JPS622468Y2 - - Google Patents
Info
- Publication number
- JPS622468Y2 JPS622468Y2 JP11775581U JP11775581U JPS622468Y2 JP S622468 Y2 JPS622468 Y2 JP S622468Y2 JP 11775581 U JP11775581 U JP 11775581U JP 11775581 U JP11775581 U JP 11775581U JP S622468 Y2 JPS622468 Y2 JP S622468Y2
- Authority
- JP
- Japan
- Prior art keywords
- cooling
- heat insulating
- aircraft
- refrigerant
- cooling section
- 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
Links
- 238000001816 cooling Methods 0.000 claims description 63
- 239000003507 refrigerant Substances 0.000 claims description 19
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims description 18
- 235000011089 carbon dioxide Nutrition 0.000 claims description 15
- 235000013305 food Nutrition 0.000 claims description 5
- 239000010813 municipal solid waste Substances 0.000 claims description 4
- LYCAIKOWRPUZTN-UHFFFAOYSA-N Ethylene glycol Chemical compound OCCO LYCAIKOWRPUZTN-UHFFFAOYSA-N 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000001569 carbon dioxide Substances 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- WGCNASOHLSPBMP-UHFFFAOYSA-N hydroxyacetaldehyde Natural products OCC=O WGCNASOHLSPBMP-UHFFFAOYSA-N 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
Description
【考案の詳細な説明】
本考案は、航空機において乗客サービス用の食
品を冷却し、保存させる冷却装置に関するもので
ある。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a cooling device for cooling and preserving food for passenger service in an aircraft.
従来、航空機に用いられる冷却装置としては、
空冷循環方式とグリコール液を冷媒とする冷却方
式とが知られている。そのいづれの方式も圧縮機
によつてフレオンガスを循環させていた。しかし
ながら旅客機においては離陸後、高空に達する
と、−40℃程度の低温域の冷気中を飛行するの
で、機体外壁は常に−40℃という低温に冷却され
ているわけであり、この低温の外気を食品用冷却
装置に利用しようというこころみは従来より提案
されていたが、種々の問題点があるために現在ま
でに実用化されていなかつた。 Traditionally, cooling systems used in aircraft include:
An air cooling circulation system and a cooling system using glycol liquid as a refrigerant are known. Both systems circulated Freon gas using a compressor. However, when a passenger plane reaches high altitude after takeoff, it flies in cold air with a temperature of around -40℃, so the outer wall of the aircraft is always cooled to a low temperature of -40℃. Although attempts have been made to use it in food cooling devices, it has not been put to practical use to date due to various problems.
その実用化されない理由は、航空機が出発する
までの時間および離陸後に充分低温が得られる高
度に達するまでの時間、冷却源をどのようにして
確保するかという点に問題があるためである。こ
の問題の解決策として、冷却源が得られない時間
の間だけ補助的に機械的な圧縮機による冷却方式
も考えられるけれども、維持費が安くなつても設
備費や重量が増加する欠点がありこの方式も実用
化するに至つていない。 The reason why it is not put into practical use is that there are problems in how to secure a cooling source until the aircraft takes off and after takeoff until it reaches a sufficiently low altitude. As a solution to this problem, an auxiliary cooling method using a mechanical compressor can be considered only during times when a cooling source is not available, but this has the disadvantage of increasing equipment costs and weight even though maintenance costs are lower. This method has not yet been put into practical use.
したがつて、本考案の目的は、上空の飛行時に
は低温の外気を利用でき、その他のときには冷媒
で冷却できる航空機における冷却装置を提供する
にある。 SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide a cooling system for an aircraft that can utilize low-temperature outside air during overflight, and can be cooled with refrigerant at other times.
本考案によれば、乗客サービス用の食品を冷却
し、そして保存させる航空機用の冷却装置におい
て、冷却庫からの冷媒の循環ラインには第１受冷
部と第２受冷部とが接続されており、その第１受
冷部は航空機の外装板に設けられ、そしてその外
装板の内側に設けた伝熱板と、その伝熱板から離
れて設けた断熱板とで構成され、その伝熱板と断
熱板との間の空間には前記循環ラインの冷媒が送
り込まれ、また第２受冷部はギヤレーのゴミ収納
室内に設けられ、その第２受冷部はその周囲が断
熱板で包まれており、その断熱板内の空間に設け
た受冷板には冷媒の通路が形成され、かつ断熱板
内の空間にはドライアイスが充填されている。 According to the present invention, in an aircraft cooling device for cooling and preserving food for passenger service, a first cooling section and a second cooling section are connected to a refrigerant circulation line from a cooling store. The first cooling section is provided on the exterior panel of the aircraft, and consists of a heat transfer plate provided inside the exterior panel and a heat insulating plate provided apart from the heat transfer plate. The refrigerant of the circulation line is fed into the space between the heat plate and the heat insulating plate, and the second cold receiving part is provided in the garbage storage chamber of the gearlay, and the second cold receiving part is surrounded by a heat insulating board. A coolant passage is formed in the cold receiving plate provided in the space inside the heat insulating board, and the space inside the heat insulating board is filled with dry ice.
したがつて上空を飛行中は冷媒は第１受冷部に
おいて低温（例えば−40℃）の外気にさらさせる
外装板の低温が伝熱板に伝達され、冷媒は冷却さ
れる。そして上空でない場合、すなわち離陸前後
や着陸前後には冷媒は第２受冷部のドライアイス
によつて冷却される。 Therefore, while the refrigerant is flying in the sky, the low temperature of the exterior plate exposed to the low temperature (for example, -40° C.) outside air is transmitted to the heat transfer plate in the first cooling part, and the refrigerant is cooled. When the aircraft is not in the air, that is, before and after takeoff and before and after landing, the refrigerant is cooled by dry ice in the second cooling section.
第１受冷部においては外装板側から冷されて断
熱板によつて低温が維持され、また第２受冷部は
断熱板で囲まれているので、ドライアイスが不必
要に昇華しない。 In the first cold receiving part, the cooling is performed from the exterior plate side and the low temperature is maintained by the heat insulating plate, and the second cold receiving part is surrounded by the heat insulating plate, so that dry ice does not sublimate unnecessarily.
それ故にドライアイスを利用するのは比較的に
短時間であるからドライアイスの消費も少なく、
消費エネルギは最小限に止めることができる。そ
して本考案ではコンプレツサ等の機械的な装置が
必要としないので、軽量であり、航空機の重量の
軽減に資することができ、しかも冷却効果も充分
である。 Therefore, dry ice is used for a relatively short period of time, so the consumption of dry ice is low.
Energy consumption can be kept to a minimum. Since the present invention does not require a mechanical device such as a compressor, it is lightweight and can contribute to reducing the weight of the aircraft, and has a sufficient cooling effect.
以下本考案の実施例を図面を参照しつつ説明す
る。第１図は本考案を実施した航空機における冷
却装置のシステム図であり、１は冷媒の循環ライ
ンを示しており、第１受冷部Ａと第２受冷部Ｂと
が直列に連結されており、これら２つの受冷部
Ａ，Ｂで冷却された冷媒は供給管１ａを通つて冷
却ユニツトＣに送られ冷却庫としての機能を果す
ようになつている。冷却ユニツトＣで熱を受けた
冷媒は再び第１受冷部Ａと第２受冷部Ｂに送られ
冷却する。冷却ユニツトＣは冷却庫２を備え、こ
の冷却庫２で食品等を冷却させるようになつてい
る。また受冷部Ａ，Ｂと並列温度調節バルブ３が
もどりのライン１と供給ライン１ａとの間に接続
され、両ライン１，１ａの温度差を感知して自動
的に開閉し、もつて冷却ユニツトＣの排出冷気を
調節するようになつている。またこの温度調節バ
ルブ３に替えて温度感知器のみを設け、この感知
量に応じて受冷部Ａ，Ｂにおける受冷量を制御す
るように構成させることもできる。 Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is a system diagram of a cooling system in an aircraft in which the present invention is implemented, and 1 indicates a refrigerant circulation line, in which a first cooling section A and a second cooling section B are connected in series. The refrigerant cooled in these two cold receiving sections A and B is sent to a cooling unit C through a supply pipe 1a, and functions as a cooling store. The refrigerant that has received heat in the cooling unit C is sent again to the first cooling section A and the second cooling section B to be cooled. The cooling unit C includes a refrigerator 2, which is used to cool foods and the like. In addition, a parallel temperature control valve 3 is connected to the cooling sections A and B and is connected between the return line 1 and the supply line 1a, and automatically opens and closes by sensing the temperature difference between the two lines 1 and 1a, thereby cooling. It is designed to regulate the cold air discharged from unit C. It is also possible to provide only a temperature sensor instead of the temperature control valve 3, and to control the amount of cooled air received in the cooled portions A and B in accordance with the sensed amount.
次に第１受冷部Ａについて説明する。第２図お
よび第３図に示すように第１受冷部Ａは、航空機
の外装板４に密着して設けられ、外気にさらされ
る外装板４の内側に冷熱を伝えやすい伝熱板５
と、その伝熱板５から離れて設けた断熱板６で構
成されている。この伝熱板５と断熱板６との間の
空間部にはライン１から送られる冷媒７が送り込
まれるようになつている。したがつてこの第１受
冷部Ａは高圧を飛んでいる場合に用いるものであ
る。なお、この第１受冷部Ａは第２図に示すよう
に充分に冷媒７を冷す能力（例えば7000BTU／
HR）をもつように受冷面を広くし、かつ航空機
内の体積を有効に使うために広く、かつ薄く構成
させた方がよい。 Next, the first cooling section A will be explained. As shown in FIGS. 2 and 3, the first cold receiving part A includes a heat transfer plate 5 that is provided in close contact with the exterior panel 4 of the aircraft and that easily transfers cold heat to the inside of the exterior panel 4 exposed to the outside air.
and a heat insulating plate 6 provided apart from the heat transfer plate 5. A refrigerant 7 sent from the line 1 is fed into the space between the heat transfer plate 5 and the heat insulating plate 6. Therefore, this first cooling section A is used when flying at high pressure. Note that this first cooling section A has the ability to sufficiently cool the refrigerant 7 (for example, 7000 BTU/
It is better to make the cooling surface wider so that the aircraft has a higher cooling capacity (HR), and to make it wider and thinner to use the space inside the aircraft more effectively.
次に第２受冷部Ｂについて説明する。第４図に
示すようにこの第２受冷部Ｂはギヤレーのゴミ収
納室内に設けられている。そしてその周囲は断熱
板８，８で包まれており、これらの断熱板８，８
の内側には受冷板９，９が設けられている。そし
てこの受冷板９，９の内部には冷媒の通路が形成
されている。断熱板８，８で囲まれた内部にはド
ライアイス室１０が画成されており、このドライ
アイス室（ゴミ箱）１０の内に必要量だけドライ
アイス１１が充填されている。このドライアイス
１１は昇華しながら矢印で示すように炭酸ガス
CO2を発生するから、ガス抜孔１２が断熱板６の
下方部に穿設されている。このドライアイス１１
は航空機が上空に達するまでの時間を計算して積
み込むが通常7000BTU／HRの冷却能力が必要で
ある。 Next, the second cooling section B will be explained. As shown in FIG. 4, this second cooling section B is provided in the dust storage chamber of the gear train. The surrounding area is covered with heat insulating plates 8, 8, and these insulating plates 8, 8
Cold receiving plates 9, 9 are provided inside. A refrigerant passage is formed inside the cold receiving plates 9, 9. A dry ice chamber 10 is defined inside the interior surrounded by the heat insulating plates 8, 8, and the dry ice chamber (trash can) 10 is filled with a required amount of dry ice 11. As this dry ice 11 sublimates, it produces carbon dioxide gas as shown by the arrow.
Since CO2 is generated, a gas vent hole 12 is provided in the lower part of the heat insulating plate 6. This dry ice 11
The cargo is loaded by calculating the time it takes for the aircraft to reach the sky, but usually requires a cooling capacity of 7000 BTU/HR.
このように第１受冷部Ａまたは第２受冷部Ｂで
同時にまたは選択的に冷媒は冷却されライン１を
介して冷却ユニツトＣに送られ、放冷パイプ１６
に供給される。そしてこの冷却ユニツトＣにはモ
ータ１４で駆動されるフアン１５が設けられてお
り、このフアン１５の回転により放冷パイプ１６
が熱交換され、以て冷却庫２が冷却される。 In this way, the refrigerant is simultaneously or selectively cooled in the first cooling section A or the second cooling section B, and is sent to the cooling unit C via the line 1, and is then sent to the cooling pipe 16.
supplied to This cooling unit C is provided with a fan 15 driven by a motor 14, and the rotation of this fan 15 causes a cooling pipe 16 to
The heat is exchanged, and the refrigerator 2 is cooled.
以上にように、本考案によれば、航空機の冷却
ユニツトを作動するにあたつて、第１および第２
の受冷部を設け、冷却ユニツトに用いる冷媒を上
空においては、低温の冷気を利用し、かつ地上ま
たは上空に達するまでの間はドライアイスの昇華
に伴う放冷を利用して冷却装置を稼動させるの
で、外気の冷気を充分に利用でき。エネルギの節
約が計られると共に、コンプレツサ等の機械的な
装置を設けないでよいから、航空機重量を増大さ
せるという欠点もなく安定性もきわめて高い。そ
して地上においても充分に冷却効果を得ることが
できる。 As described above, according to the present invention, when operating the aircraft cooling unit, the first and second
The cooling system is operated by using low-temperature cold air when the refrigerant used in the cooling unit is in the air, and by using the radiation caused by the sublimation of dry ice until it reaches the ground or the sky. This allows you to make full use of the cold air outside. In addition to saving energy, there is no need to provide mechanical devices such as compressors, so there is no disadvantage of increasing the weight of the aircraft, and stability is extremely high. A sufficient cooling effect can also be obtained on the ground.
なお図示の実施例において、第１受冷部および
第２受冷部はライン１に対し直列に接続させた
が、並列に接続させ、第１受冷部と第２受冷部を
選択的に用いることもできる。 In the illustrated embodiment, the first cold receiving section and the second cold receiving section are connected in series to line 1, but they are connected in parallel, and the first cold receiving section and the second cold receiving section are selectively connected. It can also be used.
第１図は本考案の実施例を示すシステム図、第
２図は第１受冷部の断面図、第３図は第２図の
部分の拡大断面図、第４図は第２受冷部の断面図
である。
Ａ……第１受冷部、Ｂ……第２受冷部、Ｃ……
冷却ユニツト、１，１ａ……ライン、２……冷却
庫、３……温度調節バルブ、４……外装板、５…
…伝熱板、６……断熱板、７……冷媒、８……断
熱板、９……受冷板、１０……ドライアイス室
（ゴミ箱）、１１……ドライアイス、１２……ガス
抜孔、１６……放冷パイプ。
Fig. 1 is a system diagram showing an embodiment of the present invention, Fig. 2 is a sectional view of the first cooling section, Fig. 3 is an enlarged sectional view of the part shown in Fig. 2, and Fig. 4 is a second cooling section. FIG. A...First cooling section, B...Second cooling section, C...
Cooling unit, 1, 1a... Line, 2... Refrigerator, 3... Temperature control valve, 4... Exterior plate, 5...
...Heat transfer plate, 6...Insulation plate, 7...Refrigerant, 8...Insulation plate, 9...Cold receiving plate, 10...Dry ice chamber (trash can), 11...Dry ice, 12...Gas vent hole , 16... Cooling pipe.
Claims (1)
せる航空機用の冷却装置において、冷却庫からの
冷媒の循環ラインには第１受冷部と第２受冷部と
が接続されており、その第１受冷部は航空機の外
装板に設けられ、そしてその外装板の内側に設け
た伝熱板と、その伝熱板から離れて設けた断熱板
とで構成され、その伝熱板と断熱板との間の空間
には前記循環ラインの冷媒が送り込まれ、また第
２受冷部はギヤレーのゴミ収納室内に設けられ、
その第２受冷部はその周囲が断熱板で包まれてお
り、その断熱板内の空間に設けた受冷板には冷媒
の通路が形成され、かつ断熱板内の空間にはドラ
イアイスが充填されていることを特徴とする航空
機における冷却装置。 In an aircraft cooling system that cools and preserves food for passenger service, a first cooling section and a second cooling section are connected to a refrigerant circulation line from a cooling store. The cooling section is provided on the exterior panel of the aircraft, and consists of a heat transfer plate provided inside the exterior panel and a heat insulating plate provided away from the heat transfer plate, and the heat transfer plate and the heat insulating plate are The refrigerant of the circulation line is fed into the space between, and the second cooling part is provided in the garbage storage chamber of the gear train,
The second cooling section is surrounded by a heat insulating plate, and a refrigerant passage is formed in the cold receiving plate provided in the space inside the heat insulating plate, and dry ice is placed in the space inside the heat insulating plate. A cooling device in an aircraft, characterized in that it is filled.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11775581U JPS5824685U (en) | 1981-08-10 | 1981-08-10 | Cooling system in aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11775581U JPS5824685U (en) | 1981-08-10 | 1981-08-10 | Cooling system in aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5824685U JPS5824685U (en) | 1983-02-16 |
| JPS622468Y2 true JPS622468Y2 (en) | 1987-01-21 |
Family
ID=29911911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11775581U Granted JPS5824685U (en) | 1981-08-10 | 1981-08-10 | Cooling system in aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5824685U (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9238398B2 (en) * | 2008-09-25 | 2016-01-19 | B/E Aerospace, Inc. | Refrigeration systems and methods for connection with a vehicle's liquid cooling system |
| JP7205969B2 (en) * | 2018-12-27 | 2023-01-17 | 川崎重工業株式会社 | Skin cooling system |
| JP7168945B2 (en) * | 2020-01-29 | 2022-11-10 | アイ ピース，インコーポレイテッド | pump |
-
1981
- 1981-08-10 JP JP11775581U patent/JPS5824685U/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5824685U (en) | 1983-02-16 |
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