JPH0757637B2 - Air conditioning system for aircraft - Google Patents
Air conditioning system for aircraftInfo
- Publication number
- JPH0757637B2 JPH0757637B2 JP1032023A JP3202389A JPH0757637B2 JP H0757637 B2 JPH0757637 B2 JP H0757637B2 JP 1032023 A JP1032023 A JP 1032023A JP 3202389 A JP3202389 A JP 3202389A JP H0757637 B2 JPH0757637 B2 JP H0757637B2
- Authority
- JP
- Japan
- Prior art keywords
- outside air
- air
- heat exchanger
- turbine
- circulation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000004378 air conditioning Methods 0.000 title claims description 9
- 230000001143 conditioned effect Effects 0.000 claims description 21
- 238000001816 cooling Methods 0.000 claims description 13
- 239000003507 refrigerant Substances 0.000 claims description 9
- 230000008929 regeneration Effects 0.000 claims description 7
- 238000011069 regeneration method Methods 0.000 claims description 7
- 239000002826 coolant Substances 0.000 claims description 2
- 239000003344 environmental pollutant Substances 0.000 description 4
- 231100000719 pollutant Toxicity 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000000356 contaminant Substances 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000002730 additional effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000002528 anti-freeze Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013529 heat transfer fluid Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000000746 purification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
- 230000004043 responsiveness Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- 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
- B64D2013/0603—Environmental Control Systems
Landscapes
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Description
【発明の詳細な説明】 ［産業上の利用分野］ 本発明は、コクピットやキャビンなどの与圧室に調和空
気を供給するために利用される航空機用空気調和システ
ムに関するものである。Description: TECHNICAL FIELD The present invention relates to an air conditioning system for an aircraft used for supplying conditioned air to a pressure chamber such as a cockpit or a cabin.
［従来の技術］ 航空機のターボエンジンは、ケース内に燃焼器を挾んで
単軸結合されたタービンとコンプレッサとを配置してお
り、燃焼器によってタービンを回し、その動力でコンプ
レッサを駆動し外気を取込んで圧縮するものである。こ
の際、タービン後方に噴射されるブリードエアのスラス
ト力によって、機体に推力が得られるようになってい
る。[Prior Art] In a turbo engine of an aircraft, a turbine and a compressor that are uniaxially coupled with a combustor sandwiched in a case are arranged. The turbine is rotated by the combustor, and the compressor drives the compressor to remove outside air. It is something that is taken in and compressed. At this time, the thrust force of the aircraft is obtained by the thrust force of the bleed air injected to the rear of the turbine.
一方、従来の空気調和システムは、そのようなエンジン
からコンプレッサ抽気の一部を取出し、これを調和して
与圧室に呼吸用空気として供給するようにしている。こ
のために、エンジン抽気を別途に取込んだ外気（ラムエ
ア）によって冷却する熱交換器と、この熱交換器を通過
した抽気を断熱膨脹によって更に冷却するタービンとを
備えており、タービンで冷却された低温空気をエンジン
から直接バイパスさせた高温抽気と適度に混合して調和
空気をつくるようにしている。On the other hand, the conventional air conditioning system takes out a part of the compressor bleed air from such an engine and harmonizes it to supply it to the pressure chamber as breathing air. For this purpose, a heat exchanger for cooling the engine bleed air by the outside air (ram air) separately taken in and a turbine for further cooling the bleed air passing through this heat exchanger by adiabatic expansion are provided, and are cooled by the turbine. The low temperature air is mixed with the high temperature bleed air bypassed directly from the engine to create conditioned air.
［発明が解決しようとする課題］ ところで、近年の航空機は急速な勢いで高性能化が進
み、さらに可及的な高運動能力、軽量化、安全性などが
求められている。しかるに、このような航空機に上述し
た現行の空調システムを適用する場合、大きく次の３つ
の問題が生じる。第１はエンジン出力が低下する問題で
ある。既述のように、エンジンはタービン後方に噴射さ
れるブリードエアのスラスト力によって、機体に推力が
得られるようになっている。しかし、ブリードエアの一
部を抽出してしまうと、タービン後方に噴射されるブリ
ードエア量が減少するので、推力の低下は免れ得なくな
り、高性能化を達成する上で致命的欠陥となってしま
う。[Problems to be Solved by the Invention] By the way, in recent years, aircraft have been rapidly increasing in performance, and further, high exercise capacity, weight reduction, and safety have been demanded. However, when the above-mentioned existing air conditioning system is applied to such an aircraft, the following three problems occur. The first is a problem that the engine output decreases. As described above, the engine is configured to obtain thrust on the airframe by the thrust force of the bleed air injected to the rear of the turbine. However, if a part of the bleed air is extracted, the amount of bleed air injected to the rear of the turbine will decrease, and a reduction in thrust cannot be avoided, which is a fatal defect in achieving high performance. I will end up.
また、第２の問題は、適量の調和空気を与圧室にコンス
タントに供給するのが容易ではないという点である。す
なわち、コンプレッサの回転は航空機の高加速や急減速
など、飛行状態に伴って大きく変化するため、抽気量
（抽気温度）がその都度一定しない。このため、多数の
バルブ類等を用いて応答性の高い流量（温度）制御を行
う必要があり、系の複雑化、重量増加を招くことは避け
難い。The second problem is that it is not easy to constantly supply an appropriate amount of conditioned air to the pressure chamber. That is, since the rotation of the compressor changes greatly with the flight conditions such as high acceleration and rapid deceleration of the aircraft, the extraction amount (extraction temperature) is not constant each time. Therefore, it is necessary to control the flow rate (temperature) with high responsiveness using a large number of valves, and it is inevitable that the system becomes complicated and the weight increases.
さらに、第３の問題として、調和空気に汚染物質が混入
し易い欠点が挙げられる。すなわち、現行のシステムは
上述したエアサイクルによってエンジン抽気を適温に
し、それをフィルタ等で浄化した後に、与圧室に供給す
るようにしている。しかし、放射能を始め、化学物質や
生物物質など人体に有害な汚染空域を飛行する場合、フ
ィルタはこれらを捕獲できないため、それが調和空気に
混入して人体に悪影響を及ぼす恐れがある。Further, as the third problem, there is a drawback that pollutants are easily mixed in the conditioned air. That is, the current system makes the engine bleed air have an appropriate temperature by the above-mentioned air cycle, purifies it by a filter or the like, and then supplies it to the pressurizing chamber. However, when flying in a contaminated airspace that is harmful to the human body, such as radioactivity, chemical substances and biological substances, the filter cannot capture them, which may mix with the conditioned air and adversely affect the human body.
本発明は、このような種々の問題点に着目してなされた
ものであって、これらを同時に解決することを目的とし
ている。The present invention has been made by paying attention to such various problems, and an object thereof is to solve these problems at the same time.
［課題を解決するための手段］ 本発明は、かかる目的を達成するために、次のような構
成を採用したものである。[Means for Solving the Problems] The present invention adopts the following configuration in order to achieve such an object.
すなわち、本発明の空気調和システムは、外気をエンジ
ンを介さずに吸入圧縮する電動コンプレッサと、この電
動コンプレッサにより昇温昇圧された外気を冷却する第
１の熱交換器と、この熱交換器により冷却された外気を
更に断熱膨脹によって冷却するタービンと、与圧室の調
和空気を循環させるために配設した循環系路と、この循
環系路内を流通する調和空気を前記タービンから排出さ
れる外気によって冷却する第２の熱交換器とを具備して
なることを特徴としている。That is, the air conditioning system of the present invention includes an electric compressor that sucks and compresses outside air without passing through the engine, a first heat exchanger that cools the outside air whose temperature is raised by the electric compressor, and this heat exchanger. A turbine that further cools the cooled outside air by adiabatic expansion, a circulation path that is arranged to circulate the conditioned air in the pressure chamber, and conditioned air that circulates in the circulation path is discharged from the turbine. It is characterized by comprising a second heat exchanger which is cooled by outside air.
また、このような基本システムを更に有効利用するため
には、与圧室以外の部位を冷却するための冷媒を循環さ
せる第２の循環系路と、この循環系路内を流通する冷媒
を前記タービンから排出される外気によって冷却する第
３の熱交換器とを付加してなる構成や、循環系路と熱交
換を終えた外気を前記第１の熱交換器に導入するための
再生系路を設け、これによりその外気を新たに取込まれ
る外気と再生熱交換させるような構成を併用すると好都
合である。Further, in order to make more effective use of such a basic system, a second circulation system passage for circulating a coolant for cooling a region other than the pressurizing chamber and a refrigerant circulating in the circulation system passage are described above. A configuration in which a third heat exchanger that cools by the outside air discharged from the turbine is added, and a regeneration system path for introducing the outside air that has completed heat exchange with the circulation system path into the first heat exchanger It is convenient to use a structure in which the outside air is regenerated and heat exchanged with the outside air newly taken in.
なお、本明細書における限り、「与圧室」とはキャビン
やコクピットなど調和空気を必要とする箇所を指称し、
「与圧室以外の部位」とは機内の与圧室でない箇所は勿
論のこと、たとえ与圧室内であっても調和空気の不要な
機器類の配設場所などを含めて実質的に解釈されるもの
とする。Incidentally, as long as in the present specification, the "pressurization chamber" refers to a place requiring conditioned air, such as a cabin or cockpit,
"Parts other than the pressurizing chamber" is understood to include not only the part that is not the pressurizing chamber in the aircraft, but also the places where equipment that does not require conditioned air is installed even in the pressurizing chamber. Shall be.
［作用］ エンジン以外の部位から外気を吸入するようにすれば、
ブリードエアを減少させることがないので、エンジンパ
ワーの低下は生じない。これにより、第１の問題点は確
実に解消することができる。また、循環系路内には常時
一定の調和空気を流通させておくことができるので、与
圧室への供給量の一定化が果たされる。しかも、取込ん
だ外気は調和空気としてではなく、その調和空気を間接
冷却するための冷媒として主に利用されるだけなので、
汚染物質が混入する恐れも少ない。したがって、第２、
第３の問題点も同時に克服し得るものとなる。[Operation] If outside air is sucked in from a part other than the engine,
Since the bleed air is not reduced, the engine power will not be reduced. As a result, the first problem can be reliably solved. Further, since a certain amount of conditioned air can always be circulated in the circulation system passage, the supply amount to the pressurizing chamber can be made constant. Moreover, the outside air taken in is mainly used not as conditioned air but as a refrigerant for indirectly cooling the conditioned air.
There is little risk of contaminants getting mixed in. Therefore, the second,
The third problem can be overcome at the same time.
さらに、第２の熱交換器で熱交換を終えて出てきた外気
は尚もって低温状態にあることから、これを第３の熱交
換器で与圧室以外の部位を冷却するために用い、さら
に、再生系路を通じて第１の熱交換器に帰還し新たに取
込まれる外気を冷却するために用いれば、システム効率
の向上につながる。Furthermore, since the outside air that has exited after the heat exchange in the second heat exchanger is still in a low temperature state, this is used to cool the parts other than the pressurizing chamber in the third heat exchanger, Further, if it is used to cool the outside air that is returned to the first heat exchanger through the regeneration system and is newly taken in, it will lead to improvement in system efficiency.
［実施例］ 以下、本発明の一実施例を図面を参照して説明する。[Embodiment] An embodiment of the present invention will be described below with reference to the drawings.
第１図は本実施例の空気調和システムであり、図中破線
及び矢印は機外から取込んだ外気が流通するラインを示
している。このラインに沿って基本的な構成を説明する
と、外気をエンジン以外の部位（後述する吸気口72）か
ら吸入圧縮する電動コンプレッサ１と、この電動コンプ
レッサ１により昇温昇圧された外気を冷却する第１の熱
交換器（初段）２と、この熱交換器２によって降温した
外気を再度圧縮するコンプレッサ３と、これにより圧縮
された外気を冷却する第１の熱交換器（次段）４と、こ
の熱交換器４により冷却された外気を更に断熱膨脹によ
って冷却するタービン５とを備えており、このタービン
５を出たところで、外気は例えば０℃以下の低温となる
ように設定されている。FIG. 1 shows the air conditioning system of this embodiment, and the broken lines and arrows in the drawing show the lines through which the outside air taken in from outside the machine flows. The basic configuration will be described along this line. An electric compressor 1 that sucks and compresses outside air from a part other than the engine (intake port 7 2 described later), and the outside air whose temperature is raised by the electric compressor 1 is cooled. A first heat exchanger (first stage) 2, a compressor 3 for re-compressing the outside air cooled by the heat exchanger 2, and a first heat exchanger (next stage) 4 for cooling the outside air compressed by the heat exchanger 2. And a turbine 5 for further cooling the outside air cooled by the heat exchanger 4 by adiabatic expansion. When the turbine 5 exits, the outside air is set to have a low temperature of 0 ° C. or less, for example. .
電動コンプレッサ１は、コントローラ等によって飛行高
度に応じて駆動力を可変制御されるようにしてあり、常
時一定の外気を取込み得るようになっている。また、タ
ービン５と前記コンプレッサ３とはシャフト６によって
単軸結合されており、膨脹仕事がタービン５に与える発
生動力でコンプレッサ３が駆動されるようにしてある。
さらに、機体には外気を取込んで排出するための一対の
吸気口71、72および排気口81、82が設けてあり、吸気口
71と排気口81とを初段の熱交換器２を介し外気流路91に
よって接続するとともに、吸気口72と排気口82とを次段
の熱交換器４を介し外気流路92によって接続している。The electric compressor 1 is configured to variably control the driving force according to the flight altitude by a controller or the like, and can always take in constant outside air. Further, the turbine 5 and the compressor 3 are uniaxially connected by a shaft 6, and the compressor 3 is driven by the generated power given to the turbine 5 by the expansion work.
Furthermore, the airframe is provided with a pair of intake ports 7 1 , 7 2 and exhaust ports 8 1 , 8 2 for taking in and discharging outside air.
7 1 and the exhaust port 8 1 are connected by the outside air flow passage 9 1 via the first stage heat exchanger 2, and the intake port 7 2 and the exhaust port 8 2 are connected via the next stage heat exchanger 4 to the outside air flow passage. Connected by 9 2 .
一方、この航空機の与圧室であるキャビン10には、図中
実線（太線）で示すような循環系路11が設けてあり、系
路途中に介設したファン12によってキヤビン10内の空気
を強制循環させ得るように設けてある。そして、この循
環系路11内を流通する調和空気を前記タービン５から排
出される外気によって冷却するために、第２の熱交換器
13を配置して両者を熱交換させるようにしている。な
お、前記タービン５から排出された外気の一部はフィル
タ18を通じて循環系路11に適宜取り込まれるようになっ
ている。フィルタ18には従来に比してより精密な汚染物
質除去機能を有したものが用いられる。On the other hand, the cabin 10 which is the pressurizing chamber of this aircraft is provided with the circulation path 11 as shown by the solid line (thick line) in the figure, and the air inside the cabin 10 is blown by the fan 12 provided in the middle of the path. It is provided to allow forced circulation. Then, in order to cool the conditioned air flowing in the circulation path 11 by the outside air discharged from the turbine 5, the second heat exchanger is used.
13 is arranged to exchange heat between them. A part of the outside air discharged from the turbine 5 is appropriately taken into the circulation path 11 through the filter 18. As the filter 18, a filter having a more precise pollutant removal function than the conventional one is used.
また、この航空機は与圧室以外の部位に多数のアビオニ
クス（航空機搭載用電子機器）14が装備されており、こ
れらのアビスオニクス14を不凍液などの冷媒によって冷
却するために、機内に、図中二点鎖線に示すような第２
の循環系路15を敷設している。そして、この循環系路15
内を流通する冷媒を前記タービン５から排出される外気
によって冷却するために、前記第２の熱交換器13の下流
にさらに第３の熱交換器16を配置して両者を熱交換させ
るようにしている。In addition, this aircraft is equipped with a large number of avionics (electronic equipment for mounting on aircraft) 14 in parts other than the pressurizing chamber. In order to cool these avionics 14 with a refrigerant such as antifreeze, in the figure, Second as shown by the chain double-dashed line
Circulation system path 15 is laid. And this circulation path 15
In order to cool the refrigerant flowing in the inside by the outside air discharged from the turbine 5, a third heat exchanger 16 is further arranged downstream of the second heat exchanger 13 to exchange heat between them. ing.
以上のようにして、取込まれた外気は図中破線に示すラ
インに沿って流通し両循環系路11、15を冷却し得るわけ
であるが、その低温外気をさらに有効利用するために、
前記第３の熱交換器16の出口を破線（太線）に示す再生
系路171、172によってそれぞれ外気流路91、92と接続
し、サイクルを終えた外気を前記第１の熱交換器２、４
に送り込むようにしている。As described above, the taken-in outside air can flow along the line shown by the broken line in the figure to cool both circulation system paths 11 and 15, but in order to further effectively use the low-temperature outside air,
The outlet of the third heat exchanger 16 is connected to the outside air flow passages 9 1 and 9 2 by regeneration system passages 17 1 and 17 2 shown by a broken line (thick line), respectively, and the outside air that has finished the cycle is connected to the first heat exchanger. Exchangers 2, 4
I am sending it to.
しかして、このような構成であると、吸気口71、72から
電動コンプレッサ１によってエンジンを介さずに外気が
吸入されるので、ブリードエアを減少させることがな
く、エンジンのパワーの低下を招来せずに機外から一定
して十分な空気を摂取することが可能となる。また、循
環系路11内には常時一定の調和空気が流通可能となり、
航空機が急加速、急減速などを行ってもその流通量は変
化しないばかりか、外気温度が急激に変化しても、流通
空気温度がそれによって急激に変化するようなことはな
くなる。このため、キャビン10への調和空気の供給量お
よび温度が安定化し、制御も比較的容易となるので、従
来のような複雑な流量制御機構が不要となり系の小型軽
量化に奏効する。しかも、取込んだ外気は、フィルタ18
を介して補充する以外は調和空気を間接冷却するための
冷媒として利用されるだけであり、フィルタ18において
も従来のように大量の空気が流通しないため、浄化機能
の優れたものを用いても圧損等の不都合が生じることは
ない。したがって、汚染物質が与圧室に混入することを
好適に防止することができる。また、フィルタ18にO2だ
けを選択分離するようなものを用いれば、汚染物質の問
題を完全に解決することも可能である。このようにし
て、汚染空域の飛行も不都合なく行い得るものとなる。However, with such a configuration, the outside air is taken in from the intake ports 7 1 , 7 2 by the electric compressor 1 without passing through the engine, so that the bleed air is not reduced and the engine power is reduced. It is possible to constantly ingest sufficient air from outside the aircraft without inviting. Further, a constant conditioned air can always flow in the circulation system path 11,
Even if the aircraft undergoes sudden acceleration or deceleration, the flow rate does not change, and even if the outside air temperature changes rapidly, the circulating air temperature does not change suddenly. Therefore, the supply amount and temperature of the conditioned air to the cabin 10 are stabilized, and the control is relatively easy. Therefore, a complicated flow rate control mechanism as in the past is not required, which is effective in reducing the size and weight of the system. Moreover, the outside air taken in is filtered by the filter 18
It is only used as a refrigerant for indirectly cooling the conditioned air other than being replenished via, and even in the filter 18, since a large amount of air does not circulate as in the conventional case, even if a filter having an excellent purification function is used. No inconvenience such as pressure loss occurs. Therefore, it is possible to preferably prevent contaminants from entering the pressurizing chamber. Further, by using a filter that selectively separates only O 2, it is possible to completely solve the problem of pollutants. In this way, it is possible to fly in the contaminated airspace without inconvenience.
さらに、付加的な効果として、アビオニクス14の冷却の
ための各別な冷却手段を設ける必要がなくなる点があ
る。すなわち、極低温で冷却しなければならない特殊機
器はさておき、一般的な電子機器のオーバーヒートを防
止する程度の冷却であれば、第２の熱交換器13を通過し
た後の外気によって機器冷却用の冷媒を冷却するだけで
十分賄い得るからである。また、この第３の熱交換器16
を通過した後の外気温度においても、吸気口71、72から
新たに取込まれる外気よりも低くなると考えられるた
め、これを第１の熱交換器２、４に送り込むことによっ
て再生熱交換に供し、システム効率を向上することが可
能となる。Further, as an additional effect, it is not necessary to provide separate cooling means for cooling the avionics 14. That is, aside from special equipment that has to be cooled at an extremely low temperature, if the cooling is such that general electronic equipment is prevented from overheating, it is possible to cool equipment by the outside air after passing through the second heat exchanger 13. This is because it is sufficient to cover the refrigerant only. In addition, this third heat exchanger 16
It is considered that the outside air temperature after passing through is also lower than the outside air newly taken in through the intake ports 7 1 and 7 2 , so this is sent to the first heat exchangers 2 and 4 for regeneration heat exchange. It is possible to improve the system efficiency.
このように、調和空気を間接冷却するために構成した外
気の流通ラインを有効利用することによって、航空機全
体としての小型軽量化が更に促進される効果が得られ
る。As described above, by effectively utilizing the outside air distribution line configured to indirectly cool the conditioned air, it is possible to obtain the effect of further reducing the size and weight of the entire aircraft.
以上、本発明の一実施例について説明したが、各部の構
成は図示実施例に限定されるものではない。例えば、簡
単な他の実施例として第２図に示すような変形例が考え
られる。第１図との相違点を挙げると、同図では、前記
実施例のコンプレッサ３を省略して単体でタービンＴを
構成している。この場合、その発電で電動コンプレッサ
１を駆動するようにしてもよい。電動コンプレッサ１を
タービンＴと単軸結合して電動機の負担を軽減する方法
もある。また、第１図では第１の熱交換器を初段２と次
段４の二連構成にしているが、第２図では最少限１個の
熱交換器20で賄っている。この熱交換器20において再生
熱交換を行わせる場合、前半部20aで本来の熱交換を行
い、後半部20bで再生熱交換を行うようにしても効率的
である。173はこのための再生系路であり、93は外気流
路、21は冷媒移送用ポンプ、22は空気流入バルブであ
る。さらに、図示変形例以外にも、アビオニクス14の冷
媒に循環系路11の調和空気を一部分岐させて用いたり、
第２の循環系路15で水や空気などの適当な熱移動用流体
を用いたりすることは当然考えられることである。ま
た、電動コンプレッサ１に増速ギャを組込むといった工
夫も随所に行い得る。その他、各部の構成等も図示実施
例に限定されず、本発明の趣旨を逸脱しない範囲で種々
変形が可能である。Although one embodiment of the present invention has been described above, the configuration of each part is not limited to the illustrated embodiment. For example, a modified example shown in FIG. 2 can be considered as another simple example. The difference from FIG. 1 is that, in FIG. 1, the compressor 3 of the above-described embodiment is omitted and the turbine T is constituted by a single unit. In this case, the electric compressor 1 may be driven by the power generation. There is also a method of uniaxially coupling the electric compressor 1 with the turbine T to reduce the load on the electric motor. Further, in FIG. 1, the first heat exchanger has a double structure of the first stage 2 and the second stage 4, but in FIG. 2, it is covered by at least one heat exchanger 20. When regenerating heat exchange is performed in this heat exchanger 20, it is also efficient to perform original heat exchange in the first half portion 20a and regenerate heat exchange in the second half portion 20b. 17 3 is a regeneration system path for this purpose, 9 3 is an outside air flow path, 21 is a refrigerant transfer pump, and 22 is an air inflow valve. Further, in addition to the modification shown in the figure, the conditioned air of the circulation path 11 may be partly branched and used for the refrigerant of the avionics 14,
It is naturally conceivable to use an appropriate heat transfer fluid such as water or air in the second circulation path 15. Further, a device such as a speed increasing gear may be incorporated in the electric compressor 1 everywhere. In addition, the configuration of each unit is not limited to the illustrated embodiment, and various modifications can be made without departing from the spirit of the present invention.
［発明の効果］ 本発明の航空機用空気調和システムは、以上のような構
成によって、エンジン推力を低下させずに外気を取込む
ことができるので、高運動能力を阻害せずに済む。ま
た、循環系路から飛行状態によらず常時一定量、安定し
た温度の調和空気を与圧室に供給することができるの
で、システム制御が容易となり、その構成も簡略化でき
て小形軽量化にも奏効する。さらに、間接冷却構造によ
って与圧室への汚染物質の混入が回避されるので、汚染
空域の飛行にも支障が少なくなる。さらにまた、使用後
の外気を、システムの終段において更に与圧室以外の部
位の冷却や新たに取込まれた外気の再生冷却に利用する
ことによって、システム効率を向上させ、系の小形軽量
化を尚一層促進することができる。[Advantages of the Invention] With the above-described configuration, the aircraft air conditioning system of the present invention can take in outside air without lowering the engine thrust, and thus does not impede high exercise capacity. Also, since a constant amount of conditioned air with a stable temperature can always be supplied to the pressurizing chamber from the circulation system regardless of the flight conditions, system control becomes easy, and its configuration can be simplified and reduced in size and weight. Also works. Further, since the indirect cooling structure avoids the entry of pollutants into the pressurizing chamber, the flight in the contaminated airspace is less disturbed. Furthermore, by using the outside air after use to cool the parts other than the pressurizing chamber at the final stage of the system and to regenerate and cool the newly taken outside air, the system efficiency is improved and the system is small and lightweight. Can be further promoted.
第１図は本発明の一実施例を示す概略的な構成説明図、
第２図は他の実施例を示す模式的な構成説明図である。 １…電動コンプレッサ ２、４、20…第１の熱交換器 ５…タービン 10…与圧室（キャビン） 11…循環系路 13…第２の熱交換器 15…第２の循環系路 16…第３の熱交換器 171、172、173…再生系路FIG. 1 is a schematic configuration explanatory view showing an embodiment of the present invention,
FIG. 2 is a schematic configuration explanatory view showing another embodiment. 1 ... Electric compressor 2, 4, 20 ... First heat exchanger 5 ... Turbine 10 ... Pressurizing chamber (cabin) 11 ... Circulation system path 13 ... Second heat exchanger 15 ... Second circulation system path 16 ... Third heat exchanger 17 1 , 17 2 , 17 3 ... Regeneration path
Claims (3)
動コンプレッサと、この電動コンプレッサにより昇温昇
圧された外気を冷却する第１の熱交換器と、この熱交換
器により冷却された外気を更に断熱膨脹によって冷却す
るタービンと、与圧室の調和空気を循環させるために配
設した循環系路と、この循環系路内を流通する調和空気
を前記タービンから排出される外気によって冷却する第
２の熱交換器とを具備してなることを特徴とする航空機
用空気調和システム。1. An electric compressor that sucks and compresses outside air without passing through an engine, a first heat exchanger that cools the outside air whose temperature is raised by the electric compressor, and an outside air that is cooled by this heat exchanger. Furthermore, a turbine that cools by adiabatic expansion, a circulation system path that is arranged to circulate the conditioned air in the pressure chamber, and conditioned air that circulates in the circulation system path is cooled by the outside air discharged from the turbine. An air conditioning system for an aircraft, comprising: a heat exchanger (2).
循環させる第２の循環系路と、この循環系路内を流通す
る冷媒を前記タービンから排出される外気によって冷却
する第３の熱交換器とを付加したことを特徴とする請求
項１記載の航空機用空気調和システム。2. A second circulation system passage for circulating a coolant for cooling a portion other than the pressurizing chamber, and a third circulation passage for cooling the refrigerant circulating in the circulation passage by the outside air discharged from the turbine. The air conditioning system for an aircraft according to claim 1, further comprising:
の熱交換器に導入するための再生系路を設け、これによ
りその外気を新たに取込まれる外気と再生熱交換させる
ようにしたことを特徴とする請求項１又は２記載の航空
機用空気調和システム。3. The outside air which has finished heat exchange with the circulation path is first
The air conditioner for an aircraft according to claim 1 or 2, characterized in that a regeneration system passage for introducing into the heat exchanger of (1) is provided so that the outside air is regenerated through heat exchange with the newly introduced outside air. system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1032023A JPH0757637B2 (en) | 1989-02-10 | 1989-02-10 | Air conditioning system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1032023A JPH0757637B2 (en) | 1989-02-10 | 1989-02-10 | Air conditioning system for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH02212297A JPH02212297A (en) | 1990-08-23 |
| JPH0757637B2 true JPH0757637B2 (en) | 1995-06-21 |
Family
ID=12347266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1032023A Expired - Fee Related JPH0757637B2 (en) | 1989-02-10 | 1989-02-10 | Air conditioning system for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0757637B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6083354A (en) * | 1992-07-24 | 2000-07-04 | Matsushita Electric Industrial Co., Ltd. | Treatment method for diamonds |
| US7861968B2 (en) * | 2006-10-26 | 2011-01-04 | The Boeing Company | Air inlet and method for a highspeed mobile platform |
-
1989
- 1989-02-10 JP JP1032023A patent/JPH0757637B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH02212297A (en) | 1990-08-23 |
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| LAPS | Cancellation because of no payment of annual fees |