On-board aircraft dried inert gas system

Patent metadata

Field	Value
Publication number	US-10179309-B2
Application number	US-201615238287-A
Country	US
Kind code	B2
Filing date	Aug 16, 2016
Priority date	Aug 16, 2016
Publication date	Jan 15, 2019
Grant date	Jan 15, 2019

Abstract

An on-board aircraft dried inert gas system includes a source inert gas containing water, an air cycle or vapor cycle cooling system, and a heat exchanger condenser. The heat exchanger condenser has a heat absorption side in thermal communication with the air cycle or vapor cycle cooling system. The heat exchanger condenser has a heat rejection side that receives the inert gas containing water and outputs dried inert gas.

First claim

The invention claimed is:

1. An on-board aircraft dried inert gas system, comprising:
a source of an inert gas comprising water;
an air cycle cooling system comprising a primary heat exchanger, a compressor, a secondary heat exchanger, a turbine, and a condenser/reheater and a water removal unit, or a vapor cycle cooling system comprising a two-phase refrigerant cycled through a vapor-compression loop cycle comprising a compressor, a condenser, an expansion device, and an evaporator;
a first heat exchanger condenser comprising a heat absorption side in thermal communication with the air cycle cooling system or with the vapor cycle cooling system, and a heat rejection side that receives the inert gas comprising water and outputs dried inert gas; and
a second heat exchanger condenser comprising a heat absorption side in thermal communication with ram air and a heat rejection side that receives the inert gas comprising water and outputs dried inert gas.

2. The system of claim 1 , wherein the source of inert gas comprising water comprises a proton exchange membrane electrochemical cell that reacts oxygen in air with hydrogen to produce the oxygen-depleted gas.

3. The system of claim 2 , further comprising a water recycle of condensate from the heat rejection side of the heat exchanger condenser to the proton exchange membrane electrochemical cell.

4. The system of claim 1 , wherein the source of inert gas comprising water comprises a catalytic reactor that reacts oxygen with hydrocarbon to produce the oxygen-depleted gas.

5. The system of claim 1 , wherein the heat absorption side of the heat exchanger condenser is in thermal communication with the air cycle cooling system.

6. The system of claim 5 , wherein the heat absorption side of the heat exchanger condenser receives, or is in thermal communication through a heat transfer fluid with, a conditioned air from the air cycle cooling system.

7. The system of claim 1 , wherein the heat absorption side of the heat exchanger condenser is in thermal communication with the vapor cycle cooling system.

8. An on-board aircraft inert gas system, comprising:
a source of hydrogen;
a plurality of electrochemical cells, individually comprising a cathode and an anode separated by a proton exchange electrolyte separator;
a cathode fluid flow path in fluid communication with the cell cathodes that receives a flow of air from an air source and discharges oxygen-depleted air;
an anode fluid flow path in fluid communication with the cell anodes;
a water flow path in fluid communication with the proton exchange electrolyte separator
an electrical circuit connecting the anode and the cathode that provides voltage that forms hydrogen ions at the anode and forms water at the cathode;
a heat exchanger condenser comprising a heat absorption side in thermal communication with a heat sink, and a heat rejection comprising an inlet that receives fluid from the cathode fluid flow path, a water condensate outlet in fluid communication with the water flow path, and an inert gas outlet,
wherein the heat exchanger condenser includes a first heat exchanger condenser and a second heat exchanger condenser, and said heat sink includes;
an air cycle systems or a vapor cycle cooling system in thermal communication with a heat absorption side of the first heat exchanger condenser, wherein said air cycle cooling systems comprises a primary heat exchanger, a compressor, a secondary heat exchanger, a turbine, and a condenser/reheater and a water removal unit, and wherein said vapor cycle cooling system comprises a two-phase refrigerant cycled through a vapor-compression loop cycle comprising a compressor, a condenser, an expansion device, and a evaporator, and
ram air in thermal communication with a heat absorption side of the second heat exchanger condenser.

9. The system of claim 8 , wherein the water flow path is in fluid communication with the anodes and is coincident with at least a portion of the anode fluid flow path.

10. The system of claim 8 , wherein the water flow path is in fluid communication with the cathodes and is coincident with at least a portion of the cathode fluid flow path.

11. The system of claim 8 , wherein the water flow path comprises an anode-side water flow path that is in fluid communication with the anodes and is coincident with at least a portion of the anode fluid flow path, and a cathode-side water flow path that is in fluid communication with the cathodes and is coincident with at least a portion of the cathode fluid flow path.

12. The system of claim 11 , wherein the water flow path further comprises a water reservoir in fluid communication with the heat exchanger water outlet and with the anode-side and cathode-side water flow paths.

13. The system of claim 8 , wherein the electrochemical cells are configured to operate at least a part of the time in a mode in which water is directed to the anode, electric power is provided to the electrical circuit at a voltage that electrolyzes water at the anode.

14. The system of claim 13 , wherein the electrochemical cells are configured to operate at least a part of the time in a mode in which hydrogen fuel is directed to the anode, and electric power is directed from the circuit to one or more vehicle electric power-consuming systems or components.

15. The system of claim 8 , wherein the electrochemical cells are configured to operate at least a part of the time in a mode in which hydrogen fuel is directed to the anode, and electric power is directed from the circuit to one or more vehicle electric power-consuming systems or components.

16. The system of claim 8 , wherein the proton exchange electrolyte separator comprises a polymer proton exchange membrane.

17. The system of claim 8 , wherein the plurality of electrochemical cells are connected in electrical series in a stack.

18. The system of claim 8 , wherein the heat sink comprises an on-board air cycle or vapor cycle cooling system, ram air, or liquid fuel in an on-board fuel tank.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Rheaume Jonathan
• St Rock Brian
• Lents Charles E

Classifications

• B01D2259/4575

  in aeroplanes or space ships · CPC title

• A62C99/0018

  using gases or vapours that do not support combustion, e.g. steam, carbon dioxide · CPC title

• B64D37/32

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• F24F3/1405

  in which the humidity of the air is exclusively affected by contact with the evaporator of a closed-circuit cooling system or heat pump circuit · CPC title

• B64D13/06

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