Air-conditioning system for aircraft
View Patent ↗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 ).
1. Air-conditioning system ( 10 ) for aircraft, in particular for commercial aircraft, with two independent redundant air-conditioning system sections, each section comprising
a tapped air source ( 12 ),
a tapped air line ( 22 - 30 ) comprising a main valve ( 16 ), and
an air-conditioning unit ( 32 ),
wherein a mass air flow conveyed from the tapped air source ( 12 ) via the tapped air line ( 22 - 30 ) to the air-conditioning unit ( 32 ) can be controlled by means of the main valve ( 16 ), characterised in that between the tapped air source ( 12 ) and the air-conditioning unit ( 32 ) there is provided 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 tapped air line, the by-pass line ( 42 - 50 ) being part of a second air system that is at least partly independent of the air-conditioning system ( 10 ), which by-pass line is designed so that it can be operated to supply the air-conditioning unit with a sufficient mass air flow.
2. Air-conditioning system according to claim 1 , characterised in that the tapped air line ( 22 - 30 ) contains an ozone converter ( 24 ).
3. Air-conditioning system according to claim 1 , characterised in that the design and construction of the by-pass valve ( 34 , 50 ) differs from that of the first valve ( 16 ).
4. Air-conditioning system according to claim 1 , characterised in that the by-pass valve ( 34 , 50 ) comprises a damping control.
5. Air-conditioning system according to claim 1 , characterised in that the by-pass valve ( 34 , 50 ) is an on-off valve.
6. Air-conditioning system according to claim 1 , characterised in that the by-pass valve ( 34 , 50 ) can be controlled by a control unit of the air-conditioning system ( 10 ).
7. Air-conditioning system according to claim 1 , characterised in that the second air system is a cooled service air system and/or a fuel tank inerting system.
8. Air-conditioning system according to claim 1 , characterised in that the tapped air source ( 12 ) is an auxiliary turbine ( 14 ).
9. Method for air conditioning an aircraft, in particular a commercial aircraft, comprising an air-conditioning system with two independent redundant air-conditioning system comprising the steps:
providing a tapped mass air flow;
passing the tapped mass air flow via a tapped air line to an air-conditioning unit;
passing at least a part of the tapped mass air flow sufficient for supplying the air-conditioning unit to the said air-conditioning unit via a by-pass line in the event of a malfunction of the tapped air line, the by-pass line being part of a second air system that is at least partly independent of the air-conditioning system.