| 摘要 |
An electricity production system for feeding electrical energy to a device of anaircraft comprises a generator 10 for generating gaseous hydrogen from hydrogen in non-gaseous form, a main tank 30 connected downstream of the generator for containing the generated gaseous hydrogen under a pressure substantially higher than atmospheric pressure, at least one fuel cell 50, an expander 40 connected downstream of the main tank and upstream of the fuel cell(s), a control device 70 that regulates the flow rate and the pressure of the gaseous hydrogen from the main tank to the fuel cell(s) via the expander, and a secondary tank 35 interposed between the main tank and the fuel cell(s), and connected upstream of the fuel cell(s) via the expander. A filter 20 may also be provided between the generator 10 and the main tank 30 so that only hydrogen is passed to the main tank. The gaseous hydrogen generator 10 may contain hydrogen in solid form. More than one fuel cell (51, 52; figure 2) may be provided, and the fuel cell(s) may be a high temperature PEMFC. The expander 40 serves to reduce the pressure of the hydrogen to a working pressure suitable for the fuel cell(s) 50. |
