Air conditioning system for an aircraft

Abstract

The purpose of this invention is to provide an aircraft air conditioning system that can increase the oxygen content of cabin air and reduce the amount of bleed air from the power unit. The aircraft air conditioning system of this invention includes: an air separator that separates oxygen and nitrogen from the bleed air from the power unit to form an oxygen-enriched gas with an oxygen concentration higher than that in the bleed air and a nitrogen-enriched gas with a nitrogen concentration higher than that in the bleed air; and an air mixing chamber connected to the air separator, wherein the oxygen-enriched gas formed in the air separator is supplied to the air mixing chamber, and the oxygen-enriched gas is mixed with secondary air in the aircraft cabin in the air mixing chamber, and the mixed gas is supplied to the aircraft cabin.

Description

Technical Field

[0001] This utility model relates to an aircraft air conditioning system for regulating the air inside an aircraft cabin. Background Technology

[0002] The bleed air in an aircraft's air supply system comes from the power unit. The high-temperature, high-pressure gas from the air supply system is regulated by the refrigeration components and then sent to the downstream distribution system. After being used by downstream users, the air is directly discharged outside the aircraft cabin, resulting in very low utilization. To save on bleed air, some aircraft are equipped with recirculation systems that can recover 35% to 50% of the cabin air, but this leads to a decrease in the oxygen content of the cabin air.

[0003] In other words, existing aircraft air conditioning systems have the following problems: the air utilization rate of the aircraft air supply system is very low; and the oxygen content of the cabin air decreases after the recirculation system recovers a portion of the cabin air. Utility Model Content

[0004] In view of the above problems, the purpose of this utility model is to provide an aircraft air conditioning system that can increase the oxygen content of cabin air and reduce the bleed air from the power unit.

[0005] To achieve the above objectives, the aircraft air conditioning system of this utility model includes: an air separator that separates oxygen and nitrogen from the bleed air from the power unit to form an oxygen-enriched gas with an oxygen concentration higher than that in the bleed air and a nitrogen-enriched gas with a nitrogen concentration higher than that in the bleed air; and an air mixing chamber connected to the air separator, wherein the oxygen-enriched gas formed in the air separator is supplied to the air mixing chamber, and the oxygen-enriched gas is mixed with secondary air in the aircraft cabin in the air mixing chamber, and the mixed gas is supplied to the aircraft cabin.

[0006] According to the aircraft air conditioning system of this utility model, since the bleed air from the power unit is separated in the air separator to form an oxygen-enriched gas with an oxygen concentration higher than that in the bleed air, the oxygen-enriched gas is supplied to the air mixing chamber and mixed with the secondary air in the aircraft cabin. The mixed gas is then supplied to the aircraft cabin, thereby increasing the oxygen content of the cabin air and reducing the amount of bleed air from the power unit.

[0007] Preferably, a flow control valve is provided in the flow path between the air separator and the air mixing chamber, and an oxygen concentration sensor is provided in the air mixing chamber to detect the oxygen concentration in the air mixing chamber. The opening of the flow control valve is adjusted according to the data of the oxygen concentration sensor so that the oxygen content in the air mixing chamber is not lower than a preset value.

[0008] According to the present invention, the aircraft air conditioning system can adjust the opening of the flow control valve based on the data of the oxygen concentration sensor, so that the oxygen content in the air mixing chamber is not lower than the preset value, thereby ensuring the oxygen content of the cabin air.

[0009] Preferably, the temperature of the gas in the air mixing chamber is controlled by a vapor compression cycle loop, which is formed by connecting an evaporator, an expansion valve, a condenser, a four-way valve, and a compressor in series, and the evaporator is connected to the air mixing chamber.

[0010] According to the present invention, the aircraft air conditioning system can use a vapor compression cycle loop to control the temperature of the gas in the air mixing chamber.

[0011] Preferably, an air mixing chamber temperature sensor is provided in the air mixing chamber to detect the temperature in the air mixing chamber, and the working state of the vapor compression cycle is adjusted according to the data of the air mixing chamber temperature sensor so that the temperature in the air mixing chamber is maintained at a set value.

[0012] According to the present invention, the aircraft air conditioning system can adjust the working state of the vapor compression cycle based on the data of the temperature sensor of the air mixing chamber, so that the temperature in the air mixing chamber is maintained at a set value, thereby stabilizing the temperature of the gas supplied to the aircraft cabin.

[0013] Preferably, the bleed air sequentially passes through a pressure regulating valve, an ozone converter, a heat exchanger, a temperature sensor for the air separator, a filter, and a pressure sensor before entering the air separator. The aircraft air conditioning system also includes a bypass path that bypasses the heat exchanger. A temperature control valve is installed on the bypass path. The opening of the temperature control valve is adjusted according to the data from the temperature sensor for the air separator, so that the bleed air is maintained at a certain temperature before entering the air separator. The opening of the pressure regulating valve is adjusted according to the data from the pressure sensor, so that the bleed air is maintained at a certain pressure before entering the air separator.

[0014] According to the present invention, the aircraft air conditioning system can adjust the opening of the temperature control valve based on the data of the temperature sensor of the air separator, so that the bleed air is kept at a certain temperature before entering the air separator, and adjust the opening of the pressure regulating valve based on the data of the pressure sensor, so that the bleed air is kept at a certain pressure before entering the air separator. Thus, the bleed air entering the air separator can be kept at a certain temperature and pressure.

[0015] Preferably, the bleed air is heat-exchanged using ram air in the heat exchanger.

[0016] The aircraft air conditioning system according to this invention can use ram air to cool the bleed air.

[0017] Preferably, the secondary air is sent to the air mixing chamber after passing through a recirculation filter and a recirculation fan.

[0018] The aircraft air conditioning system of this invention can conveniently deliver secondary air from the aircraft cabin to the air mixing chamber. Attached Figure Description

[0019] Figure 1 This is a schematic diagram illustrating the configuration of an aircraft air conditioning system according to an embodiment of the present invention.

[0020] (Symbol Explanation)

[0021] 1: Pressure regulating valve;

[0022] 2: Ozone converter;

[0023] 3: Temperature control valve;

[0024] 4: Heat exchanger;

[0025] 5: Temperature sensor for air separator;

[0026] 6: Filter;

[0027] 7: Pressure sensor;

[0028] 8: Air separator;

[0029] 9: Flow control valve;

[0030] 10: Air mixing chamber;

[0031] 11: Recirculation fan;

[0032] 12: Recirculation filter;

[0033] 13: Temperature sensor for air mixing chamber;

[0034] 14: Oxygen concentration sensor;

[0035] 15: Evaporator;

[0036] 16: Expansion valve;

[0037] 17: Condenser;

[0038] 18: Four-way valve;

[0039] 19: Compressor;

[0040] 20: Bypass path;

[0041] 100: Aircraft air conditioning system. Detailed Implementation

[0042] Various embodiments of the present invention will now be described in detail, examples of which are shown in the accompanying drawings and described below. Although the present invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the present invention to those exemplary embodiments. Rather, the present invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the present invention as defined by the appended claims.

[0043] (Structure of aircraft air conditioning system 100)

[0044] The following reference Figure 1 The configuration of the aircraft air conditioning system 100 according to the present invention will be described.

[0045] Figure 1 This is a schematic diagram showing the configuration of an aircraft air conditioning system 100 according to an embodiment of the present invention.

[0046] like Figure 1 As shown, the aircraft air conditioning system 100 of this utility model includes a pressure regulating valve 1, an ozone converter 2, a temperature control valve 3, a heat exchanger 4, a temperature sensor for an air separator 5, a filter 6, a pressure sensor 7, an air separator 8, a flow control valve 9, an air mixing chamber 10, a recirculation fan 11, a recirculation filter 12, a temperature sensor for an air mixing chamber 13, an oxygen concentration sensor 14, an evaporator 15, an expansion valve 16, a condenser 17, a four-way valve 18, a compressor 19, and a bypass flow path 20.

[0047] The bypass flow path 20 is a flow path that bypasses the heat exchanger 4, and a temperature control valve 3 is installed on the bypass flow path 20.

[0048] In heat exchanger 4, ram air is used to exchange heat with the bleed air from the power unit.

[0049] A vapor compression cycle loop is formed by using an evaporator 15, an expansion valve 16, a condenser 17, a four-way valve 18, and a compressor 19. The evaporator 15 is connected to the air mixing chamber 10.

[0050] The gas in the air mixing chamber 10 is supplied to the cockpit and passenger cabin of the aircraft respectively.

[0051] (Operation mode of aircraft air conditioning system 100)

[0052] like Figure 1As shown, bleed air from the power unit (not shown) passes sequentially through pressure regulating valve 1, ozone converter 2, heat exchanger 4, temperature sensor 5 for air separator, filter 6, and pressure sensor 7 before entering air separator 8. In air separator 8, oxygen and nitrogen in the bleed air from the power unit are separated to form oxygen-enriched gas with an oxygen concentration higher than that in the bleed air and nitrogen-enriched gas with a nitrogen concentration higher than that in the bleed air. The oxygen-enriched gas is sent to air mixing chamber 10 through flow control valve 9, and the nitrogen-enriched gas can be sent to the aircraft's fuel inerting system (not shown).

[0053] Secondary air in the aircraft cabin (the collective name for the cockpit and passenger cabin) is sent to the air mixing chamber 10 after passing through the recirculation filter 12 and the recirculation fan 11. The secondary air is mixed with oxygen-enriched gas in the air mixing chamber 10 and then distributed to the downstream cockpit and passenger cabin, etc.

[0054] The temperature control of the air in the air mixing chamber 10 is accomplished by a vapor compression cycle loop, which includes an evaporator 15, an expansion valve 16, a condenser 17, a four-way valve 18, and a compressor 19.

[0055] The aircraft air conditioning system 100 uses data from the temperature sensor 5 of the air separator to adjust the opening of the temperature control valve 3 located in the bypass flow path 20, so that the bleed air is kept at a certain temperature before entering the air separator 8.

[0056] In addition, the aircraft air conditioning system 100 adjusts the opening of the pressure regulating valve 1 based on the data from the pressure sensor 7, so that the bleed air is maintained at a certain pressure before entering the air separator 8.

[0057] In addition, the aircraft air conditioning system 100 adjusts the opening of the flow control valve 9 based on the data from the oxygen concentration sensor 14 located in the air mixing chamber 10, so that the oxygen content in the air mixing chamber 10 is not lower than a preset value.

[0058] In addition, the aircraft air conditioning system 100 adjusts the operating state of the vapor compression cycle loop by using the data from the air mixing chamber temperature sensor 13 located in the air mixing chamber 10, so that the temperature of the air mixing chamber 10 is maintained at a set value.

[0059] Therefore, this utility model provides an aircraft air conditioning system 100 that can increase the oxygen content. Compared with existing aircraft air conditioning systems, it can reduce the bleed air from the power unit and increase the oxygen content of the cabin air.

[0060] (Features and technical effects of this utility model)

[0061] As described above, the aircraft air conditioning system 100 of this utility model includes: an air separator 8, which separates oxygen and nitrogen from the bleed air from the power unit to form an oxygen-rich gas with an oxygen concentration higher than that in the bleed air and a nitrogen-rich gas with a nitrogen concentration higher than that in the bleed air; and an air mixing chamber 10, which is connected to the air separator 8. The oxygen-rich gas formed in the air separator 8 is supplied to the air mixing chamber 10, and the oxygen-rich gas is mixed with the secondary air in the aircraft cabin in the air mixing chamber 10. The mixed gas is then supplied to the aircraft cabin.

[0062] According to the aircraft air conditioning system 100 of this utility model, since the bleed air from the power unit is separated in the air separator 8 to form an oxygen-enriched gas with an oxygen concentration higher than that in the bleed air, the oxygen-enriched gas is supplied to the air mixing chamber 10 and mixed with the secondary air in the aircraft cabin. The mixed gas is then supplied to the aircraft cabin, thereby increasing the oxygen content of the cabin air and reducing the amount of bleed air from the power unit.

[0063] In addition, a flow control valve 9 is provided in the flow path between the air separator 8 and the air mixing chamber 10, and an oxygen concentration sensor 14 is provided in the air mixing chamber 10 to detect the oxygen concentration in the air mixing chamber 10. The opening of the flow control valve 9 is adjusted according to the data of the oxygen concentration sensor 14 so that the oxygen content in the air mixing chamber 10 is not lower than the preset value.

[0064] According to the present invention, the aircraft air conditioning system 100 can adjust the opening of the flow control valve 9 based on the data of the oxygen concentration sensor 14, so that the oxygen content in the air mixing chamber 10 is not lower than the preset value, thereby ensuring the oxygen content of the cabin air.

[0065] In addition, the temperature of the gas in the air mixing chamber 10 is controlled by a vapor compression cycle loop, which is formed by connecting the evaporator 15, expansion valve 16, condenser 17, four-way valve 18, and compressor 19 in series. The evaporator 15 is connected to the air mixing chamber 10.

[0066] According to the aircraft air conditioning system 100 of this invention, the temperature of the gas in the air mixing chamber 10 can be controlled by using a vapor compression cycle loop.

[0067] In addition, an air mixing chamber temperature sensor 13 is provided in the air mixing chamber 10 to detect the temperature in the air mixing chamber 10. The working state of the vapor compression cycle is adjusted according to the data of the air mixing chamber temperature sensor 13 so that the temperature in the air mixing chamber 10 is maintained at a set value.

[0068] According to the present invention, the aircraft air conditioning system 100 can adjust the working state of the vapor compression loop based on the data of the temperature sensor 13 for the air mixing chamber, so that the temperature inside the air mixing chamber 10 is maintained at a set value, thereby stabilizing the temperature of the gas supplied to the aircraft cabin.

[0069] In addition, the bleed air sequentially passes through pressure regulating valve 1, ozone converter 2, heat exchanger 4, temperature sensor 5 for air separator, filter 6, and pressure sensor 7 before entering air separator 8. The aircraft air conditioning system 100 also includes a bypass flow path 20 that bypasses heat exchanger 4. A temperature control valve 3 is installed on the bypass flow path 20. The opening of the temperature control valve 3 is adjusted according to the data from the temperature sensor 5 for air separator, so that the bleed air is kept at a certain temperature before entering air separator 8. The opening of the pressure regulating valve 1 is adjusted according to the data from the pressure sensor 7, so that the bleed air is kept at a certain pressure before entering air separator 8.

[0070] According to the present invention, the aircraft air conditioning system 100 can adjust the opening of the temperature control valve 3 based on the data of the temperature sensor 5 for the air separator, so that the bleed air is kept at a certain temperature before entering the air separator 8, and adjust the opening of the pressure regulating valve 1 based on the data of the pressure sensor 7, so that the bleed air is kept at a certain pressure before entering the air separator 8. Thus, the bleed air entering the air separator 8 can be kept at a certain temperature and pressure.

[0071] In addition, ram air is used to exchange heat with the bleed air in heat exchanger 4.

[0072] The aircraft air conditioning system 100 according to this invention can use ram air to cool the bleed air.

[0073] In addition, secondary air is sent to the air mixing chamber 10 after passing through the recirculation filter 12 and the recirculation fan 11.

[0074] The aircraft air conditioning system 100 of this invention can conveniently deliver secondary air from the aircraft cabin to the air mixing chamber 10.

[0075] (Modified Example)

[0076] The placement of the pressure sensor, temperature sensor, oxygen concentration sensor, etc. in this invention is not particularly limited, as long as they can measure the pressure, temperature, oxygen concentration, etc. of the corresponding parts.

[0077] Although the structure and working principle of this utility model have been described above with reference to preferred embodiments, those skilled in the art should recognize that the above examples are merely illustrative and should not be construed as limiting the utility model. Therefore, modifications and variations can be made to this utility model within the spirit and scope of the claims, and all such modifications and variations will fall within the scope claimed by the claims of this utility model.

Claims

1. An aircraft air conditioning system, characterized in that, include: An air separator that separates oxygen and nitrogen from the bleed air from the power unit to form an oxygen-rich gas with an oxygen concentration higher than that in the bleed air and a nitrogen-rich gas with a nitrogen concentration higher than that in the bleed air. as well as An air mixing chamber is connected to the air separator. The oxygen-enriched gas formed in the air separator is supplied to the air mixing chamber. The oxygen-enriched gas is mixed with the secondary air in the aircraft cabin in the air mixing chamber, and the mixed gas is supplied to the aircraft cabin.

2. The aircraft air conditioning system as described in claim 1, characterized in that, A flow control valve is provided in the flow path between the air separator and the air mixing chamber. An oxygen concentration sensor is installed in the air mixing chamber to detect the oxygen concentration in the air mixing chamber. The opening of the flow control valve is adjusted according to the data from the oxygen concentration sensor so that the oxygen content in the air mixing chamber is not lower than a preset value.

3. The aircraft air conditioning system as described in claim 1, characterized in that, The temperature of the gas in the air mixing chamber is controlled by a vapor compression loop, which is formed by connecting an evaporator, an expansion valve, a condenser, a four-way valve, and a compressor in series. The evaporator is connected to the air mixing chamber.

4. The aircraft air conditioning system as described in claim 3, characterized in that, An air mixing chamber temperature sensor is installed in the air mixing chamber to detect the temperature within the air mixing chamber. The operating state of the vapor compression loop is adjusted based on the data from the temperature sensor in the air mixing chamber, so that the temperature inside the air mixing chamber is maintained at a set value.

5. The aircraft air conditioning system as described in claim 1, characterized in that, The bleed air sequentially passes through a pressure regulating valve, an ozone converter, a heat exchanger, a temperature sensor for the air separator, a filter, and a pressure sensor before entering the air separator. The aircraft air conditioning system also includes a bypass path for bypassing the heat exchanger, and a temperature control valve is installed on the bypass path. The opening of the temperature control valve is adjusted based on data from the temperature sensor of the air separator, so that the bleed air is maintained at a certain temperature before entering the air separator. The opening of the pressure regulating valve is adjusted according to the data from the pressure sensor, so that the bleed air is maintained at a certain pressure before entering the air separator.

6. The aircraft air conditioning system as described in claim 5, characterized in that, In the heat exchanger, ram air is used to exchange heat with the bleed air.

7. The aircraft air conditioning system as claimed in claim 1, characterized in that, The secondary air is sent to the air mixing chamber after passing through a recirculation filter and a recirculation fan.

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