CN110481791B - Air conditioning system for aircraft cabin - Google Patents
Air conditioning system for aircraft cabin Download PDFInfo
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- CN110481791B CN110481791B CN201910879791.2A CN201910879791A CN110481791B CN 110481791 B CN110481791 B CN 110481791B CN 201910879791 A CN201910879791 A CN 201910879791A CN 110481791 B CN110481791 B CN 110481791B
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- membrane dehumidification
- pipeline
- aircraft cabin
- conditioning system
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- 238000004378 air conditioning Methods 0.000 title claims abstract description 40
- 238000007791 dehumidification Methods 0.000 claims abstract description 152
- 239000012528 membrane Substances 0.000 claims abstract description 133
- 238000010926 purge Methods 0.000 claims description 27
- 238000010438 heat treatment Methods 0.000 claims description 18
- 238000001816 cooling Methods 0.000 claims description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 14
- 238000005057 refrigeration Methods 0.000 claims description 8
- 239000000428 dust Substances 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 description 3
- 239000003507 refrigerant Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 108010066057 cabin-1 Proteins 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000035479 physiological effects, processes and functions Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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Classifications
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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, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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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, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
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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, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0651—Environmental Control Systems comprising filters, e.g. dust filters
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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, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0662—Environmental Control Systems with humidity control
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- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Separation Using Semi-Permeable Membranes (AREA)
Abstract
The invention discloses an air conditioning system for an aircraft cabin. The aircraft cabin air conditioning system comprises: the dehumidification device, the cold and hot device and the air supply device are connected in sequence; the dehumidification device comprises a primary membrane dehumidification assembly, a gas compressor and a secondary membrane dehumidification assembly; the air inlet end of the primary membrane dehumidification assembly is communicated with the atmosphere; the air outlet end of the primary membrane dehumidification assembly is connected with the air inlet end of the air compressor through a pipeline; the air inlet end of the secondary membrane dehumidification assembly is connected with the air outlet end of the air compressor through a pipeline; the compressor is used for supercharging and sucking air from the atmosphere. By arranging the air compressor, the air compressor is used for boosting pressure, air is sucked from the atmosphere to serve as an air source, and the traditional air supply mode that the air compressor of the engine serves as a power source is replaced, so that the power loss of an airplane engine is reduced, and the performance of the engine is improved.
Description
Technical Field
The invention relates to the technical field of aircraft environment control, in particular to an air conditioning system of an aircraft cabin.
Background
Along with the continuous improvement of living standard of people, the requirement on the comfort of an airplane cabin is also continuously improved, and the traditional airplane air conditioning system can not meet the requirement gradually. With the ever increasing altitude, the outside environment changes and the regulation of the air inside the cabin becomes of great importance. The purpose of cabin air conditioning is to adjust parameters such as humidity, temperature and pressure in the cabin according to human physiology, and improve the comfort requirement of passengers.
At present, an existing air conditioning system mainly comprises a refrigerating system, a heating system and a supercharging air supply system, an engine compressor of an airplane is used as a power source of an air source, and the air supply mode needs to utilize the output power of the engine, so that the power loss of the engine of the airplane is increased, and the performance of the engine is not favorably improved.
Disclosure of Invention
The invention aims to provide an air conditioning system of an aircraft cabin, which reduces the power loss of an engine and improves the performance of the engine.
In order to achieve the purpose, the invention provides the following scheme:
an aircraft cabin air conditioning system disposed inside an aircraft cabin, the aircraft cabin air conditioning system comprising:
the dehumidification device, the cold and hot device and the air supply device are connected in sequence;
the dehumidification device comprises a primary membrane dehumidification assembly, a gas compressor and a secondary membrane dehumidification assembly;
the air inlet end of the primary membrane dehumidification assembly is communicated with the atmosphere; the air outlet end of the primary membrane dehumidification assembly is connected with the air inlet end of the air compressor through a pipeline; the primary membrane dehumidification assembly is used for carrying out primary dehumidification on the passing gas;
the air inlet end of the secondary membrane dehumidification assembly is connected with the air outlet end of the air compressor through a pipeline; the air outlet end of the secondary membrane dehumidification assembly is connected with the cold and hot device; the secondary membrane dehumidification assembly is used for carrying out secondary dehumidification on passing gas;
the steam outlet of the primary membrane dehumidification assembly and the steam outlet of the secondary membrane dehumidification assembly are communicated with the atmosphere through a first pipeline;
the air compressor is used for supercharging and sucking air from the atmosphere;
the cold and hot device is used for cooling or heating the gas flowing through;
the air supply device is arranged at the top of the aircraft cabin and is used for sending the dehumidified gas into the aircraft cabin.
Optionally, the aircraft cabin air conditioning system further comprises a filter;
one end of the filter is communicated with the atmosphere, and the other end of the filter is connected with the air inlet end of the primary membrane dehumidification component; the filter is used for filtering dust in the sucked air.
Optionally, the air inlet end of the primary membrane dehumidification assembly is connected with the air outlet end of the primary membrane dehumidification assembly through a second pipeline;
a first valve is arranged on the second pipeline; the first valve is used for shunting the dry gas dehumidified by the primary membrane dehumidification component, and introducing the shunted dry gas dehumidified by the primary membrane dehumidification component into the primary membrane dehumidification component as a first purge gas; the first purge gas is used for purging water vapor accumulated in the primary membrane dehumidification assembly;
the air inlet end of the secondary membrane dehumidification assembly is connected with the air outlet end of the secondary membrane dehumidification assembly through a third pipeline;
a second valve is arranged on the third pipeline; the second valve is used for shunting the dry gas dehumidified by the secondary membrane dehumidification component, and introducing the dry gas obtained by shunting and dehumidified by the secondary membrane dehumidification component into the secondary membrane dehumidification component as second purge gas; the second purge gas is used for purging accumulated moisture in the secondary membrane dehumidification module.
Optionally, the aircraft cabin air conditioning system further comprises a fourth duct;
one end of the fourth pipeline is connected to the second pipeline between the first valve and the air inlet end of the primary membrane dehumidification assembly;
the other end of the fourth pipeline is connected to a third pipeline between the second valve and the air outlet end of the secondary membrane dehumidification assembly;
a third valve is arranged on the fourth pipeline; the third valve is used for introducing the second purge gas into the primary membrane dehumidification module.
Optionally, a fourth valve is arranged at the tail end of the first pipeline.
Optionally, the cooling and heating device comprises an evaporator, a throttle valve, a condenser and a compressor;
one end of the evaporator is connected with one end of the throttle valve and the air outlet end of the secondary membrane dehumidification assembly respectively; the other end of the evaporator is respectively connected with one end of the compressor and the air supply device; the evaporator is used for cooling or heating the flowing dry air;
the other end of the throttle valve is connected with one end of the condenser;
the other end of the compressor is connected with the other end of the condenser;
the condenser is used for exchanging heat with the atmosphere.
Optionally, the steam outlet of the primary membrane dehumidification assembly and the steam outlet of the secondary membrane dehumidification assembly are further connected to a fifth pipeline respectively;
a fifth valve is arranged on the fifth pipeline;
a sprayer is arranged at the tail end of the fifth pipeline;
the sprayer is arranged right below the condenser;
the sprayer is used for spraying the water vapor discharged by the primary membrane dehumidification assembly and the water vapor discharged by the secondary membrane dehumidification assembly to a condenser in a refrigeration mode.
Optionally, the cooling and heating device further comprises a fan;
the fan is arranged under the sprayer.
Optionally, the air supply device includes a plurality of air supply outlets;
the plurality of air supply outlets are all arranged at the top of the aircraft cabin;
and each air supply outlet is connected with the cold and hot device through a pipeline.
Optionally, the aircraft cabin air conditioning system further comprises a pressure regulator;
the pressure regulator is arranged in the aircraft cabin;
the pressure regulator is used for regulating the pressure in the aircraft cabin according to the flying height.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the air conditioning system of the aircraft cabin comprises a dehumidifying device, a cooling and heating device and an air supply device which are connected in sequence. The dehumidification device comprises a primary membrane dehumidification assembly, a gas compressor and a secondary membrane dehumidification assembly; the air inlet end of the primary membrane dehumidification component is communicated with the atmosphere, and the air outlet end of the primary membrane dehumidification component is connected with the air inlet end of the air compressor through a pipeline; the air inlet end of the secondary membrane dehumidification assembly is connected with the air outlet end of the air compressor through a pipeline, and the air outlet end of the secondary membrane dehumidification assembly is connected with the cold and hot device; the air supply device is arranged at the top of the aircraft cabin.
The air inlet end of the primary membrane dehumidification component is communicated with the atmosphere, the air outlet end of the primary membrane dehumidification component is connected with the air inlet end of the air compressor, the air compressor is used for boosting, air is sucked from the atmosphere to serve as an air source, namely, the air compressor is used as a power source, and the traditional air supply mode that the engine air compressor is used as the power source is replaced, so that the power loss of an airplane engine is reduced, and the performance of the engine is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a block diagram of an aircraft cabin air conditioning system provided by an embodiment of the present invention;
description of reference numerals:
1-cabin, 2-fifth pipeline, 3-fourth pipeline, 4-filter, 5-primary membrane dehumidification component, 6-compressor, 7-secondary membrane dehumidification component, 8-evaporator, 9-air supply outlet, 10-pressure regulator, 11-compressor, 12-condenser, 13-throttle valve, 14-first valve, 15-second valve, 16-third valve, 17-fourth valve, 18-fifth valve, 19-sprayer, 20-fan, 21-first pipeline, 22-second pipeline, 23-third pipeline.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide an air conditioning system of an aircraft cabin, which reduces the power loss of an engine and improves the performance of the engine.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Fig. 1 is a block diagram of an aircraft cabin air conditioning system according to an embodiment of the present invention, and as shown in fig. 1, an aircraft cabin air conditioning system provided inside an aircraft cabin 1 includes: the dehumidification device, the cold and hot device and the air supply device are connected in sequence.
The dehumidification device comprises a primary membrane dehumidification component 5, a gas compressor 6 and a secondary membrane dehumidification component 7;
the air inlet end of the primary membrane dehumidification component 5 is communicated with the atmosphere; the air outlet end of the primary membrane dehumidification component 5 is connected with the air inlet end of the air compressor 6 through a pipeline; the primary membrane dehumidification component 5 is used for carrying out primary dehumidification on the gas passing through;
the air inlet end of the secondary membrane dehumidification component 7 is connected with the air outlet end of the air compressor 6 through a pipeline; the air outlet end of the secondary membrane dehumidification component 7 is connected with the cold and hot device; the secondary membrane dehumidification assembly 7 is used for carrying out secondary dehumidification on the passing gas;
the primary membrane dehumidification module 5 in this embodiment is a low-pressure module, and the secondary membrane dehumidification module 7 is a high-pressure module.
The steam outlet of the primary membrane dehumidification assembly 5 and the steam outlet of the secondary membrane dehumidification assembly 7 are both communicated with the atmosphere through a first pipeline 21; the end of the first pipe 21 is provided with a fourth valve 17.
The air compressor 6 is used for supercharging and sucking air from the atmosphere;
in the embodiment, the compressor 6 is an electric compressor, the primary membrane dehumidification component 5 is arranged in front of the air inlet to perform primary dehumidification, air inlet parameters entering the compressor 6 can be optimized, and energy consumption is reduced.
The air supply mode of the air compressor 6 is that the air compressor 11 is used for pressurizing and supplying air, air does not need to be led from an engine, and the performance of the engine can be improved.
The cold and hot device is used for cooling or heating the gas flowing through;
the air supply device is arranged at the top of the aircraft cabin and is used for sending the dehumidified gas into the aircraft cabin.
The aircraft cabin air conditioning system further comprises a filter 4;
one end of the filter 4 is communicated with the atmosphere, and the other end of the filter 4 is connected with the air inlet end of the primary membrane dehumidification component 5; the filter 4 is used to filter dust in the intake air.
The air inlet end of the primary membrane dehumidification component 5 is connected with the air outlet end of the primary membrane dehumidification component 5 through a second pipeline 22;
the second pipeline 22 is provided with a first valve 14; the first valve 14 is configured to split the dry gas dehumidified by the primary membrane dehumidification module 5, and introduce the split dry gas dehumidified by the primary membrane dehumidification module 5 into the primary membrane dehumidification module 5 as a first purge gas; the first purge gas is used to purge moisture accumulated in the primary membrane dehumidification module 5.
The air inlet end of the secondary membrane dehumidification component 7 is connected with the air outlet end of the secondary membrane dehumidification component 7 through a third pipeline 23;
a second valve 15 is arranged on the third pipeline 23; the second valve 15 is configured to split the dry gas dehumidified by the secondary membrane dehumidification module 7, and introduce the split dry gas dehumidified by the secondary membrane dehumidification module 7 into the secondary membrane dehumidification module 7 as a second purge gas; the second purge gas is used to purge moisture accumulated in the secondary membrane dehumidification module 7.
Introduce primary membrane dehumidification subassembly 5 with first purge gas through setting up first valve 14, set up second valve 15 and introduce secondary membrane dehumidification subassembly 7 with second purge gas, avoid along with the continuous dehumidification in-process of primary membrane dehumidification subassembly 5 and secondary membrane dehumidification subassembly 7, the steam in the membrane outside is more and more, leads to the steam in the humid air to be difficult to dehumidify more and more. Namely, the water vapor focused on the outer side of the membrane is removed through purging with the purge gas, so that the primary membrane dehumidification component 5 and the secondary membrane dehumidification component 7 can perform dehumidification in normal operation.
The aircraft cabin air conditioning system further comprises a fourth duct 3;
one end of the fourth pipeline 3 is connected to the second pipeline 22 between the first valve 14 and the air inlet end of the primary membrane dehumidification assembly 5;
the other end of the fourth pipeline 3 is connected to a third pipeline 23 between the second valve 15 and the air outlet end of the secondary membrane dehumidification assembly 7;
a third valve 16 is arranged on the fourth pipeline 3; the third valve 16 is used for introducing the second purge gas into the primary membrane dehumidification module 5.
The cooling and heating device comprises an evaporator 8, a throttle valve 13, a condenser 12 and a compressor 11;
one end of the evaporator 8 is respectively connected with one end of the throttle valve 13 and the air outlet end of the secondary membrane dehumidification component 7; the other end of the evaporator 8 is respectively connected with one end of the compressor 11 and the air supply device; the evaporator 8 is used for cooling or heating the drying air flowing through;
the other end of the throttle valve 13 is connected with one end of the condenser 12;
the other end of the compressor 11 is connected with the other end of the condenser 12;
the condenser 12 is used for heat exchange with the atmosphere.
In the embodiment, both the evaporator 8 and the condenser 12 adopt micro-channel heat exchangers to improve the heat exchange performance and reduce the volume and weight;
when the cold and hot device is in a refrigeration mode, the refrigerant sequentially flows through the compressor 11, the condenser 12, the throttle valve 13 and the evaporator 8, and the water vapor generated by the dehumidification module is sprayed to the condenser 12, so that the heat exchange performance is further improved;
when the cooling and heating apparatus is in the heating mode, the refrigerant flows in the opposite direction to that in the cooling mode, the evaporator 8 in the cooling mode is changed to the condenser 12 in the heating mode, and the condenser 12 is changed to the evaporator 8 in the heating mode.
The air inlet of the evaporator 8 is connected with the air outlet end of the secondary membrane dehumidification assembly 7, and the dry air exchanges heat with the refrigerant in the evaporator 8. The condenser 12 exchanges heat with the air outside the cabin, and removes heat to the outside of the cabin in the cooling mode and absorbs heat from the outside of the cabin in the heating mode.
The steam outlet of the primary membrane dehumidification assembly 5 and the steam outlet of the secondary membrane dehumidification assembly 7 are also respectively connected with a fifth pipeline 2;
a fifth valve 18 is arranged on the fifth pipeline 2;
the tail end of the fifth pipeline 2 is provided with a sprayer 19;
the sprayer 19 is arranged right below the condenser 12;
the sprayer 19 is used for spraying the water vapor discharged from the primary membrane dehumidification assembly 5 and the water vapor discharged from the secondary membrane dehumidification assembly 7 to the condenser 12 in the refrigeration mode.
And the fourth valve 17 is arranged to directly discharge the water vapor in the air discharged by the primary membrane dehumidification assembly 5 and the secondary membrane dehumidification assembly 7 out of the cabin, and the fifth valve 18 is arranged to spray the water vapor discharged by the primary membrane dehumidification assembly 5 and the secondary membrane dehumidification assembly 7 to the condenser 12 in the refrigeration model, so that refrigeration is facilitated.
The cooling and heating device further comprises a fan 20;
the fan 20 is disposed directly below the sprayer 19.
The air supply device comprises a plurality of air supply outlets 9;
the plurality of air supply outlets 9 are all arranged at the top of the aircraft cabin;
each air supply outlet 9 is connected with the cold and hot device through a pipeline.
In this embodiment, the air supply outlets 9 are distributed at equal intervals or distributed according to the requirement of thermal comfort of human body after the optimization of airflow organization.
The aircraft cabin air conditioning system further comprises a pressure regulator 10;
the pressure regulator 10 is arranged in the aircraft cabin;
the pressure regulator 10 is used to regulate the pressure in the aircraft cabin according to the flight altitude.
The aircraft cabin air conditioning system of the invention is realized by the following steps:
after introduction from the environment outside the aircraft cabin, the air is first compressed at a lower pressure through the primary membrane dehumidification module 5, then enters the electric compressor 6, is compressed again at a higher pressure through the secondary membrane dehumidification module 7, then exchanges heat through the evaporator 8 or the condenser 12 and finally enters the cabin through the cabin roof supply distribution line.
The water vapor generated by the primary membrane dehumidification assembly 5 and the secondary membrane dehumidification assembly 7 can be directly sprayed out of the cabin and also can be sprayed to the condenser 12 of the cold and hot device when the cold and hot device is in a refrigeration mode. When the pressure of the purge gas flow of the primary membrane dehumidification module 5 is too low, the partial purge gas flow introduced into the secondary membrane dehumidification module 7 can be mixed and supplemented. The dehumidification module provides required dehumidification ability according to the cabin humidity requirement, and cold and hot device requires real-time suitable refrigerating output or the heating volume of providing according to the cabin temperature, and pressure boost air feed module requires according to cabin pressure, adjusts exhaust valve in real time.
In this embodiment, the pressure regulator 10 regulates the opening degree and the opening/closing speed of the exhaust valve according to a pressure system. The pressure system is a curve of pressure along with altitude change, namely, different flight altitudes correspond to different cabin pressures. The pressure regulator 10 automatically regulates the opening of an exhaust valve according to the set pressure in the cabin to ensure that the pressure in the cabin meets the set value. The switching speed is to ensure that the pressure change speed also meets the set requirement so as not to cause discomfort to passengers.
The aircraft cabin air conditioning system of the invention has the following effects:
the aircraft cabin air conditioning system of the invention can be applied to both fixed-wing aircraft and rotary-wing aircraft.
The invention realizes the effective regulation of different air parameters of the airplane cabin, the system is based on the membrane dehumidification technology, and simultaneously utilizes the electric compressor 6 to pressurize the air supply technology and the evaporative refrigeration cycle technology, has the advantages of small volume, light weight, low energy consumption, high reliability and the like, and can meet the design requirements of environmental control of the airplane and the airplane cabin in the future.
The invention is provided with a primary membrane dehumidification component 5 and a secondary membrane dehumidification component 7, when one of the components fails, the other component can still work normally, and the air conditioning in the cabin is guaranteed.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. An aircraft cabin air conditioning system, the aircraft cabin air conditioning system being disposed inside an aircraft cabin, the aircraft cabin air conditioning system comprising:
the dehumidification device, the cold and hot device and the air supply device are connected in sequence;
the dehumidification device comprises a primary membrane dehumidification assembly, a gas compressor and a secondary membrane dehumidification assembly;
the air inlet end of the primary membrane dehumidification assembly is communicated with the atmosphere; the air outlet end of the primary membrane dehumidification assembly is connected with the air inlet end of the air compressor through a pipeline; the primary membrane dehumidification assembly is used for carrying out primary dehumidification on the passing gas;
the air inlet end of the secondary membrane dehumidification assembly is connected with the air outlet end of the air compressor through a pipeline; the air outlet end of the secondary membrane dehumidification assembly is connected with the cold and hot device; the secondary membrane dehumidification assembly is used for carrying out secondary dehumidification on passing gas;
the air inlet end of the primary membrane dehumidification assembly is connected with the air outlet end of the primary membrane dehumidification assembly through a second pipeline;
a first valve is arranged on the second pipeline; the first valve is used for shunting the dry gas dehumidified by the primary membrane dehumidification component, and introducing the shunted dry gas dehumidified by the primary membrane dehumidification component into the primary membrane dehumidification component as a first purge gas; the first purge gas is used for purging water vapor accumulated in the primary membrane dehumidification assembly;
the air inlet end of the secondary membrane dehumidification assembly is connected with the air outlet end of the secondary membrane dehumidification assembly through a third pipeline;
a second valve is arranged on the third pipeline; the second valve is used for shunting the dry gas dehumidified by the secondary membrane dehumidification component, and introducing the dry gas obtained by shunting and dehumidified by the secondary membrane dehumidification component into the secondary membrane dehumidification component as second purge gas; the second purge gas is used for purging water vapor accumulated in the secondary membrane dehumidification module;
the steam outlet of the primary membrane dehumidification assembly and the steam outlet of the secondary membrane dehumidification assembly are communicated with the atmosphere through a first pipeline;
the air compressor is used for supercharging and sucking air from the atmosphere;
the cold and hot device is used for cooling or heating the gas flowing through;
the air supply device is arranged at the top of the aircraft cabin and is used for sending the dehumidified gas into the aircraft cabin.
2. An aircraft cabin air conditioning system according to claim 1,
the aircraft cabin air conditioning system further comprises a filter;
one end of the filter is communicated with the atmosphere, and the other end of the filter is connected with the air inlet end of the primary membrane dehumidification component; the filter is used for filtering dust in the sucked air.
3. An aircraft cabin air conditioning system according to claim 1,
the aircraft cabin air conditioning system further comprises a fourth duct;
one end of the fourth pipeline is connected to the second pipeline between the first valve and the air inlet end of the primary membrane dehumidification assembly;
the other end of the fourth pipeline is connected to a third pipeline between the second valve and the air outlet end of the secondary membrane dehumidification assembly;
a third valve is arranged on the fourth pipeline; the third valve is used for introducing the second purge gas into the primary membrane dehumidification module.
4. An aircraft cabin air conditioning system according to claim 1,
and a fourth valve is arranged at the tail end of the first pipeline.
5. An aircraft cabin air conditioning system according to claim 1,
the cold and hot device comprises an evaporator, a throttle valve, a condenser and a compressor;
one end of the evaporator is connected with one end of the throttle valve and the air outlet end of the secondary membrane dehumidification assembly respectively; the other end of the evaporator is respectively connected with one end of the compressor and the air supply device; the evaporator is used for cooling or heating the flowing dry air;
the other end of the throttle valve is connected with one end of the condenser;
the other end of the compressor is connected with the other end of the condenser;
the condenser is used for exchanging heat with the atmosphere.
6. An aircraft cabin air conditioning system according to claim 5,
the steam outlet of the primary membrane dehumidification assembly and the steam outlet of the secondary membrane dehumidification assembly are also connected with a fifth pipeline respectively;
a fifth valve is arranged on the fifth pipeline;
a sprayer is arranged at the tail end of the fifth pipeline;
the sprayer is arranged right below the condenser;
the sprayer is used for spraying the water vapor discharged by the primary membrane dehumidification assembly and the water vapor discharged by the secondary membrane dehumidification assembly to a condenser in a refrigeration mode.
7. An aircraft cabin air conditioning system according to claim 6,
the cold and hot device also comprises a fan;
the fan is arranged under the sprayer.
8. An aircraft cabin air conditioning system according to claim 1,
the air supply device comprises a plurality of air supply outlets;
the plurality of air supply outlets are all arranged at the top of the aircraft cabin;
and each air supply outlet is connected with the cold and hot device through a pipeline.
9. An aircraft cabin air conditioning system according to claim 1,
the aircraft cabin air conditioning system further comprises a pressure regulator;
the pressure regulator is arranged in the aircraft cabin;
the pressure regulator is used for regulating the pressure in the aircraft cabin according to the flying height.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910879791.2A CN110481791B (en) | 2019-09-18 | 2019-09-18 | Air conditioning system for aircraft cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910879791.2A CN110481791B (en) | 2019-09-18 | 2019-09-18 | Air conditioning system for aircraft cabin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110481791A CN110481791A (en) | 2019-11-22 |
| CN110481791B true CN110481791B (en) | 2020-12-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910879791.2A Active CN110481791B (en) | 2019-09-18 | 2019-09-18 | Air conditioning system for aircraft cabin |
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| CN111060431B (en) * | 2020-01-09 | 2020-12-25 | 北京航空航天大学 | Airborne passive air intake special pollution real-time rapid monitoring system |
| CN113358688A (en) * | 2021-06-02 | 2021-09-07 | 中国商用飞机有限责任公司 | Icing environment simulation system and test method thereof |
| CN113353267A (en) * | 2021-07-20 | 2021-09-07 | 南京航空航天大学 | Helicopter cabin air conditioning system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101148197A (en) * | 2007-10-26 | 2008-03-26 | 北京航空航天大学 | Cabin circumstance control system used for passenger plane |
| CN101743166A (en) * | 2007-07-11 | 2010-06-16 | 空中客车作业有限公司 | Air conditioning system for aircraft cabins |
| CN102506514A (en) * | 2011-11-08 | 2012-06-20 | 中国商用飞机有限责任公司 | Refrigeration system for aircraft |
| WO2018233274A1 (en) * | 2017-06-22 | 2018-12-27 | 北京航空航天大学 | Aircraft environmental control and fuel tank inerting coupling system based on membrane separation method |
| CN109100389A (en) * | 2018-10-29 | 2018-12-28 | 北京航空航天大学 | A kind of high and low temperature environment cabin dew-point control system |
| CN110044953A (en) * | 2019-03-26 | 2019-07-23 | 南京航空航天大学 | Boiling crisis Heat Flow Experiment device is flowed under a kind of hypergravity |
| EP3514065A1 (en) * | 2018-01-19 | 2019-07-24 | Hamilton Sundstrand Corporation | Aircraft environmental control system |
-
2019
- 2019-09-18 CN CN201910879791.2A patent/CN110481791B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101743166A (en) * | 2007-07-11 | 2010-06-16 | 空中客车作业有限公司 | Air conditioning system for aircraft cabins |
| CN101148197A (en) * | 2007-10-26 | 2008-03-26 | 北京航空航天大学 | Cabin circumstance control system used for passenger plane |
| CN102506514A (en) * | 2011-11-08 | 2012-06-20 | 中国商用飞机有限责任公司 | Refrigeration system for aircraft |
| WO2018233274A1 (en) * | 2017-06-22 | 2018-12-27 | 北京航空航天大学 | Aircraft environmental control and fuel tank inerting coupling system based on membrane separation method |
| EP3514065A1 (en) * | 2018-01-19 | 2019-07-24 | Hamilton Sundstrand Corporation | Aircraft environmental control system |
| CN109100389A (en) * | 2018-10-29 | 2018-12-28 | 北京航空航天大学 | A kind of high and low temperature environment cabin dew-point control system |
| CN110044953A (en) * | 2019-03-26 | 2019-07-23 | 南京航空航天大学 | Boiling crisis Heat Flow Experiment device is flowed under a kind of hypergravity |
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