EP2340202A1 - Système et procédé de climatisation d'une cabine d'aéronef permettant d'obtenir une puissance de refroidissement améliorée - Google Patents

Système et procédé de climatisation d'une cabine d'aéronef permettant d'obtenir une puissance de refroidissement améliorée

Info

Publication number
EP2340202A1
EP2340202A1 EP09736856A EP09736856A EP2340202A1 EP 2340202 A1 EP2340202 A1 EP 2340202A1 EP 09736856 A EP09736856 A EP 09736856A EP 09736856 A EP09736856 A EP 09736856A EP 2340202 A1 EP2340202 A1 EP 2340202A1
Authority
EP
European Patent Office
Prior art keywords
recirculation
air
mixer
aircraft cabin
air conditioning
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Withdrawn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
EP09736856A
Other languages
German (de)
English (en)
Inventor
Juergen Kelnhofer
Dariusz Krakowski
Ahmet Kayihan Kiryaman
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 EP2340202A1 publication Critical patent/EP2340202A1/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Withdrawn legal-status Critical Current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
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • 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
    • B64D2013/0655—Environmental Control Systems with zone or personal climate controls
    • 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

Definitions

  • the present invention relates to a system and a method for air conditioning an aircraft cabin, which provide improved cooling performance compared to known systems and methods.
  • the cabin of a modern passenger aircraft is usually air-conditioned both in flight and in ground operation of the aircraft by means of an air-conditioning system.
  • the air conditioning units of the aircraft air conditioning system which are arranged, for example, in the wing roots of the aircraft, are supplied with bleed air taken from the engine compressors or auxiliary power plant compressors, which air is cooled to a desired low temperature in the air conditioning units.
  • the air conditioning units may also supply warm air for heating the aircraft cabin.
  • the cooled air in the air conditioning units of the aircraft air conditioning system is passed into a mixer, where it is mixed with air extracted from the aircraft cabin recirculation.
  • an air-conditioning system described for example in DE 44 25 871 C2 which comprises two recirculation systems for extracting recirculation air from the aircraft cabin.
  • a low pressure recirculation system extracts air from an upper deck area of the cabin, while a high pressure recirculation system serves to extract air from a middle deck area of the cabin.
  • 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 lower deck area of the cabin by the low pressure recirculation system is supplied to local mixers fed by the central mixer with pre-mixed air, ie an air mixture of cold fresh air provided by the air conditioning units and recirculation air from the middle deck area of the cabin ,
  • pre-mixed air ie an air mixture of cold fresh air provided by the air conditioning units and recirculation air from the middle deck area of the cabin
  • the air mix of premixed air generated in the local mixers from the central mixer and recirculation air from the upper deck area of the cabin is finally used for air conditioning of the aircraft cabin.
  • air from a local mixer arranged in the area of the middle deck is directed into the middle deck area of the cabin, while air from a local mixer arranged in the area of the upper deck is blown into the upper deck area of the cabin.
  • auxiliary power compressor Increasing the performance of the auxiliary power compressor, however, in turn results in additional costs, additional weight and integration problems, or at least a significant reduction in the service life of the compressor.
  • increasing the size of the air conditioning units may require adjustments to other aircraft components and systems, such as air conditioning systems. the circulating air blowers and the piping systems, which can again result in additional costs, additional weight and integration problems.
  • the invention is directed to the object of specifying a system and a method for the air conditioning of an aircraft cabin, which, while avoiding the disadvantages described above, which are associated with an increase in the air conditioning units, provides improved cooling performance compared to known systems and methods.
  • a system for air conditioning an aircraft cabin comprises an air conditioning unit which is connected to a central mixer to the central Mixer to supply air at a desired low temperature.
  • 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. If desired or necessary, the air conditioning system according to the invention can also have several air conditioning units.
  • a first recirculation system of the air conditioning system according to the invention is adapted to remove recirculation air from a first 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 for directing the recirculation air discharged from the first cabin area into the central mixer.
  • the air conditioning system comprises a second recirculation system, which is adapted to discharge recirculation air from a second aircraft cabin area.
  • the second recirculation system may also include a plurality of air outlet openings 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 recirculation 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 middle 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 in the central mixer from the air conditioning unit provided cold fresh air and recirculation air from the first aircraft cabin area can thus be directed from the central mixer in the local mixer.
  • the mixed air supplied from the central mixer is still mixed with the recirculation air discharged from the second aircraft cabin area. mixes before passing the mixed air from the local mixer into the aircraft cabin.
  • mixed air from a first local mixer arranged in the region of a middle deck can be used to air-condition the middle deck area of the aircraft cabin
  • mixed air from a local mixer arranged in the area of an upper deck can be used to air-condition the upper deck area of the aircraft cabin.
  • the second recirculation system comprises a cooling unit formed separately from the air conditioning unit or the air conditioning units of the air conditioning system.
  • the cooling unit is arranged upstream of the local mixer in the second recirculation system relative to the flow direction of the recirculation air discharged from the second aircraft cabin area and is configured to cool the recirculation air discharged from the second aircraft cabin area to a desired temperature.
  • the refrigeration unit of the second recirculation system causes the recirculation air discharged from the second cabin area to be pre-cooled to a desired temperature before being directed into the local mixer.
  • the temperature of the air conditioning air exiting the local mixer can be effectively reduced without it being necessary to supply mixing air to the local mixer from the central mixer at a lower temperature.
  • the air conditioning system according to the invention can thus be lowered, the temperature of the guided from the local mixer in the aircraft cabin air conditioning air, without it being necessary to increase the cooling capacity of the air conditioning unit or the air conditioning units.
  • the air conditioning system according to the invention thus makes it possible to increase the cooling capacity of the entire system by integrating an additional requirement-specific dimensioned cooling unit into the second recirculation system, without requiring an increase in the air conditioning unit or the air conditioning units.
  • the air conditioning system according to the invention can therefore typically avoid disadvantages associated with an increase in the air conditioning unit or the air conditioning units, such as additional costs, additional weight and integration problems.
  • the air conditioning unit is located in a central recirculation discharge line of the second recirculation system.
  • the refrigeration unit may be arranged in the central recirculation air tabschreibtechnisch the second recirculation system with respect to the flow direction of discharged from the second aircraft cabin area recirculation air in the second recirculation system also downstream of a recirculation fan.
  • the cooling unit is arranged in a first recirculation air distribution line of the second recirculation system.
  • the first recirculation air distribution line preferably branches off from the central recirculation air discharge line of the second recirculation system and connects the central recirculation air discharge line to a first local mixer.
  • the refrigeration unit can be arranged upstream of the local mixer in relation to the flow direction of the recirculation air discharged from the second aircraft cabin area in the second recirculation system.
  • the cooling unit can also be arranged in a second recirculation air distribution line of the second recirculation system, which connects the central recirculation air discharge line with a second local mixer.
  • the refrigeration unit is preferably arranged upstream of the second local mixer with respect to the flow direction of the recirculation air discharged from the second aircraft cabin area in the second recirculation system.
  • the second recirculation system of the air conditioning system according to the invention may also comprise more than one refrigeration unit.
  • the refrigeration units can then be arranged at the above-described positions in the second recirculation system, wherein two or more refrigeration units can be arranged one behind the other at one position or the refrigeration units can be distributed at different positions in the second recirculation system.
  • the cooling unit provided in the second recirculation system of the air conditioning system according to the invention may be adapted to be supplied with cooling energy by an existing cooling system of the aircraft.
  • the cooling unit may be designed in the form of a heat exchanger to which cooling energy is supplied from an existing cooling system of the aircraft.
  • Cooling systems which supply cooling energy to the cooling unit of the air-conditioning system according to the invention include, for example, cooling systems installed in the area of the galleys or cooling systems serving to cool the aircraft electronics.
  • the cooling unit provided in the second recirculation system of the air conditioning system according to the invention may also be designed as an independent cooling system, ie as a cooling system which itself generates cooling energy.
  • the cooling unit may be configured in the form of an air chili.
  • air having a desired low temperature is generated by means of an air conditioning unit.
  • the cold fresh air generated by the air conditioning unit is fed into a central mixer.
  • a first recirculation system recirculation air is discharged from a first cabin area.
  • the air discharged from the first cabin area by the first recirculation system is directed to the central mixer.
  • a second recirculation system recirculation air is discharged from a second aircraft cabin area.
  • the air discharged from the second aircraft cabin area by the second recirculation system is directed to a local mixer.
  • Mixed air from the central mixer is fed to the local mixer.
  • the recirculation air discharged from the second aircraft cabin area is cooled to a desired temperature by a refrigeration unit of the second recirculation system, which is formed separately from the air conditioning unit or the air conditioning units of the air conditioning system, before it is fed into the local mixer.
  • the chiller may be located in a central recirculation air discharge line of the second recirculation system upstream or downstream from a recirculation fan, in a first recirculation air distribution line of the second recirculation system upstream of a first local mixer or in a second recirculation air distribution line of the second recirculation system upstream be arranged by a second mixer.
  • the cooling unit can be supplied with cooling energy by an existing cooling system of the aircraft or can be designed as an independent cooling system.
  • FIG. 1 shows an overview of a system for air conditioning of an aircraft cabin
  • FIG. 2 shows a detailed representation of a first embodiment of an air conditioning system according to the invention
  • FIG. 3 shows a detailed representation of a second embodiment of an air-conditioning system according to the invention
  • FIG. 4 shows a detailed representation of a third embodiment of an air-conditioning system according to the invention.
  • Figure 5 shows a detailed view of a fourth embodiment of an air conditioning system according to the invention.
  • FIG. 1 shows a system 10 for air conditioning of an aircraft cabin 12.
  • 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 comprises two air conditioning units 14a, 14b arranged in the wing root regions of the aircraft for generating cold fresh air, which is supplied to a central mixer 16.
  • Check valves 17a, 17b prevent backflow of air from the mixer 16 into the air conditioning units 14a, 14b.
  • the central mixer 16 the cold fresh air generated by the air conditioning units 14a, 14b mixed with recirculation air, which is discharged from a first recirculation system 18 from the first aircraft cabin area 12a, ie the middle deck of the aircraft cabin 12.
  • the recirculation air removal from the first aircraft cabin area 12a is effected by means of two recirculation fans 19a, 19b by 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 5 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 further supplied with recirculation air which is drawn from the second aircraft cabin area 12b by a second recirculation system 24.
  • Recirculation air removal from the second aircraft cabin area 12b takes place by means of a recirculation fan 25 through air outlet openings arranged in a side wall area of the second aircraft cabin area 12b.
  • a filter 26 arranged upstream of the recirculation fan 25, relative to the flow direction of the recirculation air discharged from the second aircraft cabin area 12b, cleans the recirculation air discharged from the second aircraft cabin area 12b.
  • the second recirculation system 24 further comprises a cooling unit 28 formed separately from the air conditioning units 14a, 14b, the possible arrangements of which are illustrated in the second recirculation system 24 in FIGS. 2 to 5.
  • the cooling unit 28 serves to cool the recirculation air discharged from the second aircraft cabin area 12b before it is fed into the local mixers 20, 22 to a desired temperature.
  • the cooling unit 28 may be designed, for example, in the form of a heat exchanger and be supplied with cooling energy by an existing cooling system of the aircraft. For example, one in the field of
  • cooling unit 28 25 galleys of the aircraft installed cooling system or an aircraft electronics cooling system to supply the cooling unit 28 are used with cooling energy.
  • the cooling unit 28 may also be embodied as an independent cooling system, for example in the form of an air chill.
  • the cooling unit 28 is arranged in a central recirculation air discharge line 30 of the second recirculation system 24. Relative to the flow direction of the recirculation air discharged from the second aircraft cabin area 12b in the second recirculation system 24, the refrigeration unit 28 is downstream of the latter
  • J5 recirculation fan 25 of the second recirculation system 24 is arranged.
  • the cooling unit 28 in the central recirculation air discharge line 30 of the second recirculation system 24 may also be arranged upstream of the recirculation fan 25.
  • the refrigeration unit 28 is positioned downstream of the filter 26. Alternatively, however, the refrigeration unit 28 may be disposed upstream of the filter 26.
  • the refrigeration unit 28 is arranged in a first recirculation air distribution line 32 of the second recirculation system 24, which connects the central recirculation air discharge line 30 to the first local mixer 20.
  • the refrigeration unit 28 is downstream with respect to the flow direction of the recirculation air discharged from the second aircraft cabin area 12b in the second recirculation system 24 from a connection point 36 of the central recirculation air discharge line 30 to the first recirculation air distribution line 32 and upstream of the first recirculation air distribution line 32 local mixer 20 arranged.
  • FIG. 5 shows a further alternative embodiment of an air-conditioning system 10, in which the cooling unit 28 is operated in a second recirculation air-conditioning system.
  • the 20 distribution line 38 is arranged, which connects the central Rezirkulations Kunststoffabschreibtechnisch 30 with the second local mixer 22. Based on the flow direction of the recirculation air discharged from the second aircraft cabin area 12b in the second recirculation system 24, the refrigeration unit 28 in the second recirculation air distribution line 38 is downstream of a connection point 36 of FIG.

Landscapes

  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (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 est 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). Le deuxième système de recirculation (24) comprend un module de refroidissement (28) qui est disposé en amont du mélangeur local (20, 22) dans le deuxième système de recirculation (24), par rapport au sens d'écoulement de l'air de recirculation évacué de la deuxième zone de cabine d'aéronef (12b), et qui est conçu pour refroidir l'air de recirculation évacué de la deuxième zone de cabine d'aéronef (12b) à une température souhaitée.
EP09736856A 2008-10-29 2009-10-13 Système et procédé de climatisation d'une cabine d'aéronef permettant d'obtenir une puissance de refroidissement améliorée Withdrawn EP2340202A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US10933608P 2008-10-29 2008-10-29
DE200810053668 DE102008053668B4 (de) 2008-10-29 2008-10-29 System und Verfahren zur Klimatisierung einer Flugzeugkabine mit verbesserter Kühlleistung
PCT/EP2009/007350 WO2010049060A1 (fr) 2008-10-29 2009-10-13 Système et procédé de climatisation d'une cabine d'aéronef permettant d'obtenir une puissance de refroidissement améliorée

Publications (1)

Publication Number Publication Date
EP2340202A1 true EP2340202A1 (fr) 2011-07-06

Family

ID=42096282

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09736856A Withdrawn EP2340202A1 (fr) 2008-10-29 2009-10-13 Système et procédé de climatisation d'une cabine d'aéronef permettant d'obtenir une puissance de refroidissement améliorée

Country Status (9)

Country Link
US (1) US9085368B2 (fr)
EP (1) EP2340202A1 (fr)
JP (1) JP2012506815A (fr)
CN (1) CN102202970B (fr)
BR (1) BRPI0919967A2 (fr)
CA (1) CA2740642A1 (fr)
DE (1) DE102008053668B4 (fr)
RU (1) RU2011118857A (fr)
WO (1) WO2010049060A1 (fr)

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Also Published As

Publication number Publication date
RU2011118857A (ru) 2012-12-10
US9085368B2 (en) 2015-07-21
DE102008053668A1 (de) 2010-05-12
US20110237173A1 (en) 2011-09-29
JP2012506815A (ja) 2012-03-22
WO2010049060A1 (fr) 2010-05-06
CN102202970B (zh) 2016-01-20
BRPI0919967A2 (pt) 2015-12-08
DE102008053668B4 (de) 2010-11-25
CN102202970A (zh) 2011-09-28
WO2010049060A4 (fr) 2010-06-24
CA2740642A1 (fr) 2010-05-06

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