CN113232627A - Aircraft windshield jet flow demisting system and demisting method - Google Patents
Aircraft windshield jet flow demisting system and demisting method Download PDFInfo
- Publication number
- CN113232627A CN113232627A CN202110651746.9A CN202110651746A CN113232627A CN 113232627 A CN113232627 A CN 113232627A CN 202110651746 A CN202110651746 A CN 202110651746A CN 113232627 A CN113232627 A CN 113232627A
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- Prior art keywords
- air
- defogging
- demisting
- aircraft
- membrane
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 239000012528 membrane Substances 0.000 claims abstract description 41
- 230000007613 environmental effect Effects 0.000 claims abstract description 17
- 238000010521 absorption reaction Methods 0.000 claims abstract description 7
- 230000001105 regulatory effect Effects 0.000 claims description 6
- 238000010926 purge Methods 0.000 claims description 4
- 238000010992 reflux Methods 0.000 claims 1
- 239000011521 glass Substances 0.000 abstract description 16
- 239000003570 air Substances 0.000 description 64
- 238000007664 blowing Methods 0.000 description 4
- 238000004378 air conditioning Methods 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000007791 dehumidification Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000012466 permeate Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60S—SERVICING, CLEANING, REPAIRING, SUPPORTING, LIFTING, OR MANOEUVRING OF VEHICLES, NOT OTHERWISE PROVIDED FOR
- B60S1/00—Cleaning of vehicles
- B60S1/02—Cleaning windscreens, windows or optical devices
- B60S1/023—Cleaning windscreens, windows or optical devices including defroster or demisting means
- B60S1/026—Cleaning windscreens, windows or optical devices including defroster or demisting means using electrical means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60S—SERVICING, CLEANING, REPAIRING, SUPPORTING, LIFTING, OR MANOEUVRING OF VEHICLES, NOT OTHERWISE PROVIDED FOR
- B60S1/00—Cleaning of vehicles
- B60S1/02—Cleaning windscreens, windows or optical devices
- B60S1/54—Cleaning windscreens, windows or optical devices using gas, e.g. hot air
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Air-Conditioning For Vehicles (AREA)
Abstract
The invention relates to a defogging system and a defogging method for an aircraft windshield, and belongs to the field of aircraft environmental control. The utility model provides an aircraft windscreen efflux defogging system, the defogging system includes bleed pipe, membrane desicator and defogging nozzle, bleed pipe one end and aircraft environmental control system turbine inlet end intercommunication for introduce through refrigerated high-pressure air, the other end and membrane desicator intercommunication, the other end of membrane desicator passes through the three-way pipe respectively with defogging nozzle, membrane desicator intercommunication, the dry air moisture absorption back that flows back to in the membrane desicator is discharged through exhaust duct, exhaust duct sets up on the membrane desicator, the export of defogging nozzle as dry air, thereby directly blow the windscreen. The invention has the following advantages: 1. the requirements on the air entrainment quantity of an engine compressor and the thermal load of an environmental control system are reduced, and the transparency of the windshield glass is ensured; 2. the system has simple structure, safe and reliable operation and no moving part, and meets the requirements of airborne equipment.
Description
Technical Field
The invention relates to a defogging system and a defogging method for a windshield of an aircraft, in particular to a defogging system and a defogging method for purging the surface of the windshield by using dried air, reducing the dew point temperature of the ambient air and realizing dehumidification, belonging to the field of environmental control of the aircraft.
Background
During the flight of the aircraft, fog will form on the inner surface of the windscreen of the cockpit of the aircraft due to the effect of the high altitude cold air flow when the temperature of the inner surface of the windscreen is lower than the dew point temperature of the ambient air in the cockpit. The fog layer on the inner surface of the windshield not only reduces clarity and visibility, but also causes refraction and reflection of light, thereby causing distortion of the visual appearance and affecting the pilot's field of vision. Therefore, in order to provide a clear and accurate view for pilots and ensure the flight safety of aircrafts, a windshield defogging system is required to be designed and installed.
The existing demisting mode of the aircraft windshield glass is two, namely hot air demisting, which directly sprays high-temperature and high-pressure air from an aircraft engine compressor onto the windshield glass through a nozzle and realizes demisting through the temperature of the surface of the glass; and secondly, defogging is carried out on the resistance wire, the resistance wire is arranged in the interlayer of the windshield glass, and the surface temperature of the windshield glass is increased through the heating of the resistance wire, so that the defogging effect is achieved.
For the current hot air demisting mode of the aircraft, the following defects exist: firstly, high-temperature and high-pressure gas from an aircraft engine compressor is directly blown to the surface of a windshield glass, and extremely uncomfortable hot airflow is brought to the face of a pilot while demisting is carried out, so that the normal operation of the pilot is influenced; secondly, the uncooled high-temperature and high-pressure demisting airflow greatly increases the heat load of a cabin environment control system, and according to analysis of relevant information, the hot airflow for demisting the windshield glass increases the heat load of an air conditioning system responsible for cabin environment control by 5-15%; meanwhile, the method also increases the requirement on the air entraining quantity of the engine, and the compensation loss is high.
For the current demisting mode of the resistance wire of the aircraft, the defects are as follows: because the resistance silk threads are arranged in the windshield glass interlayer, the transparency of the windshield glass is reduced, and the visual ability of a pilot is seriously influenced; meanwhile, a certain amount of onboard electric energy is consumed in the mode, and the heat load of the environment control system is increased.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides an aircraft windshield jet flow demisting system which does not directly increase cabin air conditioning load and has high demisting efficiency.
In order to achieve the purpose, the invention adopts the following technical scheme: the utility model provides an aircraft windscreen efflux defogging system, the defogging system includes bleed pipe, membrane desicator and defogging nozzle, bleed pipe one end and aircraft environmental control system turbine inlet end intercommunication for introduce through refrigerated high-pressure air, the other end and membrane desicator intercommunication, the other end of membrane desicator passes through the three-way pipe respectively with defogging nozzle, membrane desicator intercommunication, the dry air moisture absorption back that flows back to in the membrane desicator is discharged through exhaust duct, exhaust duct sets up on the membrane desicator, the export of defogging nozzle as dry air, thereby directly blow the windscreen.
Preferably, a flow regulator is arranged between the three-way pipe and the demisting nozzle and used for regulating the flow of the demisting air.
Preferably, a flow regulator is arranged between the three-way pipe and the membrane dryer and used for regulating the air flow of the purge gas.
Preferably, an electromagnetic valve is arranged between the bleed air guide pipe and the air inlet end of the turbine of the aircraft environmental control system, and the electromagnetic valve is opened when demisting bleed air is needed.
It is a further object of the present invention to provide a method of demisting an aircraft windshield jet, using a demisting system as claimed in any one of claims 1 to 4, comprising the steps of:
(1) introducing the cooled high-pressure air at the air inlet end of the aircraft environmental control system into the membrane dryer through an air guide conduit;
(2) after being dehumidified in the film dryer, the air is divided into two parts, most of which enter the demisting nozzles and are sprayed out by the demisting nozzles to directly blow the windshield glass; a small part of the air is used as purge gas to flow back to the membrane dryer, and the air is exhausted through an exhaust duct after moisture absorption.
Preferably, the air inlet end of the aircraft environmental control system is a cooled turbine air inlet end.
The working principle is as follows: the efficient membrane dryer is used as a demisting and drying air treatment device, and the preparation of high-degree drying air is realized by controlling the back blowing flow in the membrane dryer; the high-pressure air at the turbine inlet end of the cooled environmental control system is introduced to realize the simplification of the system and the aim of not increasing the heat load of the environmental control system; the windshield glass is directly blown by the dry low-temperature airflow, and the dew point temperature of air contacting with the glass surface is further reduced by utilizing the strong water absorption capacity of the windshield glass, so that the defogging of the glass is realized, and the discomfort to a pilot is reduced.
The working process is as follows: the supercooled high-pressure air at the turbine air inlet end of the aircraft environment control system is introduced into the membrane dryer through an air guide pipe, in the membrane dryer, moisture contained in the air permeates to the outer side of the membrane and is taken away by blowback airflow in the membrane dryer, and the air flowing out of the membrane dryer is highly dried air; the dry air passes through the flow regulator, enters the demisting nozzle and is sprayed out by the demisting nozzle.
Compared with the prior art, the invention has the following advantages:
1. the requirements on the air entrainment quantity of an engine compressor and the thermal load of an environmental control system are reduced, and the transparency of the windshield glass is ensured;
2. the system has simple structure, safe and reliable operation and no moving part, and meets the requirements of airborne equipment.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic diagram of an exemplary embodiment of the present invention;
in the figure, 1, a bleed air duct; 2. an exhaust conduit; 3. a membrane dryer; 4. a three-way pipe; 5. a flow regulator; 6. a flow regulator; 7. a demisting nozzle; 8. bleed air from an aircraft engine; 9. a primary heat exchanger; 10. a compressor; 11. a secondary heat exchanger; 12. a three-way pipe; 13. a turbine; 14. introducing air into the cabin; 15. an electromagnetic valve.
Detailed Description
In this embodiment, the "connection" and the "communication" may be directly connected or indirectly connected through an intermediate medium. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The invention is described in further detail below with reference to the accompanying figures 1-2: the utility model provides an aircraft windscreen efflux defogging system, as shown in figure 1, defogging system includes bleed pipe 1, membrane dryer 3 and defogging nozzle 7, bleed pipe 1 one end and aircraft environmental control system turbine inlet end intercommunication for introduce through refrigerated high-pressure air, the other end and membrane dryer 3 intercommunication, the other end of membrane dryer 3 passes through three-way pipe 4 respectively with defogging nozzle 7, membrane dryer 3 intercommunication, dry air that flows back to in the membrane dryer 3 absorbs the moisture after the exhaust duct 2 discharges, exhaust duct 2 sets up on membrane dryer 3, defogging nozzle 7 is as the export of dry air, thereby directly blow the windscreen.
The system introduces air at the air inlet end of a turbine in an aircraft environmental control system through an air guide conduit 1, the air is divided into two parts through a three-way pipe 4 after being dehumidified in a membrane dryer 3, most of the dry air flows through a flow regulator 6 to enter a demisting nozzle 7 and is sprayed out from the demisting nozzle 7, only a small part of the dry air is used as blowing air and flows back into the membrane dryer 3 through the flow regulator 5, and the air is exhausted through an exhaust conduit 2 after moisture absorption. The flow regulator 5 is used for regulating the flow of the blowing air, so as to regulate the dew point temperature of the demisting air, and the flow regulator 6 is used for regulating the flow of the demisting air.
The present embodiment will be further described with reference to a simple two-wheel boost air cycle refrigeration system as shown in FIG. 2:
the high-temperature and high-pressure aircraft engine bleed air 8 firstly flows through the primary heat exchanger 9, then is compressed by the compressor 10 driven by the turbine 13, and then enters the secondary heat exchanger 11 for cooling, and the air pressure after cooling is higher. When the demisting is not needed, the electromagnetic valve 15 is closed, and the cooled high-pressure air flows through the three-way pipe, enters the turbine 13, expands and enters the cabin as cabin bleed air 14. When defogging is needed, the electromagnetic valve 15 is opened, the cooled high pressure passes through the three-way pipe 12 and then is divided into two parts, most of air is cooled and depressurized through the turbine 13 and then is used as cabin bleed air 14, and a small part of air is used as defogging bleed air of the invention and enters the bleed air guide pipe 1 of the invention after the electromagnetic valve 15 is opened. The flow regulator 5 can regulate the flow of the blowing air, further control the dew point temperature of the demisting air, and the flow regulator 6 can regulate the flow of the demisting air.
The above examples are merely preferred embodiments of the present invention and are not to be construed as limiting the invention. Any extensions, variations, equivalents and the like of those skilled in the art without departing from the principle of the present invention shall be included in the protection scope of the present invention.
Claims (6)
1. An aircraft windshield jet defogging system, comprising: the defogging system includes bleed conduit, membrane dryer and defogging nozzle, bleed conduit one end and aircraft environmental control system inlet end intercommunication for introduce through refrigerated high-pressure air, the other end and membrane dryer intercommunication, the other end of membrane dryer pass through the three-way pipe respectively with the defogging nozzle, membrane dryer intercommunication, dry air that refluxes to in the membrane dryer is discharged through exhaust duct after the moisture absorption, exhaust duct sets up on the membrane dryer, the export of defogging nozzle as dry air, thereby directly blow windshield.
2. The aircraft windshield jet demisting system according to claim 1, wherein: and a flow regulator is arranged between the three-way pipe and the demisting nozzle and is used for regulating the flow of demisting air.
3. The aircraft windshield jet demisting system according to claim 1, wherein: and a flow regulator is arranged between the three-way pipe and the membrane dryer and is used for regulating the air flow of the sweep gas.
4. The aircraft windshield jet demisting system according to claim 1, wherein: an electromagnetic valve is arranged between the bleed air guide pipe and the air inlet end of the turbine of the aircraft environmental control system, and the electromagnetic valve is opened when defogging and bleed air are needed.
5. An aircraft windshield jet demisting method, characterized by: a defogging system as recited in any one of claims 1 through 4 including the steps of:
(1) introducing the cooled high-pressure air at the air inlet end of the aircraft environmental control system into the membrane dryer through an air guide conduit;
(2) after being dehumidified in the membrane dryer, the air is divided into two parts, wherein most of the air enters the demisting nozzles and is sprayed out by the demisting nozzles, and a small part of the air is used as purge gas to flow back to the membrane dryer and is exhausted through the exhaust duct after moisture absorption.
6. The aircraft windshield jet demisting method of claim 5, wherein: and the air inlet end of the aircraft environmental control system is a cooled turbine air inlet end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110651746.9A CN113232627A (en) | 2021-06-11 | 2021-06-11 | Aircraft windshield jet flow demisting system and demisting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110651746.9A CN113232627A (en) | 2021-06-11 | 2021-06-11 | Aircraft windshield jet flow demisting system and demisting method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113232627A true CN113232627A (en) | 2021-08-10 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110651746.9A Pending CN113232627A (en) | 2021-06-11 | 2021-06-11 | Aircraft windshield jet flow demisting system and demisting method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113232627A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1268089A (en) * | 1997-06-24 | 2000-09-27 | 显微加热公司 | Wind shield de-icing |
| US20060097111A1 (en) * | 2004-10-04 | 2006-05-11 | Wood Jeffrey H | Methods and systems for rain removal and de-icing of monolithic windshields |
| US20110005255A1 (en) * | 2009-07-09 | 2011-01-13 | Denso Corporation | Vehicular air-conditioning system |
| JP2012166683A (en) * | 2011-02-14 | 2012-09-06 | Mitsubishi Heavy Ind Ltd | De-fogging device and aircraft including the same |
| US20140338883A1 (en) * | 2012-08-05 | 2014-11-20 | Yokohama Heat Use Technology | Dehumidifying Device for Vehicle, Flexible Dehumidifying Member, and HVAC Device for Vehicle |
| CN110630383A (en) * | 2018-06-22 | 2019-12-31 | 通用电气公司 | Aircraft anti-icing system |
| CN110936923A (en) * | 2019-12-17 | 2020-03-31 | 重庆交通大学 | Defogging system for airplane windshield |
-
2021
- 2021-06-11 CN CN202110651746.9A patent/CN113232627A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1268089A (en) * | 1997-06-24 | 2000-09-27 | 显微加热公司 | Wind shield de-icing |
| US20060097111A1 (en) * | 2004-10-04 | 2006-05-11 | Wood Jeffrey H | Methods and systems for rain removal and de-icing of monolithic windshields |
| US20110005255A1 (en) * | 2009-07-09 | 2011-01-13 | Denso Corporation | Vehicular air-conditioning system |
| JP2012166683A (en) * | 2011-02-14 | 2012-09-06 | Mitsubishi Heavy Ind Ltd | De-fogging device and aircraft including the same |
| US20140338883A1 (en) * | 2012-08-05 | 2014-11-20 | Yokohama Heat Use Technology | Dehumidifying Device for Vehicle, Flexible Dehumidifying Member, and HVAC Device for Vehicle |
| CN110630383A (en) * | 2018-06-22 | 2019-12-31 | 通用电气公司 | Aircraft anti-icing system |
| CN110936923A (en) * | 2019-12-17 | 2020-03-31 | 重庆交通大学 | Defogging system for airplane windshield |
Non-Patent Citations (1)
| Title |
|---|
| （英）理查德•布洛克利, 北京理工大学出版社 * |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210810 |
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| RJ01 | Rejection of invention patent application after publication |