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Air-conditioning system with icing protection for an aircraft

A technology for air conditioning systems and aircraft, which is applied in air handling equipment, aircraft parts, energy-saving board measures, etc., can solve installation problems, increase system weight and other problems, and achieve the effect of reducing costs and types.

Active Publication Date: 2009-08-05
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, two hot air supply lines must be used for the first zone supply line adjustment valve 76 and the second zone supply line adjustment valve 70, and the two hot air supply lines must cross the L1 section, which causes installation problems and will increase the weight of the system

Method used

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  • Air-conditioning system with icing protection for an aircraft
  • Air-conditioning system with icing protection for an aircraft

Examples

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Embodiment Construction

[0026] figure 1 A first area 2 and a second area 4 of the aircraft are shown. In a cargo aircraft, the first area 2 can be, for example, the cockpit and cabins for crew members, while the second area 4 can be, for example, cabins for cargo representatives. Utilize the temperature T1 detected by sensor 8 act. The cool air is supplied to various areas of the aircraft via the first pipeline 6 . The air branches off into a second line 14 at a branch point 10 . The remainder of the air may be supplied to other zones or other groups of zones having a different or the same set zone temperature as the first zone 2 and the second zone 4 . For example, other areas or groups of areas may be cargo holds transporting perishable goods that must be cooled. Other regions or other groups of regions may be located upstream or downstream of the branch point.

[0027] For example, the first line 6 may be connected to a common cold air source for several zones. The air flowing in the first l...

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PUM

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Abstract

Aircraft air-conditioning system (1) for an aircraft having a plurality of zones (2, 4), comprising a first line (6) for feeding cold air at an actual temperature T1act., a second line (14) which branches off a portion of the air from the first line (6) at a branching point (10) and feeds the air to a plurality of zones (2, 4) of an aircraft, wherein warm air is fed through a first trim valve (12) into the second line (14) so that the air in the second line (14) is heated to the actual temperature T2act., and a first zone feed line (24) feeding the air downstream of the first trim valve (12) to a first zone (2), wherein a second trim valve (26) is arranged in the first zone feed line (24), through which valve warm air is fed into the first zone feed line (24) so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act., and the first line (6) downstream and / or upstream of the branching point (1) feeds cold air at least to one further zone. A second feed line (18) feeds air downstream of the first adjustment (12) to a second zone (4). A heating device (20) can be arranged in the second feed line (18).

Description

technical field [0001] The invention relates to an anti-icing air-conditioning system for air-conditioning several regions of an aircraft. Background technique [0002] In aircraft, especially in cargo aircraft, tapping and temperature conditioning of air streams with cool process air to supply properly temperature conditioned air to multiple areas such as the cargo hold, cockpit and / or or part of an aircraft cabin. Each zone requires an independent supply air temperature to achieve the set temperature for that zone. [0003] FIG. 2 shows a conventional aircraft air conditioning system 50 for air conditioning a first zone 52 and a second zone 54 . Cool air is supplied via the first line 56 and is tapped into the second line 64 at a tap point 60 . Air is directed from the second line 64 into the first zone 52 via the first zone supply line 74 . Air is directed from the second line 64 to the second zone 54 via the second zone supply line 68 . The first zone supply line ad...

Claims

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Application Information

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IPC IPC(8): B64D13/08
CPCB64D2013/0688Y02T50/56B64D13/08B64D2013/0618Y02T50/50
Inventor 亚历山大·索恩塞夫约翰内斯·艾希霍尔茨霍尔格·巴曼
Owner AIRBUS OPERATIONS GMBH
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