Autonomous aircraft fuel cell system

Patent metadata

Field	Value
Publication number	US-2016159492-A1
Application number	US-201514963850-A
Country	US
Kind code	A1
Filing date	Dec 9, 2015
Priority date	Dec 9, 2014
Publication date	Jun 9, 2016
Grant date	—

Abstract

Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply.

First claim

What is claimed is:

1 . An aircraft fuel cell system, comprising
a high pressure hydrogen concentration zone; a low pressure hydrogen concentration zone; each of the high pressure hydrogen concentration zone and the low pressure hydrogen concentration zone comprising a hydrogen concentration sensor; and a blower system configured to provide dilution air to one or both of the zones based on hydrogen-containing gas concentration detected by the hydrogen concentration sensor.

2 . The system of claim 1 , wherein the high pressure hydrogen concentration zone houses one or more hydrogen-containing sources.

3 . The system of claim 2 , wherein the one or more hydrogen containing sources comprise one or more hydrogen cylinders.

4 . The system of claim 1 , wherein the low-pressure hydrogen concentration zone houses a fuel-cell.

5 . The system of claim 1 , wherein the blower system comprises one or more fans associated with a heat exchanger associated with the fuel-cell system.

6 . The system of claim 1 , further comprising one or more conduits for delivering air from the blower system to one or both of the a high pressure hydrogen concentration zone and the a low pressure hydrogen concentration zone.

7 . The system of claim 1 , further comprising a controller that receives hydrogen concentration information from the one or more hydrogen concentration sensors.

8 . The system of claim 1 , further comprising a venting line.

9 . The system of claim 1 , further comprising a hybrid regulator that provides a single stage regulation of pressure in the fuel-cell.

10 . The system of claim 9 , wherein the hybrid regulator comprises a first hybrid regulator on a hydrogen supply line and a second hybrid regulator on an oxygen supply line.

11 . An aircraft fuel-cell system, comprising:
a fuel-cell; related ancillary equipment for fuel-cell functioning; a battery; a battery charger; a preload resistor; and a series of contactors configured to control the flow of electricity generated by the fuel cell.

12 . The system of claim 11 , wherein the series of contactors comprise a resistor contactor, a fuel-cell contactor, a battery contactor, and a bus contactor.

13 . The system of claim 12 , wherein upon power request from aircraft loads, the battery contactor is closed and the bus contactor is closed and fuel-cell startup procedure is launched.

14 . The system of claim 12 , wherein closing of the resistor contactor brings fuel-cell voltage to a predefined voltage level that is at or close to the battery voltage.

15 . The system of claim 12 , wherein closing of the fuel-cell contactor powers the ancillary equipment and recharges the battery via the battery charger.

16 . The system of claim 11 , wherein the system operates autonomously and without being linked to an aircraft power supply.

17 . The system of claim 11 , wherein the system delivers power to aircraft loads without using a power converter.

18 . The system of claim 11 , wherein the system is configured to provide immediate power to aircraft loads via delivery of initial power from the battery and supplemental power from the fuel cell system once the fuel cell system has completed start up.

19 . A method for diluting a hydrogen-containing gas atmosphere, comprising:
providing at least two separate zones based on differing operating pressures of equipment contained therein; each zone comprising a hydrogen concentration sensor; detecting a hydrogen concentration within at least one of the zones; if the hydrogen concentration is above a predetermined level, delivering dilution gas to the zone.

20 . A method for powering aircraft loads, comprising:
providing an aircraft fuel-cell system of claim 11 ; receiving a request for power from one or more of the aircraft loads; delivering an initial power supply to the loads from the battery; and delivering further power supply to the loads from the fuel-cell.

Assignees

• Zodiac Aerotechnics

Inventors

• Filangi Jr Sébastien
• D Arbigny Julien
• Bouillo Loic
• Elleboode Christophe
• Masset Franck
• Gager Guillaume
• Marty Claire
• Zraiaa Hanane

Classifications

• H02J2105/32

  for aircrafts · CPC title

• H02J2101/30

  Fuel cells · CPC title

• H01M16/006

  of fuel cells with rechargeable batteries · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H01M8/2475 Primary

  Enclosures, casings or containers of fuel cell stacks · CPC title