US20050230488A1 - Air dispersion system - Google Patents
Air dispersion system Download PDFInfo
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- 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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- Prior art keywords
- air
- dispersion system
- heating element
- outlets
- supply line
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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
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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
-
- 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 .
Abstract
An air dispersion system has a main supply line, a plurality of air outlets, which are connected via respective air exhaust routes to the main supply line, and at least one heating element, which is associated with at least one of the air outlets and can temper the air in the exhaust route of this air outlet.
Description
- 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.
- In order to control or regulate the cabin temperature of an aircraft, the cabin typically is subdivided into a certain number of temperature zones. However, it is also possible that 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, however, connotes a restriction of thermal comfort.
- Whether there is an inhomogeneous distribution of the heat sources and heat sinks depends, then, on the individual arrangement of the seat layout. This can appear differently for each aircraft customer.
- In order to counteract the inhomogeneity of the thermal load distribution within a temperature zone, typically 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, however, 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. For temperature adjustment, air conditioning systems are used, respectively for an upper deck circuit and a main deck circuit. In each air conditioning system, the drawn air removed from the drive works is cooled. The air conditioning aggregates, in addition, are connected to an exterior air line, in order to cool the hot drawn air from the drive works with external air during operation.
- According to an exemplary embodiment of the present invention, an air dispersion system is provided 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.
- It is believed that this air dispersion system according to an exemplary embodiment of the present invention may allow for a homogenous temperature distribution in each zone.
- According to a further embodiment of the invention, 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.
- In this manner, for example, 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.
- Since 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.
- According to another exemplary embodiment of the present invention, 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.
- According to still another exemplary embodiment of the present invention, 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.
- Further exemplary embodiments of the invention will be described with reference to the accompanying figures. In the figures:
-
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 inFIG. 1 according to a first exemplary embodiment; -
FIG. 3 shows a schematic view of the air dispersion system of the aircraft cabin shown inFIG. 1 according to a second exemplary embodiment; -
FIG. 4 shows a installation point for the heating system with the air dispersion system shown inFIG. 3 ; and -
FIG. 5 shows a side view from the right of the air outlet shown inFIG. 4 . - In the figures, the same or similar elements will be provided with the same reference numerals.
-
FIG. 1 shows a section through anaircraft cabin 1, which is subdivided into a certain number oftemperature zones 2. InFIG. 1 , for example, in the left half, afirst temperature zone 2 a is shown and in the right half, asecond temperature zone 2 b is shown. - Via
air outlets 3, thetemperature zones 2 are supplied with air. In particular, for example, air is blown into thetemperature zone 2 a via theair outlet 3 a, and via theair outlet 3 b, air is blown into thetemperature zone 2 b. - The
air outlets 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. - In addition,
FIG. 1 shows sensors 4, for example,temperature sensors temperature zone 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. With thesetemperature sensors 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. In one region of the aircraft cabin, in whichmany seats 5 occupied with passengers is located, generally the temperature of thistemperature zone 2 is greater than the temperature in a region of the cabin, in which few or no occupiedseats 5 are located (a minimal seating density), for example, in the area of the door. The region with many seats, then, 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 inFIG. 1 according to a first exemplary embodiment. This air dispersion system has amain supply line 6, via whichmultiple air outlets 3 are supplied with air. In the figure, for purposes of simplicity, the air outlet 3 c according toFIG. 1 is shown. Eachair outlet 3 is associated with aspecific temperature zone 2. Theair outlet 3 a, then, supplies thetemperature zone 2 a with air. From themain supply line 6, a plurality ofauxiliary supply lines 7 branch off, in order to supply theindividual air outlets 3, respectively, with air. Therefore, the air exhaust routes of anair outlet 3 are defined by a correspondingauxiliary 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. - Alternatively, also only one group of
air outlets 3 can be connected via an individualauxiliary supply line 7 with themain supply line 6, so that air is fed via themain supply line 6 and the individualauxiliary supply line 7 to the group of air outlets. -
FIG. 2 shows further aheating element 8, which is formed on theauxiliary supply line 7 a, which supplies theair outlet 3 a with air, which is blown heated into thetemperature zone 2 a, when theheating 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 theauxiliary supply line 7 a, so that any air flow flowing through theauxiliary supply line 7 a comes into contact with theheating element 8 and is thereby heated in an effective manner. - Alternatively, it is possible to mount the
heating element 8 externally on theauxiliary supply line 7 a, so that no direct contact with the air flowing in theauxiliary supply line 7 a occurs. This has the advantage that theheating 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 theair outlet 3 a and is blown out viaair nozzles 9 a into thetemperature zone 2 a. -
FIG. 3 shows a schematic view of an air dispersion system in the aircraft cabin shown inFIG. 1 , according to a second exemplary embodiment. - With this air dispersion system, a
main supply line 6 a branches off into aleft supply line 6 a and aright supply line 6 b. Via theleft supply line 6 a, one group of air outlets is supplied with air (for purposes of simplicity, only oneair 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. Eachair outlet 3 hasair nozzles 9, via which the air is blown out into atemperature zone 2. - In contrast to the first embodiment, a
heating element 8 is located directly on anair outlet 3 a, in order to blow out heated air viaair nozzles 9 a. Theheating element 8 can be formed integrally with this on the air inlet side and/or air exhaust side of theair outlet 3 a, in order to heat air first on the ends of an exhaust route of theair 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 theair nozzles 9 a of theair outlet 3 a, whereby an exchange or a subsequent installation of theheating element 8 is very simple. - As shown in
FIG. 3 , only theair 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. - In the first exemplary embodiment according to
FIG. 2 and the second exemplary embodiment shown inFIG. 3 , respectively, only oneheating element 8 is shown by way of example. Depending on the requirements, however, alsomultiple air outlets 3 can be associated with aheating element 8 ormultiple heating elements 8. Theheating element 8, then, preferably is associated with anair outlet 3, in order to heat air in its exhaust route, when thisair outlet 3 lies in a so-called heat sink. Such a heat sink can be formed, for example, by a door area. - Alternatively, 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. Preferably, 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. - As with the first exemplary embodiment, 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, for example, can be constant or adjustable both in the first exemplary embodiment as well as in the second exemplary embodiment. - Preferably, 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 theheating element 8. - According to this exemplary embodiment, the
heating element 8 is formed on the air exhaust side of theair outlet 3, so that the air blown out through theair nozzles 9 is heated. However, it also can be formed on an air inlet side of theair outlet 3. - When the
air outlet 3 hasmultiple air nozzles 9, it is possible that theheating element 8 extends only over a part of theair nozzles 9. -
FIG. 5 shows a side view of the outlet shown inFIG. 4 from the right. As shown inFIG. 5 , theair outlet 3 is supplied from the right with air, which exits downwardly in part over theair nozzles 9 and in part, flows further to the left, in order to supply the air outlets lying downstream shown inFIG. 3 . The exhaust air flow branching off downwardly from the supply air flow (that is, the air exhaust route) is heated by theheating element 8 formed directly on theair outlet 3, so that heated air is blown into a correspondingtemperature zone 2, which is associated with thisair outlet 3. - The exhaust route of the
air outlet 3, then, is heated by theheating element 8, so that heated air is blown into atemperature zone 2. - Although the invention is described above with reference to an aircraft cabin, it is obvious to the practitioner to modify the air dispersion system of the present invention, such that it also can be used in a bus, a PKW, a train, etc., without departing from the scope of protection of the invention.
- It should be noted that the term “comprising” does not exclude other elements or steps and the “a” or “an” does not exclude a plurality. Also elements described in association with different embodiments may be combined.
- It should also be noted that reference signs in the claims shall not be construed as limiting the scope of the claims.
Claims (8)
1. Air dispersion system, comprising:
a main supply line;
a plurality of air outlets, which are connected via respective air exhaust routes to the main supply line; and
at least one heating element, which is associated with at least one first air outlet of the plurality of air outlets and is adapted to temper air in the respective exhaust route of this at least one first air outlet of the plurality of air outlets.
2. The air dispersion system of claim 1 ,
wherein the respective air exhaust routes are auxiliary supply lines branching off from the main supply line, via which the plurality of the air outlets are supplied individually with air.
3. The air dispersion system of claim 2 ,
wherein the heating element is mounted on at least one of the auxiliary supply lines, in order to enable warming of air in the respective auxiliary supply line.
4. The air dispersion system of claim 1 , further comprising:
an air supply from a second air outlet of the plurality of air outlets to a third air outlet of the plurality of air outlets.
5. The air dispersion system of claim 1 ,
wherein the at least one heating element is formed directly on one of an air inlet side and air exhaust side of at least one fourth air outlet of the plurality of air outlets.
6. The air dispersion system of claim 1 ,
wherein the at least one heating element has a constantly adjustable heat output.
7. The air dispersion system of claim 1 , further comprising:
at least one temperature sensor providing a temperature readout;
wherein, on the basis of the temperature readout, the heat output of the heating element is controlled to a predetermined value.
8. The air dispersion system of claim 1 , wherein
a volume flowing in the air dispersion system remains essentially constant.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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DE10361392.7 | 2003-12-29 | ||
DE10361392A DE10361392B4 (en) | 2003-12-29 | 2003-12-29 | Air distribution system |
Publications (1)
Publication Number | Publication Date |
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US20050230488A1 true US20050230488A1 (en) | 2005-10-20 |
Family
ID=34559774
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US11/020,617 Abandoned US20050230488A1 (en) | 2003-12-29 | 2004-12-23 | Air dispersion system |
Country Status (5)
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US (1) | US20050230488A1 (en) |
EP (1) | EP1550569B1 (en) |
AT (1) | ATE367941T1 (en) |
CA (1) | CA2490588C (en) |
DE (2) | DE10361392B4 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 (en) * | 2008-10-06 | 2011-08-31 | 空中客车作业有限公司 | Side feeder air guiding element for an aircraft air-conditioning system |
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 (en) * | 2019-05-31 | 2020-12-02 | Hamilton Sundstrand Corporation | Aircraft cabin air thermodynamic control |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006005037B4 (en) * | 2006-02-03 | 2012-03-29 | Airbus Operations Gmbh | Air conditioning arrangement for an aircraft with several individually temperature-controllable climates |
Citations (59)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1391113A (en) * | 1920-08-27 | 1921-09-20 | Andrew J Holmes | Electric heater |
US1909144A (en) * | 1930-05-29 | 1933-05-16 | Burd High Compression Ring Com | Heater |
US2199840A (en) * | 1939-01-14 | 1940-05-07 | Royall Ralph | Heating system |
US2218468A (en) * | 1937-02-23 | 1940-10-15 | Honeywell Regulator Co | Air conditioning system |
US2242630A (en) * | 1940-02-09 | 1941-05-20 | Steingruber George | Electric heater |
US2260900A (en) * | 1937-12-30 | 1941-10-28 | Gen Motors Corp | Air conditioning |
US2341439A (en) * | 1942-05-06 | 1944-02-08 | Alfred L Greenlaw | Grill |
US2357112A (en) * | 1943-04-02 | 1944-08-29 | Stewart Warner Corp | Airplane heating system |
US2412110A (en) * | 1943-02-04 | 1946-12-03 | Stewart Warner Corp | Air conditioning apparatus for aircraft |
US2427698A (en) * | 1944-04-28 | 1947-09-23 | Solar Aircraft Co | Insulating and ventilating structure |
US2429619A (en) * | 1943-01-21 | 1947-10-28 | Clyde M Hamblin | Air conditioning system |
US2565769A (en) * | 1949-03-02 | 1951-08-28 | Tennessee Valley Authority | Electric heater |
US2706942A (en) * | 1951-06-27 | 1955-04-26 | William J Caldwell | Rifled air control nozzles |
US2760725A (en) * | 1951-01-03 | 1956-08-28 | Budd Co | Thermal conditioning and ventilating means and method |
US2980785A (en) * | 1959-03-30 | 1961-04-18 | Nicholas E Whitney Sr | Electric heating |
US3067316A (en) * | 1960-05-20 | 1962-12-04 | Worthington Corp | Electrical duct heater |
US3111571A (en) * | 1962-01-26 | 1963-11-19 | Williamson Company | Electric heating unit |
US3203473A (en) * | 1960-10-05 | 1965-08-31 | Lockheed Aircraft Corp | Aircraft heating system |
US3482503A (en) * | 1968-12-20 | 1969-12-09 | Jenn Air Corp | System for comfort conditioning structures |
US3605797A (en) * | 1970-05-18 | 1971-09-20 | Dunham Bush Inc | Shut off damper assembly for high velocity ducted air type conditioning system |
US3687054A (en) * | 1970-11-24 | 1972-08-29 | Lockheed Aircraft Corp | Air outlet apparatus |
US3697728A (en) * | 1968-12-13 | 1972-10-10 | Air Plastic Service Gmbh | Heating devices |
US3799046A (en) * | 1972-04-06 | 1974-03-26 | Mitco Corp | Diffuser valve |
US3951205A (en) * | 1972-08-18 | 1976-04-20 | Brandt Engineering Co. | Air-conditioning apparatus |
US3974752A (en) * | 1974-11-25 | 1976-08-17 | The Garrett Corporation | Pressure control system |
US4232211A (en) * | 1978-10-19 | 1980-11-04 | Hill Johnnie L | Automobile auxiliary heater |
US4263786A (en) * | 1979-07-10 | 1981-04-28 | The Boeing Company | Fuel conserving air-conditioning apparatus and method for aircraft |
US4283924A (en) * | 1978-08-04 | 1981-08-18 | Vereinigte Flugtechnische Werke-Fokker Gmbh | Climatizing of aircraft |
US4446774A (en) * | 1980-05-19 | 1984-05-08 | Gershon Meckler | Air conditioning apparatus |
US4473107A (en) * | 1981-08-19 | 1984-09-25 | Building Facilities Corporation | Fan/coil induction unit, system, and method |
US4505124A (en) * | 1983-09-22 | 1985-03-19 | The United States Of America As Represented By The Secretary Of The Air Force | Heat management system for aircraft |
US4513574A (en) * | 1984-04-30 | 1985-04-30 | Tempmaster Corporation | Low Temperature air conditioning system and method |
US4742760A (en) * | 1987-07-06 | 1988-05-10 | The Boeing Company | Aircraft cabin ventilation system |
US4742761A (en) * | 1987-07-20 | 1988-05-10 | The Boeing Company | Method and apparatus for controlling the concentration of carbon dioxide in an aircraft cabin |
US4814579A (en) * | 1986-04-07 | 1989-03-21 | Innovative Scientific Development, Inc. | Electric resistance air reating system for an aircraft cabin |
US4819548A (en) * | 1987-05-07 | 1989-04-11 | The Boeing Company | Dual nozzle cabin ventilation system |
US4844150A (en) * | 1985-10-11 | 1989-07-04 | Sanden Corporation | Air distributing mechanism for an automotive air conditioning system |
US5093895A (en) * | 1988-10-24 | 1992-03-03 | Robert Brouillette | Humidifier attachable to baseboard radiator |
US5295531A (en) * | 1991-09-02 | 1994-03-22 | Sanyo Electric Co., Ltd. | Air conditioner with outside air introduction path |
US5520578A (en) * | 1993-05-19 | 1996-05-28 | Nord-Micro Elektronik Feinmechanik Ag | Aircraft cabin pressure control system |
US5533568A (en) * | 1994-11-08 | 1996-07-09 | Carrier Corporation | Managing supplementary heat during defrost on heat pumps |
US5632334A (en) * | 1995-01-13 | 1997-05-27 | Nutech Energy Systems Inc. | Heat recovery ventilator with room air defrosting feature |
US5701755A (en) * | 1997-01-15 | 1997-12-30 | Sundstrand Corporation | Cooling of aircraft electronic heat loads |
US5702073A (en) * | 1993-04-27 | 1997-12-30 | E-Systems, Inc. | Modular liquid skin heat exchanger |
US5704218A (en) * | 1996-04-08 | 1998-01-06 | United Technologies Corporation | Integrated environmental control system |
US5760376A (en) * | 1996-06-19 | 1998-06-02 | Cox 3 Company, Inc. | Air heater with self-supporting heater element |
US5897079A (en) * | 1997-08-18 | 1999-04-27 | Mcdonnell Douglas Corporation | Air curtain insulating system for aircraft cabin |
JPH11159782A (en) * | 1997-11-28 | 1999-06-15 | Mitsubishi Electric Corp | Warm air heater |
US6024639A (en) * | 1997-07-04 | 2000-02-15 | Daimlerchrysler Aerospace Airbus Gmbh | Injector air outlet with a sensor for temperature and smoke monitoring |
US6216981B1 (en) * | 1998-03-06 | 2001-04-17 | Rolls-Royce Plc | Environmental control system |
US6295822B1 (en) * | 1999-08-04 | 2001-10-02 | Daimlerchrysler Aerospace Airbus Gmbh | Aircraft air-conditioning apparatus with water separators |
US6393717B1 (en) * | 2001-01-24 | 2002-05-28 | Victor M. Santos | Foot dryer device with diffused heated air flow system |
US6413159B1 (en) * | 2000-06-28 | 2002-07-02 | The Boeing Company | Airplane cabin overhead air outlets |
US6510696B2 (en) * | 1998-06-15 | 2003-01-28 | Entrosys Ltd. | Thermoelectric air-condition apparatus |
US6551184B1 (en) * | 1998-03-26 | 2003-04-22 | Fraunhofer. Gesellschaft Zur Forderung Der Angewandten Forschung E.V. | Method and device for air conditioning in vehicles |
US20030102121A1 (en) * | 2001-11-30 | 2003-06-05 | Samsung Electronics Co., Ltd. | Air conditioner and method of controlling the same |
US20030141412A1 (en) * | 2002-01-28 | 2003-07-31 | Fieldson Charles A. | Flight crew rest and attendant rest environmental control system |
US6694765B1 (en) * | 2002-07-30 | 2004-02-24 | Thermo King Corporation | Method and apparatus for moving air through a heat exchanger |
US7203416B2 (en) * | 2003-11-21 | 2007-04-10 | Broan-Nutone Llc | Ventilating and heating apparatus with heater shielded by tapered discharge duct |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT8553106V0 (en) * | 1985-03-08 | 1985-03-08 | Foggini Progetti | AIR CONDITIONING AIR VENT FOR MOTOR VEHICLES INCORPORATING ELECTRIC HEATING VEHICLES |
DE4335152C1 (en) * | 1993-10-15 | 1995-04-20 | Deutsche Aerospace Airbus | Air-conditioning system for the air conditioning of fuselage units of a passenger aircraft |
DE4425871C2 (en) * | 1994-07-21 | 1998-07-02 | Daimler Benz Aerospace Airbus | Method for air conditioning two passenger decks of an aircraft, in particular a wide-body aircraft, and device for carrying out the method |
DE19509773C1 (en) * | 1995-03-17 | 1996-06-27 | Daimler Benz Aerospace Airbus | Ventilating system for reducing concentration of impurities in aircraft passenger area |
DE10121906B4 (en) * | 2001-05-03 | 2006-12-14 | Saia-Burgess Ozd Kft. | Ventilation device for vehicles |
US6619589B2 (en) * | 2002-01-28 | 2003-09-16 | The Boeing Company | Flight crew and attendant rest environmental control system |
-
2003
- 2003-12-29 DE DE10361392A patent/DE10361392B4/en not_active Expired - Fee Related
-
2004
- 2004-12-21 EP EP04030273A patent/EP1550569B1/en not_active Not-in-force
- 2004-12-21 AT AT04030273T patent/ATE367941T1/en not_active IP Right Cessation
- 2004-12-21 DE DE502004004424T patent/DE502004004424D1/en active Active
- 2004-12-21 CA CA2490588A patent/CA2490588C/en not_active Expired - Fee Related
- 2004-12-23 US US11/020,617 patent/US20050230488A1/en not_active Abandoned
Patent Citations (59)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1391113A (en) * | 1920-08-27 | 1921-09-20 | Andrew J Holmes | Electric heater |
US1909144A (en) * | 1930-05-29 | 1933-05-16 | Burd High Compression Ring Com | Heater |
US2218468A (en) * | 1937-02-23 | 1940-10-15 | Honeywell Regulator Co | Air conditioning system |
US2260900A (en) * | 1937-12-30 | 1941-10-28 | Gen Motors Corp | Air conditioning |
US2199840A (en) * | 1939-01-14 | 1940-05-07 | Royall Ralph | Heating system |
US2242630A (en) * | 1940-02-09 | 1941-05-20 | Steingruber George | Electric heater |
US2341439A (en) * | 1942-05-06 | 1944-02-08 | Alfred L Greenlaw | Grill |
US2429619A (en) * | 1943-01-21 | 1947-10-28 | Clyde M Hamblin | Air conditioning system |
US2412110A (en) * | 1943-02-04 | 1946-12-03 | Stewart Warner Corp | Air conditioning apparatus for aircraft |
US2357112A (en) * | 1943-04-02 | 1944-08-29 | Stewart Warner Corp | Airplane heating system |
US2427698A (en) * | 1944-04-28 | 1947-09-23 | Solar Aircraft Co | Insulating and ventilating structure |
US2565769A (en) * | 1949-03-02 | 1951-08-28 | Tennessee Valley Authority | Electric heater |
US2760725A (en) * | 1951-01-03 | 1956-08-28 | Budd Co | Thermal conditioning and ventilating means and method |
US2706942A (en) * | 1951-06-27 | 1955-04-26 | William J Caldwell | Rifled air control nozzles |
US2980785A (en) * | 1959-03-30 | 1961-04-18 | Nicholas E Whitney Sr | Electric heating |
US3067316A (en) * | 1960-05-20 | 1962-12-04 | Worthington Corp | Electrical duct heater |
US3203473A (en) * | 1960-10-05 | 1965-08-31 | Lockheed Aircraft Corp | Aircraft heating system |
US3111571A (en) * | 1962-01-26 | 1963-11-19 | Williamson Company | Electric heating unit |
US3697728A (en) * | 1968-12-13 | 1972-10-10 | Air Plastic Service Gmbh | Heating devices |
US3482503A (en) * | 1968-12-20 | 1969-12-09 | Jenn Air Corp | System for comfort conditioning structures |
US3605797A (en) * | 1970-05-18 | 1971-09-20 | Dunham Bush Inc | Shut off damper assembly for high velocity ducted air type conditioning system |
US3687054A (en) * | 1970-11-24 | 1972-08-29 | Lockheed Aircraft Corp | Air outlet apparatus |
US3799046A (en) * | 1972-04-06 | 1974-03-26 | Mitco Corp | Diffuser valve |
US3951205A (en) * | 1972-08-18 | 1976-04-20 | Brandt Engineering Co. | Air-conditioning apparatus |
US3974752A (en) * | 1974-11-25 | 1976-08-17 | The Garrett Corporation | Pressure control system |
US4283924A (en) * | 1978-08-04 | 1981-08-18 | Vereinigte Flugtechnische Werke-Fokker Gmbh | Climatizing of aircraft |
US4232211A (en) * | 1978-10-19 | 1980-11-04 | Hill Johnnie L | Automobile auxiliary heater |
US4263786A (en) * | 1979-07-10 | 1981-04-28 | The Boeing Company | Fuel conserving air-conditioning apparatus and method for aircraft |
US4446774A (en) * | 1980-05-19 | 1984-05-08 | Gershon Meckler | Air conditioning apparatus |
US4473107A (en) * | 1981-08-19 | 1984-09-25 | Building Facilities Corporation | Fan/coil induction unit, system, and method |
US4505124A (en) * | 1983-09-22 | 1985-03-19 | The United States Of America As Represented By The Secretary Of The Air Force | Heat management system for aircraft |
US4513574A (en) * | 1984-04-30 | 1985-04-30 | Tempmaster Corporation | Low Temperature air conditioning system and method |
US4844150A (en) * | 1985-10-11 | 1989-07-04 | Sanden Corporation | Air distributing mechanism for an automotive air conditioning system |
US4814579A (en) * | 1986-04-07 | 1989-03-21 | Innovative Scientific Development, Inc. | Electric resistance air reating system for an aircraft cabin |
US4819548A (en) * | 1987-05-07 | 1989-04-11 | The Boeing Company | Dual nozzle cabin ventilation system |
US4742760A (en) * | 1987-07-06 | 1988-05-10 | The Boeing Company | Aircraft cabin ventilation system |
US4742761A (en) * | 1987-07-20 | 1988-05-10 | The Boeing Company | Method and apparatus for controlling the concentration of carbon dioxide in an aircraft cabin |
US5093895A (en) * | 1988-10-24 | 1992-03-03 | Robert Brouillette | Humidifier attachable to baseboard radiator |
US5295531A (en) * | 1991-09-02 | 1994-03-22 | Sanyo Electric Co., Ltd. | Air conditioner with outside air introduction path |
US5702073A (en) * | 1993-04-27 | 1997-12-30 | E-Systems, Inc. | Modular liquid skin heat exchanger |
US5520578A (en) * | 1993-05-19 | 1996-05-28 | Nord-Micro Elektronik Feinmechanik Ag | Aircraft cabin pressure control system |
US5533568A (en) * | 1994-11-08 | 1996-07-09 | Carrier Corporation | Managing supplementary heat during defrost on heat pumps |
US5632334A (en) * | 1995-01-13 | 1997-05-27 | Nutech Energy Systems Inc. | Heat recovery ventilator with room air defrosting feature |
US5704218A (en) * | 1996-04-08 | 1998-01-06 | United Technologies Corporation | Integrated environmental control system |
US5760376A (en) * | 1996-06-19 | 1998-06-02 | Cox 3 Company, Inc. | Air heater with self-supporting heater element |
US5701755A (en) * | 1997-01-15 | 1997-12-30 | Sundstrand Corporation | Cooling of aircraft electronic heat loads |
US6024639A (en) * | 1997-07-04 | 2000-02-15 | Daimlerchrysler Aerospace Airbus Gmbh | Injector air outlet with a sensor for temperature and smoke monitoring |
US5897079A (en) * | 1997-08-18 | 1999-04-27 | Mcdonnell Douglas Corporation | Air curtain insulating system for aircraft cabin |
JPH11159782A (en) * | 1997-11-28 | 1999-06-15 | Mitsubishi Electric Corp | Warm air heater |
US6216981B1 (en) * | 1998-03-06 | 2001-04-17 | Rolls-Royce Plc | Environmental control system |
US6551184B1 (en) * | 1998-03-26 | 2003-04-22 | Fraunhofer. Gesellschaft Zur Forderung Der Angewandten Forschung E.V. | Method and device for air conditioning in vehicles |
US6510696B2 (en) * | 1998-06-15 | 2003-01-28 | Entrosys Ltd. | Thermoelectric air-condition apparatus |
US6295822B1 (en) * | 1999-08-04 | 2001-10-02 | Daimlerchrysler Aerospace Airbus Gmbh | Aircraft air-conditioning apparatus with water separators |
US6413159B1 (en) * | 2000-06-28 | 2002-07-02 | The Boeing Company | Airplane cabin overhead air outlets |
US6393717B1 (en) * | 2001-01-24 | 2002-05-28 | Victor M. Santos | Foot dryer device with diffused heated air flow system |
US20030102121A1 (en) * | 2001-11-30 | 2003-06-05 | Samsung Electronics Co., Ltd. | Air conditioner and method of controlling the same |
US20030141412A1 (en) * | 2002-01-28 | 2003-07-31 | Fieldson Charles A. | Flight crew rest and attendant rest environmental control system |
US6694765B1 (en) * | 2002-07-30 | 2004-02-24 | Thermo King Corporation | Method and apparatus for moving air through a heat exchanger |
US7203416B2 (en) * | 2003-11-21 | 2007-04-10 | Broan-Nutone Llc | Ventilating and heating apparatus with heater shielded by tapered discharge duct |
Non-Patent Citations (1)
Title |
---|
"Handbook of HVAC Design", Nils R. Grimm, PE, et al, 1990, McGraw-Hill Publishing Co., Pp. 32.2-32.5. * |
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US8118648B2 (en) * | 2007-04-25 | 2012-02-21 | Airbus Deutschland Gmbh | Air infeed device for air-conditioning passenger areas in aircraft |
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 |
US9561855B2 (en) | 2008-05-01 | 2017-02-07 | The Boeing Company | Alternate directional momentum ventilation nozzle for passenger cabins |
US9067678B2 (en) * | 2008-10-06 | 2015-06-30 | Airbus Operations Gmbh | Side feeder air guiding element for an aircraft air-conditioning system |
US20110294409A1 (en) * | 2008-10-06 | 2011-12-01 | Airbus Operations Gmbh | Side Feeder Air Guiding Element For An Aircraft Air-Conditioning System |
CN102171099A (en) * | 2008-10-06 | 2011-08-31 | 空中客车作业有限公司 | Side feeder air guiding element for an aircraft air-conditioning system |
US9011217B2 (en) * | 2008-10-22 | 2015-04-21 | Airbus Operations Gmbh | Air guide element and air guide element arrangement for an aircraft air conditioning system |
US20100099347A1 (en) * | 2008-10-22 | 2010-04-22 | Thorsten Raible | Air guide element and air guide element arrangement for an aircraft air conditioning system |
US20140295746A1 (en) * | 2011-02-04 | 2014-10-02 | Bombardier Transportation Gmbh | Ventilation System for a Passenger Transit Vehicle |
US9623722B2 (en) * | 2011-02-04 | 2017-04-18 | Bombardier Transportation Gmbh | Ventilation system for a passenger transit vehicle |
WO2013087534A1 (en) | 2011-12-14 | 2013-06-20 | Airbus Operations Gmbh | Temperature regulation of heated air distribution systems in passenger rooms |
DE102011121053A1 (en) | 2011-12-14 | 2013-06-20 | Airbus Operations Gmbh | Temperature control of heated air distribution systems in passenger spaces |
CN103998265A (en) * | 2011-12-14 | 2014-08-20 | 空中客车德国运营有限责任公司 | Temperature regulation of heated air distribution systems in passenger rooms |
US20140284314A1 (en) * | 2011-12-14 | 2014-09-25 | Airbus Operations Gmbh | Temperature regulation of heated air distribution systems in passenger rooms |
EP3744638A1 (en) * | 2019-05-31 | 2020-12-02 | Hamilton Sundstrand Corporation | Aircraft cabin air thermodynamic control |
EP4140890A1 (en) * | 2019-05-31 | 2023-03-01 | Hamilton Sundstrand Corporation | Aircraft cabin air thermodynamic control |
Also Published As
Publication number | Publication date |
---|---|
DE10361392A1 (en) | 2005-07-28 |
CA2490588C (en) | 2013-01-29 |
ATE367941T1 (en) | 2007-08-15 |
EP1550569A1 (en) | 2005-07-06 |
DE502004004424D1 (en) | 2007-09-06 |
CA2490588A1 (en) | 2005-06-29 |
EP1550569B1 (en) | 2007-07-25 |
DE10361392B4 (en) | 2009-07-30 |
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