WO2006015858A1 - System for producing process air - Google Patents

System for producing process air Download PDF

Info

Publication number
WO2006015858A1
WO2006015858A1 PCT/EP2005/008692 EP2005008692W WO2006015858A1 WO 2006015858 A1 WO2006015858 A1 WO 2006015858A1 EP 2005008692 W EP2005008692 W EP 2005008692W WO 2006015858 A1 WO2006015858 A1 WO 2006015858A1
Authority
WO
WIPO (PCT)
Prior art keywords
air
cooling system
cooling
integrated
heat exchanger
Prior art date
Application number
PCT/EP2005/008692
Other languages
French (fr)
Inventor
Jürgen KELNHOFER
Thomas Scherer
Original Assignee
Airbus Deutschland 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 Deutschland Gmbh filed Critical Airbus Deutschland Gmbh
Priority to DE602005019414T priority Critical patent/DE602005019414D1/en
Priority to JP2007525250A priority patent/JP5336077B2/en
Priority to CA2573660A priority patent/CA2573660C/en
Priority to BRPI0513758-6A priority patent/BRPI0513758A/en
Priority to AT05774315T priority patent/ATE457926T1/en
Priority to US11/573,531 priority patent/US7922118B2/en
Priority to EP05774315A priority patent/EP1776271B1/en
Publication of WO2006015858A1 publication Critical patent/WO2006015858A1/en

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
    • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
    • 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
    • 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
    • B64D2013/0677—Environmental Control Systems comprising on board oxygen generator systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
    • F28D2021/0021—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for aircrafts or cosmonautics
    • 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
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to a system for producing process air, in particular to a system for producing temperature-controlled, highly-compressed process air in an aircraft.
  • Different systems may be used to produce temperature-controlled, highly- compressed process air in an aircraft. These systems predominantly comprise a heat exchanger and numerous control valves and control sensors for pressure and temperature (wherein the number of said sensors differs depending on the system).
  • the associated process air is taken from the hot air system (bleed air system) which is either fed by the engines or by the aircraft's auxiliary turbine (APU).
  • bleed air system hot air system
  • APU auxiliary turbine
  • the hot process air it is for example necessary for the hot process air to be cooled to cold process air and to be relaxed, for the purpose of supplying fresh air to the cabin or the cockpit of an aircraft.
  • a ram-air cooling channel results in added aircraft weight, increased production expenditure and increased maintenance costs. Furthermore, the provision of a ram-air cooling channel may lead to an increase in the air resistance of the aircraft.
  • the use of external cooling air results in a moment resistance which has the effect of "negative thrust”. "Sucking in” external cooling air, and “blowing out” external cooling air results in disturbances in the overall airflow around the aircraft, which in turn has a negative influence on the overall aircraft resistance.
  • a further cooling system is integrated in a channel which serves as a cooling sink of an already existing and installed cooling system.
  • This integrated cooling system comprises a heat exchanger, corresponding control valves, control sensors, a process-air inlet line and a process-air outlet line, which are integrated in the already existing cooling system such that the process-air inlet line of the integrated cooling system branches off from a process-air inlet line of the already existing cooling system.
  • the heat exchanger of the integrated cooling system is arranged upstream or downstream of the heat exchanger of the already existing cooling system in the ram-air cooling channel. If the cooling output of the cooling system to be integrated is lower than that of the already existing cooling system, the heat exchanger of the cooling system to be integrated is preferably integrated in the ram- air cooling channel upstream of the heat exchanger of the already existing cooling system. If the cooling output of the already existing cooling system is lower than that of the cooling system to be integrated, then it is preferred to install the heat exchanger of the cooling system to be integrated in a position in the ram-air cooling channel, which position is located downstream of the already existing cooling system.
  • an ozone filter (hereinafter also referred to as an ozone converter) is arranged in the process-air inlet line for filtering ozone in the process-air inlet line.
  • an individual ozone converter is provided for the already existing cooling system and for the cooling system to be integrated.
  • an aircraft air conditioning system or a ventilation system for aircraft regions that are not pressurised constitutes an already existing cooling system.
  • the system according to the invention may for example be used in an A380 for operating the OBIGGS system. Further A380 applications for the therapeutic oxygen system or for pressurising the fresh water system may be possible.
  • Fig. 1 shows a diagrammatic view of a system for providing temperature-controlled highly-compressed process air according to an exemplary embodiment of the invention.
  • the system 1 comprises an already existing air cooling system 2.
  • the cooling system comprises an already existing air cooling system 2.
  • Fig. 1 is based on so-called air-air technology.
  • a system which is based on liquid-air technology or some other technology may also be possible to use.
  • the cooling system 2 which according to the exemplary embodiment is based on air-air technology, requires a ram-air cooling channel 3.
  • This ram-air cooling channel 3
  • ram-air cooling channel 3 comprises a ram-air cooling channel inlet 4 and a ram-air cooling channel outlet 5; in the already existing air cooling system 2 said ram-air cooling channel 3 is used for producing a necessary cooling sink in order to cool hot process air down to cold process air.
  • the cooling system 2 comprises a process-air inlet line 6, by way of which hot process air, for example from the engines, is fed to the cooling system 2.
  • hot process air for example from the engines
  • the cooling system 2 By means of the heat exchanger (not shown) contained in the cooling system 2, and the ram-air cooling channel 3, which serves as a cooling sink, this hot process air is transformed into cold process air in order to be issued as cooled highly- compressed process air by way of a process-air outlet line 7 from the cooling system 2 for further use at corresponding destinations.
  • the system 1 comprises a further (integrated) cooling system 8, comprising a heat exchanger 9, a control sensor 10 and a control valve 11 for controlling the quantity of process air.
  • This integrated cooling system 8 is integrated in the already existing cooling system 2 such that according to the preferred embodiment the heat exchanger 9 of the integrated cooling system 8 is arranged upstream in the ram-air cooling channel 3 of the cooling system 2.
  • a control valve 15 for controlling bypass process air for temperature control is provided for the cooling system 8 and/or the process air.
  • Reference number 16 designates a bypass line for process air.
  • a control sensor 17 is provided for pressure control and temperature control for the cooling system 8 and/or the process air.
  • the heat exchanger 9 of the cooling system 8 to be integrated is installed upstream of the heat exchanger (not shown) of the already existing cooling system 2 in the ram-air cooling channel, because the cooling output of the integrated cooling system 8 is lower than that of the already existing cooling system 2. If the cooling performance of the cooling system 2 is lower than that of the cooling system 8 to be integrated, then installation of the heat exchanger 9 of the cooling system to be integrated preferably takes place downstream of the heat exchanger of the already existing cooling system 2 in the ram-air cooling channel 3.
  • the cooling system 8 to be integrated comprises a process-air inlet line 12 by way of which the cooling system 8 is supplied with hot process air.
  • the process-air inlet line 12 of the cooling system 8 may be, e.g. connected to the process-air inlet line 6 of the already existing cooling system 2.
  • the integrated cooling system 8 issues temperature-controlled highly-compressed cold process air for further use at corresponding destinations.
  • the system 1 further comprises an ozone converter 14.
  • Said ozone converter 14 may be arranged in such a way that hot process air, for example from the engines, is ozone filtered before it is supplied, by way of the process-air inlet line 6 to the already existing cooling system 2, and by way of the process-air inlet line 12 to the integrated cooling system 8.
  • Providing an ozone converter 14 may be necessary when the cold process air, which has been cooled by the cooling systems 2, 8, is used as a fresh-air supply to the cabin and the cockpit.
  • the OBIGGS system not shown
  • a further cooling system into an already existing cooling system, wherein an increase in weight of the vehicle may virtually be prevented because the new cooling system is integrated into an already existing ram-air cooling channel.
  • additional expenditure in the production of the aircraft may virtually be prevented because there is no need to install a further ram-air cooling channel.
  • increased expenditure for maintenance may virtually be prevented because there is no need to install any further systems in the aircraft.
  • increase in the air resistance or drag of the aircraft can virtually be compensated for. While external cooling air is still used (moment resistance still occurs), as a result of integration into an already existing ram-air cooling channel the negative influences on "sucking in” and "blowing out” external cooling air may however be virtually prevented.

Landscapes

  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Cooling Or The Like Of Electrical Apparatus (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Continuous Casting (AREA)
  • Other Air-Conditioning Systems (AREA)
  • Oxygen, Ozone, And Oxides In General (AREA)
  • Sorption Type Refrigeration Machines (AREA)

Abstract

A system for the provision of process air comprises a first cooling system (2) with a first heat exchanger, which is arranged in a channel (3) that serves as a cooling sink, and a cooling system (8), integrated in the first cooling system (2), wherein said cooling system (8) comprises a heat exchanger (9) which is integrated in the channel (3) either upstream or downstream of the first heat exchanger.

Description

System for producing process air
This application claims the benefit of the filing date of United States Provisional Patent Application No. 60/600,274 filed on August 10, 2004, the disclosure of which is hereby incorporated herein by reference and of the German Patent Application No. 10 2004 038 860.1 filed on August 10, 2004, the disclosure of which is hereby incorporated herein by reference.
The present invention relates to a system for producing process air, in particular to a system for producing temperature-controlled, highly-compressed process air in an aircraft.
Different systems may be used to produce temperature-controlled, highly- compressed process air in an aircraft. These systems predominantly comprise a heat exchanger and numerous control valves and control sensors for pressure and temperature (wherein the number of said sensors differs depending on the system).
The associated process air is taken from the hot air system (bleed air system) which is either fed by the engines or by the aircraft's auxiliary turbine (APU).
It is for example necessary for the hot process air to be cooled to cold process air and to be relaxed, for the purpose of supplying fresh air to the cabin or the cockpit of an aircraft.
Already existing air cooling systems (whose heat exchangers are based on air-air refrigeration technology or liquid-air refrigeration technology) require a ram-air cooling channel of their own to produce the necessary cooling sink.
However, the provision of such a ram-air cooling channel results in added aircraft weight, increased production expenditure and increased maintenance costs. Furthermore, the provision of a ram-air cooling channel may lead to an increase in the air resistance of the aircraft. The use of external cooling air results in a moment resistance which has the effect of "negative thrust". "Sucking in" external cooling air, and "blowing out" external cooling air results in disturbances in the overall airflow around the aircraft, which in turn has a negative influence on the overall aircraft resistance.
It may therefore be desirable to provide a system which minimises or almost completely prevents the above-mentioned negative effects on the aircraft.
In the system according to an exemplary embodiment of the invention, a further cooling system is integrated in a channel which serves as a cooling sink of an already existing and installed cooling system.
This integrated cooling system comprises a heat exchanger, corresponding control valves, control sensors, a process-air inlet line and a process-air outlet line, which are integrated in the already existing cooling system such that the process-air inlet line of the integrated cooling system branches off from a process-air inlet line of the already existing cooling system.
Furthermore, the heat exchanger of the integrated cooling system is arranged upstream or downstream of the heat exchanger of the already existing cooling system in the ram-air cooling channel. If the cooling output of the cooling system to be integrated is lower than that of the already existing cooling system, the heat exchanger of the cooling system to be integrated is preferably integrated in the ram- air cooling channel upstream of the heat exchanger of the already existing cooling system. If the cooling output of the already existing cooling system is lower than that of the cooling system to be integrated, then it is preferred to install the heat exchanger of the cooling system to be integrated in a position in the ram-air cooling channel, which position is located downstream of the already existing cooling system.
According to another exemplary embodiment of the invention, an ozone filter (hereinafter also referred to as an ozone converter) is arranged in the process-air inlet line for filtering ozone in the process-air inlet line. E.g. an individual ozone converter is provided for the already existing cooling system and for the cooling system to be integrated. By connecting the process-air inlet line for the cooling system to be integrated so that it is positioned downstream of the already existing ozone converter of the existing cooling system, there may be no need to install it for the cooling system to be integrated. This may result in savings in both weight and cost.
According to another exemplary embodiment of the invention, for example an aircraft air conditioning system or a ventilation system for aircraft regions that are not pressurised constitutes an already existing cooling system.
The system according to the invention may for example be used in an A380 for operating the OBIGGS system. Further A380 applications for the therapeutic oxygen system or for pressurising the fresh water system may be possible.
Because of the special integration concept according to the invention, i.e. the integration in an already existing cooling system, at the aircraft level it is possible to achieve savings in weight and in additional work and at the same time reduce the air resistance or drag.
Below, a preferred embodiment of the system according to the invention is described with reference to the enclosed Fig. 1. Fig. 1 shows a diagrammatic view of a system for providing temperature-controlled highly-compressed process air according to an exemplary embodiment of the invention.
The system 1 comprises an already existing air cooling system 2. The cooling system
2 shown in Fig. 1 is based on so-called air-air technology. As an alternative it may also be possible to use a system which is based on liquid-air technology or some other technology.
The cooling system 2, which according to the exemplary embodiment is based on air-air technology, requires a ram-air cooling channel 3. This ram-air cooling channel
3 comprises a ram-air cooling channel inlet 4 and a ram-air cooling channel outlet 5; in the already existing air cooling system 2 said ram-air cooling channel 3 is used for producing a necessary cooling sink in order to cool hot process air down to cold process air.
As shown in Fig. 1, the cooling system 2 comprises a process-air inlet line 6, by way of which hot process air, for example from the engines, is fed to the cooling system 2. By means of the heat exchanger (not shown) contained in the cooling system 2, and the ram-air cooling channel 3, which serves as a cooling sink, this hot process air is transformed into cold process air in order to be issued as cooled highly- compressed process air by way of a process-air outlet line 7 from the cooling system 2 for further use at corresponding destinations.
As shown in Fig. 1, the system 1 comprises a further (integrated) cooling system 8, comprising a heat exchanger 9, a control sensor 10 and a control valve 11 for controlling the quantity of process air. This integrated cooling system 8 is integrated in the already existing cooling system 2 such that according to the preferred embodiment the heat exchanger 9 of the integrated cooling system 8 is arranged upstream in the ram-air cooling channel 3 of the cooling system 2. Furthermore, a control valve 15 for controlling bypass process air for temperature control is provided for the cooling system 8 and/or the process air. Reference number 16 designates a bypass line for process air. A control sensor 17 is provided for pressure control and temperature control for the cooling system 8 and/or the process air.
According to the exemplary embodiment, as shown in Fig. 1, it is important that the heat exchanger 9 of the cooling system 8 to be integrated is installed upstream of the heat exchanger (not shown) of the already existing cooling system 2 in the ram-air cooling channel, because the cooling output of the integrated cooling system 8 is lower than that of the already existing cooling system 2. If the cooling performance of the cooling system 2 is lower than that of the cooling system 8 to be integrated, then installation of the heat exchanger 9 of the cooling system to be integrated preferably takes place downstream of the heat exchanger of the already existing cooling system 2 in the ram-air cooling channel 3.
As shown in Fig. 1, the cooling system 8 to be integrated comprises a process-air inlet line 12 by way of which the cooling system 8 is supplied with hot process air. The process-air inlet line 12 of the cooling system 8 may be, e.g. connected to the process-air inlet line 6 of the already existing cooling system 2.
By way of a process-air outlet line 13 the integrated cooling system 8 issues temperature-controlled highly-compressed cold process air for further use at corresponding destinations.
As shown in Fig. 1, the system 1 further comprises an ozone converter 14. Said ozone converter 14 may be arranged in such a way that hot process air, for example from the engines, is ozone filtered before it is supplied, by way of the process-air inlet line 6 to the already existing cooling system 2, and by way of the process-air inlet line 12 to the integrated cooling system 8. Providing an ozone converter 14 may be necessary when the cold process air, which has been cooled by the cooling systems 2, 8, is used as a fresh-air supply to the cabin and the cockpit. Especially for use with the OBIGGS system (not shown) it is necessary to provide ozone-free process air, because otherwise the air separation module (not shown) would be damaged.
Although, above, a preferred embodiment of the invention for use in an aircraft is described, it goes without saying that application may also be possible in other areas, for example in railway equipment, a motor vehicle etc., provided a cooling system exists therein which comprises a channel which is used as a cooling sink, in which areas a further cooling system according to the invention may be integrated.
Moreover, it may be possible to not only install (integrate) one further cooling system into an already existing cooling system in the way according to the invention, but to install (integrate) a plural number of further cooling systems.
According to an exemplary embodiment of the invention as shown in Fig. 1, it may be possible to integrate a further cooling system into an already existing cooling system, wherein an increase in weight of the vehicle may virtually be prevented because the new cooling system is integrated into an already existing ram-air cooling channel. Furthermore, in the exemplary embodiment described above, additional expenditure in the production of the aircraft may virtually be prevented because there is no need to install a further ram-air cooling channel. Moreover, increased expenditure for maintenance may virtually be prevented because there is no need to install any further systems in the aircraft. Finally, according to the exemplary embodiment, as shown in Fig. 1, increase in the air resistance or drag of the aircraft can virtually be compensated for. While external cooling air is still used (moment resistance still occurs), as a result of integration into an already existing ram-air cooling channel the negative influences on "sucking in" and "blowing out" external cooling air may however be virtually prevented.
List of reference numbers
1 System
2 Existing cooling system
3 Ram-air cooling channel
4 Ram-air cooling channel inlet
5 Ram-air cooling channel outlet
6 Process-air inlet line
7 Process-air outlet line
8 Further cooling system (cooling system to be integrated)
9 Heat exchanger of the cooling system to be integrated
10 First control sensor
11 First control valve
12 Process-air inlet line
13 Process-air outlet line
14 Ozone converter
15 Second control valve
16 Bypass line for process air
17 Second control sensor

Claims

C l a i m s
1. A system for providing process air, the system comprising: a first cooling system with a first heat exchanger; and an integrated cooling system integrated in the first cooling system, the integrated cooling system comprising a heat exchanger which is integrated in the channel, either upstream or downstream of the first heat exchanger; wherein the first heat exchanger is arranged in a channel that serves as a cooling sink.
2. The system of claim 1, wherein the integrated cooling system comprises the heat exchanger, corresponding control valves, control sensors, a process-air inlet line and a process-air outlet line, which are integrated in the first cooling system.
3. The system of claim 1 or 2, wherein the upstream or downstream arrangement of the heat exchanger in the channel depends on the cooling performance of the integrated cooling system.
4. The system of any one of the preceding claims, wherein the process-air inlet line of the integrated cooling system branches off from a process-air inlet line of the first cooling system.
5. The system of claim 4, comprising an ozone converter, which is arranged upstream of the branch-off of the process-air inlet line, for filtering ozone in supplied hot process air.
6. The system of any one of the preceding claims, wherein the first cooling system is at least one of an already existing air conditioning system and a ventilation system.
7. The system of any one of the preceding claims, wherein the first cooling system and the integrated cooling system are based on at least one of liquid-air technology and air-air technology.
8. The system of any one of the preceding claims, further comprising a bypass line for process air.
9. Use of the system of any one of claims 1 to 8 in an aircraft system.
PCT/EP2005/008692 2004-08-10 2005-08-10 System for producing process air WO2006015858A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
DE602005019414T DE602005019414D1 (en) 2004-08-10 2005-08-10 SYSTEM FOR PRODUCING PROCESS AIR
JP2007525250A JP5336077B2 (en) 2004-08-10 2005-08-10 System that generates process air
CA2573660A CA2573660C (en) 2004-08-10 2005-08-10 System for producing process air
BRPI0513758-6A BRPI0513758A (en) 2004-08-10 2005-08-10 process air production system
AT05774315T ATE457926T1 (en) 2004-08-10 2005-08-10 SYSTEM FOR PRODUCING PROCESS AIR
US11/573,531 US7922118B2 (en) 2004-08-10 2005-08-10 System for producing process air
EP05774315A EP1776271B1 (en) 2004-08-10 2005-08-10 System for producing process air

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US60027404P 2004-08-10 2004-08-10
US60/600,274 2004-08-10
DE102004038860A DE102004038860A1 (en) 2004-08-10 2004-08-10 Process air production system for aircraft has existing cooling system whose heat exchanger is arranged in ram-air cooling channel serving as cooling sink
DE102004038860.1 2004-08-10

Publications (1)

Publication Number Publication Date
WO2006015858A1 true WO2006015858A1 (en) 2006-02-16

Family

ID=35721250

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2005/008692 WO2006015858A1 (en) 2004-08-10 2005-08-10 System for producing process air

Country Status (10)

Country Link
US (1) US7922118B2 (en)
EP (1) EP1776271B1 (en)
JP (1) JP5336077B2 (en)
CN (1) CN1993265A (en)
AT (1) ATE457926T1 (en)
BR (1) BRPI0513758A (en)
CA (1) CA2573660C (en)
DE (2) DE102004038860A1 (en)
RU (1) RU2372253C2 (en)
WO (1) WO2006015858A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008030097A1 (en) * 2006-09-08 2008-03-13 Parker Filtration & Separation B.V. Use of an ozone conversion means in aircraft air management
US20080242209A1 (en) * 2006-05-18 2008-10-02 Libeherr-Aerospace Lindenberg Gmbh Air-conditioning system with a redundant feed of supply air
JP2009532261A (en) * 2006-04-07 2009-09-10 エアバス ドイチェランド ゲゼルシャフト ミット ベシュレンクテル ハフツング Air conditioning system for aircraft

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101187897B1 (en) 2007-02-26 2012-10-04 삼성테크윈 주식회사 Cbr protection and cooling-heating integrated apparatus
DE102008053668B4 (en) * 2008-10-29 2010-11-25 Airbus Deutschland Gmbh System and method for air conditioning an aircraft cabin with improved cooling performance
US8484983B2 (en) * 2009-12-07 2013-07-16 The Boeing Company Thermoelectric generator on an aircraft bleed system
DE102010047970A1 (en) * 2010-10-08 2012-04-12 Airbus Operations Gmbh Airconditioned air conditioning with conditioned heat sink
US9429076B2 (en) 2011-01-11 2016-08-30 Bae Systems Plc Turboprop-powered aircraft with thermal system
WO2012095645A1 (en) 2011-01-11 2012-07-19 Bae Systems Plc Turboprop-powered aircraft
CN102179140B (en) * 2011-01-27 2013-05-01 中国商用飞机有限责任公司 Drying system used in airplane
DE102011011976B4 (en) 2011-02-22 2013-11-14 Airbus Operations Gmbh Decompression assembly for an aircraft
DE102011105968A1 (en) 2011-06-29 2013-01-03 Airbus Operations Gmbh Ram air channel arrangement for air conditioning apparatus of commercial airplane to cool airplane cabin, has control device placed downstream to air outlet such that control device exhibits cross section extending in direction of outlet
US20160146511A1 (en) * 2014-11-24 2016-05-26 Hamilton Sundstrand Corporation Heat exchanger assembly for aircraft ecs

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1273514A2 (en) * 2001-07-05 2003-01-08 Shimadzu Corporation Aircraft air conditioner
EP1293426A2 (en) * 2001-09-14 2003-03-19 The Boeing Company Electric air conditioning system for an aircraft
JP2003240375A (en) * 2002-02-20 2003-08-27 Sumitomo Precision Prod Co Ltd Air cycle type air conditioner
EP1375349A1 (en) * 2002-06-25 2004-01-02 Litton Systems, Inc. Oxygen/inert gas generator
DE102004010366A1 (en) * 2004-03-03 2005-09-22 Liebherr-Aerospace Lindenberg Gmbh System for compressed air preparation

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3711044A (en) * 1971-03-17 1973-01-16 Garrett Corp Automatic interface control system
US4021215A (en) * 1976-05-03 1977-05-03 United Technologies Corporation Dual combined cycle air-conditioning system
US4445342A (en) * 1982-08-26 1984-05-01 United Technologies Corporation Multi-zone temperature control in air cycle refrigeration systems
US4493195A (en) * 1983-05-11 1985-01-15 The United States Of America As Represented By The Secretary Of The Navy Air conditioning system with evaporative cooling apparatus
US4665973A (en) * 1984-12-21 1987-05-19 The Garrett Corporation Environmental control system
US4735056A (en) * 1986-06-30 1988-04-05 United Technologies Corporation Pressure regulating valve controller
US5145124A (en) * 1990-07-12 1992-09-08 Allied-Signal Inc. Fluid conditioning system and apparatus
US5333470A (en) * 1991-05-09 1994-08-02 Heat Pipe Technology, Inc. Booster heat pipe for air-conditioning systems
JP2979802B2 (en) * 1991-12-27 1999-11-15 株式会社デンソー Air conditioner
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
US5511385A (en) * 1994-12-23 1996-04-30 United Technologies Corp. Independent compartment temperature control for single-pack operation
US5704218A (en) * 1996-04-08 1998-01-06 United Technologies Corporation Integrated environmental control system
WO1998006480A1 (en) 1996-08-16 1998-02-19 Alliedsignal Inc. Environmental control system incorporating a catalytic reactor for the decomposition of ozone
RU2111152C1 (en) 1996-12-03 1998-05-20 Акционерное общество открытого типа "Нижегородский авиастроительный завод "Сокол" Air-conditioning system for cabin and equipment compartments of aerobatic aeroplane
US5911388A (en) * 1997-01-15 1999-06-15 Sundstrand Corporation Environmental control system with energy recovery and bleed air assist
US5899805A (en) * 1997-10-20 1999-05-04 United Technologies Corporation Distribution damper valve
GB9804784D0 (en) * 1998-03-06 1998-04-29 Rolls Royce Plc Environmental control system
US6199387B1 (en) * 1999-07-30 2001-03-13 Liebherr-Aerospace Lindenberg Gmbh Air-conditioning system for airplane cabin
RU2168122C1 (en) 1999-11-19 2001-05-27 Московский государственный авиационный институт (технический университет) Cooling turbine plant with bleed-off of air from by-pass engine
US6381969B1 (en) * 1999-12-17 2002-05-07 Honeywell International Inc. ECS with 2-stage water separation
DE19963280C1 (en) * 1999-12-27 2001-08-23 Liebherr Aerospace Gmbh Air conditioning system for aircraft cabins
DE10009373C2 (en) * 2000-02-29 2002-03-14 Airbus Gmbh Air conditioning system for a commercial aircraft
DE10011238B4 (en) * 2000-03-08 2007-10-25 Airbus Deutschland Gmbh High-performance air conditioning system with redundant and stepped recirculation air mixing for a commercial aircraft
DE10036443A1 (en) * 2000-07-26 2002-04-04 Liebherr Aerospace Gmbh Air conditioning system for aircraft
JP4203705B2 (en) * 2000-09-01 2009-01-07 株式会社島津製作所 Aircraft explosion-proof system
US6845630B2 (en) * 2001-02-16 2005-01-25 Hamilton Sundstrand Corporation Electric power and cooling system for an aircraft
DE10119433C1 (en) * 2001-04-20 2002-08-22 Liebherr Aerospace Gmbh Ram air duct for an aircraft air conditioning system
US6655168B2 (en) * 2001-07-05 2003-12-02 Shimadzu Corporation Aircraft air conditioner
US6729359B2 (en) * 2002-06-28 2004-05-04 Shaw Aero Devices, Inc. Modular on-board inert gas generating system
US6739359B2 (en) * 2002-10-04 2004-05-25 Shaw Aero Devices, Inc. On-board inert gas generating system optimization by pressure scheduling
RU2223203C1 (en) 2002-11-28 2004-02-10 ОАО "Санкт-Петербургская авиаремонтная компания" (СПАРК) Helicopter saloon air-conditioning system
US6913636B2 (en) * 2002-12-17 2005-07-05 Hamilton Sundstrand Corporation Low power nitrogen enriched air generation system
RU45711U1 (en) 2004-11-10 2005-05-27 Открытое акционерное общество Научно-производственное объединение "Наука" (ОАО НПО "Наука") AIRCRAFT AIR CONDITIONING SYSTEM
US20090084896A1 (en) * 2007-09-27 2009-04-02 Hamilton Sundstrand Corporation Cabin air system for aviation electronics

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1273514A2 (en) * 2001-07-05 2003-01-08 Shimadzu Corporation Aircraft air conditioner
EP1293426A2 (en) * 2001-09-14 2003-03-19 The Boeing Company Electric air conditioning system for an aircraft
JP2003240375A (en) * 2002-02-20 2003-08-27 Sumitomo Precision Prod Co Ltd Air cycle type air conditioner
EP1375349A1 (en) * 2002-06-25 2004-01-02 Litton Systems, Inc. Oxygen/inert gas generator
DE102004010366A1 (en) * 2004-03-03 2005-09-22 Liebherr-Aerospace Lindenberg Gmbh System for compressed air preparation

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 2003, no. 12 5 December 2003 (2003-12-05) *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009532261A (en) * 2006-04-07 2009-09-10 エアバス ドイチェランド ゲゼルシャフト ミット ベシュレンクテル ハフツング Air conditioning system for aircraft
US20080242209A1 (en) * 2006-05-18 2008-10-02 Libeherr-Aerospace Lindenberg Gmbh Air-conditioning system with a redundant feed of supply air
US9365293B2 (en) * 2006-05-18 2016-06-14 Liebherr-Aerospace Lindenberg Gmbh Air-conditioning system with a redundant feed of supply air
WO2008030097A1 (en) * 2006-09-08 2008-03-13 Parker Filtration & Separation B.V. Use of an ozone conversion means in aircraft air management
EP2243541A1 (en) 2006-09-08 2010-10-27 Parker Filtration & Separation B.V. Use of an ozone conversion means in aircraft air treatment

Also Published As

Publication number Publication date
US20090095004A1 (en) 2009-04-16
DE602005019414D1 (en) 2010-04-01
RU2372253C2 (en) 2009-11-10
RU2007102025A (en) 2008-09-20
JP2008509049A (en) 2008-03-27
ATE457926T1 (en) 2010-03-15
CN1993265A (en) 2007-07-04
BRPI0513758A (en) 2008-05-20
DE102004038860A1 (en) 2006-02-23
CA2573660C (en) 2013-06-11
JP5336077B2 (en) 2013-11-06
US7922118B2 (en) 2011-04-12
EP1776271A1 (en) 2007-04-25
CA2573660A1 (en) 2006-02-16
EP1776271B1 (en) 2010-02-17

Similar Documents

Publication Publication Date Title
US7922118B2 (en) System for producing process air
US8397487B2 (en) Environmental control system supply precooler bypass
US6401473B1 (en) Aircraft air conditioning system and method
CA2551922C (en) Cooling air supply for the cooling of different systems requiring cooling air in an aircraft
EP1874625B2 (en) Systems and methods for cargo compartment air conditioning using recirculated air
US7828874B2 (en) On-board inert gas generation system with air separation module temperature control
US8074927B2 (en) System for improving air quality in an aircraft pressure cabin
CN101415606B (en) Air-conditioning system for aircraft
BR102014028182B1 (en) AIR CYCLE MACHINE ASSEMBLY SYSTEM FOR AN AIRCRAFT, AND, METHOD FOR IMPROVING LOW PRESSURE INLET COOLING PERFORMANCE OF AN AIR CYCLE MACHINE ASSEMBLY SYSTEM
EP3333078B1 (en) Air distribution system with recirculating zone trim tec
CN103249643B (en) There is the aircraft environment control system of modulated low-temperature receiver
GB2166542A (en) Air conditioning systems for aircraft cabins
US6786279B2 (en) Forward in flight (IFE) entertainment cooling system
EP2791005B1 (en) Mixer assembly and method for operating a mixer assembly
US20230079592A1 (en) Vehicle, environmental control system, and method for operating an environmental control system
EP3747772B1 (en) Aircraft environmental control system
Pernatiy AIR CONDITIONING SYSTEMS

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KM KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NG NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SM SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU LV MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

WWE Wipo information: entry into national phase

Ref document number: 2005774315

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2573660

Country of ref document: CA

WWE Wipo information: entry into national phase

Ref document number: 200580026811.8

Country of ref document: CN

WWE Wipo information: entry into national phase

Ref document number: 11573531

Country of ref document: US

Ref document number: 2007525250

Country of ref document: JP

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 2007102025

Country of ref document: RU

WWP Wipo information: published in national office

Ref document number: 2005774315

Country of ref document: EP

ENP Entry into the national phase

Ref document number: PI0513758

Country of ref document: BR