US20050230488A1 - Air dispersion system - Google Patents

Air dispersion system Download PDF

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Publication number
US20050230488A1
US20050230488A1 US11/020,617 US2061704A US2005230488A1 US 20050230488 A1 US20050230488 A1 US 20050230488A1 US 2061704 A US2061704 A US 2061704A US 2005230488 A1 US2005230488 A1 US 2005230488A1
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US
United States
Prior art keywords
air
dispersion system
heating element
outlets
supply line
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
US11/020,617
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English (en)
Inventor
Michael Markwart
Klaus Arnold
Frank Bracker
Jens Lohmar
Thomas Scherer
Torsten Schwan
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
Original Assignee
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
Assigned to AIRBUS DEUTSCHLAND GMBH reassignment AIRBUS DEUTSCHLAND GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SCHERER, THOMAS, BRACKER, FRANK, ARNOLD, KLAUS, LOHMAR, JENS, MARKWART, MICHAEL, SCHWAN, TORSTEN
Publication of US20050230488A1 publication Critical patent/US20050230488A1/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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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B60—VEHICLES IN GENERAL
    • B60H—ARRANGEMENTS OF HEATING, COOLING, VENTILATING OR OTHER AIR-TREATING DEVICES SPECIALLY ADAPTED FOR PASSENGER OR GOODS SPACES OF VEHICLES
    • B60H1/00—Heating, cooling or ventilating [HVAC] devices
    • B60H1/00357—Air-conditioning arrangements specially adapted for particular vehicles
    • B60H1/00371—Air-conditioning arrangements specially adapted for particular vehicles for vehicles carrying large numbers of passengers, e.g. buses
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B60—VEHICLES IN GENERAL
    • B60H—ARRANGEMENTS OF HEATING, COOLING, VENTILATING OR OTHER AIR-TREATING DEVICES SPECIALLY ADAPTED FOR PASSENGER OR GOODS SPACES OF VEHICLES
    • B60H1/00—Heating, cooling or ventilating [HVAC] devices
    • B60H1/00007—Combined heating, ventilating, or cooling devices
    • B60H1/00207—Combined heating, ventilating, or cooling devices characterised by the position of the HVAC devices with respect to the passenger compartment
    • B60H2001/00235—Devices in the roof area of the passenger compartment

Definitions

  • the invention relates to an air dispersion system or air distribution system, e.g. for homogenizing a thermal load dispersion or distribution within a chamber, in particular, the heat dispersion or distribution within a cabin of an aircraft.
  • the cabin In order to control or regulate the cabin temperature of an aircraft, the cabin typically is subdivided into a certain number of temperature zones.
  • the distribution of the heat sources and heat sinks in the zone is inhomogeneous. This is the case, for example, when the seating density within the zone varies. A high density of passengers forms a heat source, while an empty door area represents a heat sink. The result is that in regions with a heat source, a warmer temperature prevails and, conversely, in a region with heat sinks, a colder temperature prevails.
  • An inhomogeneous temperature distribution within the zone connotes a restriction of thermal comfort.
  • the supply amount through the air outlets is reduced at the positions with colder supply temperature, whereby the temperature level of the corresponding cabin part is raised.
  • One disadvantage of reducing the air volume is that the air distribution system must be calibrated anew, which is connected with a large expenditure of time.
  • DE 43 35 152 C1 discloses a cabin air circulation system for air conditioning of the fuselage of a passenger aircraft.
  • This cabin air circulation system regulates the fresh air volume flow including the temperature monitoring for the fuselage pressure of a passenger aircraft and allows a high degree of purity of the air-conditioned air.
  • the temperature regulation takes place by means of a separate heat exchanger in the circulating air.
  • DE 195 90 773 C1 discloses a ventilation system for reducing the concentration of impurities in passenger areas, in particular, in the smoking zones.
  • DE 44 25 871 C2 discloses a method for air conditioning two passenger decks of an aircraft.
  • air conditioning systems are used, respectively for an upper deck circuit and a main deck circuit.
  • the air conditioning aggregates are connected to an exterior air line, in order to cool the hot drawn air from the drive works with external air during operation.
  • an air dispersion system which may have at least one main supply line, through which air is distributed via respective exhaust routes with a predetermined pressure to air outlets and is blown into respective temperature zone regions.
  • the air dispersion system of the present invention further has at least one heating element, which is associated with at least one of the air outlets and tempers the air, which flows in a corresponding exhaust route of this air outlet, to a predetermined temperature, and the heated air can blow out into a corresponding region.
  • this air dispersion system may allow for a homogenous temperature distribution in each zone.
  • the air dispersion or distribution system has auxiliary supply lines, which branch off from the main supply line, whereby the individual air outlets are supplied with air individually via an auxiliary line.
  • the heating element can be mounted in the area of the auxiliary supply line, in order to heat the air flowing therethrough, before it exits into the respective region via the air outlet.
  • each temperature zone is supplied by an air outlet (or a group of air outlets), with failure or malfunction of one auxiliary supply line, it is believed that only the corresponding air outlet (or the group of air outlets) is affected, and the manner of functioning of the remaining air outlets, which are not supplied via this auxiliary supply line, remains essentially maintained.
  • the air supply takes place from air outlet to air outlet, which may have the advantage that the air dispersion system has a simpler structure.
  • the heating element is mounted, for example, on the air discharge side and/or the air inlet side of an air outlet, in order to heat the air flowing therethrough, before it is blown out into a corresponding region.
  • FIG. 1 shows a cross section through an aircraft cabin
  • FIG. 2 shows a schematic view of the air dispersion system of the air craft cabin shown in FIG. 1 according to a first exemplary embodiment
  • FIG. 3 shows a schematic view of the air dispersion system of the aircraft cabin shown in FIG. 1 according to a second exemplary embodiment
  • FIG. 4 shows a installation point for the heating system with the air dispersion system shown in FIG. 3 ;
  • FIG. 5 shows a side view from the right of the air outlet shown in FIG. 4 .
  • FIG. 1 shows a section through an aircraft cabin 1 , which is subdivided into a certain number of temperature zones 2 .
  • a first temperature zone 2 a is shown and in the right half, a second temperature zone 2 b is shown.
  • the temperature zones 2 are supplied with air.
  • air is blown into the temperature zone 2 a via the air outlet 3 a, and via the air outlet 3 b, air is blown into the temperature zone 2 b.
  • the air outlets 3 a, 3 b shown in FIG. 1 are arranged in the upper region (ceiling region) of the aircraft cabin, but, however, can be formed at any other desired position within the cabin.
  • FIG. 1 shows sensors 4 , for example, temperature sensors 4 a, 4 b, which are arranged respectively in each temperature zone 2 a, 2 b in the upper region (ceiling region) of the cabin.
  • the temperature zones can be arranged alternatively virtually at any position within the temperature zone.
  • the sensor may be positioned within the temperature zone 2 at a position, which corresponds to the mean temperature of the temperature zone (not thermal load). This temperature results naturally from the thermal load within the temperature zone.
  • the temperature within a temperature zone 2 is typically measured at the point, which corresponds with the mean temperature in the zone.
  • the engaged local temperatures are affected, therefore, by the occurring thermal load (sources and sinks).
  • FIG. 1 further shows seats, for example, for receiving passengers.
  • the temperature of this temperature zone 2 is greater than the temperature in a region of the cabin, in which few or no occupied seats 5 are located (a minimal seating density), for example, in the area of the door.
  • the region with many seats represents a heat source, for example, and the region at the door represents a heat sink.
  • FIG. 2 shows a schematic view of the air dispersion system in the aircraft cabin shown in FIG. 1 according to a first exemplary embodiment.
  • This air dispersion system has a main supply line 6 , via which multiple air outlets 3 are supplied with air.
  • the air outlet 3 c according to FIG. 1 is shown.
  • Each air outlet 3 is associated with a specific temperature zone 2 .
  • the air outlet 3 a then, supplies the temperature zone 2 a with air.
  • a plurality of auxiliary supply lines 7 branch off, in order to supply the individual air outlets 3 , respectively, with air. Therefore, the air exhaust routes of an air outlet 3 are defined by a corresponding auxiliary line 7 supplying it with air and by an air route within the air outlet to the exhaust side of the air from the air outlet.
  • only one group of air outlets 3 can be connected via an individual auxiliary supply line 7 with the main supply line 6 , so that air is fed via the main supply line 6 and the individual auxiliary supply line 7 to the group of air outlets.
  • FIG. 2 shows further a heating element 8 , which is formed on the auxiliary supply line 7 a, which supplies the air outlet 3 a with air, which is blown heated into the temperature zone 2 a, when the heating element 8 is in operation.
  • the heating element 8 can be a heating coil, for example, an electrical heater, or the like.
  • the heating element can be located within the auxiliary supply line 7 a, so that any air flow flowing through the auxiliary supply line 7 a comes into contact with the heating element 8 and is thereby heated in an effective manner.
  • the heating element 8 it is possible to mount the heating element 8 externally on the auxiliary supply line 7 a, so that no direct contact with the air flowing in the auxiliary supply line 7 a occurs. This has the advantage that the heating element 8 can be installed subsequently, without having to engage in the tube line system.
  • the air heated by the heating element 8 is fed to the air outlet 3 a and is blown out via air nozzles 9 a into the temperature zone 2 a.
  • FIG. 3 shows a schematic view of an air dispersion system in the aircraft cabin shown in FIG. 1 , according to a second exemplary embodiment.
  • a main supply line 6 a branches off into a left supply line 6 a and a right supply line 6 b.
  • one group of air outlets is supplied with air (for purposes of simplicity, only one air outlet 3 a is shown in the figure), whereby the air outlets are connected directly among each other, so that an air supply from air outlet to air outlet is ensured.
  • Each air outlet 3 has air nozzles 9 , via which the air is blown out into a temperature zone 2 .
  • a heating element 8 is located directly on an air outlet 3 a, in order to blow out heated air via air nozzles 9 a.
  • the heating element 8 can be formed integrally with this on the air inlet side and/or air exhaust side of the air outlet 3 a, in order to heat air first on the ends of an exhaust route of the air outlet 3 a. In this manner, a heating element can be used with less heat output, compared with the first exemplary embodiment, in which air already is heated relative to the beginning of an exhaust route.
  • the heating element 8 also can be formed separately and, for example, can be inserted into the air nozzles 9 a of the air outlet 3 a, whereby an exchange or a subsequent installation of the heating element 8 is very simple.
  • only the air outlet 3 a is provided with a heating element, so that only the air blown out from this air outlet is heated, and with reference to the supply air flow, air outlets 3 lying upstream or downstream are not affected; that is, air blown out through these air outlets is not heated.
  • heating element 8 In the first exemplary embodiment according to FIG. 2 and the second exemplary embodiment shown in FIG. 3 , respectively, only one heating element 8 is shown by way of example. Depending on the requirements, however, also multiple air outlets 3 can be associated with a heating element 8 or multiple heating elements 8 .
  • the heating element 8 then, preferably is associated with an air outlet 3 , in order to heat air in its exhaust route, when this air outlet 3 lies in a so-called heat sink.
  • a heat sink can be formed, for example, by a door area.
  • the heating element also can be used in the standard manner for all of the air outlets 3 , in order to temper accordingly the air blown out from the air outlets to a predetermined temperature, whereby the heat output of the heating element can be dispersed differently.
  • the heat output of the heating element which is located in the region of a heat sink, is greater than that of a heating element which is located in the region of a heat source.
  • a heat source for example, is formed by a high density of passengers.
  • a heating element 8 can be a heating coil, an electric heater, or the like, for example.
  • the heat output of the heating element 8 can be constant or adjustable both in the first exemplary embodiment as well as in the second exemplary embodiment.
  • the heat output is regulated with the aid of the temperature sensors 4 shown in FIG. 1 (sensors 4 a, and/or 4 b ), such that the exhaust route of an air outlet is heated, in order to raise the temperature level of regions that are too cold to the temperature level of the sensor point.
  • FIG. 4 shows a possible installation point for the heating element 8 .
  • the heating element 8 is formed on the air exhaust side of the air outlet 3 , so that the air blown out through the air nozzles 9 is heated.
  • it also can be formed on an air inlet side of the air outlet 3 .
  • the heating element 8 extends only over a part of the air nozzles 9 .
  • FIG. 5 shows a side view of the outlet shown in FIG. 4 from the right.
  • the air outlet 3 is supplied from the right with air, which exits downwardly in part over the air nozzles 9 and in part, flows further to the left, in order to supply the air outlets lying downstream shown in FIG. 3 .
  • the exhaust air flow branching off downwardly from the supply air flow (that is, the air exhaust route) is heated by the heating element 8 formed directly on the air outlet 3 , so that heated air is blown into a corresponding temperature zone 2 , which is associated with this air outlet 3 .
  • the exhaust route of the air outlet 3 is heated by the heating element 8 , so that heated air is blown into a temperature zone 2 .
US11/020,617 2003-12-29 2004-12-23 Air dispersion system Abandoned US20050230488A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10361392.7 2003-12-29
DE10361392A DE10361392B4 (de) 2003-12-29 2003-12-29 Luftverteilungssystem

Publications (1)

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US20050230488A1 true US20050230488A1 (en) 2005-10-20

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US (1) US20050230488A1 (de)
EP (1) EP1550569B1 (de)
AT (1) ATE367941T1 (de)
CA (1) CA2490588C (de)
DE (2) DE10361392B4 (de)

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US20080268762A1 (en) * 2007-04-25 2008-10-30 Airbus Deutschland Gmbh Air infeed device for air-conditioning passenger areas in aircraft
US20090275277A1 (en) * 2008-05-01 2009-11-05 Al-Alusi Thamir R Alternate directional momentum ventilation nozzle for passenger cabins
US20100099347A1 (en) * 2008-10-22 2010-04-22 Thorsten Raible Air guide element and air guide element arrangement for an aircraft air conditioning system
CN102171099A (zh) * 2008-10-06 2011-08-31 空中客车作业有限公司 用于飞机空调系统的侧向供给器空气导向元件
WO2013087534A1 (en) 2011-12-14 2013-06-20 Airbus Operations Gmbh Temperature regulation of heated air distribution systems in passenger rooms
US20140295746A1 (en) * 2011-02-04 2014-10-02 Bombardier Transportation Gmbh Ventilation System for a Passenger Transit Vehicle
EP3744638A1 (de) * 2019-05-31 2020-12-02 Hamilton Sundstrand Corporation Thermodynamische steuerung von flugzeugkabinenluft

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DE102006005037B4 (de) * 2006-02-03 2012-03-29 Airbus Operations Gmbh Klimatisierungsanordnung für ein Flugzeug mit mehreren individuell temperaturregelbaren Klimazonen

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DE10361392B4 (de) 2009-07-30
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EP1550569A1 (de) 2005-07-06
DE502004004424D1 (de) 2007-09-06

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