US20100071386A1 - Cooling Device for Installation in an Aircraft - Google Patents

Cooling Device for Installation in an Aircraft Download PDF

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Publication number
US20100071386A1
US20100071386A1 US12/513,794 US51379407A US2010071386A1 US 20100071386 A1 US20100071386 A1 US 20100071386A1 US 51379407 A US51379407 A US 51379407A US 2010071386 A1 US2010071386 A1 US 2010071386A1
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US
United States
Prior art keywords
cooling device
cooling
heat exchanger
liquid coolant
aircraft
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.)
Abandoned
Application number
US12/513,794
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English (en)
Inventor
Matthias Reiss
Wolfgang Ebigt
Andreas Grey
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
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Airbus Operations GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Priority to US12/513,794 priority Critical patent/US20100071386A1/en
Assigned to AIRBUS DEUTSCHLAND GMBH reassignment AIRBUS DEUTSCHLAND GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: REISS, MATTHIAS, EBIGT, WOLFGANG, FREY, ANDREAS
Publication of US20100071386A1 publication Critical patent/US20100071386A1/en
Assigned to AIRBUS OPERATIONS GMBH reassignment AIRBUS OPERATIONS GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: AIRBUS DEUTSCHLAND GMBH
Abandoned legal-status Critical Current

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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
    • 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
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D11/04—Galleys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B21/00—Machines, plants or systems, using electric or magnetic effects
    • F25B21/02—Machines, plants or systems, using electric or magnetic effects using Peltier effect; using Nernst-Ettinghausen effect
    • 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
    • B64D2013/0629—Environmental Control Systems with subsystems for cooling food, catering or special loads
    • 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
    • B64D2013/0674—Environmental Control Systems comprising liquid subsystems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B2321/00—Details of machines, plants or systems, using electric or magnetic effects
    • F25B2321/02—Details of machines, plants or systems, using electric or magnetic effects using Peltier effects; using Nernst-Ettinghausen effects
    • F25B2321/025—Removal of heat
    • F25B2321/0252—Removal of heat by liquids or two-phase fluids
    • 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 invention relates to a cooling device for installation in an aircraft, in particular a passenger aircraft.
  • Certain food such as, for example, fish or ice cream, must be cooled or kept frozen, in particular on long-distance flights, until it is prepared for consumption.
  • This relates not only to food, but also to medicines or other pharmaceutical preparations which are intended as an emergency supply for the passengers.
  • Cooling appliances are provided for cooling or freezing on board a passenger aircraft, these normally being connected to the electrical power supply of the aircraft. These cooling appliances operate according to the known principle of a refrigeration cycle process. In a process of this kind the coolant cyclically changes its state of aggregation from liquid to gaseous and back. When the state of aggregation changes from liquid to gaseous, the coolant absorbs thermal energy, whereas it releases thermal energy when a change takes place from gaseous to liquid.
  • FIG. 1 A schematic representation of a conventional compression-type refrigerating machine is shown in FIG. 1 .
  • the gaseous refrigerant is firstly compressed by a compressor 19 . It is subsequently condensed (liquefied), while releasing heat, in a condenser 17 .
  • a nozzle 16 causes the liquefied refrigerant to expand, this being evaporated, while absorbing heat, in an evaporator 14 . Due to the cooling capacity provided by the evaporator 14 , heat is removed from the air in a cooling compartment 11 .
  • the cycle is now concluded and can recommence in the compressor 19 . Energy must be supplied to the compressor 19 from outside in order to keep this process going.
  • a fan 15 is used in order to improve the heat transfer as well as the temperature distribution in the cooling compartment 11 .
  • a further fan 18 sucks in, through an air inlet 12 , outside air which is heated by the heat released by the evaporator 17 . This heated air is delivered to the environment through the fan 18 via an air outlet 13 .
  • WO 2004/071239 A1 discloses a cooling unit for a service trolley for use in an aircraft or train.
  • the cooling unit comprises a Peltier element located inside a heat-insulating material which divides a drawer of the trolley in a forward cooling section and a rearward intermediate section defined by the rear wall of the drawer and the heat-insulating material. Each end of the Peltier element is connected in a heat-transferring manner with a heat exchanger.
  • the Peltier element serves to cool the cooling section of the drawer of the service trolley.
  • a fan for circulating the relatively warm air in the intermediate section and the relatively cold air in the cooling section.
  • an opening in the rear wall of the drawer is aligned with an opening in the wall of the galley. Warm air from the intermediate section of the drawer is circulated through the wall opening into a central air circulation system.
  • thermoelectric cooling device in particular for a cooler for an automobile, is described in DE 36 39 089 A1.
  • the thermoelectric cooling device includes at least one Peltier block.
  • the warm side of the Peltier block is connected in a heat-transferring manner with a first heat exchanger through which a liquid coolant from a liquid coolant supply circuit is circulated, and the cold side of the Peltier block is in thermal contact with a ribbed recuperator which takes up the entire cross section of a flow channel through which air to be cooled is circulated.
  • the cooled air is then discharged by means of a fan into the cooling space of the cooler.
  • the liquid coolant supply circuit is provided with a third heat exchanger for cooling the liquid coolant. Both the first heat exchanger and the ribbed recuperator are disposed outside the cooling space of the cooler.
  • the invention is therefore based on the object of providing a cooling device for installation in an aircraft which requires little construction space, is easy to install and in the case of which the air surrounding the cooling device does not have to be exchanged.
  • a cooling device for installation in an aircraft in particular a passenger aircraft, which comprises a heat exchanger configured for flow-through of a liquid coolant for pre-cooling a cooling chamber of the cooling device to a temperature of the liquid coolant, the heat exchanger being coupled in a heat-transferring manner to a refrigerant which is in thermal contact with the cooling chamber of the cooling device for cooling the cooling chamber ( 34 ) to a temperature which is below the temperature of the liquid coolant, wherein the heat exchanger and the refrigerant are disposed inside the cooling chamber of the cooling device, and wherein the heat exchanger is configured for connection to a liquid coolant supply system installed on board the aircraft.
  • the heat exchanger which is disposed in the cooling device and through which a liquid coolant can flow causes heat to be removed from the air in the cooling chamber of the cooling device and therefore the cooling chamber to be cooled. Since, moreover, a refrigerant which is in thermal contact with the cooling chamber of the cooling device is coupled in a heat-transferring manner to the heat exchanger, the air in the cooling chamber of the cooling device can be cooled to a temperature which is lower than the temperature of the liquid coolant.
  • the heat exchanger is configured for connection with a liquid coolant supply system which is installed on board the aircraft, the liquid coolant which is provided by the supply system is used to dissipate the heat which is removed from the cooling chamber of the cooling device.
  • the cooling device can therefore be installed in a space-saving manner and without a high constructional expenditure in a push-in compartment of a galley.
  • the heat exchanger and the refrigerant are disposed inside the cooling chamber of the cooling device, efficient pre-cooling of the air in the cooling chamber of the cooling device through the heat exchanger and even further cooling of the air to below the temperature level of the liquid coolant flowing through the heat s exchanger can be achieved.
  • a liquid coolant flows through the heat exchanger.
  • a liquid coolant has a higher energy density on account of its higher thermal capacity.
  • the liquid coolant can as a result absorb and dissipate more energy (heat) per unit of volume.
  • the requirements to be met in terms of tightness of the heat exchanger are lower.
  • the refrigerant is a Peltier element. If the warm side of the Peltier element is cooled by the heat exchanger through which the liquid coolant can flow, the cold side of the Peltier element is cooled further, resulting in a large temperature difference between the two sides of the Peltier element, according to the material which is used for the Peltier element and the applied current. Peltier elements of this kind can be installed very easily and in a space-saving manner and require just one power connection to produce the desired temperature difference.
  • the heat exchanger can be connected through an intake and a return for the liquid coolant to a line system which is installed on board the aircraft.
  • the line system which is installed on board the aircraft provides the liquid coolant for the cooling device.
  • the line connections require a comparatively small construction space and the heat is dissipated via this so-called refrigeration bus. It is as a result possible to install the cooling device in small compartments which are closed off from the aircraft cabin.
  • the heat exchanger is preferably formed according to the counterflow principle, which results in a further increase in the efficiency of the heat exchanger with regard to its cooling effect.
  • the heat exchanger comprises a throttle element which throttles the flow volume of the liquid coolant through the heat exchanger.
  • a specific temperature can be set in the cooling chamber of the cooling device through this throttle element, which is preferably formed as a control valve.
  • the throttle element is disposed in the return.
  • a fan is disposed in the cooling chamber of the cooling device. This fan circulates the air in the cooling chamber, as a result of which the heat transfer to the refrigerant as well as the heat exchanger is improved and the temperature distribution in the cooling chamber of the cooling device is rendered more homogeneous.
  • the liquid coolant does not undergo a phase transition during operation of the cooling device.
  • the cooling device can thus be operated in a more energy-saving manner, as energy is absorbed or released upon each phase transition, this subsequently being required again in order to again attain the original phase state of the liquid coolant.
  • one is form of energy cannot be completely converted into another form of energy, so that a cooling system in which the liquid coolant undergoes a phase transition must be supplied with energy from outside after each complete cooling cycle. This additional energy is not required in the case of the cooling device according to this preferred embodiment.
  • the heat exchanger and the refrigerant are formed such that the cooling chamber can be cooled to a temperature below 0° C.
  • the cooling device can therefore be used to freeze food and other products such as, for example, medicines, which must be available as an emergency supply for the passengers during a long-distance flight.
  • FIG. 1 represents a conventional compression-type refrigerating machine
  • FIG. 2 represents a cooling device according to a preferred embodiment of the invention
  • FIG. 3 depicts a heat exchanger which can be used in the cooling device of FIG. 2 and which is configured according to the counterflow principle.
  • the cooling device 20 which is represented in FIG. 2 comprises a cooling chamber 34 in which a heat exchanger 26 and a refrigerant 28 , for example a Peltier element, are disposed.
  • the heat exchanger 26 is coupled in a heat-transferring manner to the Peltier element 28 .
  • the heat exchanger 26 is connected via an intake 22 and a return 24 to a line system (not shown) which is installed on board the aircraft.
  • a liquid coolant which is provided by the line system can thus flow through the heat exchanger.
  • the temperature of the liquid coolant which is used in this embodiment typically lies below 0° C.
  • a throttle element 32 for example a control valve, is disposed in the return 24 , which element controls the flow volume of the liquid coolant through the heat exchanger 26 .
  • a fan 30 is in addition provided in the cooling chamber 34 to circulate the air in order to improve the heat transfer to the heat exchanger 26 as well as the refrigerant 28 and to provide a more homogeneous temperature distribution in the cooling chamber 34 of the cooling device 20 .
  • the heat exchanger 26 through which the liquid coolant can flow guarantees pre-cooling of the air in the cooling chamber 34 , while the temperature level in the cooling chamber 34 can be lowered further by the Peltier element 28 . It is as a result possible to attain temperatures in the cooling chamber 34 which are sufficient for freezing products, for example food or medicines.
  • the cooling device 20 comprises an open cooling circuit, the heat which is released upon cooling can be dissipated through the liquid coolant via a refrigeration bus.
  • the cooling device 20 does not therefore require a refrigerating machine with a closed cooling circuit in which the heat which is generated by the refrigerating machine must be dissipated through a separate suction system on account of the changes of the state of aggregation of the liquid coolant.
  • the line connections 22 , 24 of the refrigeration bus require only a small construction space when compared with the conventional compression-type refrigerating machine which is represented in FIG. 1 .
  • the cooling device 20 can thereby be installed in small compartments which are closed off from the aircraft cabin.
  • FIG. 3 shows a heat exchanger 26 ′ which can be used in the cooling device 20 of
  • FIG. 2 The heat exchanger 26 ′ of FIG. 3 is configured according to the counter-flow principle.
  • the heat exchanger 26 ′ comprises an upper conduit through which a liquid coolant from a liquid coolant supply system installed on board the aircraft flows in one direction (in FIG. 3 from left to right), and a second conduit through which air to be cooled flows in an opposite direction (in FIG. 3 from right to left).
  • a Peltier element 28 ′ is located in the second conduit and is in thermal contact with the heat exchanger 26 ′.
  • Means 27 ′ such as zig-zag arranged portions of metal sheet, are provided in the first conduit in order to avoid, or at least minimise, any turbulences caused by the flow of liquid coolant through the first conduit.
  • Cooling fins 29 ′ are arranged inside the second conduit in order to more evenly distribute the cooling power provided by the Peltier element 28 ′ and to extend the time period during which the incoming air to be cooled stays within the second conduit.
  • a fan 30 ′ is also provided in order to promote air flow through the second conduit, and thus air circulation inside the cooling chamber 34 of the cooling device 20 of FIG. 2 .
  • the entire assembly shown in FIG. 3 may be disposed within the cooling chamber 34 of the cooling device 20 of FIG. 2 .
  • a throttle element 32 such as a control valve, may be arranged in the return (the right hand side of the first conduit in FIG. 3 ) in order to control the flow volume of the liquid coolant through the first conduit of the heat exchanger 26 ′.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Pulmonology (AREA)
  • General Health & Medical Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Thermal Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Devices That Are Associated With Refrigeration Equipment (AREA)
  • Air-Conditioning For Vehicles (AREA)
  • Details Of Measuring And Other Instruments (AREA)
  • Cooling Or The Like Of Electrical Apparatus (AREA)
US12/513,794 2006-11-09 2007-10-30 Cooling Device for Installation in an Aircraft Abandoned US20100071386A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US12/513,794 US20100071386A1 (en) 2006-11-09 2007-10-30 Cooling Device for Installation in an Aircraft

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US86499606P 2006-11-09 2006-11-09
DE102006052959.6 2006-11-09
DE102006052959A DE102006052959B4 (de) 2006-11-09 2006-11-09 Kühlvorrichtung für den Einbau in ein Flugzeug
PCT/EP2007/009427 WO2008055607A1 (en) 2006-11-09 2007-10-30 Cooling device for installation in an aircraft
US12/513,794 US20100071386A1 (en) 2006-11-09 2007-10-30 Cooling Device for Installation in an Aircraft

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US20100071386A1 true US20100071386A1 (en) 2010-03-25

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US12/513,794 Abandoned US20100071386A1 (en) 2006-11-09 2007-10-30 Cooling Device for Installation in an Aircraft

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US (1) US20100071386A1 (ja)
EP (1) EP2079635B1 (ja)
JP (1) JP2010509117A (ja)
CN (1) CN101547830B (ja)
AT (1) ATE520592T1 (ja)
BR (1) BRPI0716690A2 (ja)
CA (1) CA2667847A1 (ja)
DE (1) DE102006052959B4 (ja)
RU (1) RU2448022C2 (ja)
WO (1) WO2008055607A1 (ja)

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US20110188198A1 (en) * 2008-08-27 2011-08-04 Airbus Operations Gmbh Aircraft Signal Computer System Having A Plurality Of Modular Signal Computer Units
US9134053B2 (en) 2011-08-23 2015-09-15 B/E Aerospace, Inc. Vehicle refrigerator having a liquid line subcooled vapor cycle system
EP3012189A1 (en) * 2014-10-22 2016-04-27 Airbus Operations GmbH Galley system, method for operating electrical galley devices and use of a fuel cell in a galley system
CN113375362A (zh) * 2020-03-10 2021-09-10 B/E航空公司 用于厨房制冷系统的制冷液体再循环装置

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US20120291459A1 (en) * 2011-05-17 2012-11-22 The Boeing Company Method and apparatus for aircraft galley cooling
DE102013211505A1 (de) * 2013-06-19 2014-12-24 Behr Gmbh & Co. Kg Temperiervorrichtung
US9840125B2 (en) * 2013-08-30 2017-12-12 B/E Aerospace, Inc. Aircraft galley with air-through carts
DE102015006557A1 (de) * 2014-06-16 2015-12-17 Liebherr-Hausgeräte Lienz Gmbh Thermoelektrisch gekühltes oder beheiztes Behältnis
DE102015006560A1 (de) * 2014-06-16 2015-12-17 Liebherr-Hausgeräte Lienz Gmbh Kühl- und/oder Gefriergerät
CN205316736U (zh) * 2015-12-25 2016-06-15 广州亿航智能技术有限公司 多轴载人飞行器
CN111186582A (zh) * 2020-01-16 2020-05-22 清华大学 设备舱温度和压力的控制系统及调控方法

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US5653111A (en) * 1993-07-07 1997-08-05 Hydrocool Pty. Ltd. Thermoelectric refrigeration with liquid heat exchange
US6003319A (en) * 1995-10-17 1999-12-21 Marlow Industries, Inc. Thermoelectric refrigerator with evaporating/condensing heat exchanger
US6293107B1 (en) * 1996-11-08 2001-09-25 Matsushita Refrigeration Company Thermoelectric cooling system
US6338251B1 (en) * 1999-07-22 2002-01-15 International Business Machines Corporation Mixed thermoelectric cooling apparatus and method
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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110188198A1 (en) * 2008-08-27 2011-08-04 Airbus Operations Gmbh Aircraft Signal Computer System Having A Plurality Of Modular Signal Computer Units
US8508934B2 (en) * 2008-08-27 2013-08-13 Airbus Operations Gmbh Aircraft signal computer system having a plurality of modular signal computer units
US9134053B2 (en) 2011-08-23 2015-09-15 B/E Aerospace, Inc. Vehicle refrigerator having a liquid line subcooled vapor cycle system
EP3012189A1 (en) * 2014-10-22 2016-04-27 Airbus Operations GmbH Galley system, method for operating electrical galley devices and use of a fuel cell in a galley system
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ATE520592T1 (de) 2011-09-15
WO2008055607A1 (en) 2008-05-15
DE102006052959B4 (de) 2011-02-17
RU2448022C2 (ru) 2012-04-20
CN101547830B (zh) 2013-02-13
RU2009119386A (ru) 2010-12-20
EP2079635B1 (en) 2011-08-17
CN101547830A (zh) 2009-09-30
JP2010509117A (ja) 2010-03-25
CA2667847A1 (en) 2008-05-15
EP2079635A1 (en) 2009-07-22
DE102006052959A1 (de) 2008-05-15
BRPI0716690A2 (pt) 2013-09-17

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