Aircraft air conditioning system with a cabin exhaust air turbine

Patent metadata

Field	Value
Publication number	US-11542017-B2
Application number	US-201916720597-A
Country	US
Kind code	B2
Filing date	Dec 19, 2019
Priority date	Nov 11, 2015
Publication date	Jan 3, 2023
Grant date	Jan 3, 2023

Abstract

An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

First claim

What is claimed is:

1. An aircraft air conditioning system with:
a mixer,
a recirculation air line connected to the mixer, wherein recirculation air taken from an aircraft cabin flows through the recirculation air line to the mixer,
an ambient air line configured to be flown through with ambient air and being connected to the mixer, in order to supply ambient air to the mixer,
a first ambient air compressor and a second ambient air compressor, each arranged in the ambient air line for compressing the ambient air flowing through the ambient air line,
a refrigerating apparatus, which comprises a refrigerant circuit configured to be flown through with a refrigerant as well as a refrigerant compressor arranged in the refrigerant circuit, wherein the refrigerant circuit is coupled thermally to the ambient air line, in order to transfer heat from the ambient air flowing through the ambient air line to the refrigerant circulating in the refrigerant circuit before the ambient air is supplied to the mixer,
a cabin exhaust air line, and
a cabin exhaust air turbine, which is connected to the cabin exhaust air line and is coupled to the first ambient air compressor arranged in the ambient air line and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the first ambient air compressor arranged in the ambient air line,
wherein the refrigerating apparatus further comprises a first evaporator, which is configured to thermally couple the refrigerant circuit and the recirculation air line, in order to transfer heat from the recirculation air flowing through the recirculation air line to the refrigerant flowing through the refrigerant circuit,
wherein the mixer receives a first flow of the recirculation air via the first evaporator, a second flow of a bypass ambient air via a second evaporator of the refrigerating apparatus, and a third flow via a second turbine arranged on a common shaft with the second ambient air compressor, and
wherein the first ambient air compressor receives a non-compressed ambient air flow, and the second ambient air compressor is downstream from the first ambient air compressor and receives ambient air flow downstream from a ram air duct.

2. The aircraft air conditioning system according to claim 1 , wherein the ambient air line comprises a first section, in which the first ambient air compressor is arranged for compressing the ambient air flowing through the first section of the ambient air line, and in that the cabin exhaust air turbine is coupled to the first ambient air compressor and is configured to drive the first ambient air compressor.

3. The aircraft air conditioning system according to claim 2 , wherein a post-heater is arranged in the first section of the ambient air line downstream of the first ambient air compressor and is coupled thermally to the cabin exhaust air line upstream of the cabin exhaust air turbine, which post-heater is configured to transfer heat from the ambient air flowing through the ambient air line downstream of the first ambient air compressor to the cabin exhaust air flowing through the cabin exhaust air line upstream of the cabin exhaust air turbine.

4. The aircraft air conditioning system according to claim 3 , further comprising a post-heater bypass line, which branches off from the first section of the ambient air line upstream of the post-heater and opens into the first section of the ambient air line again downstream of the post-heater, wherein a post-heater bypass valve is preferably arranged in the post-heater bypass line, which post-heater bypass valve is configured to control the ambient air flow through the post-heater bypass line.

5. The aircraft air conditioning system according to claim 1 , wherein a turbine exhaust air line connected to an outlet of the cabin exhaust air turbine opens into the ram air duct.

6. The aircraft air conditioning system according to claim 1 , further comprising a controller, which is configured to control the operation of the cabin exhaust air turbine in dependence on the flight altitude of an aircraft equipped with the aircraft air conditioning system.

7. The aircraft air conditioning system according to claim 6 , wherein the controller is configured to operate the cabin exhaust air turbine when an aircraft equipped with the aircraft air conditioning system is flying at a flight altitude of at least 6000 m.

8. A method for operating an aircraft air conditioning system
conducting ambient air through an ambient air line, which is connected to a mixer of the aircraft air conditioning system, in order to supply ambient air to the mixer,
compressing the ambient air flowing through the ambient air line in a first ambient air compressor and a second ambient air compressor arranged in the ambient air line, wherein the first ambient air compressor receives a non-compressed ambient air flow, and the second ambient air compressor is downstream from the first ambient air compressor and receives ambient air flow downstream from a ram air duct,
providing a refrigerating apparatus, which comprises a refrigerant circuit configured to be flown through with a refrigerant as well as a refrigerant compressor arranged in the refrigerant circuit,
thermal coupling of the refrigerant circuit of the refrigerating apparatus to the ambient air line, in order to transfer heat from the ambient air flowing through the ambient air line to the refrigerant circulating in the refrigerant circuit before the ambient air is supplied to the mixer,
characterised by
providing a cabin exhaust air turbine, which is connected to a cabin exhaust air line and is coupled to the first ambient air compressor arranged in the ambient air line, expands the cabin exhaust air flowing through the cabin exhaust air line and drives the first ambient air compressor arranged in the ambient air line,
connecting the mixer to a recirculation air line, through which recirculation air taken from an aircraft cabin flows to the mixer, and
thermal coupling the refrigerant circuit and the recirculation air line by a first evaporator of the refrigerating apparatus, in order to transfer heat from the recirculation air flowing through the recirculation air line to the refrigerant flowing through the refrigerant circuit,
wherein the mixer receives a first flow of the recirculation air via the first evaporator, a second flow of a bypass ambient air via a second evaporator of the refrigerating apparatus, and a third flow via a second turbine arranged on a common shaft with the second ambient air compressor.

9. The method according to claim 8 , wherein the ambient air line comprises a first section, in which the first ambient air compressor of the first section is arranged for compressing the ambient air flowing through the first section of the ambient air line, and in that the cabin exhaust air turbine is coupled to the first ambient air compressor and drives the first ambient air compressor.

10. The method according to claim 9 , wherein in the first section of the ambient air line downstream of the first ambient air compressor, a post-heater is arranged, which is coupled thermally to the cabin exhaust air line upstream of the cabin exhaust air turbine and transfers heat from the ambient air flowing through the ambient air line downstream of the first ambient air compressor to the cabin exhaust air flowing through the cabin exhaust air line upstream of the cabin exhaust air turbine.

11. The method according to claim 10 , further comprising a post-heater bypass line, which branches off from the first section of the ambient air line upstream of the post-heater and opens into the first section of the ambient air line again downstre

Assignees

• Airbus Operations Gmbh

Inventors

• Bammann Holger
• Klimpel Frank

Classifications

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title

• B64D13/02

  the air being pressurised · CPC title

• B64D2013/0648

  with energy recovery means, e.g. using turbines · CPC title

• B64D2013/0625

  comprising means for distribution effusion of conditioned air in the cabin · CPC title

• B64D13/08 Primary

  the air being heated or cooled · CPC title