JP4483150B2 - Air conditioning system for aircraft - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an air conditioning system for an aircraft.
[0002]
[Prior art]
As shown in FIG. 4, the conventional aircraft air conditioning system cools the engine bleed air from the engine 102 compressed by the compressor 101 by heat exchange with the ram air in the heat exchanger 103, and the cooled bleed air is reheater 105. Is further cooled by heat exchange in the condenser 106, and then is cooled by heat exchange with the low-temperature air in the condenser 106 to cool the moisture in the extracted air below the dew point, and the water separator 107 separates the moisture using centrifugal force. is doing. The extracted air from which the moisture has been separated is used for cooling the extracted air before the moisture separation in the reheater 105, and then is expanded in the expansion turbine 108 to form low-temperature air. The low-temperature air is used for cooling the bleed air in the condenser 106 and then sent out to the aircraft cabin. Note that the extracted air expands and rotates the expansion turbine 108, thereby acting as a driving force for the compressor 101 via the rotation shaft S. In addition, by allowing high-temperature engine bleed air to be introduced between the expansion turbine 108 and the condenser 106 via the valve 109, moisture icing in the bleed passage of the condenser 106 is prevented.
[0003]
If dust is included in the engine bleed air from the engine 102 that is taken into such an air conditioning system for aircraft, the dust increases the pressure loss of the heat exchanger 103 or promotes erosion of the nozzles of the turbine 108. Adversely affect the performance and components of the air conditioning system.
[0004]
Therefore, when taking the engine bleed into the air conditioning system for aircraft, (1) passing through the filter and removing the dust after taking in the engine bleed, or (2) a dust separator described later for separating and removing the dust by centrifugal force The above-mentioned adverse effects on the air-conditioning system are reduced by passing the air through and removing the dust.
[0005]
[Problems to be solved by the invention]
However, when the engine bleed air is taken in through the filter as in (1) above, pressure loss occurs in the filter and the pressure of the engine bleed air decreases, so that even after passing through the compressor 101, the predetermined compressed air Cannot be obtained. Thereby, a predetermined cooling capacity cannot be obtained. In the case of the above (2), as will be described later, since the dust separated by centrifugal force is discharged to the outside using a part of the engine bleed air to be taken in, the engine that is taken into the air conditioning system as a result. The amount of bleed air is reduced and the cooling capacity of the air conditioning system is reduced.
[0006]
Accordingly, an object of the present invention is to provide an aircraft air conditioning system that can suppress pressure loss and reduce the amount of engine bleed air taken into the air conditioning system and that can remove dust from the engine bleed air.
[0007]
[Means for Solving the Problems]
The aircraft air conditioning system according to the first aspect of the present invention separates and removes dust from the engine bleed by the dust separator when taking in the engine bleed for air conditioning, and further removes the dust removed by the dust separator together with a part of the engine bleed. After discharging and passing through a filter for capturing dust, a part of the engine bleed air is merged with the engine bleed air that has passed through the dust separator.
[0009]
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 shows an aircraft air conditioning system according to an embodiment of the first invention. The air conditioning system main body is the same as the conventional aircraft air conditioning system shown in FIG. 4, and a description thereof will be omitted.
[0010]
In FIG. 1, a dust separator 11 that removes dust from engine bleed air is provided, and the engine bleed air that has passed through the dust separator 11 is configured to be taken into the air conditioning system main body via the flow rate control valve 12.
[0011]
The dust separator 11 removes dust together with part of the engine bleed using centrifugal force. As shown in FIG. 2, a screw-like swivel plate 52 is fixed inside the cylindrical body 51. The engine bleed air passing through the inside of the body 51 becomes a vortex flow by the swirl plate 52, and the dust is pushed to the inner peripheral wall side of the body 51 by the centrifugal force caused by the vortex flow. On the other hand, the engine bleed air F that does not contain dust is discharged through an outlet tube 53 inserted into the body 51. As shown in FIG. Engine bleed SA including such dust is discharged from a gap 54 formed between the body 51 and the outlet tube 53. In addition, about 5% of the engine bleed gas taken into the dust separator 11 is discharged through the gap 54 as engine bleed air SA containing dust, and the remaining 95% as engine bleed air F containing no dust is used as an outlet tube. It passes through 53 and is discharged. It is also possible to change the amount of engine bleed through the gap 54 by changing the size of the gap 54.
[0012]
Further, as shown in FIG. 1, the engine bleed SA including dust discharged from the dust separator 11 passes through a filter 13 that captures dust provided in the pipe 15 while passing through the pipe 15. After being removed, it is configured to pass through the outlet tube 53 of the dust separator 11 and merge with the engine bleed air F that does not contain dust that has passed through the pipe 16.
[0013]
Further, a differential pressure sensor 14 for detecting the differential pressure between the inlet side and the outlet side of the filter 13 is provided in the pipe 15 to detect a pressure loss caused by clogging of the filter due to dust, thereby adversely affecting the air conditioning system. It is possible to check the filter 13 by detecting that the pressure loss has been reached. In addition, it is also possible to omit such a differential pressure sensor 14 by checking the filter 13 regularly.
[0014]
Next, the operation of the aircraft air conditioning system of FIG. 1 according to the present embodiment will be described with reference to FIG. When the engine bleed extracted for air conditioning from the engine is taken into the dust separator 11, a vortex flow is generated by the screw-like swirl plate 52 fixed inside the body 51.
[0015]
The engine bleed air contains dust, and the dust is pushed to the inner peripheral wall side of the body 51 by centrifugal force generated by the swirl flow generated by the swirl plate 52, and about 5 of all engine bleed air taken into the dust separator 11. The engine bleed SA including dust is discharged together with a part of the engine bleed occupying%, and is discharged from a gap 54 formed between the body 51 and the outlet tube 53. On the other hand, the engine bleed air from which dust has been removed passes through the outlet tube 53 and is discharged as engine bleed air F that does not contain dust.
[0016]
The engine bleed SA including dust discharged from the dust separator 11 passes through the pipe 15 and passes through the filter 13. The engine bleed SA is trapped when passing through the filter 13. , And the engine bleed air F that does not contain dust that has passed through the pipe 16 is merged, and then taken into the air conditioning system main body.
[0017]
Thus, dust is collected in a small amount of engine bleed, about 5% of the total engine bleed, and passed through the filter 13 to capture the dust, so that the pressure loss in the filter 13 occurs for about 5% of the total engine bleed. Yes, the pressure loss in all engine bleeds is extremely small. In addition, even a small amount of engine bleed air after dust has been captured is finally taken into the air conditioning system main body, so that the engine bleed air can be used effectively, and thus the cooling capacity of the air conditioning system is not reduced. And since the magnitude | size of the filter 13 can also be reduced in size, cost reduction, weight reduction, and the simplification of a maintenance can also be aimed at.
[0018]
A reference example is shown in FIG. In this reference example , in particular, a shutoff valve 21 is provided in a pipe 15 connected to the dust separator 11 and exhausting engine bleed SA including dust to the outside of the machine, and the shutoff is only performed when the shutoff valve 21 is opened. By configuring the engine extraction SA containing dust to the outside of the machine via the valve 21, the dust separator 11 can function only when it is necessary to remove the dust from the engine extraction. The shutoff valve 21 can be controlled to open and close by a signal from the controller based on the operation of the operator.
[0019]
For example, when the engine bleed always contains dust, such as when flying over volcanic ash or in the desert, the dust separator 11 functions when the shut-off valve 21 is opened based on the operator's operation. Since the engine bleed SA including dust passing through the valve 21 can be discharged out of the apparatus, the dust is removed from the engine bleed. On the other hand, when the shut-off valve 21 is closed, the function of the dust separator 11 is stopped, and engine bleed (about 5% of the total engine bleed) is not discharged from the dust separator to the valve 21 side.
[0020]
As a result, the valve 21 is opened only when flying in an environment such as ash fall, and the dust separator 11 is made to function, and the engine bleed SA containing about 5% of the total engine bleed is discharged out of the machine. However, when flying in a normal environment, the valve 21 is closed and the function of the dust separator 11 is stopped, so that all engine bleed air can be taken into the air conditioning system, so that the cooling capacity of the air conditioning system does not deteriorate. . Therefore, since the amount of engine bleed air taken into the air conditioning system does not decrease except when dust removal is necessary, it is possible to suppress a decrease in the cooling capacity of the air conditioning system during flight.
[0021]
【The invention's effect】
According to the present invention, since dust is not mixed into the air conditioning system, engine bleed air can be taken into the air conditioning system without pressure loss, so that the cooling capacity of the air conditioning system does not deteriorate. In addition, erosion of the component parts can be prevented, and opportunities for parts replacement and maintenance can be reduced. Furthermore, since it is possible to suppress a reduction in the amount of engine bleed air taken into the air conditioning system, it is possible to suppress a decrease in cooling capacity.
[Brief description of the drawings]
FIG. 1 is a block diagram of an aircraft air conditioning system according to a first invention.
FIG. 2 is a schematic configuration diagram of a dust separator.
FIG. 3 is a block diagram of an aircraft air conditioning system according to a second invention.
FIG. 4 is a schematic configuration diagram of a conventional aircraft air conditioning system.
[Explanation of symbols]
11 Dust separator 13 Filter 15 Piping

Claims (1)

 In an air conditioning system for an aircraft, comprising a dust separator that separates dust from engine bleed air and discharges it together with some engine bleed air, and configured to take in the engine bleed air from which dust has been removed by passing through the dust separator for air conditioning. A filter that captures dust is provided in a pipe that allows passage of the engine bleed exhausted together with dust, and the engine bleed that has passed through the filter is merged with the engine bleed that has passed through the dust separator. An aircraft air conditioning system characterized by being configured to allow

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