EP2307275A2 - Système et procédé de climatisation d'une cabine d'aéronef - Google Patents

Système et procédé de climatisation d'une cabine d'aéronef

Info

Publication number
EP2307275A2
EP2307275A2 EP09777402A EP09777402A EP2307275A2 EP 2307275 A2 EP2307275 A2 EP 2307275A2 EP 09777402 A EP09777402 A EP 09777402A EP 09777402 A EP09777402 A EP 09777402A EP 2307275 A2 EP2307275 A2 EP 2307275A2
Authority
EP
European Patent Office
Prior art keywords
air
aircraft cabin
recirculation system
air conditioning
cabin area
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.)
Withdrawn
Application number
EP09777402A
Other languages
German (de)
English (en)
Inventor
Holger Brunnberg
Dariusz Krakowski
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
Publication of EP2307275A2 publication Critical patent/EP2307275A2/fr
Withdrawn legal-status Critical Current

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0018—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only
    • B64C2001/0027—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only arranged one above the other
    • 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
    • B64D2013/0688—Environmental Control Systems with means for recirculating cabin air
    • 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 system and a method for air conditioning of an aircraft cabin.
  • the cabin of a modern passenger aircraft is usually conditioned both in flight operation and in ground operation of the aircraft by means of an aircraft-specific air conditioning system.
  • the aircraft air conditioning system is supplied to the engine compressors or auxiliary engine compressors drawn bleed air, which is cooled in the air conditioning units, the so-called air conditioning of the aircraft air conditioning system to a desired low temperature.
  • the cooled air in the air conditioning of the aircraft air conditioning system is passed into a mixer, where it is mixed with extracted from the aircraft cabin i5 recirculation air.
  • the mixed air generated in the mixer from cold air supplied by the air-conditioning packs and recirculation air extracted from the aircraft cabin is finally introduced into the aircraft cabin for the purpose of air-conditioning the aircraft cabin.
  • an air-conditioning system described, for example, in DE 44 25 871 C1 which comprises two recirculation systems for extracting exhaust air from the aircraft cabin.
  • a low pressure recirculation system extracts air from an upper deck area of the cab, while a high pressure recirculation system serves to extract air from a middle deck area of the cab.
  • the recirculation air discharged from the high deck recirculation system from the center deck area of the cabin is blown into a central mixer of the aircraft air conditioning system.
  • the air drawn from the upper deck area of the cabin by the low pressure circulation system is supplied to local mixers fed by the central mixer with premixed air, ie an air mix of cold air supplied by the air conditioning packs and recirculation air from the center deck area of the cabin.
  • premixed air ie an air mix of cold air supplied by the air conditioning packs and recirculation air from the center deck area of the cabin.
  • the air mixture of premixed air from the central mixer and recirculation air from the upper deck area of the cabin, generated in the local mixers, is finally used for air conditioning of the aircraft cabin.
  • air is directed from a local mixer arranged in the region of the middle deck into the middle deck area of the cabin, while air is arranged from one in the area of the upper deck local mixer is blown into the upper deck area of the cabin.
  • An air conditioning system equipped with two recirculation systems is designed so that both recirculation systems must always provide a defined minimum airflow to ensure adequate ventilation of the aircraft cabin. During operation of the aircraft air conditioning system, it is therefore not possible to switch off a recirculation system or both recirculation systems. During operation of the recirculation systems, however, additional heat loads are generated by the waste heat generated by the blowers of the recirculation systems. The cooling energy required to cool the recirculation fans must be provided by the air conditioning system so that the operation of the recirculation systems reduces the cooling power available for cooling the aircraft cabin.
  • the additional heat input of the recirculation systems can significantly increase the time required to cool the aircraft cabin to a desired temperature.
  • the air conditioning then requires a longer lead time until the cabin has cooled sufficiently and can begin with the boarding of the passengers. This delays the handling of the aircraft at the airport. Since the A / C system is supplied with bleed air by the A / C compressors during this phase of operation, the increased lead time of the A / C system further increases fuel costs. Finally, the auxiliary engine operating time is extended, which can lead to higher maintenance costs.
  • the invention is directed to the object of providing a system and a method for the air conditioning of an aircraft cabin, which allow a shortening of the time required for cooling the aircraft cabin in ground operation of the aircraft.
  • An aircraft cabin air conditioning system comprises an air conditioning unit connected to a central mixer for supplying air at a desired low temperature to the central mixer.
  • the air conditioning unit may be supplied with bleed air from the engine compressors or the auxiliary engine compressors of the aircraft under an increased pressure.
  • a first Recirculation system of the air conditioning system according to the invention is adapted to remove exhaust air from a first aircraft cabin area.
  • the first recirculation system may comprise a plurality of air outlet openings arranged in the first aircraft cabin area, which are formed, for example, in a ground-level sidewall area or in a floor area of the first aircraft cabin area.
  • the first recirculation system of the air conditioning system according to the invention is further connected to the central mixer to direct the exhaust air discharged from the first cabin area into the central mixer.
  • the air conditioning system comprises a second recirculation system, which is adapted to remove exhaust air from a second aircraft cabin area.
  • the second recirculation system may also comprise a plurality of air outlet openings which are formed in a bottom-side sidewall region or in a bottom region of the second aircraft cabin region.
  • the first aircraft cabin area can be, for example, a middle deck area of the aircraft cabin.
  • the second aircraft cabin area may then be, for example, an upper deck area of the cabin.
  • the second recirculation system is connected to a local mixer to direct the exhaust air from the second aircraft cabin area to the local mixer.
  • the air conditioning system may also comprise a plurality of local mixers.
  • a system for air conditioning the cabin of a wide-bodied aircraft with two passenger decks may, for example, comprise a first local mixer arranged in the area of the mid-deck and a second local mixer arranged in the area of the upper deck.
  • the local mixer is connected to the central mixer.
  • the mixed air generated by the air conditioning unit and provided by the air conditioning unit cold fresh air and recirculation air from the first aircraft cabin area can thus be passed from the central mixer in the local mixer.
  • the mixed air supplied from the central mixer is finally mixed with the recirculation air discharged from the second aircraft cabin area before the mixed air is passed from the local mixer into the aircraft cabin.
  • the mixing air can be used from a the region of a middle deck angeord ⁇ Neten first local mixer to air-condition the middle deck region of the aircraft cabin, while the mixed air from a one in the field - A -
  • Upper deck arranged local mixer can be used to air condition the upper deck area of the aircraft cabin.
  • the system according to the invention for air conditioning of an aircraft cabin further comprises a control device, which is set up to control the second recirculation system in normal operation of the air conditioning system such that the second recirculation system discharges a predetermined air volume flow from the second aircraft cabin area.
  • the control device may be, for example, an electronic control device.
  • the air volume flow discharged from the second aircraft cabin area by the second recirculation system is approximately equal to the air volume flow discharged from the first aircraft cabin area by the first recirculation system.
  • control device of the system according to the invention for air conditioning of an aircraft cabin is further configured to control the second recirculation system in certain operating situations of the air conditioning system such that the air volume flow discharged from the second aircraft cabin area by the second recirculation system is greater than that during normal operation of the air conditioning system
  • control device 20 is designed to reduce the power of the second recirculation system in certain operating situations of the air conditioning system, but without completely setting the operation of the second recirculation system.
  • the idea on which the present invention is based is based on the finding that, in particular, the additional heat load, which arises as a result of the waste heat generated by the blowers of the second recirculation system, has a negative effect on the air conditioning performance of the overall system.
  • the cause of this effect o is the fact that the exhaust air discharged from the second aircraft cabin area, which is additionally heated by the waste heat of the components of the second recirculation system, is fed into the local mixer, where it does not have cold fresh air generated by the air conditioning unit but only mixed with pre-mixed and thus preheated mixed air from the central mixer before being returned to the second aircraft cabin area.
  • the amount of waste heat generated by the blowers of the second recirculation system can be reduced.
  • less heat exhaust air is supplied to the local mixer from the second aircraft cabin area. This allows a much more efficient
  • the air conditioning system according to the invention thus enables a rapid cooling of the aircraft cabin even in ground operation of the aircraft on hot days. As a result, it is easier to start boarding passengers, thus shortening the time the aircraft takes to leave the airport. In addition, the operating times of the auxiliary power unit to supply the air conditioning unit with bleed air are reduced, which fuel savings and lower maintenance costs can be realized.
  • Another advantage of the air conditioning system of the invention is that it is weight neutral, i. Optimized utilization of the cooling capacity of the air conditioning unit without additional weight.
  • the control device of the air conditioning system is preferably configured to evaluate at least one predetermined parameter and to control the second recirculation system as a function of the evaluation of the at least one predetermined parameter.
  • the evaluation of the at least one predetermined parameter is used to determine the utilization status of the air conditioning unit and components associated with the air conditioning unit.
  • the evaluation of the at least one predetermined parameter can serve to detect the presence of an operating situation in which a reduction of the additional heat input caused by the second recirculation system is desired or required.
  • the control means may so control the second recirculation system that discharged from the second recirculation system from the second aircraft cabin area air volume flow is reduced only with respect to the discharged from the second recirculation system from the second aircraft cabin area during normal operation of the air conditioning system predetermined HeilVO ⁇ volume flow when the air conditioning unit is not yet fully utilized, ie the air conditioning unit is still in an operating state, in which it can provide additional cooling power.
  • the parameter (s) evaluated by the controller (s) may be, for example, a cabin temperature feedback value for the first aircraft cabin area, a cabin temperature setpoint for the first aircraft cabin area, a cabin temperature actual value for the second aircraft cabin area, a cabin temperature setpoint for the second aircraft cabin area , an outdoor temperature actual value, an actual temperature value of the air provided by the air conditioning unit, a temperature set point of the air provided by the air conditioning unit, an actual temperature value of the air provided by the central mixer, a temperature set value provided by the central mixer Air, a temperature feedback value of the air provided by the local mixer and / or a temperature setpoint of the air provided by the local mixer.
  • control device of the air conditioning system can be set up for different air volume flow actual and / or desired values, for example the exhaust air discharged from the first aircraft cabin area, the exhaust air discharged from the second aircraft cabin area, the mixed air supplied to the local mixer by the central mixer and / or evaluate the air conditioning air injected from the local mixer into the aircraft cabin.
  • control device of the system according to the invention for air conditioning of an aircraft cabin can be set up to control the first recirculation system such that the air volume flow discharged from the first aircraft cabin area by the first recirculation system is out of the first aircraft cabin area by the first recirculation system during normal operation of the air conditioning system removed predetermined air volume flow is increased.
  • the amount of recirculation air supplied to the central mixer is increased and the loss of recirculation air is at least partially compensated by the reduction of the power of the second recirculation system.
  • the increase in the output of the first recirculation system increases the amount of waste heat generated by the first recirculation system
  • the additional heat input produced by the first recirculation system has a much smaller effect on the cooling capacity of the overall air conditioning system than that of the first recirculation system additional heat input generated by the second recirculation system during operation, as the heated by the waste heat of the blower of the first recirculation system air from the first cabin area is passed directly into the central mixer and mixed with cold fresh air.
  • the cooling of the air 5 in the aircraft cabin is therefore hardly delayed by an increase in the output of the first recirculation system.
  • the control device is configured to control the first recirculation system such that the air volume flow discharged from the first aircraft cabin area by the first recirculation system is greater than that of the first recirculation system during normal operation of the air conditioning system first predetermined air volume flow is increased by an amount which is equal to the amount by which the i5 of the second recirculation system from the second cabin area reduced air volume flow compared to the normal operation of the air conditioning system from the second recirculation system discharged from the second aircraft cabin area predetermined air volume flow ,
  • the cold fresh air generated by the air conditioning unit is fed into a central mixer.
  • a first recirculation system exhaust air is discharged from a first cabin area.
  • the air discharged from the first cabin area by the first recirculation system 5 is directed into the central mixer.
  • a second recirculation system exhaust air is discharged from a second aircraft cabin area.
  • Those of the second recirculation System discharged air from the second cabin area is directed into a local mixer.
  • Mixed air from the central mixer is fed to the local mixer.
  • the second recirculation system is controlled by a control device, which may be in the form of an electronic control device for example, in normal operation of the air conditioning system such that the second recirculation system discharges a predetermined volume of air flow from the second aircraft cabin area.
  • the second recirculation system is controlled by the control device such that the air volume flow discharged from the second aircraft cabin area by the second recirculation system is reduced compared to the air volume flow discharged from the second aircraft cabin area by the second recirculation system during normal operation of the air conditioning system.
  • the control device preferably evaluates at least one predetermined parameter and controls the second recirculation system as a function of the evaluation of the at least one predetermined parameter.
  • control device can be a cabin temperature actual value for the first aircraft cabin area, a cabin temperature setpoint for the first aircraft cabin area, a cabin temperature actual value for the second aircraft cabin area, a cabin temperature setpoint for the second aircraft cabin area, an outside temperature actual value, a temperature actual value of air provided by the air conditioning unit, a temperature setpoint of the air provided by the air conditioning unit, a temperature feedback value of the air provided by the central mixer, a setpoint temperature of the air provided by the central mixer, an actual temperature value from the local mixer provided air and / or evaluate a temperature setpoint of the air provided by the local mixer and control the second recirculation system depending on the evaluation of this / these parameters.
  • control means controls the former recirculation system such that the discharged from the first recirculation system from the first aircraft cabin area air volume flow is increased compared to a discharged from the first recirculation system from the first aircraft cabin area during normal operation of the internal climate ⁇ sticianssystems predetermined air flow rate.
  • the control device controls the first recirculation system such that the air flow discharged from the first aircraft cabin area by the first recirculation system is reduced by an amount from the predetermined air volume flow discharged from the first aircraft cabin area by the first recirculation system during normal operation of the air conditioning system which is equal to the amount by which the air volume flow discharged from the second aircraft cabin area by the second recirculation system is reduced compared to the predetermined air volume flow discharged from the second aircraft cabin area by the second recirculation system during normal operation of the air conditioning system.
  • FIG. 1 shows a schematic representation of a system according to the invention for the air conditioning of an aircraft cabin.
  • the aircraft cabin 12 comprises two passenger decks and consequently a first aircraft cabin area 12a formed by a middle deck of the aircraft cabin 12 and a second aircraft cabin area 12b formed by an upper deck of the aircraft cabin 12.
  • the air conditioning system 10 includes an air conditioning unit 14 for generating cold fresh air, which is supplied to a central mixer 16.
  • the central mixer 16 the cold fresh air produced by the air conditioning unit 14 is mixed with recirculation air supplied by a first recirculation system 18 from the first aircraft cabin area 12a, i. the middle deck of the aircraft cabin 12 is discharged.
  • the exhaust air discharge from the first aircraft cabin area 12a takes place through air outlet openings arranged in the floor area of the first aircraft cabin area.
  • the first local mixer 20 is arranged in the region of the middle deck of the aircraft cabin 12, while the second local mixer 22 is arranged in the region of the upper deck of the aircraft cabin 12.
  • the local mixers 20, 22 are also fed with recirculation air, which is supplied by a second recirculation lation system 24 is sucked out of the second aircraft cabin area 12b.
  • the recirculation air discharge from the second aircraft cabin area 12b takes place through air outlet openings arranged in a side wall area of the second aircraft cabin area 12b.
  • the air mixture generated in the first local mixer 20 is supplied to the first aircraft cabin area 12a as air conditioning air.
  • the air mixture generated in the second local mixer 22 is supplied to the second aircraft cabin area 12b as air conditioning air.
  • Excess air from the aircraft cabin 12, i. Air from the first and second aircraft cabin areas 12a, 12b, which is not supplied from recirculation air to the central mixer 16 or the local mixers 20, 22, is discharged from the aircraft cabin 12 to the environment via an air outlet valve 26.
  • the first recirculation system 18 includes blowers not illustrated in detail in the figure, which generate waste heat during operation.
  • the second recirculation system 24 also includes blowers not further illustrated in the figure and producing waste heat during operation.
  • the waste heat generated by the Rezirkulationsgebläsen provides additional heat input into the aircraft cabin 12, which must be dissipated by the air conditioning system 10.
  • the air delivered by the fans of the first recirculation system 18 from the first aircraft cabin area 12a and additionally heated by the waste heat from the fans of the first recirculation system 18 is mixed directly in the central mixer 16 with cold fresh air.
  • the air delivered by the second recirculation system 24 from the second aircraft cabin area 12b and additionally heated by the waste heat from the blowers of the second recirculation system 24 is directed into the local mixers 20, 22, from where they reappear after mixing with already premixed air is returned to the aircraft cabin 12. While the additional heat input generated by the blowers of the first recirculation system 18 has little effect on the overall system 10 efficiency, the cooling performance of the overall system 10 is significantly affected by the additional heat input from the blower of the second recirculation system 24.
  • the air conditioning system 10 further includes an electronic control device 20 configured to control the first and second recirculation systems 18, 24.
  • the control device 28 evaluates a number of parameters that are provided to the control device 28 by various sensors and / or memory devices.
  • control device 28 may have a cabin temperature actual value for the first aircraft cabin area 12a, a cabin temperature setpoint for the first aircraft cabin area 12a, a cabin temperature actual value for the second aircraft cabin area 12b, a cabin temperature setpoint for the second aircraft cabin area 12b, an outside temperature actual value, an actual temperature value of the air provided by the air-conditioning unit 14, a temperature set value of the air provided by the air-conditioning unit 14, an actual temperature value of the air provided by the central mixer 16, a temperature set value of the air provided by the central mixer 16, an actual temperature value of the air provided by the local mixers 20, 22 and / or a temperature setpoint value of the air provided by the local mixers 20, 22.
  • the controller 28 controls the first recirculation system 18 such that the first recirculation system 18 removes a predetermined volume of airflow from the second cabin area.
  • the controller 28 controls the second recirculation system 24 such that the second recirculation system 24 removes a predetermined volume of airflow from the second cabin area 12b.
  • the control device 28 for example, based on the parameter evaluation performed by it, the presence of a specific operating situation of the air conditioning system 10, i. For example, detects an operating situation in which a rapid cooling of the aircraft cabin 12 is desired or required, the controller 28 checks by evaluating the provided her parameters whether the air conditioning unit 14 is already fully utilized or capable of doing even more cooling energy provide.
  • control device 28 determines from the parameter evaluation that it has performed that the air conditioning unit 14 is not yet operated under full load and can provide additional cooling power, the control device 28 controls the second recirculation system 24 such that the second recirculation system 24 from the second aircraft cabin area 12b discharged air volume is reduced in relation to the predetermined air volume flow discharged from the second aircraft cabin area 12b during the normal operation of the air conditioning system 10 by the second recirculation system 24.
  • the air volume flow discharged from the second aircraft cabin area 12b by the second recirculation system 24 can be reduced by 20%.
  • the amount by which the air volume flow discharged from the second aircraft cabin region 12b by the second recirculation system 24 is reduced relative to the predetermined air volume flow discharged from the second aircraft cabin region 12b by the second recirculation system 24 during normal operation of the air conditioning system 10 is also dependent on the electronic control unit 28 the result of the parameter evaluation carried out by it.
  • the first recirculation system 18 is controlled by the electronic control unit 28, again depending on the parameter evaluation performed by it, such that the air volume flow discharged from the first aircraft cabin area 12a by the first recirculation system 18 is opposite the predetermined air volume flow discharged from the first aircraft cabin area 12a by the first recirculation system 18 during normal operation of the air conditioning system 10 is increased by an amount equal to the air volume flow discharged from the second aircraft cabin area 12b by the second recirculation system 24 is reduced in the normal operation of the air conditioning system 10 of the second recirculation system 24 from the second aircraft cabin area 12b discharged predetermined air flow.
  • the control device 28 ensures a redistribution of the recirculation air delivery rate between the first and the recirculation system 18, 24.
  • the increased delivery rate of the first recirculation system 18 also increases the amount of waste heat generated by the blowers of the first recirculation system 18.
  • the waste heat generated by the blowers of the first recirculation system 18 can be removed relatively easily, since the air heated by the waste heat in the central mixer 16 can be mixed directly with cold fresh air. Cooling power additionally provided by the air-conditioning unit 14 can therefore be used in a very efficient way to dissipate this waste heat.
  • Recirculation system 14 however, the generated by the blowers of the second recirculation system 14 additional heat input into the recirculation air from the second aircraft cabin area 12b significantly reduced.
  • the air in the local mixers 20, 22 may also be cooled much faster to a desired low temperature by mixing with premixed air from the central mixer 16.
  • the time required to cool the aircraft cabin 12 to a desired temperature during ground operation of the aircraft can be significantly shortened.

Landscapes

  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Air Conditioning Control Device (AREA)
  • Ventilation (AREA)
  • Air-Conditioning For Vehicles (AREA)
  • Central Air Conditioning (AREA)

Abstract

La présente invention concerne un système (10) de climatisation d'une cabine d'aéronef (12), comprenant un module de climatisation (14) qui est relié à un mélangeur central (16) pour fournir au mélangeur central (16) de l'air ayant une température basse souhaitée. Un premier système de recirculation (18) est agencé pour évacuer l'air issu d'une première zone de cabine d'aéronef (12a), et relié au mélangeur central (16) pour faire pénétrer l'air issu de la première zone de cabine d'aéronef (12a) dans le mélangeur central (16). Un deuxième système de recirculation (24) est agencé pour évacuer l'air issu d'une deuxième zone de cabine d'aéronef (12b) et est relié à un mélangeur local (20, 22) pour faire pénétrer l'air issu de la deuxième zone de cabine d'aéronef (12b) dans le mélangeur local (20, 22). Le mélangeur local (20, 22) est relié au mélangeur central (16) pour faire pénétrer de l'air mélangé issu du mélangeur central (16) dans le mélangeur local (20, 22). Un dispositif de commande (28) est agencé pour commander le deuxième système de recirculation (24) lorsque le système de climatisation (10) se trouve dans un mode de fonctionnement normal, de sorte que le deuxième système de recirculation (24) évacue un débit volumique d'air prédéterminé de la deuxième zone de cabine d'aéronef (12). Le dispositif de commande (28) est également agencé pour commander le deuxième système de recirculation (24) lorsque le système de climatisation (10) se trouve dans des situations de fonctionnement déterminées, de sorte que le débit volumique d'air évacué de la deuxième zone de cabine d'aéronef (12b) par le deuxième système de recirculation (24), est réduit par rapport au débit volumique d'air prédéterminé évacué de la deuxième zone de cabine d'aéronef (12b) par le deuxième système de recirculation (24) lorsque le système de climatisation (10) se trouve dans un mode de fonctionnement normal.
EP09777402A 2008-07-28 2009-07-23 Système et procédé de climatisation d'une cabine d'aéronef Withdrawn EP2307275A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US8397608P 2008-07-28 2008-07-28
DE102008035123.7A DE102008035123B4 (de) 2008-07-28 2008-07-28 System und Verfahren zur Klimatisierung einer Flugzeugkabine
PCT/EP2009/005361 WO2010012415A2 (fr) 2008-07-28 2009-07-23 Système et procédé de climatisation d'une cabine d'aéronef

Publications (1)

Publication Number Publication Date
EP2307275A2 true EP2307275A2 (fr) 2011-04-13

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Application Number Title Priority Date Filing Date
EP09777402A Withdrawn EP2307275A2 (fr) 2008-07-28 2009-07-23 Système et procédé de climatisation d'une cabine d'aéronef

Country Status (9)

Country Link
US (1) US9011219B2 (fr)
EP (1) EP2307275A2 (fr)
JP (1) JP2011529010A (fr)
CN (1) CN102131701B (fr)
BR (1) BRPI0916646A2 (fr)
CA (1) CA2732074A1 (fr)
DE (1) DE102008035123B4 (fr)
RU (1) RU2011105761A (fr)
WO (1) WO2010012415A2 (fr)

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DE102008035123B4 (de) 2015-01-15
WO2010012415A3 (fr) 2010-05-27
JP2011529010A (ja) 2011-12-01
DE102008035123A1 (de) 2010-02-11
RU2011105761A (ru) 2012-09-10
CA2732074A1 (fr) 2010-02-04
US9011219B2 (en) 2015-04-21
CN102131701A (zh) 2011-07-20
CN102131701B (zh) 2013-10-09
US20110212678A1 (en) 2011-09-01
WO2010012415A2 (fr) 2010-02-04
WO2010012415A4 (fr) 2010-07-08
BRPI0916646A2 (pt) 2015-11-17

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