Autonomous air conditioning system for aircraft

Patent metadata

Field	Value
Publication number	US-12534209-B2
Application number	US-202318527617-A
Country	US
Kind code	B2
Filing date	Dec 4, 2023
Priority date	Dec 6, 2022
Publication date	Jan 27, 2026
Grant date	Jan 27, 2026

Abstract

An autonomous air conditioning system for an aircraft includes a compressor compressing ambient air and supplying compressed air, a first portion of the compressed air being injected into a cabin of the aircraft so as to condition the cabin air in terms of pressure and of temperature. The autonomous system further includes an electric motor providing mechanical energy to the compressor. The system includes a fuel cells stack supplied with air by a second portion of the compressed air supplied by the compressor and supplying electrical energy, the electric motor being electrically powered with electrical energy supplied by the fuel cells stack. Thus, the cabin air conditioning is performed autonomously, avoiding the need to modify a pre-existing electrical network of the aircraft.

First claim

The invention claimed is:

1 . An autonomous air conditioning system for an aircraft, comprising:
a primary compressor compressing air bled from outside the aircraft and supplying compressed air, a first portion of said compressed air being injected into a cabin of the aircraft so as to condition cabin air in terms of pressure and of temperature, a first electric motor supplying mechanical energy to the primary compressor, a fuel cells stack supplied with air by a second portion of the compressed air supplied by the primary compressor, the fuel cells stack supplying electrical energy to power the first electric motor, and a closed cooling circuit in which a heat transfer fluid cools the fuel cells stack and the first electric motor by circulating between the fuel cells stack and the first electric motor, wherein the closed cooling circuit allows exchange of heat between air bled from outside the aircraft and the heat transfer fluid so as to cool the heat transfer fluid.

2 . The autonomous air conditioning system according to claim 1 , further comprising a first heat exchanger performing exchange of heat between the compressed air supplied by the primary compressor and air bled from outside the aircraft, the first heat exchanger being located downstream of the primary compressor and upstream of the fuel cells stack and of the aircraft cabin.

3 . The autonomous air conditioning system according to claim 2 , wherein the primary compressor is further supplied with mechanical energy by a first turbine, the first turbine receiving at its inlet a third portion of the compressed air supplied by the primary compressor and being located downstream of the first heat exchanger.

4 . The autonomous air conditioning system according to claim 1 , further comprising a secondary compressor, the secondary compressor being located between the primary compressor and the fuel cells stack and compressing the second portion of the compressed air supplied by the primary compressor.

5 . The autonomous air conditioning system according to claim 4 , wherein the secondary compressor is supplied with mechanical energy by a second turbine, the second turbine receiving at its inlet compressed air coming from the fuel cells stack.

6 . The autonomous air conditioning system according to claim 5 , further comprising a second electric motor electrically powered by the electrical energy supplied by the fuel cells stack, the second electric motor providing mechanical energy to the secondary compressor.

7 . The autonomous air conditioning system according to claim 1 , further comprising a controller configured to implement an algorithm to regulate compressed air temperature, pressure and flow rate parameters and configured to send control commands to active elements of the system providing control functions for the flow rate, pressure and temperature of the compressed air.

8 . The autonomous air conditioning system according to claim 1 , further comprising a switch configured to electrically connect to the fuel cells stack, and to do so alternatively, a first electrical assembly and a second electrical assembly, the first electrical assembly being configured to supply electrical power to the system, the second electrical assembly being configured to supply electrical energy to equipment external to the system and providing safety functions in the aircraft.

9 . An aircraft comprising at least one autonomous air conditioning system according to claim 1 .

10 . The autonomous air conditioning system according to claim 2 , further comprising a first air bleed device, a second heat exchanger configured to transfer heat from the heat transfer fluid to air, which is cooler, bled from outside the aircraft by a second air bleed device in order to cool the heat transfer fluid, and a third heat exchanger configured to transfer heat from air exiting the fuel cells stack to the compressed air entering the fuel cells stack, thereby warming the air entering the fuel cells stack.

11 . The autonomous air conditioning system according to claim 10 , wherein the first air bleed device is a ram air inlet and the second air bleed device is a scoop inlet.

12 . The autonomous air conditioning system according to claim 3 , further comprising a diffuser configured to distribute the compressed air leaving the first heat exchanger towards the fuel cells stack and towards the cabin.

13 . The autonomous air conditioning system according to claim 12 , further comprising a dehumidifier located between the diffuser and the first turbine, and configured to reduce a quantity of water present in the compressed air.

14 . The autonomous air conditioning system according to claim 7 , wherein the controller is further configured to send instructions to a valve to adjust the flow rate of the compressed air at an inlet of the cabin.

15 . The autonomous air conditioning system according to claim 8 , wherein the first electrical assembly further comprises electrical connections supplying power to at least one valve.

16 . The autonomous air conditioning system according to claim 8 , further comprising a converter configured to obtain an alternating current at a voltage adapted to priority electrical energy loads.

17 . The autonomous air conditioning system according to claim 8 , further comprising a switch configured to electrically connect to the fuel cells stack, and a control unit configured to control the switch.

18 . The autonomous air conditioning system according to claim 17 , wherein the control unit transmits a switching instruction to the switch when an emergency situation is detected and when the emergency situation ends.

19 . An aircraft comprising:
a primary compressor compressing air bled from outside the aircraft and supplying compressed air, a first portion of said compressed air being injected into a cabin of the aircraft so as to condition cabin air in terms of pressure and of temperature, a first electric motor supplying mechanical energy to the primary compressor, a fuel cells stack supplied with air by a second portion of the compressed air supplied by the primary compressor, the fuel cells stack supplying electrical energy to power the first electric motor, and a switch configured to electrically connect to the fuel cells stack, and to do so alternatively, a first electrical assembly and a second electrical assembly, the first electrical assembly being configured to supply electrical power to the system, the second electrical assembly being configured to supply electrical energy to equipment external to the system and providing safety functions in the aircraft; wherein the switch is controlled by a control unit and the control unit is configured to upon detection of an emergency situation corresponding to the reception of an alarm, transmit a switching instruction to the switch to stop the power supply to an autonomous system and to power a priority electrical loads, and upon detection of the end of an emergency situation, transmit a switching instruction to the switch to stop the power supply to the priority electrical loads and to power the autonomous system.

Assignees

• Airbus Operations Sas
• Airbus Sas
• Airbus Operations Gmbh

Inventors

• Josset Thomas
• Poirier Didier
• Bammann Holger

Classifications

• B64D2013/0659

  comprising provisions for cooling fuel systems · CPC title

• B64D2013/0648

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

• B64D2013/0644

  including electric motors or generators · CPC title

• B64D2013/0618

  with arrangements for reducing or managing bleed air, using another air source, e.g. ram air · CPC title

• B64D13/06 Primary

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