CN218751444U - Aircraft ground air conditioning system - Google Patents
Aircraft ground air conditioning system Download PDFInfo
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- CN218751444U CN218751444U CN202223442869.0U CN202223442869U CN218751444U CN 218751444 U CN218751444 U CN 218751444U CN 202223442869 U CN202223442869 U CN 202223442869U CN 218751444 U CN218751444 U CN 218751444U
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Abstract
The utility model discloses an aircraft ground air conditioning system relates to the air conditioner field of adjusting for increase aircraft ground air conditioning system's air-out mode. An aircraft ground air conditioning system comprising: the air conditioner comprises a first air duct, a second air duct, a third air duct, a fourth air duct, a fifth air duct, a first air outlet flow channel and a second air outlet flow channel. The first air duct is configured to introduce air. The second air duct is located downstream of and in fluid communication with the first air duct; the second air duct is configured to regulate a temperature of the air. The third air duct is located downstream of and in fluid communication with the second air duct; the third air duct is configured to regulate the pressure of the air. The fourth air duct is located downstream of and in fluid communication with the third air duct; the fourth air duct is configured to equalize air. The fifth air duct is downstream of and in fluid communication with the fourth air duct. The first air outlet flow channel is located at the downstream of the fifth air duct and is communicated with the fluid. The second air outlet flow channel and the first air outlet flow channel are arranged in parallel and are independent respectively. The scheme can realize multiple air supply modes.
Description
Technical Field
The utility model relates to an air conditioner field of adjusting, concretely relates to aircraft ground air conditioning system.
Background
Aircraft ground air conditioning systems are used to provide cooled or heated air to aircraft landing on the ground. Civil aircrafts comprise various models, and the sizes and passenger capacities of different models of aircrafts are different, and the requirements on air volume of an air conditioner are also different. The existing airplane ground air conditioning system can only be suitable for specific airplane models and cannot be suitable for various airplane models. When the types of the airplanes stopped on the ground are different, the corresponding airplane ground air conditioning system needs to be replaced, so that the construction cost of the airport is greatly increased.
SUMMERY OF THE UTILITY MODEL
The utility model provides an aircraft ground air conditioning system for increase aircraft ground air conditioning system's air-out mode.
An embodiment of the utility model provides an aircraft ground air conditioning system, include:
a first duct configured to introduce air;
a second air duct downstream of the first air duct and in fluid communication with the first air duct; the second air duct is configured to regulate a temperature of the air;
a third air chute downstream of the second air chute and in fluid communication with the second air chute; the third air duct is configured to regulate a pressure of the air;
a fourth air chute downstream of the third air chute and in fluid communication with the third air chute; the fourth air duct is configured to equalize the air;
a fifth air duct downstream of the fourth air duct and in fluid communication with the fourth air duct; and
the first air outlet flow channel is positioned at the downstream of the fifth air channel and is communicated with the fifth air channel in a fluid mode;
the second air outlet flow channel is arranged in parallel with the first air outlet flow channel; the second air outlet flow channel is positioned at the downstream of the fifth air channel and is communicated with the fifth air channel in a fluid mode; the first air outlet flow channel and the second air outlet flow channel are independent and are independent respectively.
In some embodiments, the aircraft ground air conditioning system further comprises:
the first-stage evaporator is arranged inside the second air duct; and/or
The second-stage evaporator is arranged inside the second air duct; the second stage evaporator is located downstream of the first stage evaporator.
In some embodiments, the aircraft ground air conditioning system further comprises:
and the heater is arranged inside the second air duct.
In some embodiments, the aircraft ground air conditioning system further comprises:
a first fan in fluid communication with the third air chute, the first fan configured to introduce air into the third air chute via the first air chute and the second air chute; and
a second fan disposed separately from the first fan; the second fan is also in fluid communication with the third air chute, the second fan configured to introduce air into the third air chute via the first air chute and the second air chute.
In some embodiments, the first fan and the second fan are symmetrically arranged with respect to a central axis of the aircraft ground air conditioning system.
In some embodiments, the first fan and the second fan are independently controlled.
In some embodiments, the aircraft ground air conditioning system further comprises:
the flow equalizing plate is arranged inside the fourth air duct; the flow equalizing plate is provided with a first flow equalizing hole and a second flow equalizing hole; the arrangement density of the first flow equalizing holes is larger than that of the second flow equalizing holes.
In some embodiments, the opening size of the first flow equalizing hole is smaller than the opening size of the second flow equalizing hole.
In some embodiments, the flow equalization plate is divided into a first region, a second region, and a third region; the first area and the second area are provided with the first flow equalizing hole, and the third area is provided with the second flow equalizing hole; the first area faces the air outlet of the first fan, and the second area faces the air outlet of the second fan.
In some embodiments, the opening size of one end of the third air duct, which is communicated with the second air duct, is larger than the opening size of the other end of the third air duct, which is communicated with the fourth air duct.
In some embodiments, the aircraft ground air conditioning system further comprises:
a first flexible joint through which the third air duct is in fluid communication with the fourth air duct; and/or
A second flexible joint through which the third air duct is in fluid communication with the fourth air duct.
In some embodiments, the aircraft ground air conditioning system further comprises:
a first air valve installed inside the fourth air duct, the first air valve being configured to control an opening degree of the fourth air duct; and/or
A second air valve installed inside the fifth air duct, the second air valve being configured to control an opening degree of the fourth air duct.
In some embodiments, the opening size of one end of the fourth air duct in fluid communication with the third air duct is smaller than the opening size of the other end of the fourth air duct in fluid communication with the fifth air duct.
In some embodiments, the aircraft ground air conditioning system further comprises:
the third-stage evaporator is clamped between the fourth air duct and the fifth air duct; the third stage evaporator is positioned downstream of the fourth duct; and
the fourth-stage evaporator is clamped between the third-stage evaporator and the fifth air duct; the fourth stage evaporator is located downstream of the third stage evaporator.
The aircraft ground air conditioning system provided by the technical scheme comprises a first air duct, a second air duct, a third air duct, a fourth air duct, a fifth air duct, a first air outlet flow channel and a second air outlet flow channel. The first air outlet flow channel and the second air outlet flow channel are selected to be in a working state and can be in a working state together. The airplane ground air conditioning system has multiple air supply modes, can meet the requirements of airplanes with different air output, has very strong adaptability and wide air output adjustment range, and can meet the air supply requirements of airplanes with different models.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:
fig. 1 is a schematic perspective view of an aircraft ground air conditioning system according to an embodiment of the present invention.
Fig. 2 is a schematic view of a third air duct three-dimensional structure of an aircraft ground air conditioning system provided by an embodiment of the present invention.
Fig. 3 is a schematic view of a fourth air duct spatial structure of an aircraft ground air conditioning system according to an embodiment of the present invention.
Fig. 4 is a schematic view of a fourth air duct of the aircraft ground air conditioning system according to an embodiment of the present invention.
Fig. 5 is a schematic view of a three-dimensional structure of a flow equalizing plate of an aircraft ground air conditioning system according to an embodiment of the present invention.
Fig. 6 is a schematic flow chart of a control method of an aircraft ground air conditioning system according to an embodiment of the present invention.
Reference numerals:
1. a first air duct; 2. a second air duct; 3. a third air duct; 4. a fourth air duct; 5. a fifth air duct; 6. a first air outlet flow channel; 7. a second air outlet flow channel; 8. a first stage evaporator; 9. a second stage evaporator; 10. a heater; 11. a first fan; 12. a second fan; 13. a flow equalizing plate; 14. a first flexible joint; 15. a second flexible joint; 16. a first air valve; 17. a second air valve; 18. a third stage evaporator; 19. a fourth stage evaporator;
101. a steam-water separator; 102. an air filter;
131. a first flow equalizing hole; 132. a second flow equalizing hole; 133. a first region; 134. a second region; 135. a third region;
301. an air outlet; 302. a side plate; 303. an access panel; 304. a reinforcing beam; 305. a flange plate; 306. a first lifting lug; 307. an access hole;
401. a first seal plate; 402. a second seal plate; 403. an end plate; 404. an air inlet; 405. reinforcing ribs; 406. a second flange plate; 407. a second lifting lug; 41. a diffusion region; 42. a flow equalizing zone; 43. a rectifying section.
Detailed Description
The technical solution provided by the present invention will be explained in more detail with reference to fig. 1 to 6.
The embodiment of the utility model provides an aircraft ground air conditioning system for the civil aircraft of various models such as A319, A320, B737-300, B777-500, B767-700, A330-200, A330-300, B787, A380 provide the air after adjusting the temperature, the pressure regulating, the peace and quiet.
The aircraft ground air conditioning system comprises a first air duct 1, a second air duct 2, a third air duct 3, a fourth air duct 4, a fifth air duct 5, a first air outlet flow channel 6 and a second air outlet flow channel 7. The first air path 1 is configured to introduce air. The second air duct 2 is located downstream of the first air duct 1 and is in fluid communication with the first air duct 1; the second air duct 2 is configured to regulate the temperature of air. The third air duct 3 is located downstream of the second air duct 2 and is in fluid communication with the second air duct 2; the third air duct 3 is configured to regulate the pressure of air. The fourth air duct 4 is located downstream of the third air duct 3 and is in fluid communication with the third air duct 3; the fourth air duct 4 is configured to equalize air flow. The fifth air duct 5 is located downstream of the fourth air duct 4 and is in fluid communication with the fourth air duct 4. The first air outlet channel 6 is located downstream of the fifth air duct 5 and is in fluid communication with the fifth air duct 5. The second air outlet flow channel 7 and the first air outlet flow channel 6 are arranged in parallel; the second air outlet flow channel 7 is positioned at the downstream of the fifth air duct 5 and is communicated with the fifth air duct 5 by fluid; the first air outlet flow channel 6 and the second air outlet flow channel 7 are independent and independent from each other.
The first air duct 1, the second air duct 2, the third air duct 3, the fourth air duct 4 and the fifth air duct 5 perform temperature adjustment and pressure adjustment on introduced air.
In order to filter impurities in the air entering the first air duct 1, a steam-water separator 101 and an air filter 102 are installed upstream of the first air duct 1. The steam-water separator 101 is used for separating rainwater from air; the air filter 102 is used to filter dust and impurities in the air. Air enters the first air duct 1 after passing through the steam-water separator 101 and the air filter 102. The first air duct 1 is of a cuboid structure.
In some embodiments, the aircraft ground air conditioning system further comprises a first stage evaporator 8 and a second stage evaporator 9. The first stage evaporator 8 is installed inside the second air duct 2. The second-stage evaporator 9 is arranged inside the second air duct 2; the second stage evaporator 9 is located downstream of the first stage evaporator 8.
The first-stage evaporator 8 and the second-stage evaporator 9 are used for dehumidification and cooling. The two-stage evaporator of the first-stage evaporator 8 and the second-stage evaporator 9 has better dehumidification and cooling effects.
In some embodiments, the aircraft ground air conditioning system further comprises a heater 10. The heater 10 is installed inside the second duct 2. The heater 10 is embodied as an electric heater 10 for heating the air flow at low ambient temperatures.
In some embodiments, the aircraft ground air conditioning system further comprises a first fan 11 and a second fan 12. The first fan 11 is in fluid communication with the third air duct 3, and the first fan 11 is configured to introduce air into the third air duct 3 via the first air duct 1 and the second air duct 2. The second fan 12 is arranged separately from the first fan 11; the second fan 12 is also in fluid communication with the third air duct 3, the second fan 12 being configured to introduce air into the third air duct 3 via the first air duct 1 and the second air duct 2. At least one of the first fan 11 and the second fan 12 is a high-voltage variable-frequency centrifugal fan which is a power source for driving airflow, and the high-voltage variable-frequency centrifugal fan is a fan with an anti-reverse function.
In some embodiments, the first fan 11 and the second fan 12 are independently controlled. The first fan 11 and the second fan 12 operate independently of each other. When only the first fan 11 or only the second fan 12 is operated, this state is referred to as a single fan operation state. The single fan working state can prevent air supply short circuit and avoid energy loss. When the first fan 11 and the second fan 12 work simultaneously, the two fans are called as a double-fan system, the first fan 11 and the second fan 12 can work alternately and are mutually standby, and the reliability of the system is greatly improved.
In some embodiments, the first fan 11 and the second fan 12 are arranged symmetrically with respect to a central axis of the aircraft ground air conditioning system. The main portions of the first fan 11 and the second fan 12 are located outside the third air duct 3. This arrangement allows the first fan 11 and the second fan 12 to be configured to match the third air duct 3, and allows the components to be more reasonably arranged.
Referring to fig. 1, in some embodiments, the opening size of one end of the third air duct 3 communicating with the second air duct 2 is larger than the opening size of the other end of the third air duct 3 communicating with the fourth air duct 4. The third air duct 3 is substantially T-shaped. Specifically, the third air duct 3 includes two sections, which are integrated, and the third air duct 3 is formed by assembling a plurality of plates into a desired shape. The third air duct 3 has a substantially trapezoidal first section in plan view and a rectangular second section in plan view. An access cover is arranged on the inclined surface of the first section. The access cover is closable and openable.
The first fan 11 and the second fan 12 are both installed on both sides of the second section of the third air duct 3. Since the third air duct 3 is formed in a special shape, the two sides of the second section of the third air duct 3 have enough space for installing the first fan 11 and the second fan 12.
The third air duct 3 has the functions of sealing, transferring, converging and diverging. The third air duct 3 includes a plurality of side plates 302, a plurality of access plates 303, a plurality of reinforcing beams 304, a first flange plate 305, and a first lifting lug 306. The side plates 302 and the access plate 303 surround the shell of the third air duct 3. The first flange plate 305 is used for increasing strength and rigidity, and is convenient for mounting and dismounting the access cover; the reinforcing beam 304 is used for increasing the strength and rigidity of each surface of the air duct; the first lifting lug 306 is used for carrying and lifting the third air duct 3. And 2 access holes 307 are formed in the third air duct 3, so that the electric heater 10 can be maintained conveniently.
The air inlet of the third air duct 3 is in fluid connection with the second air duct 2, the air outlet of the third air duct 3 is connected with the first fan 11 and the second fan 12, the air inlet is rectangular, the air outlet is circular, the number of the air outlets is 2, and the air flow is changed into split flow from confluence. The air inlet bottom is lower than the air outlet bottom, and the difference in height is H, and the purpose is in time to discharge the comdenstion water, avoids bringing into first fan 11 and second fan 12.
Referring to fig. 3-5, in some embodiments, the opening size of the end of the fourth air chute 4 in fluid communication with the third air chute 3 is smaller than the opening size of the other end of the fourth air chute 4 in fluid communication with the fifth air chute 5.
The fourth air duct 4 is substantially a trapezoidal, bell-mouthed structure. Specifically, the fourth air duct 4 includes a plurality of first cover plates 401, and the plurality of first cover plates 401 enclose a closed rectangular shape. The fourth air duct 4 further includes a plurality of second cover plates 402, and the plurality of second cover plates 402 are pieced together to form a bell-mouth shape. An end plate 403 is provided on the second cover plate 402 at a section remote from the first cover plate 401. The end plate 403 is provided with two air intakes 404, wherein one intake 404 is in fluid communication with the first flexible coupling 14 and the other intake 404 is in fluid communication with the second flexible coupling 15.
In order to increase the structural strength of the fourth air duct 4, the fourth air duct 4 further includes reinforcing ribs 405. The stiffeners 405 are attached to the first cover plate 401 and/or the second cover plate 402. The reinforcing ribs 405 are welded and fixed to the first cover plate 401 and the second cover plate 402.
In some embodiments, the aircraft ground air conditioning system further comprises a flow equalizing plate 13, the flow equalizing plate 13 being mounted inside the fourth air duct 4; the flow equalizing plate 13 is provided with a first equalizing hole 131 and a second equalizing hole 132; the arrangement density of the first flow equalizing holes 131 is greater than that of the second flow equalizing holes 132. The first uniforming hole 131 may more uniformly equalize the flow.
In some embodiments, the opening size of first flow equalizing hole 131 is smaller than the opening size of second flow equalizing hole 132.
In some embodiments, the flow equalization plate 13 is divided into a first area 133, a second area 134, and a third area 135; the first area 133 and the second area 134 are provided with a first flow equalizing hole 131, and the third area 135 is provided with a second flow equalizing hole 132; the first area 133 is opposite to the outlet of the first fan 11, and the second area 134 is opposite to the outlet of the second fan 12.
As shown in fig. 4, the flow equalizing plate 13 is a porous plate with four folded edges, and is divided into 3 zones: a first region 133, a second region 134, and a third region 135. The first area 133 is opposite to the projected area of the first fan 11 and the second area 134 is opposite to the projected area of the second fan 12. The third region 135 is a non-fan exit projection region. The fan outlet projection areas (i.e. the first area 133 and the second area 134) are determined according to the range of the orthographic projection of the spray angle of the fan outlet on the flow equalizing plate 13. The first area 133 and the second area 134 are symmetrically distributed on the left side and the right side of the center line, and the porosity and the pore size of the first flow equalizing hole 131 in the first area 133 and the second area 134 are the same, but are different from the second flow equalizing hole 132 in the non-fan outlet projection area. The first flow equalizing holes 131 of the first and second regions 133 and 134 have a small pore size and a low porosity. The second flow equalizing holes 132 of the third region 135 have a large pore size and a large porosity. The flow equalizing plate 13 with the structure can effectively adjust the flow, realize flow equalization, fully exert the heat exchange capacity of the heat exchanger, improve the heat exchange efficiency and realize energy conservation. Under the retardation action of the flow equalizing plate 13, the wind speed is reduced, the dynamic pressure is reduced, and the static pressure is increased.
The number of the air inlets of the fourth air duct 4 is 2, and the number of the air outlets is 1. The distance between the air inlet of the fourth air duct 4 and the air outlet of the fourth air duct 4 is set to be L, and the size of L depends on the airflow jet angle alpha of the high-pressure centrifugal fan and the full pressure of the fan. L is too large, the overall dimension of the unit is increased, and the head-on wind speed of the evaporator is too low; too small L, too large head-on wind speed and uneven distribution. In short, too large and too small L are not favorable for the heat exchange capacity of the evaporator. For the air supply system of the airplane ground air conditioner, L = 900-1500 mm, specifically 900mm, 1000mm, 1100mm, 1200mm, 1300mm, 1400mm, 1500mm.
The fourth air duct 4 plays roles of sealing, speed reduction, pressure reduction, static pressure increase, flow distribution, flow equalization, rectification and transmission. The position relation of each component is that the end plate is at the upstream, each closing plate is at the downstream, they surround and form the wind channel shell, the upstream part is in the form of divergent funnel, the rear part is in the form of brick. And U-shaped reinforcing ribs are welded outside the shell and used for improving the strength and rigidity of the third air duct 3, increasing the pressure-bearing capacity and avoiding generating airflow pulsation noise.
The flow equalizing plate 13 is positioned inside the shell and divides the fourth air duct 4 into two parts: the front part is a diffusion area 41 and a flow equalizing area 42, and the rear part is a rectifying area 43. The air flows from the first flexible joint 14 and the second flexible joint 15 in the diffusion area 41 are firstly fused and converged and then diffused along the way, so that the effects of reducing speed, reducing pressure and increasing static pressure are generated; the flow equalizing area 42 has flow equalizing effect, and the distribution of air flow speed is regulated through the different distribution of porosity and pore diameter. In the rectifying area 43, after the airflow passes through the flow equalizing plate 13, a plurality of fine vortices exist, and because of no turbulent flow effects such as sudden change and gradual change of the cross section, the vortices are gradually driven by the main airflow in the center of the flow equalizing hole to move forward to form laminar flow, the windward side of the third-stage evaporator 18 described later reaches a flow equalizing state, and the flow velocity at each position is in the range of 1.8 m/s-2.0 m/s, and the distribution is relatively uniform.
The end plate of the fourth air duct 4 is provided with 2 rectangular holes, the number of the rectangular holes is equal to the number of the first fans 11 and the second fans 12, and the size of the rectangular holes is matched with that of the flexible joints. Threaded through holes are designed around the rectangular holes, and nuts are welded at the through holes and are used for being connected with the first flexible joint 14 and the second flexible joint 15. The rectangular holes 2 on the end plate realize that the airflow changes from split flow to confluence flow. A second flange plate 406 is welded into the end plate 403 for added strength and rigidity. Reinforcing ribs 405 are welded inside and outside the fourth air duct 4 to increase strength and rigidity and reduce airflow pulsation noise; and welding a second lifting lug 407 for mounting and hoisting. The fourth air duct 4 is used for reducing speed, reducing pressure, increasing static pressure, equalizing flow, rectifying and transferring airflow.
Referring to fig. 1, in some embodiments, the aircraft ground air conditioning system further comprises a third stage evaporator 18 and a fourth stage evaporator 19. The third-stage evaporator 18 is clamped between the fourth air duct 4 and the fifth air duct 5; the third stage evaporator 18 is located downstream of the fourth duct 4. The fourth stage evaporator 19 is clamped between the third stage evaporator 18 and the fifth air duct 5; the fourth stage evaporator 19 is located downstream of the third stage evaporator 18.
Referring to fig. 1, the aircraft ground air conditioning system further comprises a third stage evaporator 18 and a fourth stage evaporator 19. The third-stage evaporator 18 is clamped between the fourth air duct 4 and the fifth air duct 5; the third stage evaporator 18 is located downstream of the fourth duct 4. The fourth stage evaporator 19 is clamped between the third stage evaporator 18 and the fifth air duct 5; the fourth stage evaporator 19 is located downstream of the third stage evaporator 18.
The third-stage evaporator 18 and the fourth-stage evaporator 19 are integrated, so that the capacity of each evaporator can be fully exerted no matter whether the single fan or the double fans operate, and the energy saving performance is improved. The third stage evaporator 18 and the fourth stage evaporator 19 are used for further dehumidification and cooling.
In some embodiments, the aircraft ground air conditioning system further comprises a first air valve 16. The first air valve 16 is installed inside the fourth air duct 4, and the first air valve 16 is configured to control the opening degree of the fourth air duct 4. The first air valve 16 is of a conventional structure and is used for controlling the opening and closing of the fourth air duct 4 and the size of the flow area.
Referring to fig. 1, the aircraft ground air conditioning system further comprises a second air valve 17. A second air valve 17 is installed inside the fifth air duct 5, and the second air valve 17 is configured to control the opening degree of the fourth air duct 4. The second air valve 17 is of an existing structure and is used for controlling the on/off of the fifth air duct 5 and the size of the flow area.
The first air valve 16 and the second air valve 17 are controlled independently, and the valve position change of one valve does not affect the valve position of the other valve.
The flow of the airflow in the aircraft ground air-conditioning system is as follows: air enters the system from the steam-water separator, is subjected to steam-water air and rainwater separation, enters the second air channel 2 after being filtered by the filter screen, is subjected to dehumidification and cooling through the first-stage evaporator 8 and the second-stage evaporator 9 in sequence, then enters the third air channel 3 through the second air channel 2 and the electric heater 10, is sucked by the first fan 11 and the second fan 12 to become high-pressure low-temperature gas, 2 air flows enter the fourth air channel 4 after passing through respective flexible joints, and after confluence, diffusion, speed reduction, pressure increase, flow equalization and rectification occur, and then sequentially passes through the third-stage evaporator 18 and the fourth-stage evaporator 19 in a quasi laminar flow state, is further subjected to dehumidification and cooling, then enters the fifth air channel 5, and is sent out through the fifth air channel 5 by 2 groups of air pipes. And air valves are arranged on the 2 groups of air pipes, and the air supply passage and the air quantity are controlled by opening or closing the air valves.
The air current walks the series connection passageway before first fan 11 and second fan 12, and later parallelly connected earlier, establish ties again, then parallelly connected again, and structural design has been simplified greatly to this kind of structure, lets each evaporimeter integrate, ensures no matter single double fan operation, and the evaporimeter ability can both obtain full play, improves energy-conservation nature.
Referring to fig. 6, an embodiment of the present invention provides a method for controlling an aircraft ground air conditioning system, which is implemented by using the aircraft ground air conditioning system introduced in any of the above embodiments. The control method of the airplane ground air conditioning system comprises the following steps:
firstly, whether the required air volume is larger than a set value is judged. The set value can be the standard air volume determined by the civil aircraft according to the model.
Secondly, if the required air volume is larger than the set value, the first air outlet flow channel 6 and the second air outlet flow channel 7 of the airplane ground air conditioning system are both communicated.
According to the technical scheme, the model of the civil aircraft is input, the standard air volume is selected, the standard air volume and the characteristic air volume are compared, and the first fan 11 and the second fan 12 are selected to operate; the running frequency of the fan is controlled according to the outdoor environment temperature, the atmospheric pressure, the temperature in the cabin and the humidity, and reasonable and proper air supply is realized.
In some embodiments, the aircraft ground air conditioning system control method further comprises the steps of: and if the required air volume is less than or equal to the set value, the first air outlet channel 6 and/or the second air outlet channel 7 of the airplane ground air conditioning system are/is communicated.
In some embodiments, the aircraft ground air conditioning system control method further comprises the steps of: if the required air volume is larger than the set value, the first fan 11 and the second fan 12 of the aircraft ground air conditioning system work.
In some embodiments, the aircraft ground air conditioning system control method further comprises the steps of: and if the required air quantity is less than or equal to the set value, the first fan 11 and the second fan 12 of the airplane ground air conditioning system are selected to work.
Inputting the type of the airplane currently landing into an electric control box of the ground air conditioner of the airplane, automatically selecting standard air quantity by an electric control system, and enabling the standard air quantity and the characteristic air quantity to be 8000m 3 And h, comparing, automatically selecting one single fan or double fans of the first fan 11 and the second fan 12 to operate, detecting parameters such as outdoor environment temperature, atmospheric pressure, temperature in the engine room, relative humidity and the like by the air conditioner control system, controlling the frequency of the fans according to the detected values, controlling the output air quantity, and realizing the delivery of high static pressure fresh air with certain flow and comfortable temperature to the engine room.
The air supply system is designed according to the largest airplane ground air conditioner, namely an F-type airplane ground air conditioner air supply system. Through the function selection of the single fan and the double fans and the frequency conversion control of the high-pressure centrifugal fan, one set of airplane ground air-conditioning air supply system can meet the requirements of all main civil aviation models, and the main models of the current domestic and foreign civil aviation airports comprise A319, A320, B737-300, B777-500, B767-700, A330-200, A330-300, B787, A380 and the like. Therefore, the requirement of shutdown refrigeration (or heating) of the whole civil aviation airport can be met by purchasing a single-model airplane ground air conditioner, the design and the type selection of the air conditioning equipment and the equipment management are greatly simplified, and the trouble of carrying the air conditioning equipment between different airplane positions is avoided.
Simplify aircraft ground air conditioning equipment lectotype and equipment management, improve equipment utilization ratio: in order to deal with various civil aviation models, different machine position types need to be prepared, namely a C, D, E, F type airplane ground air conditioner and a corresponding air supply system are needed. Adopt the technical scheme of the utility model, can set up the requirement that one set of aircraft ground air conditioning system satisfies all models.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: it is to be understood that modifications may be made to the above-described arrangements in the embodiments or equivalents may be substituted for some of the features of the embodiments, but such modifications or substitutions do not depart from the spirit and scope of the present invention.
Claims (14)
1. An aircraft ground air conditioning system, comprising:
a first air duct (1) configured to introduce air;
a second air duct (2) located downstream of the first air duct (1) and in fluid communication with the first air duct (1); the second air duct (2) is configured to regulate the temperature of the air;
a third air duct (3) located downstream of the second air duct (2) and in fluid communication with the second air duct (2); the third air duct (3) is configured to regulate the pressure of the air;
a fourth air duct (4) located downstream of the third air duct (3) and in fluid communication with the third air duct (3); the fourth air duct (4) is configured to equalize the air flow;
a fifth air duct (5) located downstream of the fourth air duct (4) and in fluid communication with the fourth air duct (4); and
the first air outlet flow channel (6) is positioned at the downstream of the fifth air duct (5) and is communicated with the fifth air duct (5) in a fluid mode;
the second air outlet flow channel (7) is arranged in parallel with the first air outlet flow channel (6); the second air outlet flow channel (7) is positioned at the downstream of the fifth air duct (5) and is communicated with the fifth air duct (5) through fluid; the first air outlet flow channel (6) and the second air outlet flow channel (7) are independent and are independent respectively.
2. An aircraft ground air conditioning system as defined in claim 1, further comprising:
the first-stage evaporator (8) is arranged inside the second air duct (2); and/or
The second-stage evaporator (9) is arranged inside the second air duct (2); the second stage evaporator (9) is located downstream of the first stage evaporator (8).
3. An aircraft ground air conditioning system as defined in claim 1, further comprising:
and the heater (10) is installed inside the second air duct (2).
4. An aircraft ground air conditioning system as defined in claim 1, further comprising:
a first fan (11) in fluid communication with the third air duct (3), the first fan (11) being configured to introduce air into the third air duct (3) via the first air duct (1) and the second air duct (2); and
a second fan (12) arranged separately from the first fan (11); the second fan (12) is also in fluid communication with the third air duct (3), the second fan (12) being configured to introduce air into the third air duct (3) via the first air duct (1) and the second air duct (2).
5. Aircraft ground air-conditioning system according to claim 4, characterised in that the first fan (11) and the second fan (12) are arranged symmetrically with respect to a central axis of the aircraft ground air-conditioning system.
6. Aircraft ground air conditioning system according to claim 4, characterised in that the first fan (11) and the second fan (12) are controlled independently.
7. An aircraft ground air conditioning system according to claim 4, further comprising:
the flow equalizing plate (13) is arranged inside the fourth air duct (4); the flow equalizing plate (13) is provided with a first flow equalizing hole (131) and a second flow equalizing hole (132); the arrangement density of the first flow equalizing holes (131) is greater than that of the second flow equalizing holes (132).
8. Aircraft ground air conditioning system according to claim 7, characterised in that the opening size of the first flow equalizing aperture (131) is smaller than the opening size of the second flow equalizing aperture (132).
9. Aircraft ground air conditioning system according to claim 7, characterized in that the flow equalizing plate (13) is divided into a first zone (133), a second zone (134) and a third zone (135); the first area (133) and the second area (134) are provided with the first flow equalizing hole (131), and the third area (135) is provided with the second flow equalizing hole (132); the first area (133) is opposite to the air outlet of the first fan (11), and the second area (134) is opposite to the air outlet of the second fan (12).
10. Aircraft floor air-conditioning system according to claim 1, characterized in that the opening of the third air duct (3) at the end communicating with the second air duct (2) is larger than the opening of the third air duct (3) at the other end communicating with the fourth air duct (4).
11. An aircraft ground air conditioning system as defined in claim 1, further comprising:
a first flexible joint (14), said third air duct (3) being in fluid communication with said fourth air duct (4) through said first flexible joint (14); and/or
A second flexible joint (15), the third air duct (3) being in fluid communication with the fourth air duct (4) through the second flexible joint (15).
12. An aircraft ground air conditioning system according to claim 1, further comprising:
a first air valve (16) installed inside the fourth air duct (4), the first air valve (16) being configured to control an opening degree of the fourth air duct (4); and/or
A second air valve (17) installed inside the fifth air duct (5), the second air valve (17) being configured to control an opening degree of the fourth air duct (4).
13. Aircraft floor air-conditioning system according to claim 1, characterized in that the opening size of the end of the fourth air duct (4) in fluid communication with the third air duct (3) is smaller than the opening size of the other end of the fourth air duct (4) in fluid communication with the fifth air duct (5).
14. An aircraft ground air conditioning system as defined in claim 1, further comprising:
the third-stage evaporator (18) is clamped between the fourth air duct (4) and the fifth air duct (5); the third stage evaporator (18) is located downstream of the fourth duct (4); and
a fourth stage evaporator (19) which is clamped between the third stage evaporator (18) and the fifth air duct (5); the fourth stage evaporator (19) is located downstream of the third stage evaporator (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223442869.0U CN218751444U (en) | 2022-12-22 | 2022-12-22 | Aircraft ground air conditioning system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223442869.0U CN218751444U (en) | 2022-12-22 | 2022-12-22 | Aircraft ground air conditioning system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218751444U true CN218751444U (en) | 2023-03-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223442869.0U Active CN218751444U (en) | 2022-12-22 | 2022-12-22 | Aircraft ground air conditioning system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218751444U (en) |
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2022
- 2022-12-22 CN CN202223442869.0U patent/CN218751444U/en active Active
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