WO2020095477A1 - 航空機用空調装置 - Google Patents
航空機用空調装置 Download PDFInfo
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- WO2020095477A1 WO2020095477A1 PCT/JP2019/026767 JP2019026767W WO2020095477A1 WO 2020095477 A1 WO2020095477 A1 WO 2020095477A1 JP 2019026767 W JP2019026767 W JP 2019026767W WO 2020095477 A1 WO2020095477 A1 WO 2020095477A1
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- air
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- turbine
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- 238000004378 air conditioning Methods 0.000 title claims abstract description 25
- 230000001143 conditioned effect Effects 0.000 claims abstract description 24
- 238000011084 recovery Methods 0.000 claims description 17
- 230000001276 controlling effect Effects 0.000 abstract 1
- 230000001105 regulatory effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 6
- 230000006870 function Effects 0.000 description 5
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 239000000470 constituent Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/064—Environmental Control Systems comprising more than one system, e.g. dual systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0644—Environmental Control Systems including electric motors or generators
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0648—Environmental Control Systems with energy recovery means, e.g. using turbines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Definitions
- the present disclosure relates to an air conditioner for an aircraft.
- the present application claims priority based on Japanese Patent Application No. 2018-208876 filed in Japan on November 6, 2018, and the content thereof is incorporated herein.
- Patent Document 1 discloses an aircraft system (air-conditioning device for aircraft) that supplies conditioned air whose temperature is adjusted with compressed air generated by a compressor to an aircraft cabin.
- This aircraft system includes a first compressor driven by a turbine and / or a motor and at least one second compressor, and operates only the first compressor when the external pressure is high, and the external pressure is relatively low. At times, the first compressor and the second compressor are operated.
- Patent Documents 2 to 4 also disclose techniques related to aircraft air-conditioning systems.
- each system is called an ECS (Environmental Control System) unit or an AirPack.
- ECS Environmental Control System
- AirPack AirPack
- the present disclosure has been made in view of the above-mentioned circumstances, and an object thereof is to provide an aircraft air conditioner capable of increasing redundancy as compared with the related art.
- an air conditioner for an aircraft provided in an aircraft, wherein two electric motors connected in series to an air flow path are provided.
- a plurality of basic units each provided with a compressor, a temperature controller that adjusts the temperature of the air discharged from the compressors of the two electric compressors, and a control of the plurality of basic units and the temperature controller And a control device, and each of the plurality of basic units employs an aircraft air conditioner that supplies compressed air discharged from the temperature regulator as conditioned air to an air-conditioned space.
- control device may individually control two electric motors of the two electric compressors.
- the two electric compressors and the two electric compressors are axially coupled to each other.
- the turbine may constitute two electric turbochargers, and the two turbines may recover energy from the conditioned air.
- each of the plurality of basic units connects the two turbines to the air-conditioned space according to an operation mode.
- a switch that switches the relationship may be provided.
- the control device is configured to operate in the first operation mode corresponding to a state in which the aircraft is on the ground among the operation modes.
- the switch may be controlled so that the conditioned air after energy recovery by two turbines is supplied to the air-conditioned space.
- the two electric compressors are a first electric compressor, and A second electric compressor located downstream of the first electric compressor, wherein the two turbines are a first turbine axially coupled to the first electric compressor, and the second electric compressor. And a second turbine axially coupled to the control device, wherein the control device controls the harmony after energy is recovered by the second turbine in a second operation mode corresponding to a state in which the aircraft is in the sky among the operation modes.
- the switching device is controlled so that air is supplied to the conditioned space and the conditioned air recovered from the conditioned space is supplied to the first turbine, and the electric motor of the first electric compressor is used as a generator. Make it work It may be.
- FIG. 3 is a block diagram showing a detailed configuration of a basic unit according to an embodiment of the present disclosure.
- this indication it is a mimetic diagram showing the state of the basic unit in the above-ground / air-conditioned space energy non-recovery mode (1st operation mode).
- this indication it is a mimetic diagram showing the state of the basic unit in the above-mentioned space / air-conditioned space energy recovery mode (2nd operation mode).
- the aircraft air conditioner according to the present embodiment is an air conditioner provided in an aircraft (passenger aircraft), and includes a plurality of basic units U1 to U6, a temperature controller A, and an air conditioning controller S as shown in FIG. There is.
- the basic units U1 to U6 pressurize (pressurize) the outside air taken in from the outside of the cabin to a predetermined pressure and supply it to the cabin X, which is a pressurized compartment of the aircraft, and at the same time, collect the air from the cabin X outside the cabin. Exhaust to.
- FIG. 1 shows six basic units U1 to U6, the number of basic units may be any number as long as it is plural.
- the guest room X is the air-conditioned space in the present embodiment.
- the basic units U1 to U6 are all configured in the same manner and, as shown in FIG. 2, are provided with a first turbocharger K1, a second turbocharger K2, a switch D and an air conditioning controller S. Note that, as described above, all the basic units U1 to U6 have the same configuration, so in FIG. 2, “U” is used as a collective reference symbol for all the basic units U1 to U6.
- the first turbocharger K1 includes the first compressor 1, the first turbine 2, and the first electric motor 3 which are axially coupled to each other, and the first turbine 2 and / or the first electric motor 3 is provided. Is an electric turbocharger that rotationally drives the first compressor 1 by the power of.
- the first turbocharger K1 compresses the outside air in the first stage by the first compressor 1 and supplies it to the second turbocharger K2.
- the first compressor 1 and the first electric motor form a first electric compressor.
- the first compressor 1 in the first turbocharger K1, the first compressor 1 is axially coupled to the first turbine 2 and the first electric motor 3, and is centrifugally compressed by the power of the first turbine 2 and / or the first electric motor 3. It is a machine.
- the first compressor 1 compresses the outside air in the first stage and supplies it to the second turbocharger K2.
- the first turbine 2 is a power source that generates power by using compressed air input from the switch D as a working fluid, and supplies the air after power recovery to the switch D.
- the first electric motor 3 is a power source that generates power by being controlled and driven by the air conditioning control device S, and rotationally drives the first compressor 1.
- the second turbocharger K2 includes a second compressor 4, a second turbine 5 and a second electric motor 6 which are axially coupled to each other, and the power of the second turbine 5 and / or the second electric motor 6 causes the second compressor 4 to move. It is an electric turbocharger that drives to rotate.
- the second turbocharger K2 compresses the compressed air (first-stage compressed air) input from the first turbocharger K1 by the second compressor 2 in the subsequent stage and supplies the compressed air to the temperature regulator A.
- the second compressor 4 and the second electric motor 6 form a second electric compressor.
- the second compressor 4 is axially coupled to the second turbine 5 and the second electric motor 6, and is centrifugally compressed by the power of the second turbine 5 and / or the second electric motor 6. It is a machine.
- the second compressor 4 compresses compressed air (first-stage compressed air) to the latter stage and supplies the compressed air (second-stage compressed air) to the temperature controller A.
- the second turbine 5 is a power source that generates power by using the temperature-adjusted compressed air (temperature-controlled compressed air) input from the temperature controller A as a working fluid, and switches the temperature-controlled compressed air after power recovery. Supply to D.
- the second electric motor 6 is a power source that generates power by being controlled and driven by the air conditioning control device S, and rotationally drives the second compressor 4.
- such a basic unit U includes two electric turbochargers, that is, a first turbocharger K1 and a second turbocharger K2 that are connected in series to the air flow path. More specifically, the first compressor 1 of the first turbocharger K1 and the second compressor 4 of the second turbocharger K2 have an air flow in which outside air or compressed air (first-stage compressed air, second-stage compressed air) flows. Connected in series to the road.
- the aircraft includes an inlet that takes in outside air from the outside of the aircraft into the inside of the aircraft, and an outlet that discharges temperature-controlled compressed air from the inside of the aircraft to the outside of the aircraft.
- the number of entrances is not limited to one, and the number of exits is not limited to one.
- the temperature adjuster A is a temperature adjusting device that adjusts the temperature of the compressed air (second stage compressed air) input from the second turbocharger K2 to a predetermined temperature.
- the temperature controller A supplies temperature-controlled compressed air to the second turbine 5.
- Such a temperature adjuster A is, for example, a heat source that generates a heat medium of a predetermined temperature and a heat exchanger that adjusts the temperature to a predetermined temperature by exchanging heat between the heat medium and the compressed air.
- the heat medium is outside air, for example.
- the switching device D includes a first switching valve 7, a check valve 8 and a second switching valve 9 as shown in the drawing, and has a basic unit U and a passenger compartment X (a space to be conditioned) according to an operation mode of an air conditioner for an aircraft.
- the first switching valve 7 is a control valve whose opening / closing operation is controlled by the air conditioning controller S, and includes one input port and two output ports.
- the first switching valve 7 selectively outputs the temperature-controlled compressed air input from the second turbine 5 to the first output port p1 communicating with the passenger compartment X or the second output port p2 communicating with the first turbine 2. Output.
- the temperature-controlled compressed air supplied from the first switching valve 7 to the passenger compartment X is the conditioned air in the present embodiment.
- the check valve 8 is an opening / closing valve provided between the second output port p2 of the first switching valve 7 and the passenger compartment X, and opens / closes autonomously according to the pressure relationship between the two. That is, the check valve 8 is opened only when the pressure in the passenger compartment X exceeds the pressure of the second output port p2 of the first switching valve 7 by a predetermined pressure or more, and is closed otherwise. To maintain.
- the second switching valve 9 is a control valve whose opening / closing operation is controlled by the air conditioning control device S, and has one input port and two output ports.
- the second switching valve 9 selectively outputs the temperature-controlled compressed air input from the first turbine 2 to the first output port p3 communicating with the passenger compartment X or the second output port p4 communicating with the outside of the machine. ..
- the temperature-controlled compressed air supplied from the second switching valve 9 to the passenger compartment X is the conditioned air in the present embodiment.
- the air conditioning control device S is a control device that controls the basic unit U and the temperature controller A.
- This control device is a computer, and memory such as CPU (Central Processing Unit), RAM (Random Access Memory) and ROM (Read Only Memory), and storage device such as SSD (Solid State Drive) and HDD (Hard Disc Drive), Etc.
- CPU Central Processing Unit
- RAM Random Access Memory
- ROM Read Only Memory
- storage device such as SSD (Solid State Drive) and HDD (Hard Disc Drive), Etc.
- the aircraft air conditioner according to the present embodiment has two operation modes according to the state of the aircraft, the air conditioning controller S controls the basic unit U and the temperature controller A according to the above operation modes.
- the above two operation modes are a ground / air-conditioned space energy non-recovery mode (first operation mode) and a sky / air-conditioned space energy recovery mode (second operation mode).
- the first operation mode is an operation mode corresponding to a case where the aircraft is on the ground, that is, a state where the outside air pressure is relatively high.
- the second operation mode is an operation mode corresponding to the case where the aircraft is in the sky, that is, the state where the outside air pressure is relatively low.
- the air conditioning control device S controls the basic unit U and the temperature adjuster A as follows according to the first operation mode or the second operation mode.
- FIG. 3 is a schematic diagram showing the state of the basic unit U in the first operation mode.
- the air conditioning control device S operates the first electric motor 3 and the second electric motor 6 to rotationally drive the first compressor 1 and the second compressor 4, and at the same time, the input port of the first switching valve 7.
- the check valve 8 maintains the closed state.
- the outside air is compressed by the first compressor 1 and the second compressor 4 and the temperature is adjusted by the temperature adjuster A, and is supplied to the second turbine 5 as temperature adjusted compressed air. Since this temperature-controlled compressed air functions as a working fluid for the second turbine 5, a part of the thermal energy of the temperature-controlled compressed air is recovered by the second turbine 5, and the second electric motor 6 is assisted as an auxiliary power source. To do.
- the temperature-controlled compressed air after power recovery is supplied to the first turbine 2 via the first switching valve 7.
- the temperature-controlled compressed air whose power is recovered by the second turbine 5 is recovered by the first turbine 2 and assists the first electric motor 3 as an auxiliary power source.
- the temperature-controlled compressed air whose power is recovered by the first turbine 2 is supplied to the passenger compartment X via the second switching valve 9. Then, the temperature-controlled compressed air is discharged from the cabin X to the outside of the aircraft.
- the temperature-controlled compressed air discharged from the cabin X may be used for cooling the heating circuit such as the power converter, instead of directly discharging the temperature-controlled compressed air from the cabin X to the outside of the aircraft. That is, the exhaust flow path provided between the passenger compartment X and the outflow valve provided in the airframe is laid so as to pass through the heat generating circuit, and the compressed air heated by cooling the heat generating circuit is discharged to the outside of the machine. May be released.
- FIG. 4 is a schematic diagram showing the state of the basic unit U in the second operation mode in the first operation mode.
- the air conditioning control device S operates the second electric motor 6 to rotationally drive only the second compressor 4. Further, the air conditioning controller S connects the input port of the first switching valve 7 to the first output port p1 and the input port of the second switching valve 9 to the second output port p4.
- the compressed air temperature at the outlet of the second compressor 4 is significantly higher than the desired air temperature to be supplied to the cabin X regardless of whether the airplane is on the ground or in the sky.
- the temperature controller A cools it sufficiently. It's difficult.
- the temperature controller A can sufficiently cool the outside air without increasing the compression rate to the same level as when the airplane is on the ground. .. In such a situation, in the second operation mode, only the second electric motor 6 is operated and only the second compressor 4 is driven.
- the first electric motor 3 does not function as a power source but the first electric motor 3 functions as a generator, that is, a power source.
- the pressure of the second output port p2 of the first switching valve 7 is sufficiently lower than the pressure of the passenger compartment X, so the check valve 8 is opened.
- the outside air is compressed by the first compressor 1 and the second compressor 4 and the temperature is adjusted by the temperature adjuster A, and is supplied to the second turbine 5 as temperature adjusted compressed air.
- the temperature-controlled compressed air assists the second electric motor 6 as an auxiliary power source by recovering the power of the second turbine 5.
- the temperature-controlled compressed air after power recovery is supplied to the passenger compartment X via the first switching valve 7.
- the compressed air in the cabin X flows into the first turbine 2 via the check valve 8 and acts on the first turbine 2 as a working fluid to generate power.
- the first electric motor 3 functions as a generator that is rotationally driven by the power of the first turbine 2, and generates electric power.
- the compressed air after the power recovery discharged from the first turbine 2 is discharged to the outside of the machine via the second switching valve 9.
- regenerative electric power is generated by the first electric motor 3 by recovering a part of the thermal energy of the compressed air in the passenger compartment X.
- the compressed air in the passenger compartment X is used for cooling a heat generating circuit such as an electric power converter, and the compressed air heated in the heat generating circuit ( Heated compressed air), that is, heated compressed air whose heat energy has been increased by the heat generating circuit, may flow into the first turbine 2.
- a heat generating circuit such as an electric power converter
- the aircraft air conditioner provided in the aircraft includes the two electric compressors (the first compressor 1 and the first electric motor) that are connected in series to the air flow path. 3 and a plurality of basic units U1 to U6 each provided with a second compressor 4 and a second electric motor 6), and the air discharged from the compressors (second compressor 4) of the two electric compressors.
- a temperature adjuster A for adjusting temperature, a plurality of basic units U1 to U6 and a controller S for controlling the temperature adjuster A are provided, and each of the plurality of basic units U1 to U6 is the temperature adjuster.
- the compressed air discharged from A is supplied to the air-conditioned space X as conditioned air.
- control device S controls the two electric compressors (the first compressor 1 and the first electric motor 3, and the second compressor 4 and the second electric motor 6) to be two electric motors (the first electric motor 3, And the second electric motor 6) is individually controlled. Further, the two electric compressors and the two electric compressors (the first compressor 1 and the first electric motor 3, and the second compressor 4 and the second electric motor 6) are axially coupled to each other.
- the turbines (the first turbine 2 and the second turbine 5) constitute two electric turbochargers K1 and K2, and the two turbines (the first turbine 2 and the second turbine 5) are separated from the conditioned air. Perform energy recovery.
- each of the plurality of basic units U1 to U6 is a switch D for switching the connection relationship between the two turbines (first turbine 2 and second turbine 5) and the air-conditioned space X according to an operation mode. Equipped with.
- the switch D is controlled so as to supply the conditioned air to the air-conditioned space X.
- the two electric compressors (the first compressor 1 and the first electric motor 3, and the second compressor 4 and the second electric motor 6) are the first electric compressor (the first compressor 1 and the first electric motor).
- the two turbines (the first turbine 2 and the second turbine 5) are connected to the first electric compressor (the first compressor 1 and the first electric motor 3) by axial coupling.
- a second turbine 5 that is axially coupled to the second electric compressor (the second compressor 4 and the second electric motor 6), and the control device S causes the aircraft to be in the sky in the operation mode.
- the conditioned air after energy recovery by the second turbine 5 The switching device D is controlled so that the conditioned air recovered from the air-conditioned space X and recovered from the air-conditioned space X is supplied to the first turbine 2, and the first electric compressor (first compression)
- the electric motor (first electric motor 3) of the machine 1 and the first electric motor 3) functions as a generator.
- first turbocharger K1 and the second turbocharger K2 since the basic unit U compresses the outside air by the cooperation of the first turbocharger K1 and the second turbocharger K2, two electric turbochargers are used instead of one electric turbocharger. (First turbocharger K1 and second turbocharger K2) are connected in series to the air flow path. As a result, the first turbocharger K1 and the second turbocharger K2 can be configured to be relatively small.
- the present embodiment it is possible to install more basic units U than the number of conventional systems without increasing the installation volume. Therefore, the redundancy can be increased as compared with the conventional one without increasing the installation volume. Further, according to the present embodiment as described above, it is possible to reduce the compression load of the first turbocharger K1 and the second turbocharger K2.
- the air conditioning control device S individually controls the first electric motor 3 of the first turbocharger K1 and the second electric motor 6 of the second turbocharger K2. Therefore, it is possible to easily change the sharing of the first compressor 1 and the second compressor 4. That is, the sharing of the first compressor 1 and the second compressor 4 can be easily changed without changing the flow rates of the air flowing into the first compressor 1 and the second compressor 4 by switching the pipes and the like. As a result, it is possible to easily deal with fluctuations in the external atmospheric pressure.
- the present disclosure is not limited to the above-described embodiment, and the following modified examples can be considered.
- the cabin X is the air-conditioned space
- the present disclosure is not limited to this.
- the cargo room in which the cargo is housed is the air-conditioned space. That is, the aircraft to which the present disclosure is applied is not limited to passenger aircraft, and can be applied to various types of aircraft.
- the basic unit U including the two electric turbochargers that is, the first turbocharger K1 and the second turbocharger K2 is adopted, but the present disclosure is not limited to this.
- a basic unit including two electric compressors may be adopted. That is, it is possible to employ a basic unit that includes a first electric compressor that includes the first compressor 1 and the first electric motor 3, and a second electric compressor that includes the second compressor 4 and the second electric motor 6. It is possible. In this case, since power recovery by the first turbine 2 or the second turbine 5 is not performed at all, the compressed air output from the temperature controller A is directly supplied to the passenger compartment X (air-conditioned space) as conditioned air. And discharged from the cabin X (air-conditioned space) to the outside of the aircraft.
- the switch D including the first switching valve 7, the check valve 8 and the second switching valve 9 is adopted, but the present disclosure is not limited to this. There may be various forms of the configuration method of the switching device in the present disclosure.
- the temperature controller A is installed at the outlet of the second compressor 4, but another temperature controller B may be installed at the outlet of the first compressor 1.
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- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Control Of Multiple Motors (AREA)
- Air Conditioning Control Device (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
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Abstract
Description
なお、航空機は、機外から機内に外気を取り込む入口と、機内から機外に温調圧縮空気を排出する出口とを備え、空気流路は、入口と出口とを結ぶ流路である。なお、入口は1つとは限らず、出口も1つとは限らない。
A 温度調整器
K1 第1ターボチャージャ(電動ターボチャージャ)
K2 第2ターボチャージャ(電動ターボチャージャ)
D 切替器
S 空調制御装置
X 客室(被空調空間)
1 第1圧縮機
2 第1タービン
3 第1電動機
4 第2圧縮機
5 第2タービン
6 第2電動機
7 第1切換弁
8 逆止弁
9 第2切換弁
Claims (6)
- 航空機に設けられる航空機用空調装置であって、
空気流路に対して直列接続された2台の電動圧縮機を各々に備える複数の基本ユニットと、
前記2台の電動圧縮機の圧縮機から排出される空気の温度を調整する温度調整器と、
前記複数の基本ユニット及び前記温度調整器を制御する制御装置と、
を備え、
前記複数の基本ユニットの各々は、前記温度調整器から排出される圧縮空気を調和空気として被空調空間に供給する航空機用空調装置。 - 前記制御装置は、前記2台の電動圧縮機の2台の電動機を個別に制御する請求項1に記載の航空機用空調装置。
- 前記2台の電動圧縮機と、前記2台の電動圧縮機とそれぞれ軸結合する2台のタービンとは、2台の電動ターボチャージャを構成し、 前記2台のタービンは、前記調和空気からエネルギ回収を行う請求項1または2に記載の航空機用空調装置。
- 前記複数の基本ユニットの各々は、動作モードに応じて前記2台のタービンと前記被空調空間との接続関係を切り替える切替器を備える請求項3に記載の航空機用空調装置。
- 前記制御装置は、前記動作モードのうち前記航空機が地上にある状態に対応する第1動作モードにおいて、前記2台のタービンでエネルギ回収した後の前記調和空気を前記被空調空間に供給するように、前記切替器を制御する請求項4に記載の航空機用空調装置。
- 前記2台の電動圧縮機は、第1電動圧縮機と、前記空気流路において前記第1電動圧縮機よりも下流側に位置する第2電動圧縮機とから構成され、
前記2台のタービンは、前記第1電動圧縮機と軸結合する第1タービンと、前記第2電動圧縮機と軸結合する第2タービンとから構成され、
前記制御装置は、前記動作モードのうち前記航空機が上空にある状態に対応する第2動作モードにおいて、前記第2タービンでエネルギ回収した後の前記調和空気を前記被空調空間に供給し、前記被空調空間から回収した前記調和空気を前記第1タービンに供給するように、前記切替器を制御し、前記第1電動圧縮機の電動機を発電機として機能させる請求項4または請求項5に記載の航空機用空調装置。
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EP19882285.0A EP3878749B1 (en) | 2018-11-06 | 2019-07-05 | Aircraft air conditioning device |
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