Abstract: An inerting system for an aircraft includes an inert gas generation apparatus, an air supply line, a compressor and an inert gas line. The compressor supplies the inert gas generation apparatus with air from the air supply line at a pressure necessary for operation of the inert gas generation apparatus. The inert gas line carries the inert gas produced by the inert gas generation apparatus on to an inert gas consumer. The air supply line is connected to an exhaust air system of the aircraft. A method for supplying an inert gas in an aircraft includes tapping of air from an exhaust air system of the aircraft, compression of the tapped air, and production of inert gas in an inert gas generation apparatus from the compressed air. An aircraft is disclosed in which such an inerting system is arranged and/or used.

Abstract: An aircraft air conditioning system comprising an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is adapted to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

Abstract: In a method for emergency ventilation of an aircraft cabin, a leak is detected in the area of an air mixer of an aircraft air conditioning system. An emergency air flap, which in a closed position prevents an air exchange between an aircraft area adjacent to the air mixer and the aircraft cabin, is controlled into an open position. Air from the aircraft area adjacent to the air mixer is conveyed through the open emergency air flap into the aircraft cabin.

Abstract: An aircraft air conditioning system comprises a process air line configured to supply compressed process air provided by a process air source to an air conditioning unit of the aircraft air conditioning system and a trim air line branching off from the process air line upstream of the air conditioning unit and being configured such that trim air flows through the trim air line, the trim air having been branched off from the compressed process air flowing through the process air line. A compressor is arranged in the trim air line and is configured to compress the trim air flowing through the trim air line. A turbine of the aircraft air conditioning system is configured to drive the compressor. A cabin exhaust air line is configured to supply cabin exhaust air discharged from an aircraft cabin to the turbine for driving the turbine.

Abstract: An aircraft air conditioning system comprises a process air source and an air conditioning unit being connected to the process air source via a process air line and being adapted to cool and expand process air supplied to the air conditioning unit from the process air source so as to provide conditioned air. A mixing chamber of the aircraft air conditioning system is connected to the air conditioning unit via a conditioned air line and is adapted to mix conditioned air supplied to the mixing chamber from the air conditioning unit with recirculation air recirculated from an aircraft region to be air conditioned to the mixing chamber via a recirculation air line so as to provide mixed air.

Abstract: An aircraft air conditioning system comprising an ambient air supply line allowing a flow of ambient air therethrough, an ambient air cooling device to cool the air flowing through the ambient air supply line, and a discharge line connected to the ambient air cooling device and an aircraft cabin. A compressed air supply line allows a flow of compressed air therethrough, a compressed air cooling device is connected to the compressed air supply line to cool the air flowing through the compressed air supply line, and a discharge line is connected to the compressed air cooling device and to the aircraft cabin. A refrigerant circuit allows the flow of a two-phase refrigerant therethrough and converts the two-phase refrigerant from the liquid state into the gaseous state of aggregation and thereafter back again. The refrigerant circuit supplies cooling energy to the ambient air cooling device and the compressed air cooling device.

Abstract: An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

Abstract: A system for processing recirculation air discharged from an aircraft cabin comprising a recirculation air supply line which is connectable to the aircraft cabin so as to allow a flow of recirculation air discharged from the aircraft cabin therethrough. An absorber is connected to the recirculation air supply line and is adapted to remove CO2 from the recirculation air flowing through the recirculation air supply line by absorption of CO2 in a provided absorption medium. A recirculation air discharge line is connected to the absorber and is connectable to the aircraft cabin so as to allow a flow of absorption treated recirculation air exiting the absorber to the aircraft cabin. Finally, an air processing device is disposed in the recirculation air discharge line, wherein the air processing device is connected to an O2 source and is adapted to enrich the recirculation air exiting the absorber with O2.

Abstract: An aircraft air conditioning system comprises an ambient supply line, an ambient air cooling device connected to the ambient air supply line and adapted to cool ambient air flowing through the ambient air supply line, an ambient air discharge line connected to the ambient air cooling device and being connectable to an aircraft cabin to supply ambient air cooled by the ambient air cooling device to the aircraft cabin, and a refrigerating apparatus. The refrigerating apparatus comprises a refrigerant circuit allowing the flow of a two-phase refrigerant therethrough and is designed to convert the two-phase refrigerant, upon flowing through the refrigerant circuit, from the liquid state of aggregation into the gaseous state of aggregation and thereafter again back from the gaseous state of aggregation into the liquid state of aggregation. The refrigerant circuit of the refrigerating apparatus is adapted to supply cooling energy to the ambient air cooling device.

Abstract: A ram air duct flap arrangement (22) comprises at least one ram air duct flap (24, 26) which is designed to close, in a closed position, a ram air inlet (14) or a ram air outlet (18) of a ram air duct (10) and, at least partly open, in an open position, the ram air inlet (14) or the ram air outlet (18) of the ram air duct (10). Furthermore, the ram air duct flap arrangement (22) comprises an actuator (32) for actuating the ram air duct flap (24, 26) between its closed position and its open position. A pressure control device (42) is designed to control a pressure (pi), which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an inner surface (44) of the ram air duct flap (24, 26) facing an interior of the aircraft, in such a way that it corresponds substantially to a pressure (pa) which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an outer surface (38) of the ram air duct flap (24, 26) facing the external environment.

Abstract: An air system for pressurizing and air conditioning a cockpit and cabin space of a plane comprises a compressor (3) for compressing an air mass flow, wherein the air mass flow to be compressed is extracted through a ram air duct (13, 14) from the environment of the plane and supplied through a heat exchanger (15, 18) to at least one zone (10A-D) to be pressurized and air conditioned.

Abstract: In a method for emergency ventilation of an aircraft cabin (12) a leak is detected in the area of an air mixer (24) of an aircraft air conditioning system (16). An emergency air flap (38), which in a closed position prevents an air exchange between an aircraft area (40) adjacent to the air mixer (24) and the aircraft cabin (12), is controlled into an open position. Finally, air from the aircraft area (40) adjacent to the air mixer (24) is conveyed through the open emergency air flap (38) into the aircraft cabin (12).

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).

Abstract: A ram air duct flap arrangement (22) comprises at least one ram air duct flap (24, 26) which is designed to close, in a closed position, a ram air inlet (14) or a ram air outlet (18) of a ram air duct (10) and, at least partly open, in an open position, the ram air inlet (14) or the ram air outlet (18) of the ram air duct (10). Furthermore, the ram air duct flap arrangement (22) comprises an actuator (32) for actuating the ram air duct flap (24, 26) between its closed position and its open position. A pressure control device (42) is designed to control a pressure (pi), which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an inner surface (44) of the ram air duct flap (24, 26) facing an interior of the aircraft, in such a way that it corresponds substantially to a pressure (pa) which, when the ram air duct flap arrangement (22) is mounted in an aircraft, acts on an outer surface (38) of the ram air duct flap (24, 26) facing the external environment.

Abstract: The invention relates to a device (10) for heating an aircraft cabin and comprises a first hot air supply line (12) that leads to an air conditioning unit (14), a flow control valve (16) that is disposed in the first hot air supply line (12) upstream from the air conditioning unit (14), and a second hot air supply line (18) that branches off from the first hot air supply line (12) between the flow control valve (16) and the air conditioning unit (14) and bypasses the air conditioning unit (14). In order to assure air conditioning of the aircraft cabin in the event of a failure of the air conditioning unit (14) a third hot air supply line (20) branches off from the first hot air supply line (12) upstream from the flow control valve (16), which third hot air supply line (20) connects the first hot air supply line (12) to the second hot air supply line (18).

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).

Abstract: An air system for pressurizing and air conditioning a cockpit and cabin space of a plane comprises a compressor (3) for compressing an air mass flow, wherein the air mass flow to be compressed is extracted through a ram air duct (13, 14) from the environment of the plane and supplied through a heat exchanger (15, 18) to at least one zone (10A-D) to be pressurized and air conditioned.

Abstract: The invention relates to a device (10) for heating an aircraft cabin and comprises a first hot air supply line (12) that leads to an air conditioning unit (14), a flow control valve (16) that is disposed in the first hot air supply line (12) upstream from the air conditioning unit (14), and a second hot air supply line (18) that branches off from the first hot air supply line (12) between the flow control valve (16) and the air conditioning unit (14) and bypasses the air conditioning unit (14). In order to assure air conditioning of the aircraft cabin in the event of a failure of the air conditioning unit (14) a third hot air supply line (20) branches off from the first hot air supply line (12) upstream from the flow control valve (16), which third hot air supply line (20) connects the first hot air supply line (12) to the second hot air supply line (18).