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Air-conditioning system for aircraft

An air conditioning system, air system technology, applied in the direction of air handling equipment, aircraft parts, energy-saving panel measures, etc., can solve the problem of inability to provide air conditioning in the cabin, and achieve the effect of reducing structural costs

Active Publication Date: 2013-06-19
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This solution still does not provide a more comprehensive regulation of the cabin air in this case and can therefore also only be used for short-term emergencies

Method used

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  • Air-conditioning system for aircraft
  • Air-conditioning system for aircraft
  • Air-conditioning system for aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0029] figure 1 A schematic circuit diagram of the first preferred embodiment of the air conditioning system 10 is shown. The air conditioning system 10 is designed to be mirror-symmetrical along line A in the wiring diagram, that is, all basic components exist in a double-redundant manner. In the following, only the part of the air conditioning system 10 located on the left side of each figure is described, and the redundant right side part of the same design is only involved in the figure without a more detailed description.

[0030] Via a compression stage, as schematically illustrated by the bleed air source 12, high-pressure hot bleed air is extracted from a turbine unit (not shown). The extracted bleed air is supplied to the ozone converter 24 via the main bleed air line 20 and the branch bleed air line 22, from where the bleed air passes through another bleed air line section 26 to the main regulating valve 16 (FCV) and via the T line section 28 (T pipe) and another blee...

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PUM

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Abstract

Air-conditioning system (10) for aircraft, in particular for commercial aircraft, with a bleed air source (12), a bleed air line (22-30) comprising a main valve (16), and an air-conditioning unit (32), wherein a mass air flow conveyed from the bleed air source (12) through the bleed air line (22-30) to the air-conditioning unit (32) can be controlled by means of the main valve (16). According to the invention it is envisaged that a by-pass line (36-50, 58, 60) comprising a by-pass valve (34) and by-passing at least a part (22-26, 16) of the bleed air line, is present between the bleed air source (12) and the air-conditioning unit (32).

Description

Technical field [0001] The present invention relates to an air conditioning system for aircraft, especially for commercial aircraft, which has a bleed air source, a bleed air line including a main regulating valve, and an air conditioning unit, wherein the bleed air source is connected to the bleed air line via the bleed air line. The mass air flow rate that can be controlled by the main regulating valve is supplied to the air conditioning unit. The invention also relates to an air conditioning method for aircraft, especially for commercial aircraft, which includes the steps of: providing a mass flow of bleed air; and introducing the mass flow of bleed air to an air conditioning unit via a bleed air pipeline. Background technique [0002] Due to the current general flying altitudes and the low air pressure and low temperature environmental conditions that exist at these altitudes, air conditioning and air pressure regulation inside the aircraft, especially in the passenger cabin,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D13/06
CPCY02T50/44B64D13/06Y02T50/56B64D2013/0618Y02T50/40Y02T50/50
Inventor 弗兰克·克利姆佩尔
Owner AIRBUS OPERATIONS GMBH