CN110920902B - Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology - Google Patents
Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology Download PDFInfo
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- CN110920902B CN110920902B CN201910981721.8A CN201910981721A CN110920902B CN 110920902 B CN110920902 B CN 110920902B CN 201910981721 A CN201910981721 A CN 201910981721A CN 110920902 B CN110920902 B CN 110920902B
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- 238000005516 engineering process Methods 0.000 title claims abstract description 16
- 238000004378 air conditioning Methods 0.000 title claims abstract description 13
- 239000010687 lubricating oil Substances 0.000 claims abstract description 29
- 239000003507 refrigerant Substances 0.000 claims description 53
- 230000007613 environmental effect Effects 0.000 claims description 9
- 238000007599 discharging Methods 0.000 claims description 5
- 238000005728 strengthening Methods 0.000 claims description 5
- 238000005057 refrigeration Methods 0.000 abstract description 23
- 238000010438 heat treatment Methods 0.000 abstract description 18
- 230000000740 bleeding effect Effects 0.000 abstract description 3
- 230000017525 heat dissipation Effects 0.000 abstract description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 239000003570 air Substances 0.000 description 85
- 239000012080 ambient air Substances 0.000 description 8
- 238000001704 evaporation Methods 0.000 description 5
- 230000008020 evaporation Effects 0.000 description 5
- 230000002708 enhancing effect Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
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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
- B64D2013/0603—Environmental Control Systems
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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
- B64D2013/0648—Environmental Control Systems with energy recovery means, e.g. using turbines
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- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Air-Conditioning For Vehicles (AREA)
- Compression-Type Refrigeration Machines With Reversible Cycles (AREA)
Abstract
The invention discloses a multi-cabin double-system air conditioning system of a helicopter based on a compressor middle air supply technology, which can realize the conversion of cabin refrigeration and heating of electronic equipment of the helicopter aiming at the characteristics of high speed, high altitude, high maneuverability, large heat dissipation of the electronic equipment, wide flight working conditions and the like of the helicopter, and comprises a cabin pressurization system without engine air bleeding, so that the influence of an environment control system on a power source is reduced, and the maneuverability of the helicopter is improved; the heat of the lubricating oil and the heat dissipated by the electronic equipment are recycled, so that the real-time comprehensive management of the energy of the whole machine is realized, and the heating efficiency is improved; the air supply high-temperature refrigeration technology in the middle of the compressor is utilized, so that the exhaust temperature of the compressor is reduced, the normal work of a refrigeration system in a high-temperature environment is realized, and the environment control system can effectively operate in an all-weather and wide-working-condition environment.
Description
Technical Field
The invention belongs to the technical field of aviation systems, relates to a helicopter air conditioning system, and particularly relates to a multi-cabin dual-system air conditioning system of a helicopter based on a compressor intermediate air supply technology.
Background
Helicopters are aircraft that rely on a rotary output shaft powered by a turboshaft engine and directly driving rotors through a mechanical transmission system to produce lift and propulsion. The airplane can complete various flight actions which cannot be completed by conventional fixed wing airplanes, such as vertical landing, hovering, in-situ rotation, multi-directional flight and the like. In addition, when the engine is stopped, the engine can realize safe landing by utilizing the autorotation characteristic of the rotor wing, so the engine is very safe to use. In addition, the aircraft integrates the advantages of ground transportation tools and fixed-wing aircrafts, can be used for military purposes such as transportation of soldier equipment, ground attack, antitank, firepower support, search and rescue and the like, can also be applied to a plurality of civil fields such as transportation, patrol, tourism, rescue and the like, is a typical dual-purpose product for military and civil use, and is more and more widely applied in recent years.
Like fixed wing aircraft, helicopters also need to fly in harsh climatic conditions of high temperature, high humidity. In order to ensure the normal physiological requirements of flight crew, improve the comfort of passenger seats and the normal operation of electronic equipment in the cabin, the helicopter needs to be provided with an air conditioning system. Especially, in order to improve the performance of the modern military and civil helicopters, a large amount of high-power and high-integration avionic equipment is adopted, a large amount of heat is emitted when the equipment works, the heat must be timely emitted to ensure the normal work of the electronic equipment, meanwhile, the expectation of personnel on the comfort of a helicopter cabin is higher and higher, and all the requirements of the modern advanced high-performance helicopters on an air conditioning system are higher and higher.
A refrigeration cycle system is installed on a helicopter in the beginning of the 60 th 20 th century abroad, and mainly comprises an evaporation cycle system and an air cycle system. At that time, an air circulation system for engine bleed air is a commonly adopted solution for a fixed-wing aircraft environmental control system, and the weight of the air circulation system is lighter than that of an evaporation circulation system. Therefore, when developing a helicopter environmental control system, one generally considers the use of an air circulation system. But compared with an evaporative refrigeration cycle, the air circulation refrigeration system has large compensation loss and low efficiency. Along with the continuous development of the airborne evaporative cycle refrigeration technology in recent years, the problems of system refrigerant leakage, poor reliability and the like are better solved, and the evaporative cycle refrigeration scheme is more suitable for the airborne refrigeration system of the helicopter by virtue of the advantages of large refrigeration capacity, high efficiency and the like. In addition, most of the existing helicopters use engine bleed air to realize heating, which obviously increases the compensation loss of the system. The existing helicopter is low in flying height, a cabin is not closed, and cabin pressurization is not needed, and the scheme for solving cabin pressurization in a fixed-wing aircraft is mainly an air circulation system, but a large amount of engine bleed air needs to be extracted by the system, so that a large amount of engine power is consumed, and the development of the helicopter towards high speed, high altitude and high maneuverability in the future inevitably needs to develop a pressurization technology of non-engine bleed air.
Disclosure of Invention
The invention aims to solve the technical problem of providing a multi-cabin dual-system air conditioning system of a helicopter based on a compressor intermediate air supply technology aiming at the defects related in the background technology.
The invention is realized by the following steps:
a helicopter multi-cabin double-system air conditioning system based on a compressor middle air supply technology comprises a four-way reversing valve, a compressor, a first air-cooled heat exchanger, a first fan, a plate heat exchanger, a lubricating oil pump, a first control valve, a first restrictor, a second air-cooled heat exchanger, a second fan, a second control valve, a third control valve, a second restrictor, a fourth control valve, a third air-cooled heat exchanger, a third fan, an electric compressor and an exhaust valve;
the four-way reversing valve comprises a first interface, a second interface, a third interface, a fourth interface and a fourth switching valve, wherein the first interface is communicated with the second interface, the third interface is communicated with the fourth interface, or the first interface is communicated with the third interface, and the second interface is communicated with the fourth interface; the compressor comprises a low-pressure air suction inlet, a medium-pressure air suction inlet and an air exhaust port; the plate heat exchanger comprises a refrigerant channel and a lubricating oil channel;
a first interface of the four-way reversing valve is connected with one end of a third air-cooled heat exchanger through a pipeline, a second interface of the four-way reversing valve is connected with a low-pressure air suction inlet of the compressor through a pipeline, a third interface of the four-way reversing valve is connected with an air outlet of the compressor through a pipeline, and a fourth interface of the four-way reversing valve is respectively connected with one end of a third control valve and one end of a first air-cooled heat exchanger through pipelines;
the medium-pressure suction inlet of the compressor is connected with one end of the second control valve through a pipeline;
the other end of the first air-cooled heat exchanger is connected with one end of a refrigerant channel of the plate heat exchanger through a pipeline; the first fan is arranged at the first air-cooled heat exchanger and used for strengthening heat exchange between the external environment air and a refrigerant in the first air-cooled heat exchanger;
the other end of the plate heat exchanger refrigerant channel is respectively connected with one end of the first control valve and one end of the second throttler through pipelines; one end of the plate type heat exchanger lubricating oil channel is sequentially connected to the lubricating oil pump, the gear box of the helicopter engine and the other end of the plate type heat exchanger lubricating oil channel through pipelines;
the other end of the first control valve is respectively connected with one end of the first restrictor and one end of the fourth control valve through pipelines;
the other end of the first throttler is connected with one end of the second air-cooled heat exchanger through a pipeline;
the second air-cooled heat exchanger is arranged in the electronic equipment cabin, and the other end of the second air-cooled heat exchanger is respectively connected with the other end of the second control valve and the other end of the third control valve through pipelines; the second fan is arranged at the second air-cooled heat exchanger and used for strengthening heat exchange between air in the electronic equipment cabin and a refrigerant in the second air-cooled heat exchanger;
the other end of the second throttler is respectively connected with the other end of the fourth control valve and the other end of the third air-cooled heat exchanger through pipelines;
the third air-cooled heat exchanger is arranged in the cabin of the helicopter; the third fan is arranged at the third air-cooled heat exchanger and used for enhancing the heat exchange between the air in the cabin and the refrigerant in the third air-cooled heat exchanger;
the electric air compressor is used for compressing environmental bleed air of the helicopter to a preset first pressure threshold value and then discharging the compressed environmental bleed air to the cabin;
the exhaust valve is connected to the cabin and used for opening when the pressure in the cabin is greater than a preset second pressure value and exhausting air in the cabin to the outside of the machine.
The invention has the following beneficial effects:
1. the system integrates a refrigerating system, a heating system and a pressurizing system, can realize the conversion of the refrigeration of an electronic equipment cabin and the refrigeration and heating of a cabin, and comprises a cabin pressurizing system without engine air bleed, thereby reducing the influence of an environmental control system on a power source and improving the maneuvering performance of the helicopter;
2. the heat of the lubricating oil and the heat dissipation of the electronic equipment are recycled, and the real-time comprehensive management of the energy of the whole machine is realized;
3. the air supply high-temperature refrigeration technology in the middle of the compressor is utilized, so that the exhaust temperature of the compressor is reduced, the normal work of a refrigeration system in a high-temperature environment is realized, and the environment control system can effectively operate in an all-weather and wide-working-condition environment.
Drawings
FIG. 1 is a schematic view of a refrigeration mode of a multi-cabin dual-system air conditioning system of a helicopter based on a compressor intermediate air supply technology;
fig. 2 is a schematic diagram of a heating mode of a multi-cabin dual-system air conditioning system of a helicopter based on a compressor intermediate air supply technology.
In the figure, 1-four-way reversing valve, 2-compressor, 3-first air-cooled heat exchanger, 4-first fan, 5-plate heat exchanger, 6-lubricating oil pump, 7-first control valve, 8-first throttler, 9-second air-cooled heat exchanger, 10-second fan, 11-second control valve, 12-third control valve, 13-second throttler, 14-fourth control valve, 15-third air-cooled heat exchanger, 16-third fan, 17-electric compressor, 18-exhaust valve.
Detailed Description
The present invention will be further described with reference to the following examples. The following description is only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1, the invention discloses a multi-cabin dual-system air conditioning system of a helicopter based on a compressor middle air supply technology, which is characterized by comprising a four-way reversing valve 1, a compressor 2, a first air-cooled heat exchanger 3, a first fan 4, a plate heat exchanger 5, a lubricating oil pump 6, a first control valve 7, a first restrictor 8, a second air-cooled heat exchanger 9, a second fan 10, a second control valve 11, a third control valve 12, a second restrictor 13, a fourth control valve 14, a third air-cooled heat exchanger 15, a third fan 16, an electric compressor 17 and an exhaust valve 18;
the four-way reversing valve 1 comprises first to fourth interfaces, and is used for enabling the first interface to be communicated with the second interface and the third interface to be communicated with the fourth interface, or enabling the first interface to be communicated with the third interface and the second interface to be communicated with the fourth interface, wherein the first interface and the second interface in the figure correspond to the first to fourth interfaces respectively; the compressor 2 comprises a low-pressure suction inlet, a medium-pressure suction inlet and an exhaust port; the plate heat exchanger 5 comprises a refrigerant channel and a lubricating oil channel;
a first interface of the four-way reversing valve 1 is connected with one end of a third air-cooled heat exchanger 15 through a pipeline, a second interface is connected with a low-pressure air suction inlet of the compressor 2 through a pipeline, a third interface is connected with an air outlet of the compressor 2 through a pipeline, and a fourth interface is respectively connected with one end of a third control valve 12 and one end of a first air-cooled heat exchanger 3 through pipelines;
the medium-pressure suction inlet of the compressor 2 is connected with one end of the second control valve 11 through a pipeline;
the other end of the first air-cooled heat exchanger 3 is connected with one end of a refrigerant channel of the plate heat exchanger 5 through a pipeline; the first fan 4 is arranged at the first air-cooled heat exchanger 3 and used for enhancing heat exchange between the external environment air and a refrigerant in the first air-cooled heat exchanger 3;
the other end of the refrigerant channel of the plate heat exchanger 5 is respectively connected with one end of the first control valve 7 and one end of the second throttler 13 through pipelines; one end of the lubricating oil channel of the plate heat exchanger 5 is sequentially connected to the lubricating oil pump 6, the gear box of the helicopter engine and the other end of the lubricating oil channel of the plate heat exchanger 5 through pipelines;
the other end of the first control valve 7 is respectively connected with one end of a first choke 8 and one end of a fourth control valve 14 through pipelines;
the other end of the first throttling device 8 is connected with one end of a second air-cooled heat exchanger 9 through a pipeline;
the second air-cooled heat exchanger 9 is arranged in the electronic equipment cabin, and the other end of the second air-cooled heat exchanger is respectively connected with the other end of the second control valve 11 and the other end of the third control valve 12 through pipelines; the second fan 10 is arranged at the second air-cooled heat exchanger 9 and used for enhancing heat exchange between air in the electronic equipment cabin and a refrigerant in the second air-cooled heat exchanger 9;
the other end of the second choke 13 is respectively connected with the other end of the fourth control valve 14 and the other end of the third air-cooled heat exchanger 15 through pipelines;
the third air-cooled heat exchanger 15 is arranged in the cabin of the helicopter; the third fan 16 is arranged at the third air-cooled heat exchanger 15 and used for enhancing heat exchange between air in the cabin and a refrigerant in the third air-cooled heat exchanger 15;
the electric air compressor 17 is used for compressing environmental bleed air of the helicopter to a preset first pressure threshold value and then discharging the compressed environmental bleed air to a cabin;
the exhaust valve 18 is connected to the cabin and is used for opening when the pressure in the cabin is greater than a preset second pressure value and exhausting the air in the cabin to the outside of the machine.
Fig. 1 is a working flow of the refrigeration mode of the present invention, which is specifically as follows:
1) refrigeration process
In the refrigeration mode, in the four-way reversing valve 1, the first interface is communicated with the second interface, and the third interface is communicated with the fourth interface; the first control valve 7, the second control valve 11, the first throttler 8 and the second throttler 13 are opened, the third control valve 12 and the fourth control valve 14 are closed, the compressor 2, the first fan 4, the second fan 10, the third fan 16 and the electric compressor 17 work, and the lubricating oil pump 6 does not work.
The technology of air supplement in the middle of the compressor is adopted, the evaporation temperature of a cabin (when in a refrigeration mode, the third air-cooled heat exchanger 15 is an evaporator) is set to be lower than the evaporation temperature of an electronic equipment cabin (the second air-cooled heat exchanger 9 is an evaporator), refrigerant of the third air-cooled heat exchanger 15 flows into the four-way reversing valve 1 from the first interface of the four-way reversing valve 1, then flows out from the second interface of the four-way reversing valve 1 to enter the low-pressure air suction port of the compressor 2, is partially compressed and then is converged with the refrigerant of the second air-cooled heat exchanger 9 at the medium-pressure air suction port of the compressor 2, the state of the refrigerant of the second air-cooled heat exchanger 9 is controlled, the superheat degree of the mixed refrigerant can be effectively reduced, the exhaust temperature is still in the range of the operational working condition of the compressor when the ambient temperature is higher, and the normal operation of the system is ensured;
after a refrigerant at an exhaust port of the compressor 2 flows into a third interface of the four-way reversing valve 1, the refrigerant flows out of a fourth interface of the four-way reversing valve 1 to the first air-cooled heat exchanger 3, and heat is transferred to an external air heat sink in the first air-cooled heat exchanger 3 (in a refrigeration mode, the first air-cooled heat exchanger 3 is a condenser);
the refrigerant at the outlet of the first air-cooled heat exchanger 3 is divided into two paths, one path of the refrigerant is throttled in the first throttler 8 and flows into the second air-cooled heat exchanger 9, the heat of the air in the electronic equipment cabin is absorbed in the second air-cooled heat exchanger 9, the air in the electronic equipment cabin is used as a cold source to absorb the heat load of the electronic equipment cabin, and then the air returns to the second air-cooled heat exchanger 9 as power to be recycled by the second fan 10; two paths of air flow are throttled in the second throttle 13 and then flow into the third air-cooled heat exchanger 15, the heat of cabin air is absorbed in the third air-cooled heat exchanger 15, and the cabin air is used as a cold source to absorb the heat load of the cabin and then returns to the third air-cooled heat exchanger 15 for recirculation by using the third fan 16 as power;
the two paths of refrigerants absorb heat and then respectively flow back to the compressor to realize refrigeration cycle.
2) Cabin pressurization process
The cabin pressurization system for non-engine air bleed mainly comprises ambient air bleed, an electric compressor 17, an exhaust valve 18 and a cabin pressure regulator, wherein the ambient air bleed is used for bleeding air from the ambient air through the electric compressor 17 for pressurization, the cabin air return part is converged with circulating air, the circulating air flows through a third air cooling heat exchanger 15 through a third fan 16, and then the cabin pressure regulator is used for discharging all or part of the pressurized air to the outside of the cabin according to the cabin height set by a cabin pressure system.
Fig. 2 is a working flow of a heating mode of the present invention, which is different from a cooling mode in that a flow direction of a refrigerant is different, in the heating mode, the third air-cooled heat exchanger 15 is a condenser, the first air-cooled heat exchanger 3 is an evaporator, and a heat source available to a system includes: the air outside the cabin, the heat dissipation of the electronic equipment and the heat of lubricating oil; the specific flow of the heating mode is as follows:
1) heating process
In a heating mode, the four-way reversing valve 1 is electrified, the working modes are switched, the fourth interface is communicated with the second interface, and the third interface is communicated with the first interface; the heating process can be divided into three modes:
aif the requirement on the heating capacity of the cabin is low, the refrigerant only needs to absorb the heat of the electronic equipment cabin in the second air-cooled heat exchanger 9, and the heat is transferred to the cabin in the third air-cooled heat exchanger 15 through refrigeration circulation;
at this time, the first restrictor 8, the third control valve 12 and the fourth control valve 14 are opened, the first control valve 7, the second control valve 11 and the second restrictor 13 are closed, the compressor 2, the second fan 10, the third fan 16 and the electric compressor 17 work, and the first fan 4 and the lubricating oil pump 6 do not work;
after flowing through the third control valve 12, the refrigerant of the second air-cooled heat exchanger 9 flows into the four-way reversing valve 1 from the fourth interface of the four-way reversing valve 1, flows out from the second interface of the four-way reversing valve 1 to enter the low-pressure air suction port of the compressor 2, is compressed by the compressor 2, flows into the third interface of the four-way reversing valve 1 from the air outlet of the compressor 2, flows out to the third air-cooled heat exchanger 15 from the first interface of the four-way reversing valve 1, transfers heat to cabin air in the third air-cooled heat exchanger 15, flows through the fourth control valve 14, throttles in the first throttler 8, and flows back to the second air-cooled heat exchanger 9, so that the heating cycle is realized;
bif the requirement of the cabin heating capacity is large, the refrigerant absorbs the heat of the ambient air in the first air-cooled heat exchanger 3, absorbs the heat of the electronic equipment cabin in the second air-cooled heat exchanger 9, and transmits the heat to the cabin in the third air-cooled heat exchanger 15 through refrigeration cycle;
at this time, the first restrictor 8, the second restrictor 13, the second control valve 11 and the fourth control valve 14 are opened, the first control valve 7 and the third control valve 12 are closed, the compressor 2, the first fan 4, the second fan 10, the third fan 16 and the electric compressor 17 work, and the lubricating oil pump 6 does not work;
after the refrigerant of the first air-cooled heat exchanger 3 flows into the four-way reversing valve 1 from the fourth interface of the four-way reversing valve 1, the refrigerant flows out of the second interface of the four-way reversing valve 1 and enters the low-pressure air suction port of the compressor 2, part of the refrigerant is compressed and then is merged with the refrigerant of the second air-cooled heat exchanger 9 at the medium-pressure air suction port of the compressor 2, the state of the refrigerant of the second air-cooled heat exchanger 9 is controlled, the superheat degree of the mixed refrigerant can be effectively reduced, the exhaust temperature is still in the range of the working condition of the compressor when the ambient temperature is higher, and the normal work of the system is ensured;
after a refrigerant at an exhaust port of the compressor 2 flows into a third interface of the four-way reversing valve 1, the refrigerant flows out of the first interface of the four-way reversing valve 1 to a third air-cooled heat exchanger 15, heat is transferred to cabin air in the third air-cooled heat exchanger 15, the refrigerant after temperature rise is divided into two paths, one path of the refrigerant is throttled in a first throttle device 8 and then flows into a second air-cooled heat exchanger 9, the heat of the air in an electronic equipment cabin is absorbed in the second air-cooled heat exchanger 9, the air in the electronic equipment cabin is used as a cold source to absorb the heat load of the electronic equipment cabin, and then the air returns to the second air-cooled heat exchanger 9 as power to be recirculated by a second fan 10; two paths of the air flow are throttled in the second throttle 13 and then flow into the first air-cooled heat exchanger 3, the heat of the external environment air is absorbed in the first air-cooled heat exchanger 3, and the external environment air is powered by the first fan 4; realizing heating circulation;
cwhen the ambient temperature is low, the energy efficiency of the heating cycle is low, the lubricating oil pump 6 is started, the lubricating oil thermal cycle is started, the refrigerant absorbs the heat of ambient air in the first air-cooled heat exchanger 3, absorbs the heat of the lubricating oil in the plate heat exchanger 5, absorbs the heat of the electronic equipment cabin in the second air-cooled heat exchanger 9, and the heat is transmitted to the cabin in the third air-cooled heat exchanger 15 through the evaporation cycle system;
at the moment, the first restrictor 8, the second restrictor 13, the second control valve 11 and the fourth control valve 14 are opened, the first control valve 7 and the third control valve 12 are closed, and the compressor 2, the first fan 4, the second fan 10, the third fan 16, the electric compressor 17 and the lubricating oil pump 6 work;
after the refrigerant of the first air-cooled heat exchanger 3 flows into the four-way reversing valve 1 from the fourth interface of the four-way reversing valve 1, the refrigerant flows out of the second interface of the four-way reversing valve 1 and enters the low-pressure air suction port of the compressor 2, part of the refrigerant is compressed and then is converged with the refrigerant of the second air-cooled heat exchanger 9 at the medium-pressure air suction port of the compressor 2, the refrigerant state of the second air-cooled heat exchanger 9 is controlled, the superheat degree of the mixed refrigerant can be effectively reduced, the exhaust temperature is still in the range of the operational working condition of the compressor when the ambient temperature is higher, and the normal operation of the system is ensured;
after a refrigerant at an exhaust port of the compressor 2 flows into a third interface of the four-way reversing valve 1, the refrigerant flows out of the first interface of the four-way reversing valve 1 to a third air-cooled heat exchanger 15, heat is transferred to cabin air in the third air-cooled heat exchanger 15, the refrigerant after temperature rise is divided into two paths, one path of the refrigerant is throttled in a first throttle device 8 and then flows into a second air-cooled heat exchanger 9, the heat of the air in an electronic equipment cabin is absorbed in the second air-cooled heat exchanger 9, the air in the electronic equipment cabin is used as a cold source to absorb the heat load of the electronic equipment cabin, and then the air returns to the second air-cooled heat exchanger 9 as power to be recirculated by a second fan 10; two paths of the lubricating oil flow into the plate heat exchanger 5 after being throttled in the second throttle 13, the lubricating oil flow absorbs heat of the lubricating oil in the plate heat exchanger 5 and then flows into the first air-cooled heat exchanger 3, the heat of external environment air is absorbed in the first air-cooled heat exchanger 3, and the external environment air is powered by the first fan 4; and realizing heating circulation.
2) Cabin pressurization process
The cabin pressurization system for non-engine air bleed mainly comprises ambient air bleed, an electric compressor 17, an exhaust valve 18 and a cabin pressure regulator, wherein the ambient air bleed is used for bleeding air from the ambient air through the electric compressor 17 for pressurization, the cabin air return part is converged with circulating air, the circulating air flows through a third air cooling heat exchanger 15 through a third fan 16, and then the cabin pressure regulator is used for discharging all or part of the pressurized air to the outside of the cabin according to the cabin height set by a cabin pressure system.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (1)
1. The helicopter multi-cabin double-system air conditioning system based on the compressor middle air supply technology is characterized by comprising a four-way reversing valve (1), a compressor (2), a first air-cooled heat exchanger (3), a first fan (4), a plate heat exchanger (5), a lubricating oil pump (6), a first control valve (7), a first restrictor (8), a second air-cooled heat exchanger (9), a second fan (10), a second control valve (11), a third control valve (12), a second restrictor (13), a fourth control valve (14), a third air-cooled heat exchanger (15), a third fan (16), an electric compressor (17) and an exhaust valve (18);
the four-way reversing valve (1) comprises a first interface, a second interface, a third interface, a fourth interface and a fourth switching valve, wherein the first interface is communicated with the second interface, the third interface is communicated with the fourth interface, or the first interface is communicated with the third interface, and the second interface is communicated with the fourth interface; the compressor (2) comprises a low-pressure suction inlet, a medium-pressure suction inlet and an exhaust port; the plate heat exchanger (5) comprises a refrigerant channel and a lubricating oil channel;
a first interface of the four-way reversing valve (1) is connected with one end of a third air-cooled heat exchanger (15) through a pipeline, a second interface of the four-way reversing valve is connected with a low-pressure air suction inlet of the compressor (2) through a pipeline, a third interface of the four-way reversing valve is connected with an air outlet of the compressor (2) through a pipeline, and a fourth interface of the four-way reversing valve is respectively connected with one end of a third control valve (12) and one end of a first air-cooled heat exchanger (3) through pipelines;
the medium-pressure suction inlet of the compressor (2) is connected with one end of the second control valve (11) through a pipeline;
the other end of the first air-cooled heat exchanger (3) is connected with one end of a refrigerant channel of the plate heat exchanger (5) through a pipeline; the first fan (4) is arranged at the first air-cooled heat exchanger (3) and used for strengthening heat exchange between the external environment air and a refrigerant in the first air-cooled heat exchanger (3);
the other end of the refrigerant channel of the plate heat exchanger (5) is respectively connected with one end of the first control valve (7) and one end of the second throttler (13) through pipelines; one end of a lubricating oil channel of the plate heat exchanger (5) is sequentially connected to the lubricating oil pump (6), a gear box of a helicopter engine and the other end of the lubricating oil channel of the plate heat exchanger (5) through pipelines;
the other end of the first control valve (7) is respectively connected with one end of a first choke (8) and one end of a fourth control valve (14) through pipelines;
the other end of the first throttling device (8) is connected with one end of a second air-cooled heat exchanger (9) through a pipeline;
the second air-cooled heat exchanger (9) is arranged in the electronic equipment cabin, and the other end of the second air-cooled heat exchanger is respectively connected with the other end of the second control valve (11) and the other end of the third control valve (12) through pipelines; the second fan (10) is arranged at the second air-cooled heat exchanger (9) and used for strengthening heat exchange between air in the electronic equipment cabin and a refrigerant in the second air-cooled heat exchanger (9);
the other end of the second throttling device (13) is respectively connected with the other end of the fourth control valve (14) and the other end of the third air-cooled heat exchanger (15) through pipelines;
the third air-cooled heat exchanger (15) is arranged in the cabin of the helicopter; the third fan (16) is arranged at the third air-cooled heat exchanger (15) and is used for strengthening the heat exchange between the air in the cabin and the refrigerant in the third air-cooled heat exchanger (15);
the electric air compressor (17) is used for compressing environmental bleed air of the helicopter to a preset first pressure threshold value and then discharging the compressed environmental bleed air to a cabin;
and the exhaust valve (18) is connected to the cabin and is used for opening when the pressure in the cabin is greater than a preset second pressure value and exhausting the air in the cabin to the outside of the machine.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910981721.8A CN110920902B (en) | 2019-10-16 | 2019-10-16 | Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology |
| PCT/CN2020/103171 WO2021073186A1 (en) | 2019-10-16 | 2020-07-21 | Helicopter multi-cabin two-mode air conditioning system employing compressor intermediate air supplementation technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910981721.8A CN110920902B (en) | 2019-10-16 | 2019-10-16 | Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology |
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| Publication Number | Publication Date |
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| CN110920902A CN110920902A (en) | 2020-03-27 |
| CN110920902B true CN110920902B (en) | 2022-05-03 |
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| CN201910981721.8A Expired - Fee Related CN110920902B (en) | 2019-10-16 | 2019-10-16 | Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology |
Country Status (2)
| Country | Link |
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| CN (1) | CN110920902B (en) |
| WO (1) | WO2021073186A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920902B (en) * | 2019-10-16 | 2022-05-03 | 南京航空航天大学 | Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology |
| CN112407294B (en) * | 2020-10-30 | 2022-11-22 | 哈尔滨飞机工业集团有限责任公司 | Lubricating oil heat dissipation cabin heating system and method |
| CN113788148A (en) * | 2021-08-24 | 2021-12-14 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Direct heat exchange type heat pump air conditioning system of lubricating oil waste heat source |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102381479A (en) * | 2011-09-14 | 2012-03-21 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct |
| CN102390538A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet |
| BR102016011964A2 (en) * | 2016-05-25 | 2017-12-12 | Hamilton Sundstrand Corporation | PACKAGE OF ENVIRONMENTAL CONTROL SYSTEM, AND, ENVIRONMENTAL CONTROL SYSTEM |
| EP3418194A1 (en) * | 2017-06-23 | 2018-12-26 | Liebherr-Aerospace Toulouse SAS | System and method for environmental control of an aircraft cabin and aircraft provided with such a control system |
| CN109334997A (en) * | 2018-11-15 | 2019-02-15 | 中国直升机设计研究所 | A kind of helicopter ring control control system |
| CN109367791A (en) * | 2018-10-18 | 2019-02-22 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electric environment control system for multi-electric airplane |
| CN109533343A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of helicopter bleed control system |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4742761A (en) * | 1987-07-20 | 1988-05-10 | The Boeing Company | Method and apparatus for controlling the concentration of carbon dioxide in an aircraft cabin |
| CN101148197A (en) * | 2007-10-26 | 2008-03-26 | 北京航空航天大学 | Cabin circumstance control system used for passenger plane |
| CN103010466B (en) * | 2012-11-27 | 2015-10-07 | 北京航空航天大学 | Two-stage Compression air circulation refrigeration system |
| CN207299601U (en) * | 2017-07-31 | 2018-05-01 | 苏州新同创汽车空调有限公司 | A kind of automobile using Gas-supplying enthalpy-increasing air-conditioning |
| FR3072077B1 (en) * | 2017-10-05 | 2019-09-20 | Liebherr-Aerospace Toulouse | AUTONOMOUS RECOVERY MODULE OF A CABIN OF AN AIRCRAFT AND METHOD THEREOF |
| CN110920902B (en) * | 2019-10-16 | 2022-05-03 | 南京航空航天大学 | Multi-cabin dual-system air conditioning system of helicopter based on compressor intermediate air supply technology |
-
2019
- 2019-10-16 CN CN201910981721.8A patent/CN110920902B/en not_active Expired - Fee Related
-
2020
- 2020-07-21 WO PCT/CN2020/103171 patent/WO2021073186A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102381479A (en) * | 2011-09-14 | 2012-03-21 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct |
| CN102390538A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet |
| BR102016011964A2 (en) * | 2016-05-25 | 2017-12-12 | Hamilton Sundstrand Corporation | PACKAGE OF ENVIRONMENTAL CONTROL SYSTEM, AND, ENVIRONMENTAL CONTROL SYSTEM |
| EP3418194A1 (en) * | 2017-06-23 | 2018-12-26 | Liebherr-Aerospace Toulouse SAS | System and method for environmental control of an aircraft cabin and aircraft provided with such a control system |
| CN109367791A (en) * | 2018-10-18 | 2019-02-22 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electric environment control system for multi-electric airplane |
| CN109334997A (en) * | 2018-11-15 | 2019-02-15 | 中国直升机设计研究所 | A kind of helicopter ring control control system |
| CN109533343A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of helicopter bleed control system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110920902A (en) | 2020-03-27 |
| WO2021073186A1 (en) | 2021-04-22 |
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