Warming feature for aircraft fuel cells

Patent metadata

Field	Value
Publication number	US-9472819-B2
Application number	US-201213457850-A
Country	US
Kind code	B2
Filing date	Apr 27, 2012
Priority date	Apr 27, 2012
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

A system and method for warming a fuel cell on an aircraft, the system includes at least one fuel cell. The fuel cell includes an anode and a cathode for creating thermal and electrical energy. A temperature sensor measures a first temperature of the fuel cell. A control unit is coupled to the temperature sensor. The control unit increases the first temperature to a second temperature in response to the first temperature being at least equal to a selected temperature threshold. Increasing of the first temperature is indicative of the control unit operating in a warming mode. The second temperature is higher than the selected temperature threshold.

First claim

The invention claimed is:

1. A system for warming a fuel cell on an aircraft, comprising: at least one fuel cell including an anode and a cathode for creating electrical and thermal energy by an electrochemical reaction; a thermal control subsystem including a cooling loop operably coupled to an inlet and an outlet of the fuel cell and a heating loop operably coupled to the inlet and the outlet of the fuel cell, the cooling loop being separate from the heating loop; at least one temperature sensor for measuring a first temperature of the at least one fuel cell; and a control unit electrically coupled to the at least one temperature sensor, the control unit being configured for increasing the first temperature to a second temperature in response to the first temperature being at least equal to a selected temperature threshold; wherein the increasing of the first temperature is indicative of the control unit operating the fuel cell in a warming mode, and wherein the second temperature is higher than the selected temperature threshold
wherein the control unit is configured to increase the temperature while the aircraft is in flight, on ground, and during aircraft parking.

2. The system according to claim 1 , wherein the selected temperature threshold is generally in the range of between about 4° C. and about −10° C.

3. The system according to claim 2 , wherein the selected temperature threshold is generally about 0° C.

4. The system according to claim 1 , wherein the heating loop includes a warm fluid supply arranged in fluid communication with the fuel cell for heating the environment of the fuel cell.

5. The subsystem according to claim 4 , wherein the warm fluid is supplied from one or more of an aircraft air supply management system, a cabin air system of the aircraft, or engine bleed air.

6. The system according to claim 4 , wherein the temperature of the warm fluid is generally in the range of between about −10° C. and about 95° C.

7. The system according to claim 1 , wherein the heating loop further comprises a heat exchanger in fluid communication with the fuel cell for heating the environment of the fuel cell.

8. The system according to claim 1 , wherein power for operating the fuel cell in the warming mode is supplied by one of an electrical grid of the aircraft, a ground power source, or a battery.

Assignees

• Riordan Conor
• Kaap Dustin L
• Gummalla Mallika
• Hamilton Sundstrand Corp

Inventors

• Riordan Conor
• Kaap Dustin L
• Gummalla Mallika

Classifications

• H01M8/04253 Primary

  Means for solving freezing problems · CPC title

• H01M2008/1095

  Fuel cells with polymeric electrolytes · CPC title

• H01M8/04029

  Heat exchange using liquids · CPC title

• B64D2041/005

  Fuel cells · CPC title

• Y02T90/36

  Cross-Sectional Technologies · mapped topic