CN115230969B - Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment - Google Patents
Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment Download PDFInfo
- Publication number
- CN115230969B CN115230969B CN202210907003.8A CN202210907003A CN115230969B CN 115230969 B CN115230969 B CN 115230969B CN 202210907003 A CN202210907003 A CN 202210907003A CN 115230969 B CN115230969 B CN 115230969B
- Authority
- CN
- China
- Prior art keywords
- air
- sent
- vortex tube
- flow
- mixed
- 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.)
- Active
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 55
- 230000007613 environmental effect Effects 0.000 title claims abstract description 24
- 238000000034 method Methods 0.000 title abstract description 6
- 230000001105 regulatory effect Effects 0.000 claims description 30
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 30
- 238000010438 heat treatment Methods 0.000 claims description 18
- 230000003068 static effect Effects 0.000 claims description 14
- 238000005265 energy consumption Methods 0.000 claims description 6
- 238000007710 freezing Methods 0.000 claims description 4
- 239000012535 impurity Substances 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 3
- 239000012774 insulation material Substances 0.000 claims description 2
- 238000005507 spraying Methods 0.000 claims description 2
- 230000007547 defect Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 9
- 238000009413 insulation Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 229910002012 Aerosil® Inorganic materials 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D13/006—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being used to cool structural parts of the aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D2013/0607—Environmental Control Systems providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D2013/0625—Environmental Control Systems comprising means for distribution effusion of conditioned air in the cabin
-
- 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
Abstract
The invention discloses an aircraft environmental control system and method for preventing ice and cooling electronic equipment by adopting a vortex tube. The invention can overcome the defects of the traditional air circulation system that the mass, the volume and the noise are large, the turbine component structure is complex, and the additional engine bleed air is needed for deicing, so that the environmental control system can provide hot air and cold air for deicing of an aircraft and cooling electronic equipment on the premise of low performance compensation loss, and the flight safety and the flight performance are ensured.
Description
Technical Field
The invention relates to an aircraft environmental control system and method adopting a vortex tube for preventing ice and cooling electronic equipment, belonging to the technical field of aircraft environmental control.
Background
With the rapid development of the aviation industry in China, how to ensure the flight safety becomes a main problem. In the statistical data of 1 month of 1983 to 8 months of 1998, 1220 flying accidents are caused by ice accumulation of the aircraft worldwide. When an aircraft is flown in a cloud containing a large number of supercooled water droplets, the supercooled water droplets may form an ice layer on the windward side of the aircraft (e.g., windshields, wings, tail wings, propellers, etc.), with the most serious being icing of the wings and tail wings. The aerosil of the aircraft is influenced by the icing of the wing and the tail wing, so that the problems of the aircraft such as reduced lift-drag ratio, reduced maneuvering performance, increased stall speed and the like are caused. When the ice layer is thicker, the gravity center of the aircraft can be changed, so that pitching moment is generated, stability is reduced, and when the ice layer falls off, vibration of wings and tail wings can be caused, and even the aircraft is crashed. Accordingly, an anti-icing and deicing system should be provided on board an aircraft, and it is a common hot gas anti-icing system to increase the surface temperature by heating the skin with hot gas.
The electronic equipment cabin is also an important component of the aircraft, and the electronic equipment fault also can form a great threat to the flight safety of the aircraft, for example, when the working reliability of a radar transceiver is reduced, the aircraft cannot be accurately helped to send the aircraft flight height and speed to ground control personnel, so that the aircraft cannot normally run. The reliability and stability of the operation of the electronic device are determined by the operating environment conditions, and the ambient temperature directly affects the operating performance of the device. With the increase of the number of electronic devices and the heat dissipation capacity, it is more important to provide effective environmental control for the electronic device cabin in order to ensure the normal operation of the electronic devices.
The conventional aircraft deicing technology comprises a mechanical deicing prevention system, an electrothermal deicing prevention system and a hot gas deicing prevention system. The mechanical deicing system can fail under certain meteorological conditions, and has heavy weight and poor deicing effect; the electrothermal ice protection and removal system consumes a large amount of electric energy, and the hot air ice protection and removal system is a system which is reliable and widely applied at present. For the environmental control of the air in the electronic cabin, the air is conveyed to cool the equipment through the environmental control pipeline, the volume of the equipment cabin is increased by the method, the weight of the aircraft is increased, and the environment of the electronic cabin cannot be effectively controlled. The air circulation system in the traditional environmental control system adopts a turbofan component, the mass, the volume and the noise of the system are large, the structure of the turbine component is complex, and additional engine bleed air is needed for deicing. If the vortex tube and the ejector with simple structures replace the turbofan component, the total weight and fuel compensation loss of the aircraft can be reduced, and the generated hot air can be used for preventing and removing ice and preventing defogging of the aircraft, especially for military aircraft with relatively small refrigerating capacity requirement and isolation, compared with other refrigerating modes, the vortex tube system has more remarkable effect.
Disclosure of Invention
In order to overcome the defects, the invention provides an aircraft environmental control system adopting a vortex tube for preventing ice and cooling electronic equipment. The system adopts the vortex tube and the ejector to replace a turbofan component in the traditional environmental control system, so that the air circulation system has two functions of heating and refrigerating, and the temperature and the flow of cold and hot fluid are adjustable. The invention overcomes the defects of large mass, large volume and noise, complex turbine component structure and the need of additional engine bleed air for deicing of the traditional air circulation system, and ensures that the environmental control system provides hot air and cold air for deicing of an aircraft and cooling of electronic equipment on the premise of low performance compensation loss, thereby ensuring flight safety and flight performance.
In order to achieve the technical purpose, the invention adopts the following technical means:
an aircraft environmental control system adopting vortex tube for preventing ice and cooling electronic equipment,
the external air compressed by the engine compressor is divided into two paths of air after passing through a first air conveying pipeline, wherein the first path of air passes through a first water separator after passing through a first cooling unit, the separated moisture is sent to a first nozzle, the air in a cold air channel is cooled, and the dried air is sent to a first heat regenerator for heating and then is sent to a first vortex tube;
the second path of air passes through a second water separator after passing through a second cooling unit, the separated water is sent to a second nozzle, the air in a cold air duct is cooled, and the dried air is sent to a second heat regenerator for heating and then enters a second vortex tube;
cold air generated by the second vortex tube is mixed with stamping air collected by the second gas collecting hood through the second ejector and then is sent into the cold air duct, the sprayed air sprayed by the first nozzle and the second nozzle is cooled and then is heated by the heat exchanger and then is collected by the first gas collecting hood, hot air collected by the first gas collecting hood flows through the second flow valve to adjust the flow, then is mixed with high-pressure hot air of the first vortex tube in the first ejector, and the mixed air flows through the anti-freezing valve and then is sent into the wing ice preventing and removing system;
cold air of the first vortex tube and hot air of the second vortex tube are respectively mixed with return air in the electronic cabin after being converged through the air transmission pipeline, the mixed air is sent into the electronic cabin after passing through the first filter and the first temperature sensor, part of hot air in the electronic cabin is directly discharged after passing through the fan regulating valve, and the other part of hot air is sent into the electronic cabin again after passing through the third one-way valve and the sixth flow valve to regulate flow.
Further, a first flow valve, a first heat regenerator and a first condenser are sequentially arranged on a pipeline between the first gas pipeline and the first water separator along the gas flow direction, the first air is sent to the first heat regenerator for secondary cooling after the flow of the first air is regulated by the first flow valve, the cooled first air is sent to the first condenser for tertiary cooling, and the cooled first air enters the first water separator;
the pipeline between the first gas pipeline and the second water separator is sequentially provided with a second flow valve, a second heat regenerator and a second condenser along the gas flow direction, the second air is sent to the second heat regenerator for secondary cooling after the flow of the second air is regulated by the second flow valve, the cooled second air is sent to the second condenser for tertiary cooling, and the cooled second air enters the second water separator.
Further, an air stop valve, an air flow valve, an air filter and a heat exchanger are sequentially arranged in the first air transmission pipeline along the air flow direction.
Further, the wing deicing system comprises:
the air inlet end of the wing air supply pipe is connected with the antifreezing valve, the pipe body is arranged in the wing, a plurality of air outlets are uniformly formed in the pipe body of the wing air supply pipe along the axial direction of the pipe body, each air outlet is connected with one wing flow passage, and the plurality of wing flow passages are uniformly arranged in the wing;
each wing flow channel internally comprises a plurality of micro-channels and heat insulation materials filled between the micro-channels.
Furthermore, the vortex tube is internally provided with internal threads of which the thread length is 10mm and the thread pitch is 3 mm.
Further, the electronic cabin comprises a high-power cabin and a low-power cabin, wherein hot air in the high-power cabin flows to the fan damper after passing through the first outlet temperature sensor, and hot air in the low-power cabin flows to the fan damper after flowing through the second outlet temperature sensor;
and after the flow of the mixed hot air is regulated by a third one-way valve and a sixth flow valve, the mixed hot air is mixed with the mixed air from the vortex tube, passes through an air filter and an inlet temperature sensor, one part of the mixed hot air is sent to the high-power cabin through a second static pressure layer and a micro-jet hole, and the other part of the mixed hot air enters the low-power cabin through a first static pressure layer and a nozzle.
Furthermore, a heat pipe is arranged on the high-power electronic equipment in the high-power cabin.
The invention further discloses a cooling method of the aircraft environmental control system based on the anti-icing and electronic equipment cooling by adopting the vortex tube,
when the system is in operation, external air compressed by the compressor of the engine passes through the air stop valve, the air flow valve and the air filter, and enters the heat exchanger for primary cooling after the total flow of the air is regulated and impurities in the air are filtered, and then the air is divided into two paths to flow respectively;
the first path of air is sent to a first heat regenerator for secondary cooling after the flow rate is regulated by a first flow valve, the cooled air is sent to a first condenser for tertiary cooling, the cooled air enters a first water separator, the separated water is sent to a first nozzle for cooling the air in a cold air duct, the dried air enters a first vortex tube after being sent to the first heat regenerator for heating, and the air is divided into hot air and cold air;
the second path of air is sent to a second heat regenerator for secondary cooling after the flow rate of the second path of air is regulated by a second flow valve, the cooled air is sent to a second condenser for tertiary cooling, the cooled air enters a second water separator, the separated water is sent to a second nozzle for cooling the air in a cold air duct, the dried air enters a second vortex tube after being sent to the second heat regenerator for heating, and the air is divided into hot air and cold air;
cold air generated by the second vortex tube is mixed with stamping air collected by the second gas collecting hood through the second ejector and then is sent into the cold air duct, and is heated after heat exchange after being cooled by spraying sprayed by the first nozzle and the second nozzle, and is collected by the first gas collecting hood; the hot gas collected by the first gas collecting hood flows through the second flow valve to regulate the flow, and then is mixed with the high-pressure hot gas of the first vortex tube in the first ejector, and the mixed gas flows through the antifreezing valve and then is sent into the wing deicing system;
the system adopts the first vortex tube, the first ejector, the second vortex tube and the second ejector, so that the system has the heating and refrigerating functions, and can simultaneously prevent ice and regulate the air temperature in the electronic cabin for the wing, thereby achieving the purposes of high efficiency and energy consumption reduction;
the cold air of the first vortex tube and the hot air of the second vortex tube are mixed with return air in the electronic cabin after the flow rates of the cold air and the hot air of the first vortex tube are regulated by a first one-way valve, a fifth flow valve, a first one-way valve and a fourth flow valve respectively, and the mixed air is sent into the electronic cabin after passing through a first filter and a first temperature sensor; after passing through the fan regulating valve, part of hot air in the electronic cabin is directly discharged, and the other part of hot air is mixed with mixed air from the vortex tube to be sent into the electronic cabin after the flow rate of the hot air is regulated through the third one-way valve and the sixth flow valve;
the electronic cabin is divided into a high-power cabin and a low-power cabin, hot air in the high-power cabin and the low-power cabin flows to the fan adjusting valve after passing through the first outlet temperature sensor and the second outlet temperature sensor, part of mixed hot air is directly discharged, the other part of mixed hot air is mixed with mixed air from the vortex tube after passing through the third one-way valve and the sixth flow valve to adjust the flow, the mixed air is sent to the first static pressure layer and the second static pressure layer after being filtered by the mixed air filter and the inlet temperature sensor, and finally the mixed air is sent to the low-power cabin and the high-power cabin through the nozzle and the microjet hole, so that the high-power electronic equipment and the low-power electronic equipment work in a proper temperature range.
The beneficial effects are that:
the system of the invention adopts the first vortex tube, the first ejector, the second vortex tube and the second ejector, so that the system has the heating and refrigerating functions, and can simultaneously prevent ice and regulate the air temperature in the electronic cabin for the wing, thereby achieving the purposes of high efficiency and energy consumption reduction.
The first vortex tube and the second vortex tube are provided with internal thread structures with the thread length of 10mm and the thread pitch of 3mm at the parts of the hot end tube, so that the heating effect is better.
The wing deicing structure comprises a plurality of flow channels, each flow channel comprises a plurality of micro channels for heat exchange, and the heat insulation layer are arranged, so that the deicing effect is better, and the process is more efficient.
Fourth, the electronic cabin is divided into a high-power cabin and a low-power cabin, the electronic equipment in the high-power cabin is provided with the heat pipe for heat dissipation, and air is firstly sent into the static pressure layer and then into the electronic cabin, so that the distribution of the electronic equipment in the electronic cabin is more reasonable, the air flow distribution is more uniform, and the air cooling effect is better.
Drawings
FIG. 1 is a schematic diagram of an aircraft environmental control system of the present invention;
FIG. 2 is a schematic illustration of a wing ice control structure according to the present invention;
FIG. 3 is a cross-sectional view of a microchannel within a flow channel of a wing ice control structure in accordance with the present invention;
FIG. 4 is a schematic cross-sectional view of a vortex tube in accordance with the present invention;
FIG. 5 is a schematic diagram of a system of electronic cabins according to the present invention;
FIG. 6 is a velocity flow diagram within a vortex tube in accordance with the present invention;
reference numerals in the drawings: 1. the engine compressor, 2 air valves, 3 air flow valves, 4 air filter, 5 heat exchanger, 6 first flow valve, 7 first regenerator, 8 first condenser, 9 first water separator, 10 first nozzle, 11 first swirl tube, 12 first gas-collecting hood, 13 second flow valve, 14 first ejector, 15 wing anti-icing valve, 16 wing anti-icing structure, 17 third flow valve, 18 second regenerator, 19 second condenser, 20 second water separator, 21 second nozzle, 22 second swirl tube, 23 second gas-collecting hood, 24 second ejector, 25 first unidirectional valve, 26 fourth flow valve, 27 fifth flow valve, 28 second unidirectional valve, 29 mixed air filter. Inlet temperature sensor, 31, electronics compartment, 32, fan adjustment flap, 33, third check flap, 34, sixth flow flap, 35, cold wind duct, 36, wing air duct, 37, wing outer skin, 38, wing flow duct, 39, wing inner skin, 40, wing insulation, 41, wing microchannel, 42, wing insulation, 43, vortex tube inlet, 44, vortex tube cold end outlet, 45, vortex tube hot end outlet, 46, vortex tube hot end adjustment valve, 47, vortex tube internal threads, 48, heat pipe, 49, high power electronics, 50, low power electronics, 51, low power electronics compartment, 52, first static pressure layer, 53, nozzle, 54, first outlet temperature sensor, 55, second outlet temperature sensor, 56, microjet orifice, 57, high power electronics compartment, 58.
Detailed Description
In order to make the technical problems, technical schemes and beneficial effects to be solved more clear, the following detailed description of the present invention is further provided with reference to the accompanying drawings and the detailed description. The following examples or figures are illustrative of the invention and are not intended to limit the scope of the invention.
Referring to fig. 1, an aircraft environmental control system for preventing ice and cooling electronic equipment using a vortex tube mainly comprises an engine compressor 1, an air valve 2, an air flow valve 3, an air filter 4, a heat exchanger 5, a first flow valve 6, a first regenerator 7, a first condenser 8, a first water separator 9, a first nozzle 10, a first vortex tube 11, a first gas collecting hood 12, a second flow valve 13, a first ejector 14, a wing anti-freezing valve 15, a wing ice preventing and removing structure 16, a third flow valve 17, a second regenerator 18, a second condenser 19, a second water separator 20, a second nozzle 21, a second vortex tube 22, a second gas collecting hood 23, a second ejector 24, a first check valve 25, a fourth flow valve 26, a fifth flow valve 27, a second check valve 28, a mixed air filter 29, an inlet temperature sensor 30, an electronic cabin 31, a fan regulating valve 32, a third check valve 33, a sixth flow valve 34 and a cold air duct 35.
When the system is in operation, external air compressed by the engine compressor 1 passes through the air stop valve 2, the air flow valve 3 and the air filter 4, and enters the heat exchanger 5 for primary cooling after the total flow of the air is regulated and impurities in the air are filtered, and then the air is divided into two paths to flow respectively.
The first path of air is sent to the first heat regenerator 7 for secondary cooling after the flow rate is regulated by the first flow valve 6, is sent to the first condenser 8 for tertiary cooling after cooling, the cooled air enters the first water separator 9, the separated moisture is sent to the first nozzle 10 for cooling the air in the cold air channel, the dried air enters the first vortex tube 11 after being sent to the first heat regenerator 7 for heating, and the air is divided into hot air and cold air.
The second path of air is sent to a second heat regenerator 18 for secondary cooling after the flow rate of the second path of air is regulated by a second flow valve 17, the cooled air is sent to a second condenser 19 for tertiary cooling, the cooled air enters a second water separator 20, the separated moisture is sent to a second nozzle 21 for cooling the air in a cold air duct, the dried air enters a second vortex tube 22 after being sent to the second heat regenerator 18 for heating, and the air is divided into hot air and cold air.
The cold air generated by the second vortex tube 22 is mixed with the ram air collected by the second gas collecting hood 23 through the second ejector 24 and then sent into the cold air duct 35, and the cooled spray sprayed by the first nozzle 10 and the second nozzle 21 is heated by the heat exchanger 5 and then collected by the first gas collecting hood 12. The hot gas collected by the first gas collecting hood 12 flows through the second flow valve 13 to regulate the flow, then is mixed with the high-pressure hot gas of the first vortex tube 11 in the first ejector 14, and the mixed gas flows through the anti-freezing valve 15 and then is sent into the wing ice preventing and removing system.
The system adopts the first vortex tube 11, the first ejector 14, the second vortex tube 22 and the second ejector 24, so that the system has heating and refrigerating functions, and can simultaneously prevent ice and regulate the air temperature in the electronic cabin for the wing, thereby achieving the purposes of high efficiency and energy consumption reduction.
The cold air of the first vortex tube 11 and the hot air of the second vortex tube 22 are respectively mixed with the return air in the electronic cabin after the flow rates are regulated by the first check valve 28, the fifth flow valve, the first check valve 25 and the fourth flow valve 26, and the mixed air is sent into the electronic cabin after passing through the first filter 29 and the first temperature sensor 30. After passing through the fan adjusting valve 32, part of hot air in the electronic cabin is directly discharged, and the other part of hot air is mixed with mixed air from the vortex tube to be sent into the electronic cabin 31 after the flow rate of the hot air is adjusted through the third one-way valve 33 and the sixth flow valve 34.
With reference to fig. 2 and 3, the wing blast pipe 36, the wing outer skin 37, the wing runner 38, the wing inner skin 39, the wing heat insulation layer 40, the wing micro-channel 41 and the wing heat insulation layer 42 jointly form the wing ice preventing and removing structure 16, so that the effects of high efficiency, low energy consumption and ice preventing and removing are achieved. The wing blast pipe 36 feeds hot air into a plurality of wing flow passages 38 provided between the wing outer skin 37 and the wing inner skin 39, the hot air ice-preventing and deicing the wing through a plurality of wing micro-passages 41 included in each flow passage, the wing ice-preventing and deicing heat-insulating layer 42 filled between the gaps stores heat, and the wing heat-insulating layer 40 prevents heat from being dissipated from the wing inner skin.
Referring to fig. 4, after air is fed from the vortex tube inlet 43, a double-spiral structure is formed inside the vortex tube, outer hot air flows out from the vortex tube hot end outlet 45, inner cold air flows out from the vortex tube cold end outlet 44, and the vortex tube hot end regulating valve is used for regulating air flow of the vortex tube hot end outlet 45 and the vortex tube cold end outlet 44. The vortex tube is internally provided with the internal thread 47 of the vortex tube with the thread length of 10mm and the thread pitch of 3mm, so that the vortex tube has better heating effect.
Referring to fig. 5, hot air in the high power cabin 57 and the low power cabin 51 flows to the fan regulating valve 32 after passing through the first outlet temperature sensor 54 and the second outlet temperature sensor 55, part of the mixed hot air is directly discharged, the other part of the mixed hot air is mixed with the mixed air from the vortex tube after passing through the third check valve 33 and the sixth flow valve 34 to regulate the flow rate, the mixed air is filtered by the mixed air filter 29 and the inlet temperature sensor 30, impurities contained in the filtered air and the measured inlet temperature are sent to the first static pressure layer 52 and the second static pressure layer 58, and finally the mixed air is sent to the low power cabin 51 and the high power cabin 57 through the nozzle 53 and the micro-spray hole 56, so that the high power electronic device 49 and the low power electronic device 50 work in a proper temperature range, wherein the heat pipe 48 is arranged on the high power electronic device 49, the heat of the high power electronic device can be discharged quickly, and the cooling effect is better.
The electronic cabin 31 is divided into a high power cabin 57 and a low power cabin 51, and the first outlet temperature sensor 54, the second outlet temperature sensor 55 and the inlet temperature sensor 30 are used to transmit temperature information in the electronic cabin 31, and the fourth flow valve 26, the fifth flow valve 27 and the sixth flow valve 34 are used to control the flow of hot air, cold air and return air to control the temperature in the cabin, so that the accurate environmental control is realized on the premise of reducing the energy consumption, and the first static pressure layer 52 and the second static pressure layer 58 are used for supplying air, so that the air flow distribution in the cabin is more uniform, and the cooling effect is better.
Claims (6)
1. An aircraft environmental control system for preventing ice and cooling electronic equipment by adopting a vortex tube, which is characterized in that:
the external air compressed by the engine compressor is divided into two paths of air after passing through a first air conveying pipeline, wherein the first path of air passes through a first water separator after passing through a first cooling unit, the separated moisture is sent to a first nozzle, the air in a cold air channel is cooled, and the dried air is sent to a first heat regenerator for heating and then is sent to a first vortex tube;
the second path of air passes through a second water separator after passing through a second cooling unit, the separated water is sent to a second nozzle, the air in a cold air duct is cooled, and the dried air is sent to a second heat regenerator for heating and then enters a second vortex tube;
cold air generated by the second vortex tube is mixed with ram air collected by a second gas collecting cover (23) through a second ejector (24) and then is sent into a cold air duct, the heat is collected by a first gas collecting cover (12) after being heated by a heat exchanger (5) after being sprayed by a first nozzle and the spray temperature of the second nozzle is reduced, and hot air collected by the first gas collecting cover (12) is mixed with high-pressure hot air of the first vortex tube in a first ejector (14) after the flow rate of the hot air is regulated by a second flow valve (13) and then is sent into a wing ice preventing and removing system after flowing through an anti-freezing valve (15);
cold air of the first vortex tube and hot air of the second vortex tube are respectively mixed with return air in the electronic cabin after being converged through the air transmission pipeline, the mixed air is sent into the electronic cabin after passing through the first filter and the first temperature sensor, part of hot air in the electronic cabin is directly discharged after passing through the fan regulating valve (32), and the other part of hot air is sent into the electronic cabin again after the flow of the hot air is regulated through the third one-way valve and the sixth flow valve;
an air stop valve (2), an air flow valve (3), an air filter (4) and a heat exchanger (5) are sequentially arranged in the first gas pipeline along the gas flow direction;
the wing deicing system comprises:
the air inlet end of the wing air supply pipe is connected with the antifreezing valve (15), the pipe body is arranged in the wing, a plurality of air outlets are uniformly formed in the pipe body of the wing air supply pipe along the axial direction of the pipe body, each air outlet is connected with one wing flow passage, and the plurality of wing flow passages are uniformly arranged in the wing; each wing flow channel internally comprises a plurality of micro-channels and heat insulation materials filled between the micro-channels.
2. An aircraft environmental control system that employs vortex tube anti-icing and electronics cooling as claimed in claim 1, wherein:
a first flow valve, a first heat regenerator and a first condenser are sequentially arranged on a pipeline between the first gas pipeline and the first water separator along the gas flow direction, the first air is sent to the first heat regenerator for secondary cooling after the flow of the first air is regulated by the first flow valve, the cooled first air is sent to the first condenser for tertiary cooling, and the cooled first air enters the first water separator;
the pipeline between the first gas pipeline and the second water separator is sequentially provided with a second flow valve, a second heat regenerator and a second condenser along the gas flow direction, the second air is sent to the second heat regenerator for secondary cooling after the flow of the second air is regulated by the second flow valve, the cooled second air is sent to the second condenser for tertiary cooling, and the cooled second air enters the second water separator.
3. An aircraft environmental control system that employs vortex tube anti-icing and electronics cooling as claimed in claim 1, wherein: the vortex tube is internally provided with internal threads of the vortex tube, wherein the thread length of the internal threads is 10mm, and the thread pitch of the internal threads is 3 mm.
4. An aircraft environmental control system that employs vortex tube anti-icing and electronics cooling as claimed in claim 1, wherein:
the electronic cabin comprises a high-power cabin and a low-power cabin, wherein hot air in the high-power cabin flows to the fan damper after passing through the first outlet temperature sensor, and hot air in the low-power cabin flows to the fan damper after flowing through the second outlet temperature sensor;
and after the flow of the mixed part of hot air is regulated by a third one-way valve and a sixth flow valve, the other part of hot air is mixed with the mixed air from the vortex tube, and the mixed air passes through a mixed air filter (29) and an inlet temperature sensor (30), one part of hot air is sent to the high-power cabin through the second static pressure layer and the microjet hole, and the other part of hot air enters the low-power cabin through the first static pressure layer and the nozzle.
5. An aircraft environmental control system that employs vortex tube anti-icing and electronics cooling as recited in claim 4, wherein: and the high-power electronic equipment in the high-power cabin is provided with a heat pipe.
6. A cooling method of an aircraft environmental control system based on anti-deicing and electronic equipment cooling adopting a vortex tube according to any one of claims 1-5 is characterized in that,
when the system is in operation, external air compressed by the compressor of the engine passes through the air stop valve, the air flow valve and the air filter, and enters the heat exchanger for primary cooling after the total flow of the air is regulated and impurities in the air are filtered, and then the air is divided into two paths to flow respectively;
the first path of air is sent to a first heat regenerator for secondary cooling after the flow rate is regulated by a first flow valve, the cooled air is sent to a first condenser for tertiary cooling, the cooled air enters a first water separator, the separated water is sent to a first nozzle for cooling the air in a cold air duct, the dried air enters a first vortex tube after being sent to the first heat regenerator for heating, and the air is divided into hot air and cold air;
the second path of air is sent to a second heat regenerator for secondary cooling after the flow rate of the second path of air is regulated by a second flow valve, the cooled air is sent to a second condenser for tertiary cooling, the cooled air enters a second water separator, the separated water is sent to a second nozzle for cooling the air in a cold air duct, the dried air enters a second vortex tube after being sent to the second heat regenerator for heating, and the air is divided into hot air and cold air;
cold air generated by the second vortex tube is mixed with stamping air collected by the second gas collecting hood through the second ejector and then is sent into the cold air duct, and is heated after heat exchange after being cooled by spraying sprayed by the first nozzle and the second nozzle, and is collected by the first gas collecting hood; the hot gas collected by the first gas collecting hood flows through the second flow valve to regulate the flow, and then is mixed with the high-pressure hot gas of the first vortex tube in the first ejector, and the mixed gas flows through the antifreezing valve and then is sent into the wing deicing system;
the system adopts the first vortex tube, the first ejector, the second vortex tube and the second ejector, so that the system has the heating and refrigerating functions, and can simultaneously prevent ice and regulate the air temperature in the electronic cabin for the wing, thereby achieving the purposes of high efficiency and energy consumption reduction;
the cold air of the first vortex tube and the hot air of the second vortex tube are mixed with return air in the electronic cabin after the flow rates of the cold air and the hot air of the first vortex tube are regulated by a first one-way valve, a fifth flow valve, a first one-way valve and a fourth flow valve respectively, and the mixed air is sent into the electronic cabin after passing through a first filter and a first temperature sensor; after passing through the fan regulating valve, part of hot air in the electronic cabin is directly discharged, and the other part of hot air is mixed with mixed air from the vortex tube to be sent into the electronic cabin after the flow rate of the hot air is regulated through the third one-way valve and the sixth flow valve;
the electronic cabin is divided into a high-power cabin and a low-power cabin, hot air in the high-power cabin and the low-power cabin flows to the fan adjusting valve after passing through the first outlet temperature sensor and the second outlet temperature sensor, part of mixed hot air is directly discharged, the other part of mixed hot air is mixed with mixed air from the vortex tube after passing through the third one-way valve and the sixth flow valve to adjust the flow, the mixed air is sent to the first static pressure layer and the second static pressure layer after being filtered by the mixed air filter and the inlet temperature sensor, and finally the mixed air is sent to the low-power cabin and the high-power cabin through the nozzle and the microjet hole, so that the high-power electronic equipment and the low-power electronic equipment work in a proper temperature range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210907003.8A CN115230969B (en) | 2022-07-29 | 2022-07-29 | Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210907003.8A CN115230969B (en) | 2022-07-29 | 2022-07-29 | Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115230969A CN115230969A (en) | 2022-10-25 |
| CN115230969B true CN115230969B (en) | 2024-04-09 |
Family
ID=83677074
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210907003.8A Active CN115230969B (en) | 2022-07-29 | 2022-07-29 | Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115230969B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431650A (en) * | 2011-12-27 | 2012-05-02 | 东南大学 | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device |
| CN105966625A (en) * | 2016-06-01 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Electronic device cooling system |
| CN107336836A (en) * | 2016-05-02 | 2017-11-10 | 波音公司 | Prevent the system and method to be frozen on more parts of aircraft |
| CN108362025A (en) * | 2018-03-27 | 2018-08-03 | 南京工业大学 | A kind of airborne spray cooling system preventing failure using phase-change material cooling spray medium and using micro-channel heat exchanger |
| 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 |
| CN110963057A (en) * | 2018-09-28 | 2020-04-07 | 空中客车运营公司 | Device for reducing or even eliminating the noise of an aircraft power plant deicing system |
| CN111746801A (en) * | 2019-03-28 | 2020-10-09 | 庞巴迪公司 | Aircraft wing ice protection system and method |
| CN112572806A (en) * | 2021-01-27 | 2021-03-30 | 南京航空航天大学 | Loop control and nitrogen control coupling system comprehensively utilizing aircraft cabin pressure and working method |
| CN112918682A (en) * | 2021-02-03 | 2021-06-08 | 南京航空航天大学 | Four-wheel high-pressure water removal environment control system based on different cabin pressures and working method |
| CN114261523A (en) * | 2021-12-03 | 2022-04-01 | 武汉航空仪表有限责任公司 | Novel combined ice preventing and removing system |
-
2022
- 2022-07-29 CN CN202210907003.8A patent/CN115230969B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431650A (en) * | 2011-12-27 | 2012-05-02 | 东南大学 | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device |
| CN107336836A (en) * | 2016-05-02 | 2017-11-10 | 波音公司 | Prevent the system and method to be frozen on more parts of aircraft |
| CN105966625A (en) * | 2016-06-01 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Electronic device cooling system |
| CN108362025A (en) * | 2018-03-27 | 2018-08-03 | 南京工业大学 | A kind of airborne spray cooling system preventing failure using phase-change material cooling spray medium and using micro-channel heat exchanger |
| CN110963057A (en) * | 2018-09-28 | 2020-04-07 | 空中客车运营公司 | Device for reducing or even eliminating the noise of an aircraft power plant deicing 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 |
| CN111746801A (en) * | 2019-03-28 | 2020-10-09 | 庞巴迪公司 | Aircraft wing ice protection system and method |
| CN112572806A (en) * | 2021-01-27 | 2021-03-30 | 南京航空航天大学 | Loop control and nitrogen control coupling system comprehensively utilizing aircraft cabin pressure and working method |
| CN112918682A (en) * | 2021-02-03 | 2021-06-08 | 南京航空航天大学 | Four-wheel high-pressure water removal environment control system based on different cabin pressures and working method |
| CN114261523A (en) * | 2021-12-03 | 2022-04-01 | 武汉航空仪表有限责任公司 | Novel combined ice preventing and removing system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115230969A (en) | 2022-10-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10125683B2 (en) | De-icing and conditioning device for an aircraft | |
| US8397487B2 (en) | Environmental control system supply precooler bypass | |
| CA2551922C (en) | Cooling air supply for the cooling of different systems requiring cooling air in an aircraft | |
| US10100733B2 (en) | Turbine engine with anti-ice valve assembly, bleed air valve, and method of operating | |
| US11203437B2 (en) | Assembly and method for conditioning engine-heated air onboard an aircraft | |
| CN103079956A (en) | Aircraft air conditioning system comprising a separate refrigeration cycle | |
| CA2720836A1 (en) | De-icing system for an airplane | |
| EP1935783B1 (en) | Ice protection system including a plurality of segmented sub-areas and a cyclic diverter valve | |
| CN102381479B (en) | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct | |
| CN108438233B (en) | Helicopter air conditioning system | |
| CN111806700B (en) | Ventilation system suitable for air conditioning component cabin of aircraft and aircraft comprising same | |
| CN109573054A (en) | Combined fluid is anti-icing and Electronic Cooling System | |
| CN112918682B (en) | Four-wheel high-pressure water removal environment control system based on different cabin pressures and working method | |
| CN102390537A (en) | Comprehensive heat energy management system for environmental control system and liquid cooling system | |
| CN114962004A (en) | Self-adaptive flying and launching integrated thermal management system based on third flow and fuel oil heat sink | |
| CN115230969B (en) | Aircraft environmental control system and method adopting vortex tube for preventing ice and cooling electronic equipment | |
| CN108100273B (en) | Aircraft fuel cooling system | |
| CN106005431B (en) | A kind of injecting type lifting airscrew prevents/deicer | |
| EP3296208B1 (en) | Aircraft incorporating a cabin air recovery system | |
| CN106364663B (en) | Aircraft air condition component cabin | |
| CN202770042U (en) | Whole sealing air circulation refrigerating system driven by power turbine | |
| US20200317358A1 (en) | Aircraft nacelle comprising at least one heat exchanger | |
| CN103612761A (en) | Open type air refrigeration cycle device passively absorbing refrigeration capacity | |
| Redondo | Innovative jet pump ice protection system for A400M | |
| CN217233837U (en) | Bidirectional injection anti-surge and flow-stabilizing fan exhaust device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |