AIRCRAFT AIR CONDITIONING SYSTEM AND METHOD OF OPERATING AN AIRCRAFT AIR CONDITIONING SYSTEM

• US 20160083100A1
• Filed: 09/21/2015
• Published: 03/24/2016
• Est. Priority Date: 09/19/2014
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Bammann, Holger, Klimpel, Frank, Brunswig, Hans
• Granted Patent: US 10,457,399 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0618 with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
• CPC Class Codes: B64D 2013/0648 with energy recovery means, e.g. using turbines
• CPC Class Codes: B64D 2013/0688 with means for recirculating cabin air
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

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.

Claims

1. 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 arranged in the ambient air supply line and being adapted to compress the ambient air flowing through the ambient air supply line,

a bleed air supply line having a first end connected to an engine or an auxiliary power unit and a second end connected to an aircraft environment, and

a bleed air turbine driven by the bleed air flowing through the bleed air supply line and being coupled to the first compressor so as to drive the first compressor.

2. The aircraft air conditioning system according to claim 1, further comprising at least one of:

an ambient air branch line branching off from the ambient air supply line upstream of the first compressor and opening into the ambient air supply line downstream of the first compressor,

a second compressor arranged in the ambient air branch line and being adapted to compress the ambient air flowing through the ambient air branch line,

a cabin exhaust air line allowing a flow of cabin exhaust air therethrough, a cabin exhaust air control valve being arranged in the cabin exhaust air line so as to control the flow of cabin exhaust air through the cabin exhaust air line, and

a cabin exhaust air turbine driven by the cabin exhaust air flowing through the cabin exhaust air line and being coupled to the second compressor so as to drive the second compressor.

3. The aircraft air conditioning system according to claim 2, further comprising at least one of:

a connecting line connecting the ambient air supply line downstream of the first compressor to the ambient air branch line upstream of the second compressor,

an ambient air supply control valve adapted to control the supply of ambient air to the second compressor, wherein the ambient air supply control valve is adapted to control at least one of the flow of ambient air through the connecting line and the flow of ambient air through the ambient air branch line, an electronic control unit adapted to control the operation of the cabin exhaust air control valve and the ambient air supply control valve in a synchronized manner in dependence on an ambient air demand of the aircraft air conditioning system,

a compressed air recirculation line connecting a portion of the ambient air supply line which extends downstream of the first compressor with a portion of the ambient air supply line which extends upstream of the first compressor, and

a recirculation control valve adapted to control the flow of compressed air exiting the first compressor through the compressed air recirculation line back to the first compressor.

4. The aircraft air conditioning system according to claim 2, further comprising a reheater arranged in the cabin exhaust air line, upstream of the cabin exhaust air turbine, and being thermally coupled to the bleed air supply line so as to transport heat energy from the bleed air flowing through the bleed air supply line to the cabin exhaust air flowing through the cabin exhaust air line.

5. The aircraft air conditioning system according to claim 4, wherein the reheater is thermally coupled to the bleed air supply line either upstream or downstream of a precooler arranged in the bleed air supply line, the precooler being thermally coupled to a ram air channel so as to transport heat energy from the bleed air flowing through the bleed air supply line to ram air flowing through the ram air channel.

6. The aircraft air conditioning system according to claim 1, further comprising at least one of:

an ambient air cooler arranged in the ambient air supply line, downstream of the first compressor, and being thermally coupled to the ram air channel so as to transport heat energy from the ambient air flowing through the ambient air supply line to ram air flowing through the ram air channel,

a condenser arranged in the ambient air supply line, downstream of the ambient air cooler, and being thermally coupled to the bleed air supply line so as to transport heat energy from the ambient air flowing through the ambient air supply line to the bleed air flowing through the bleed air supply line,

a water separator arranged in the ambient air supply line, downstream of the condenser,

an ambient air turbine driven by the ambient air flowing through the ambient air supply line and being coupled to the first compressor so as to drive the first compressor,

a trim air line branching off from the ambient air supply line between the first compressor and the ambient air cooler and opening into the ambient air supply line downstream of the ambient air turbine,

an altitude vent line branching off from the ambient air supply line upstream of the ambient air turbine, upstream of the condenser, and opening into the ambient air supply line downstream of the ambient air turbine, an altitude vent valve being arranged in the altitude vent line so as to control the flow of ambient air through the altitude vent line,

an emergency ambient air supply line directly connecting the ambient air inlet to the mixer of the aircraft air conditioning system,

a bypass line adapted to bypass the reheater,

a bypass valve adapted to control the flow of bleed air through the bypass line,

a further bypass line adapted to bypass the precooler,

a further bypass valve adapted to control the flow of bleed air through the further bypass line,

a cabin exhaust air branch line branching off from the cabin exhaust air line, downstream of the cabin exhaust air turbine, and opening into the ram air channel, downstream of the ambient air precooler and the precooler, and

a cabin air dump valve adapted to control the flow of cabin exhaust air, downstream of the cabin exhaust air turbine, through the cabin exhaust air branch line.

7. The aircraft air conditioning system according to claim 1, further comprising at least one of:

a backup line branching off from the bleed air supply line, downstream of the condenser, and opening into the ambient air supply line, downstream of the ambient air turbine, a backup valve being arranged in the backup line so as to control the flow of bleed air through the backup line, and

a bleed air branch line branching off from the bleed air supply line and adapted to have hot bleed air flowing therethrough, wherein a hot air regulation valve is adapted to control the flow of hot bleed air through the bleed air branch line.

8. The aircraft air conditioning system according to claim 1, wherein at least one of the bleed air supply line and the cabin exhaust air line opens into the ram air channel, wherein the cabin exhaust air line is connected to an ejector disposed in the ram air channel adapted to inject the cabin exhaust air flowing through the cabin exhaust air line into the ram air channel and which is driven by the bleed air exiting the bleed air supply line.

9. A method of operating an aircraft air conditioning system, the method comprising the steps:

guiding a flow of ambient air through 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, the flow of ambient air being controlled by a shut off valve,

compressing the ambient air flowing through the ambient air supply line via a first compressor arranged in the ambient air supply line,

guiding a flow of bleed air bled off from an engine or an auxiliary power unit through a bleed air supply line having a first end connected to the engine or the auxiliary power unit and a second end connected to an aircraft environment, and

driving a bleed air turbine by the bleed air flowing through the bleed air supply line, the bleed air turbine being coupled to the first compressor so as to drive the first compressor.

10. The method according to claim 9, further comprising at least one of the steps of:

guiding a flow of ambient air through an ambient air branch line branching off from the ambient air supply line upstream of the first compressor and opening into the ambient air supply line downstream of the first compressor,

compressing the ambient air flowing through the ambient air branch line via a second compressor arranged in the ambient air branch line,

guiding a flow of cabin exhaust air through a cabin exhaust air line, the flow of cabin exhaust air through the cabin exhaust air line being controlled via a cabin exhaust air control valve arranged in the cabin exhaust air line, and

driving a cabin exhaust air turbine via the cabin exhaust air flowing through the cabin exhaust air line, the cabin exhaust air turbine being coupled to the second compressor so as to drive the second compressor.

11. The method according to claim 10, further comprising at least one of the steps of:

guiding a flow of ambient air through a connecting line connecting the ambient air supply line downstream of the first compressor to the ambient air branch line upstream of the second compressor,

controlling the supply of ambient air to the second compressor via an ambient air supply control valve, by controlling, via the ambient air supply control valve, at least one of the flow of ambient air through the connecting line and the flow of ambient air through the ambient air branch line,

controlling the operation of the cabin exhaust air control valve and the ambient air supply control valve in a synchronized manner in dependence on an ambient air demand of the aircraft air conditioning system,

guiding a flow of compressed air through a compressed air recirculation line connecting a portion of the ambient air supply line which extends downstream of the first compressor with a portion of the ambient air supply line which extends upstream of the first compressor, and

controlling the flow of compressed air exiting the first compressor through the compressed air recirculation line back to the first compressor via a recirculation control valve.

12. The method according to claim 10, further comprising at least one of the steps of:

heating the cabin exhaust air flowing through the cabin exhaust air line via a reheater arranged in the cabin exhaust air line, upstream of the cabin exhaust air turbine, by transporting heat energy from the bleed air flowing through the bleed air supply line to the cabin exhaust air flowing through the cabin exhaust air line, and

cooling the bleed air flowing through the bleed air supply line via a precooler arranged in the bleed air supply line, by transporting heat energy from the bleed air flowing through the bleed air supply line to ram air flowing through a ram air channel, wherein the reheater is thermally coupled to the bleed air supply line either upstream or downstream of the precooler.

13. The method according to claim 9, further comprising at least one of the steps of:

cooling the ambient air flowing through the ambient air supply line via an ambient air cooler arranged in the ambient air supply line, downstream of the first compressor, by transporting heat energy from the ambient air flowing through the ambient air supply line to ram air flowing through the ram air channel,

condensing water contained in the ambient air flowing through the ambient air supply line via a condenser arranged in the ambient air supply line, downstream of the ambient air cooler, by transporting heat energy from the ambient air flowing through the ambient air supply line to the bleed air flowing through the bleed air supply line,

separating water contained in the ambient air flowing through the ambient air supply line via a water separator arranged in the ambient air supply line, downstream of the condenser,

driving an ambient air turbine by the ambient air flowing through the ambient air supply line, the ambient air turbine being coupled to the first compressor so as to drive the first compressor,

guiding a flow of ambient air through a trim air line branching off from the ambient air supply line between the first compressor and the ambient air cooler and opening into the ambient air supply line downstream of the ambient air turbine,

guiding a flow of ambient air through an altitude vent line branching off from the ambient air supply line upstream of the ambient air turbine, upstream of the condenser, and opening into the ambient air supply line downstream of the ambient air turbine, wherein the flow of ambient air through the altitude vent line is controlled via an altitude vent valve arranged in the altitude vent line,

guiding a flow of ambient air through an emergency ambient air supply line directly connecting the ambient air inlet to the mixer of the aircraft air conditioning system,

guiding a flow of bleed air through a bypass line to bypass the reheater,

controlling the flow of bleed air through the bypass line via a bypass valve,

guiding a flow of bleed air through a further bypass line to bypass the precooler,

controlling the flow of bleed air through the further bypass line via a further bypass valve,

guiding a flow of cabin exhaust air through a cabin exhaust air branch line branching off from the cabin exhaust air line, downstream of the cabin exhaust air turbine, and opening into the ram air channel, downstream of the ambient air precooler and the precooler, and

controlling the flow of cabin exhaust air through the cabin exhaust air branch line, downstream of the cabin exhaust air turbine, via a cabin air dump valve.

14. The method according to claim 9, further comprising at least one of the steps of:

guiding a flow of bleed air through a backup line branching off from the bleed air supply line, downstream of the condenser, the flow of bleed air through the backup line being controlled via a backup valve arranged in the backup line, and

guiding a flow of hot bleed air through a bleed air branch line branching off from the bleed air supply line, wherein the flow of hot bleed air through the bleed air branch line is controlled via a hot air regulation valve.

15. The method according to claim 9, wherein at least one of bleed air flowing through the bleed air supply line and cabin exhaust air flowing through the cabin exhaust air line is guided into the ram air channel, wherein the cabin exhaust air is supplied to the ram air channel via an ejector disposed in the ram air channel adapted to inject the cabin exhaust air flowing through the cabin exhaust air line into the ram air channel and which is driven by the bleed air exiting the bleed air supply line.