CN110471475B - Temperature regulation system and application method implemented by same - Google Patents
Temperature regulation system and application method implemented by same Download PDFInfo
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- CN110471475B CN110471475B CN201910747044.3A CN201910747044A CN110471475B CN 110471475 B CN110471475 B CN 110471475B CN 201910747044 A CN201910747044 A CN 201910747044A CN 110471475 B CN110471475 B CN 110471475B
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- 238000000034 method Methods 0.000 title claims abstract description 22
- 230000033228 biological regulation Effects 0.000 title claims abstract description 16
- 230000001105 regulatory effect Effects 0.000 claims abstract description 63
- 238000009423 ventilation Methods 0.000 claims abstract description 22
- 238000004378 air conditioning Methods 0.000 claims abstract description 17
- 238000005259 measurement Methods 0.000 claims description 9
- 230000000740 bleeding effect Effects 0.000 claims description 2
- 230000003750 conditioning effect Effects 0.000 claims 5
- 230000001143 conditioned effect Effects 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 description 5
- 238000004132 cross linking Methods 0.000 description 4
- 238000005057 refrigeration Methods 0.000 description 4
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010792 warming Methods 0.000 description 2
- 239000000470 constituent Substances 0.000 description 1
- 230000009123 feedback regulation Effects 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D27/00—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00
- G05D27/02—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00 characterised by the use of electric means
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- Physics & Mathematics (AREA)
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Air-Conditioning For Vehicles (AREA)
- Air Conditioning Control Device (AREA)
Abstract
The invention provides a temperature regulating system and an application method realized by the same. The temperature regulation system includes: the air flow measuring and feeding device, the flow regulating valve and the air conditioning assembly are sequentially arranged on the left air-entraining main pipeline and the right air-entraining main pipeline along the flowing direction of air respectively, a left balancing air branch and a right balancing air branch are formed between the flow measuring and feeding device and the flow regulating valve respectively, different branch valves are arranged on the left balancing air branch and the right balancing air branch, and a balancing air main pipeline is formed after the left balancing air branch and the right balancing air branch are crosslinked and exhausts the air to the ventilation system. According to the invention, the branch valves arranged on the balancing air branches of the temperature adjusting system are different, so that the branch valves to be opened can be selected according to different use scenes, and the air adjusting system can use different scene environments.
Description
Technical Field
The invention relates to the field of passenger aircraft, in particular to a temperature regulating system and an application method realized by the same.
Background
In passenger aircraft, such as aircraft, it is necessary to temperature condition the air entering the pressurized cabin in order for the passengers and crewmembers to feel comfortable in flight. For example, when a passenger aircraft is cruising at ten thousand meters high altitude, the high altitude temperature outside the cabin can be reduced to about minus 50 ℃, and the temperature of the cabin of the aircraft must be ensured to meet the requirements of passengers when the aircraft is to fly at the high altitude safely. In general, cabin temperature control on passenger aircraft is mainly achieved by both air conditioning components (for cooling) and trim air systems. Common trim air systems, however, draw air downstream from the flow control valve in a common configuration as shown in fig. 1 and 2.
For the temperature-regulating system shown in fig. 1, the trim air system has only one pressure-regulating valve and this pressure-regulating valve bleed air downstream from the first flow-regulating valve; for the temperature regulating system shown in fig. 2, the two trim air systems are independent of each other and bleed air downstream from the first flow regulating valve, respectively.
The two arrangements described above cause several problems:
1. if the air conditioning assembly fails, the flow regulating valve which is fed back and regulated by the air conditioning assembly is closed, the trim air system cannot work, and hot air cannot be transmitted to the cabin;
2. if the trim air system is only provided with one pressure regulating valve, when the pressure regulating valve fails, the trim air system cannot work and cannot convey hot air to the cabin;
3. if the two trim air systems are not cross-linked, when the trim air system on one side fails, the ventilation system corresponding to the trim air system on the side has no hot gas input, and the two trim air systems have no advantages in terms of functional backup;
4. the opening of the pressure regulating valve is small, so that the air flow passing through the pressure regulating valve in unit time is small, and the main setting purpose of the pressure regulating valve is to reduce air flow noise, so that in an extreme case, the use of the pressure regulating valve can lead to prolonged heating time and influence the economy of airplane operation.
Thus, there is a need to provide a temperature regulation system and application method implemented thereby to at least partially address the above-mentioned problems.
Disclosure of Invention
The invention mainly aims to provide a temperature regulating system and an application method realized by the same. Different branch valves are arranged on each trim air branch of the temperature adjusting system, and the branch valves needing to be opened can be selected according to specific scene environments, so that the temperature adjusting system is suitable for various different scene environments, and when a refrigerating system fails, the trim air system cannot be influenced and can still provide hot air for a pressurized cabin of an airplane, so that the temperature environment in the pressurized cabin can be guaranteed under extreme conditions.
A temperature adjusting system of the present invention for introducing gas from a left gas source and a right gas source and adjusting the gas to discharge the adjusted gas to a ventilation system that mixes and discharges the gas to a plenum, the temperature adjusting system comprising:
a left bleed air main pipeline and a right bleed air main pipeline which are arranged in parallel with each other and respectively receive gas from a left gas source and a right gas source,
wherein, a flow measuring and feeding device, a flow adjusting valve and an air conditioning component are respectively and sequentially arranged on the left bleed air main pipeline and the right bleed air main pipeline along the flowing direction of the gas,
the left air-entraining main pipeline and the right air-entraining main pipeline respectively form a left balancing air branch and a right balancing air branch between the flow measuring and feeding device and the flow regulating valve, the left balancing air branch and the right balancing air branch are respectively provided with different branch valves for being applied to different application scenes, and the left balancing air branch and the right balancing air branch are crosslinked to form a balancing air main pipeline and discharge gas to the ventilation system.
In one embodiment, the bypass valve provided on one of the left trim air branch and the right trim air branch is a pressure regulating valve and the bypass valve provided on the other of the left trim air branch and the right trim air branch is a shut-off valve.
In one embodiment, the pressure regulating valve is feedback regulated by a component downstream thereof.
In one embodiment, the temperature regulation system further comprises a controller configured to determine a current application scenario of the temperature regulation system from a wheel-load signal or from a user input, and to control a valve downstream of the controller according to the current application scenario.
In one embodiment, the application scenario includes: the aircraft is located on the ground, the scene that passengers do not exist in the pressurization cabin, the scene that the aircraft is located at high altitude and passengers exist in the pressurization cabin, and the scene that the pressure regulating valve fails.
In one embodiment, the sensor comprises a pressure sensor and/or a temperature sensor.
In one embodiment, the air in the left and right main bleed air lines flows through the flow measurement and feed devices, the flow regulating valve and the air conditioning assembly and is then discharged to the ventilation system to mix with the air in the ventilation system.
In one embodiment, the controller is configured to receive a sensing signal from the flow measuring and feeding device and to control and adjust the opening of the flow regulating valve based on the sensing signal.
In one embodiment, the trim air main includes a cross-link section that merges the left and right trim air branches, and a plurality of downstream branches disposed in parallel between the cross-link section and the ventilation system.
In one embodiment, each of the downstream branches is provided with a downstream flow regulating valve.
In another aspect of the present invention, there is also provided an application method implemented by the temperature adjustment system according to any one of the above aspects, to adjust the temperature of the gas in the pressurized cabin of the aircraft, wherein the temperature adjustment system further includes a controller configured to determine a current application scenario of the temperature adjustment system according to the on-board signal or according to the user input, and to control a valve downstream of the controller according to the current application scenario, the application method including the following steps:
the controller judges the current application scene of the temperature adjusting system according to the wheel load signal, or the controller receives a signal which is input by a user and contains the current application scene of the temperature control adjusting system; and
the controller controls its downstream valve according to the current application scenario.
In one embodiment, the bypass valve provided in one of the left trim air branch and the right trim air branch is a pressure regulating valve and the bypass valve provided in the other of the left trim air branch and the right trim air branch is a shut-off valve.
In one embodiment, when the aircraft is on the ground and no passenger is in the pressurized cabin, the controller controls the closing valve to be opened and the pressure regulating valve to be closed according to the current application scene.
In one embodiment, when the aircraft is located at high altitude and passengers are in the pressurized cabin, the controller controls the opening of the pressure regulating valve and the closing of the shutoff valve according to the current application scene.
In one embodiment, when the pressure regulating valve fails, the controller controls the opening of the shut-off valve according to the current application scenario.
The temperature regulating system and the application method realized by the same provided by the invention comprise different structures and method designs meeting the operating conditions under multiple working conditions, and can be suitable for various different scene environments. Specifically, the trim air system has at least two branches, each branch has a cross-linking section at a specific position, and other branches can still work when a valve on one branch fails; the branch valves arranged on the balancing air branches are different, so that the branch valves to be opened can be selected according to different use scenes, and the air conditioning system can use different scene environments, for example, airflow in the balancing air system can not pass through a pressure regulating valve under the condition of needing emergency heat supply so as to be quickly discharged and shorten the heating time; the branches of each trim air system are gathered at the main pipeline, and the main pipeline has advantages in terms of functional backup; the trim air system is not affected when the refrigeration function fails and can still quickly heat the pressurized cabin of the aircraft, so that the temperature environment in the pressurized cabin can be guaranteed under extreme conditions. Therefore, the temperature regulating system provided by the invention has obvious improvement in multiple aspects compared with the existing temperature regulating system, and can meet different use requirements of users.
Drawings
For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.
FIGS. 1 and 2 are schematic diagrams of two prior art temperature regulation systems;
FIG. 3 is a schematic view of a temperature regulation system according to a preferred embodiment of the present invention;
FIG. 4 is a schematic circuit diagram of the flow measuring and feeding device and the controller of the temperature regulating system according to the present embodiment;
fig. 5 is a schematic diagram illustrating an application method using the temperature adjustment system according to the present embodiment.
Detailed Description
Reference will now be made in detail to the embodiments of the present invention, examples of which are illustrated in the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention.
Referring to fig. 3 to 5, a preferred embodiment of the present invention provides a temperature regulation system and application method implemented thereby for temperature or flow regulation of air entering a pressurized cabin of an aircraft, specifically, the temperature regulation system draws air from, for example, an engine (i.e., an air supply in this embodiment) and ultimately discharges the regulated air to a ventilation system that mixes and discharges the air to the pressurized cabin to provide a comfortable temperature within the pressurized cabin.
In this embodiment, the air sources include a left air source and a right air source, and the temperature adjustment system is capable of bleeding air from the two air sources, respectively. The temperature adjusting system comprises two main bleed air pipelines, namely a left bleed air pipeline and a right bleed air pipeline, which correspond to the two air sources respectively, and the left bleed air pipeline and the right bleed air pipeline are arranged in parallel to each other and receive air from the left air source and the right air source respectively. It should be noted that the temperature regulating system of the invention may be adapted to receive gas from more than two gas sources, and correspondingly, the number of main bleed air lines may also be the same as the number of gas sources, so that one main bleed air line is correspondingly connected to one gas source.
Referring to fig. 3, a flow measuring and feeding device, a flow regulating valve and an air conditioning assembly are arranged on the bleed air main pipeline along the air flowing direction, and air led out from the air conditioning assembly is discharged to the ventilation system. And a left balancing air branch and a right balancing air branch are respectively led out from the left bleed air main pipeline and the right bleed air main pipeline between the flow measurement feedback device and the flow regulating valve, the two balancing air branches are gathered to a balancing air main pipeline, and the balancing air main pipeline discharges gas to a ventilation system.
That is, after the gas extracted from the gas source passes through the flow measuring and feeding device, a part of the gas passes through the flow regulating valve and the air conditioning assembly and is discharged to the ventilation system, and the part of the gas is cooled by the air conditioning assembly, so that the part of the gas is finally discharged to the ventilation system in a cold air mode; while another part of the air is discharged to the ventilation system through the trim air branch and the trim air main, and this part of the air is not cooled and is discharged to the ventilation system in the form of hot air to be mixed with the cold air in the ventilation system, and the ventilation system finally discharges the mixed air with a proper temperature to the plenum chamber.
It is understood that the system of the piping for cooling the gas and the various components provided thereon (including the flow regulating valve and the air conditioning assembly in this embodiment) may be referred to as a refrigeration system; and the balancing air branch, the balancing air main pipeline and each part on the balancing air branch and the balancing air main pipeline jointly form a balancing air system. Of course, the constituent structures of the refrigeration system and the trim air system are not limited to the examples given in the present embodiment, and the refrigeration system and the trim air system may include other components than the examples given in the present embodiment.
When the air conditioning assembly fails, the flow regulating valve may close or decrease in opening. And the balancing air system leads out a balancing air branch from the upstream of the flow regulating valve, so that the normal work of the balancing air system cannot be influenced even if the flow regulating valve is closed. For example, in flight at high altitudes, if the air conditioning assembly fails, emergency ram air introduced from the outside high altitude atmosphere may be heated directly by the trim air system and the heated air may be discharged to the plenum chamber, so that the ambient temperature within the plenum chamber may also be ensured in such a case to ensure passenger comfort.
And the balancing air branch can bleed air at the downstream of the flow measurement feeder device, so that the problem of unbalanced bleed air caused by bleed air difference of each balancing air branch can be avoided, and balanced bleed air of each balancing air branch can be realized under the adjustment of the flow measurement feeder device.
In this embodiment, each trim air branch is provided with a branch valve, and the branch valves on the trim air branches are different from each other. For example, in fig. 3, the first bypass valve may be a pressure regulating valve and the second bypass valve may be a shut-off valve. The pressure regulating valve can be subjected to feedback regulation of downstream components, the opening degree of the pressure regulating valve is small, and noise generated by mixing hot air and cold air at the downstream of the trim air system can be reduced, so that the comfort in the pressurized cabin is improved.
The first branch valve and the second branch valve are set to be different valves, so that different operations under different scenes can be realized, and the operations are mainly controlled by the controller. Specifically, referring to FIG. 4, the controller forms part of a temperature regulation system and the flow measurement and feed device includes a temperature sensor, a pressure sensor, and a tapered and flared tube. The tapered and flared tube serves to stabilize the flow of the gas stream through the flow measurement and feed device. And the pressure sensor, the temperature sensor and the controller may be communicatively connected to transmit the sensed signals to the controller, and the controller may thereby control the opening degree of the flow rate adjustment valve based on the received signals, the path of which is shown by the long and short dashed lines in fig. 4.
Further, the controller can determine a current application scenario of the temperature regulation system according to the on-wheel signal or according to user input, and control the valve downstream of the controller according to the current application scenario. For example, if the current application scenario is: when the aircraft is located on the ground and no passenger is in the pressurized cabin, the pressurized cabin needs to be rapidly heated without considering the comfort of the passenger (a scene 1 shown in fig. 5), the controller controls to open the shutoff valve and close the pressure regulating valve, and the shutoff valve can be fully opened so as to enable airflow to rapidly pass to the maximum extent and achieve the purpose of rapidly heating the pressurized cabin; if the current application scene is: when passengers are in the pressurized cabin in the high air of the airplane, the requirement of temperature rise in the pressurized cabin and the requirement of comfort of the passengers are both considered (a scene 2 shown in fig. 5), and at the moment, the controller controls the pressure regulating valve to be opened to reduce noise and controls the closing valve to be closed; if the current application scene is: the pressure regulating valve fails (scenario 3 shown in fig. 5), the controller controls the opening of the shut-off valve to maintain warming of the pressurizing compartment in this case.
Preferably, the balancing air main pipeline comprises a cross-linking section connected downstream of each balancing air branch, and a downstream branch arranged in parallel between the cross-linking section and the ventilation system, and each downstream branch is further provided with a downstream flow regulating valve. Further, the controller may also control each downstream flow regulating valve. For example, in the scenario one mode shown in fig. 5, the opening degree of each downstream flow regulating valve can be increased as much as possible to maximize the airflow rate, so as to further shorten the warming time; while in a mode in which rapid heating is not required, the opening degree of each downstream flow rate adjustment valve may be slightly reduced.
It should be noted that the terms "bleed air", "connect", and the like, as used herein, encompass both direct and indirect implementations. For example, when the downstream conduit is bled from the upstream conduit, the downstream conduit may be directly connected to the upstream conduit to effect direct bleed air, or further conduits and/or apparatus may be provided between the downstream conduit and the upstream conduit to effect indirect bleed air.
The temperature regulating system and the application method realized by the same provided by the invention comprise different structural designs and method designs meeting the operating conditions under multiple working conditions, and can be suitable for various different scene environments. Specifically, the left trim air branch and the right trim air branch are provided with different branch valves, and the required branch valves can be selectively opened according to specific use scenes, for example, the air flow in a trim air system can be quickly discharged without passing through a pressure regulating valve under the condition of needing emergency heat supply, and the heating time is shortened; when the air conditioning assembly fails in the high altitude, the trim air system is not affected, and the emergency ram air can be heated and discharged to the pressurizing cabin, so that the temperature environment in the pressurizing cabin can be guaranteed under extreme conditions; the balancing air system is provided with at least two branches, each branch has a cross-linking section at a specific position, and other branches can still work when a valve on one branch fails; the branches of the individual trim air systems are combined at the trim air main line, which is advantageous from a functional backup point of view. In summary, the temperature adjustment system and the method using the same provided by the invention have obvious improvements in various aspects compared with the existing temperature adjustment system and method, and can meet different use requirements of users.
The foregoing description of various embodiments of the invention is provided for the purpose of illustration to one of ordinary skill in the relevant art. It is not intended that the invention be limited to a single disclosed embodiment. As mentioned above, many alternatives and modifications of the present invention will be apparent to those skilled in the art of the above teachings. Thus, while some alternative embodiments are specifically described, other embodiments will be apparent to, or relatively easily developed by, those of ordinary skill in the art. The present invention is intended to embrace all such alternatives, modifications and variances of the present invention described herein, as well as other embodiments that fall within the spirit and scope of the present invention as described above.
Claims (14)
1. A temperature conditioning system for bleeding gas from left and right gas sources and conditioning the gas to discharge the conditioned gas to a ventilation system that mixes and discharges the gas to a plenum, the temperature conditioning system comprising:
a left bleed air main pipeline and a right bleed air main pipeline which are arranged in parallel with each other and respectively receive gas from a left gas source and a right gas source,
wherein, a flow measuring and feeding device, a flow adjusting valve and an air conditioning component are respectively and sequentially arranged on the left bleed air main pipeline and the right bleed air main pipeline along the flowing direction of the gas,
the system is characterized in that a left balancing air branch and a right balancing air branch are respectively formed between the flow measuring and feeding device and the flow regulating valve by the left bleed air main pipeline and the right bleed air main pipeline, different branch valves are respectively arranged on the left balancing air branch and the right balancing air branch to be applied to different application scenes, a balancing air main pipeline is formed after the left balancing air branch and the right balancing air branch are crosslinked, and gas is discharged to the ventilation system,
and the branch valve arranged on one of the left balancing air branch and the right balancing air branch is a pressure regulating valve, and the branch valve arranged on the other of the left balancing air branch and the right balancing air branch is a shutoff valve.
2. The system of claim 1, wherein the pressure regulating valve is feedback regulated by a component downstream thereof.
3. The system of claim 1, further comprising a controller configured to determine a current application scenario of the system based on a vehicle signal or based on a user input, and to control a valve downstream of the controller based on the current application scenario.
4. The temperature conditioning system of claim 3, wherein the application scenario comprises: the aircraft is located on the ground, the scene that no passenger exists in the pressurization cabin, the scene that the aircraft is located at high altitude and the passenger exists in the pressurization cabin, and the scene that the pressure regulating valve is invalid.
5. The system of claim 3, wherein the flow measurement and feed device comprises a pressure sensor and a temperature sensor.
6. The temperature conditioning system of claim 1 wherein the air in the left and right bleed air main lines flows through the flow measurement and feed devices, the flow regulating valve and the air conditioning pack and is subsequently discharged to the ventilation system to mix with the air within the ventilation system.
7. The system of claim 3, wherein the controller is configured to receive a sense signal from the flow measurement and feed device and to control the adjustment of the opening of the flow control valve based on the sense signal.
8. The system of claim 1, wherein the trim air main includes a cross-link section that sums the left and right trim air branches and a plurality of downstream branches disposed in parallel between the cross-link section and the ventilation system.
9. The system of claim 8, wherein each of the downstream branches includes a downstream flow control valve.
10. Application method implemented by a temperature regulation system according to any one of claims 1 to 9 for regulating the temperature of a gas inside a pressurized cabin of an aircraft, wherein the temperature regulation system further comprises a controller configured to be able to determine a current application scenario of the temperature regulation system from a wheel load signal or from a user input, and to control a valve downstream of the controller according to the current application scenario, characterized in that the application method comprises the following steps:
the controller judges the current application scene of the temperature adjusting system according to the wheel load signal, or the controller receives a signal which is input by a user and contains the current application scene of the temperature control adjusting system; and
the controller controls its downstream valve according to the current application scenario.
11. The method of use of claim 10, wherein the bypass valve disposed in one of the left trim air bypass and the right trim air bypass is a pressure regulating valve and the bypass valve disposed in the other of the left trim air bypass and the right trim air bypass is a shut-off valve.
12. The method of application according to claim 11, wherein the controller controls the shut-off valve to be opened and the pressure regulating valve to be closed according to the current application scenario when an aircraft is located on the ground and no passenger is present in the pressurized cabin.
13. The application method according to claim 11, wherein when an aircraft is located at high altitude and passengers are in the pressurized cabin, the controller controls the pressure regulating valve to be opened and the shut-off valve to be closed according to the current application scenario.
14. The application method according to claim 11, wherein when a pressure regulating valve fails, the controller controls the shut-off valve to be opened according to the current application scenario.
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| CN114251602B (en) * | 2022-01-12 | 2024-10-15 | 湖南三重理想储能科技有限公司 | Pressure regulating system and pressure regulating method of gas adsorption instrument |
| CN114815934B (en) * | 2022-03-23 | 2023-02-03 | 中国商用飞机有限责任公司 | Aircraft cabin air balancing device, temperature control system and control method |
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