating cooling device 7 is wanted: the evaporating temperature of regulating evaporator 701, make the surface temperature of evaporator 701 be lower than the dew temperature of gas D602, when gas D602 flows through evaporator 701, be cooled to below its dew temperature and separate out moisture, on the heat-transfer surface of the globule that freeze-outs attached to evaporator 701, described heat-transfer surface is the surface with the contacted evaporator 701 of gas D602.Adorn a water collector 705 at the afterbody of evaporator 701, by pipeline the globule is collected and be sent to water spray fore cooler 5 and form shower waters 11 or directly be discharged to outside the machine.In order under different flight in hot day operating mode, all to reach the purpose of dehumidifying with low altitude high speed, can regulate the rotating speed of compressor 703 in the evaporation circulating cooling device 7, the pressure of control evaporator 701 that like this can be indirect, make the temperature build-up or the reduction of refrigerant, thereby the dew temperature that makes gas D602 changes and separates out the different water yields, satisfies the dehumidifying requirement.
Again as shown in Figure 1, the exhaust in the passenger cabin 12 through bleed device B13 take out draw after a part flow through and reclaim heat exchanger 3 as cold gas, the high pressure gas that come from the blwr 2 are carried out in the exhaust to atmosphere environment of first step cooling back; Another part enters filtration equipment for clarifying 9, gets back to passenger cabin 12 again after pipeline enters blending box 8, forms a cabin air circulating system.Bleed device B13 is made up of a bleed fan and an electrical motor, and electrical motor individual drive bleed fan work, and independent regulation guarantees bleed fan work efficient.
Blending box 8 is idle call gas blending boxs, the gas that mixes in blending box 8 comprises the dry cold air that comes out, pressure gas B302, gas C601, the exhaust from passenger cabin 12 after filtration equipment for clarifying 9 is handled from evaporation circulating cooling device 7, after above-mentioned gas mixes, form passenger plane idle call gas, offer the comfortable air ambient of passenger plane passenger cabin 12.
In the working process of whole cockpit environment control system, do not provide coolant air if do not need evaporation circulating cooling device 7 to carry out the 3rd step cooling, directly enter into blending box 8 from the gas C601 of secondary heat exchanger 6 by pipeline.In order to provide passenger cabin 12 required feed air temperature, in passenger cabin 12 thermal loads hour, can before entering secondary heat exchanger 6, directly enter blending box 8 by making pressure gas B302, also realize further adjusting air without evaporation circulating cooling device 7 by pipeline.In blending box 8, evenly mix the laggard passenger cabin 12 of going into through the air of overregulate.
In the above-mentioned cockpit environment control system that is applied to passenger plane, owing to used variable-frequency motor 1 directly blwr 2 to be driven, therefore ram air 10 only is used for satisfying the air pressure demand that increases passenger cabin 12 through the boost in pressure of blwrs 2 and along the droop loss of journey, compare with the environmental control system that adopts the turbine expansion refrigeration, the pressure of pressurization air source is lower, corresponding temperature is also lower, reduce the heat exchange load of the preceding heat exchanger of refrigerating apparatus, thereby reduced the size of heat exchanger and the consumption of punching press cold air.
Independently the electrical motor among bleed device A4 and the bleed device B13 only is used for driving bleed fan work separately, not coaxial with the variable-frequency motor 1 of blwr 2, therefore can the free adjustment rotating speed, bleed device A4 and bleed device B13 are remained under the peak performance operating mode to work, thereby reduce the noise of bleed device A4 and bleed device B13 outlet and the weight of total system, at the integrated thermal management system also can the operation of increase system manoevreability.Fuel oil is made the part low-temperature receiver on the use machine, improves integrated thermal management efficient.
Claims (10)
1. cockpit environment control system that is applied to passenger plane, have the passenger cabin environment control unit, it is characterized in that specifically comprising following assembly: variable-frequency motor, blwr, recovery heat exchanger, bleed device A, water spray fore cooler, secondary heat exchanger, evaporation circulating cooling device, blending box, filtration equipment for clarifying, passenger cabin and bleed device B; Variable-frequency motor is used to drive blwr work, and ram air enters blwr through pipeline, and the pressurization gas that obtains enters the recovery heat exchanger through pipeline, reclaims heat exchanger and utilizes the passenger cabin exhaust that the blwr air-out is carried out first step cooling; The cooled gas of the first step enters secondary heat exchanger through pipeline and carries out the cooling of second step, cooled gas of second step enters the evaporation circulating cooling device through pipeline and carries out cooling of the 3rd step and dehumidification treatments, enters the compression cooling gas that resupplies the passenger cabin drying after blending box mixes at last;
Connection between each above-mentioned assembly is all undertaken by pipeline, to realize the circulation of gas.
2. the cockpit environment control system that is applied to passenger plane according to claim 1, it is characterized in that: the gas through first step cooling that comes out from the recovery heat exchanger can directly enter blending box through pipeline, the gas through the cooling of second step that comes out from secondary heat exchanger also can directly enter blending box by pipeline, enters passenger cabin again after mixing.
3. the cockpit environment control system that is applied to passenger plane according to claim 1 is characterized in that: the cooling media in the secondary heat exchanger is a ram air through the cooled gas of water spray fore cooler, and this gas is taken out to draw and entered in the atmosphere by bleed device A's.
4. the cockpit environment control system that is applied to passenger plane according to claim 1 is characterized in that: described bleed device A and bleed device B are made up of bleed fan and electrical motor respectively, and the bleed fan is driven individually by two motors respectively.
5. the cockpit environment control system that is applied to passenger plane according to claim 1 is characterized in that: described ram air directly comes from the air environment air, enters blwr and water spray fore cooler by pipeline.
6. the cockpit environment control system that is applied to passenger plane according to claim 6 is characterized in that: form a cabin air circulating system between described passenger cabin-bleed device B-filtration equipment for clarifying-blending box-passenger cabin.
7. the cockpit environment control system that is applied to passenger plane according to claim 1, it is characterized in that: described evaporation circulating cooling device is made up of compressor, condenser, catcher, evaporator and expansion valve, and is connected to form the loop of a closure between compressor-condenser-expansion valve-evaporator-compressor in turn by pipeline.
8. the cockpit environment control system that is applied to passenger plane according to claim 7 is characterized in that: be provided with a catcher and link to each other with evaporator by pipeline at the afterbody of evaporator.
9. the cockpit environment control system that is applied to passenger plane according to claim 7 is characterized in that: described compressor is a frequency-changing cyclone formula refrigerating compressor.
10. the cockpit environment control system that is applied to passenger plane according to claim 7 is characterized in that: described condenser is a H Exch that utilizes fuel oil on the machine to make cooling media.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101763880A CN101148197A (en) | 2007-10-26 | 2007-10-26 | Cabin circumstance control system used for passenger plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101763880A CN101148197A (en) | 2007-10-26 | 2007-10-26 | Cabin circumstance control system used for passenger plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101148197A true CN101148197A (en) | 2008-03-26 |
Family
ID=39248923
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007101763880A Pending CN101148197A (en) | 2007-10-26 | 2007-10-26 | Cabin circumstance control system used for passenger plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101148197A (en) |
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102892674A (en) * | 2010-04-09 | 2013-01-23 | 空中客车作业有限公司 | Mixer assembly for an aircraft air conditioning system |
| CN103010466A (en) * | 2012-11-27 | 2013-04-03 | 北京航空航天大学 | Double-stage compressed air circulation refrigeration system |
| CN103373469A (en) * | 2012-04-11 | 2013-10-30 | 空中客车作业有限公司 | Aircraft thermal control system and method of operating an aircraft thermal control system |
| CN103832593A (en) * | 2012-11-23 | 2014-06-04 | 空中客车作业有限公司 | Aircraft air conditioning system and method of operating an aircraft air conditioning system |
| CN105539860A (en) * | 2014-10-31 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Heat management device suitable for large heat flux during long endurance |
| CN105966624A (en) * | 2016-05-23 | 2016-09-28 | 北京航空航天大学 | Cabin air return system driven through pressurizing and working of airplane cabin exhausted air |
| CN106882390A (en) * | 2015-12-15 | 2017-06-23 | 中航商用航空发动机有限责任公司 | Airplane air entraining precooling heat regenerative system |
| CN106892121A (en) * | 2015-12-21 | 2017-06-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft environmental control system control method |
| CN107444655A (en) * | 2016-05-26 | 2017-12-08 | 哈米尔顿森德斯特兰德公司 | Air and ram-air are released using the air cycle machine mixing with two turbines |
| CN108100263A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter integrates environmental control system |
| CN109367791A (en) * | 2018-10-18 | 2019-02-22 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electric environment control system for multi-electric airplane |
| CN110481791A (en) * | 2019-09-18 | 2019-11-22 | 南京航空航天大学 | A kind of aircraft cabin air regulating system |
| CN110645728A (en) * | 2019-09-10 | 2020-01-03 | 北京星际荣耀空间科技有限公司 | Refrigeration cycle system for aircraft and aircraft |
| CN111017235A (en) * | 2019-12-25 | 2020-04-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Energy-optimized aircraft electromechanical system thermal management method |
| CN111014702A (en) * | 2019-12-26 | 2020-04-17 | 中天上材增材制造有限公司 | Energy-saving system for gas atomization powder making equipment |
| CN111268140A (en) * | 2020-02-10 | 2020-06-12 | 南京航空航天大学 | Green environmental control system of aircraft |
| CN112492846A (en) * | 2020-11-27 | 2021-03-12 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin ventilation system |
| WO2021073186A1 (en) * | 2019-10-16 | 2021-04-22 | 南京航空航天大学 | Helicopter multi-cabin two-mode air conditioning system employing compressor intermediate air supplementation technology |
| CN113734447A (en) * | 2016-04-22 | 2021-12-03 | 哈米尔顿森德斯特兰德公司 | Environmental control system with dual channel secondary heat exchanger and cabin pressure assist |
| CN114030619A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Modular helicopter air conditioning system |
| CN114144354A (en) * | 2019-06-21 | 2022-03-04 | 利勃海尔-航空航天图卢兹有限公司 | Aircraft cabin electrical air conditioning system comprising a motorized compressor and an air circulation turbine |
| US11506121B2 (en) | 2016-05-26 | 2022-11-22 | Hamilton Sundstrand Corporation | Multiple nozzle configurations for a turbine of an environmental control system |
| US11511867B2 (en) | 2016-05-26 | 2022-11-29 | Hamilton Sundstrand Corporation | Mixing ram and bleed air in a dual entry turbine system |
| US11981440B2 (en) | 2020-11-04 | 2024-05-14 | Hamilton Sundstrand Corporation | Energy flow of an advanced environmental control system |
-
2007
- 2007-10-26 CN CNA2007101763880A patent/CN101148197A/en active Pending
Cited By (37)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102892674A (en) * | 2010-04-09 | 2013-01-23 | 空中客车作业有限公司 | Mixer assembly for an aircraft air conditioning system |
| CN102892674B (en) * | 2010-04-09 | 2015-04-08 | 空中客车作业有限公司 | Mixer assembly for an aircraft air conditioning system and method for operating the mixer assembly |
| CN103373469B (en) * | 2012-04-11 | 2016-05-18 | 空中客车作业有限公司 | Method and the aircraft of aircraft thermal control system, operation thermal control system |
| CN103373469A (en) * | 2012-04-11 | 2013-10-30 | 空中客车作业有限公司 | Aircraft thermal control system and method of operating an aircraft thermal control system |
| US9611043B2 (en) | 2012-04-11 | 2017-04-04 | Airbus Operations Gmbh | Aircraft thermal control system and method of operating an aircraft thermal control system |
| CN103832593A (en) * | 2012-11-23 | 2014-06-04 | 空中客车作业有限公司 | Aircraft air conditioning system and method of operating an aircraft air conditioning system |
| CN103010466A (en) * | 2012-11-27 | 2013-04-03 | 北京航空航天大学 | Double-stage compressed air circulation refrigeration system |
| CN105539860A (en) * | 2014-10-31 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Heat management device suitable for large heat flux during long endurance |
| CN106882390A (en) * | 2015-12-15 | 2017-06-23 | 中航商用航空发动机有限责任公司 | Airplane air entraining precooling heat regenerative system |
| CN106882390B (en) * | 2015-12-15 | 2020-06-19 | 中国航发商用航空发动机有限责任公司 | Aircraft air-entraining precooling regenerative system |
| CN106892121B (en) * | 2015-12-21 | 2019-10-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft environmental control system control method |
| CN106892121A (en) * | 2015-12-21 | 2017-06-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft environmental control system control method |
| CN113734447A (en) * | 2016-04-22 | 2021-12-03 | 哈米尔顿森德斯特兰德公司 | Environmental control system with dual channel secondary heat exchanger and cabin pressure assist |
| CN113734447B (en) * | 2016-04-22 | 2024-01-02 | 哈米尔顿森德斯特兰德公司 | Environmental control system using dual channel secondary heat exchanger and cabin pressure assist |
| CN105966624A (en) * | 2016-05-23 | 2016-09-28 | 北京航空航天大学 | Cabin air return system driven through pressurizing and working of airplane cabin exhausted air |
| CN105966624B (en) * | 2016-05-23 | 2018-06-22 | 北京航空航天大学 | A kind of cockpit air return system of aircraft cockpit air-discharging and supercharging acting driving |
| CN107444655A (en) * | 2016-05-26 | 2017-12-08 | 哈米尔顿森德斯特兰德公司 | Air and ram-air are released using the air cycle machine mixing with two turbines |
| US11511867B2 (en) | 2016-05-26 | 2022-11-29 | Hamilton Sundstrand Corporation | Mixing ram and bleed air in a dual entry turbine system |
| US11506121B2 (en) | 2016-05-26 | 2022-11-22 | Hamilton Sundstrand Corporation | Multiple nozzle configurations for a turbine of an environmental control system |
| CN107444655B (en) * | 2016-05-26 | 2022-06-10 | 哈米尔顿森德斯特兰德公司 | Mixing bleed air and ram air using an air cycle machine having two turbines |
| CN108100263A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter integrates environmental control system |
| CN109367791A (en) * | 2018-10-18 | 2019-02-22 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electric environment control system for multi-electric airplane |
| CN109367791B (en) * | 2018-10-18 | 2022-05-13 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electric environment control system for multi-electric airplane |
| CN114144354A (en) * | 2019-06-21 | 2022-03-04 | 利勃海尔-航空航天图卢兹有限公司 | Aircraft cabin electrical air conditioning system comprising a motorized compressor and an air circulation turbine |
| CN110645728A (en) * | 2019-09-10 | 2020-01-03 | 北京星际荣耀空间科技有限公司 | Refrigeration cycle system for aircraft and aircraft |
| CN110481791A (en) * | 2019-09-18 | 2019-11-22 | 南京航空航天大学 | A kind of aircraft cabin air regulating system |
| CN110481791B (en) * | 2019-09-18 | 2020-12-15 | 南京航空航天大学 | Air conditioning system for aircraft cabin |
| WO2021073186A1 (en) * | 2019-10-16 | 2021-04-22 | 南京航空航天大学 | Helicopter multi-cabin two-mode air conditioning system employing compressor intermediate air supplementation technology |
| CN111017235A (en) * | 2019-12-25 | 2020-04-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Energy-optimized aircraft electromechanical system thermal management method |
| CN111017235B (en) * | 2019-12-25 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Energy-optimized aircraft electromechanical system thermal management method |
| CN111014702A (en) * | 2019-12-26 | 2020-04-17 | 中天上材增材制造有限公司 | Energy-saving system for gas atomization powder making equipment |
| CN111268140A (en) * | 2020-02-10 | 2020-06-12 | 南京航空航天大学 | Green environmental control system of aircraft |
| US11981440B2 (en) | 2020-11-04 | 2024-05-14 | Hamilton Sundstrand Corporation | Energy flow of an advanced environmental control system |
| CN112492846B (en) * | 2020-11-27 | 2021-12-10 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin ventilation system |
| CN112492846A (en) * | 2020-11-27 | 2021-03-12 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin ventilation system |
| CN114030619A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Modular helicopter air conditioning system |
| CN114030619B (en) * | 2021-11-19 | 2023-10-27 | 中国直升机设计研究所 | Modularized helicopter air conditioning system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101148197A (en) | Cabin circumstance control system used for passenger plane | |
| US9169024B2 (en) | Environmental control system with closed loop pressure cycle | |
| CN100484834C (en) | Air system | |
| CN107531330B (en) | Controllable aircraft air conditioning system with phase dependent operation and method for operating such an aircraft air conditioning system | |
| CN101448702B (en) | Air-conditioning unit and method | |
| US6615606B2 (en) | Dual turbine bootstrap cycle environmental control system | |
| EP2322430B1 (en) | Environmental control system | |
| US7757502B2 (en) | RAM fan system for an aircraft environmental control system | |
| CN102874410B (en) | High-speed motor driven air circulating refrigeration system | |
| USRE32100E (en) | Efficiency air cycle environmental control system | |
| EP2735510B1 (en) | Aircraft air conditioning system and method of operating an aircraft air conditioning system | |
| US20080022688A1 (en) | Air cycle machine for an aircraft environmental control system | |
| CN109367791B (en) | Electric environment control system for multi-electric airplane | |
| CN102381479B (en) | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct | |
| CN203687243U (en) | Cooling-tower free cooling and refrigerant direct expansion air conditioning unit | |
| JP2010065993A (en) | Environmental conditioning system and environmental conditioning method | |
| CN102390538A (en) | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet | |
| CN101372260B (en) | Working method of dual-shaft type four-wheel high-pressure de-watering air circulation refrigeration system based on coaxial line | |
| CN109760484B (en) | Electric automobile thermal management system | |
| CN102390536A (en) | Three-wheel pressure-boosting refrigerating and liquid cooling composite thermal energy managing system | |
| CN102390537A (en) | Comprehensive heat energy management system for environmental control system and liquid cooling system | |
| CN103612760A (en) | Closed type air refrigeration circulation device for actively recycling cooling capacity | |
| CN202770042U (en) | Whole sealing air circulation refrigerating system driven by power turbine | |
| CN208090996U (en) | A kind of composite aircraft air-conditioner set | |
| CN113847666B (en) | Air conditioning system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Open date: 20080326 |