Power source for an aircraft

Patent metadata

Field	Value
Publication number	US-10814992-B2
Application number	US-201715814655-A
Country	US
Kind code	B2
Filing date	Nov 16, 2017
Priority date	Nov 16, 2016
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

A power source for an aircraft including a solid oxide fuel cell and a proton exchange membrane fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell.

First claim

What is claimed is:

1. A power source for an aircraft comprising:
a solid oxide fuel cell electrically coupled to a first power converter wherein the first power converter is electrically coupled to an aircraft distribution network to supply electricity to the aircraft;
a proton exchange membrane fuel cell electrically coupled to a second power converter wherein the second power converter is electrically coupled to the aircraft distribution network to supply electricity to the aircraft;
at least one battery electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and the aircraft distribution network to supply electricity to the aircraft and to be recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell; and
a solid oxide fuel cell multi-power unit electrically coupled to a third power converter wherein the solid oxide fuel cell multi-power unit is electrically coupled to the aircraft distribution network to supply electricity to the aircraft, to supply hydraulics to the aircraft, and to supply compressed air to the aircraft.

2. The power source of claim 1 wherein the solid oxide fuel cell, the proton exchange membrane fuel cell, and the solid oxide fuel cell multi-power unit are fluidly coupled to a fuel source.

3. The power source of claim 2 where the fuel source is at least one source of aviation fuel.

4. The power source of claim 3 further comprising at least one reformer between the fuel source and at least one of the solid oxide fuel cell, the proton exchange membrane fuel cell, and the solid oxide fuel cell multi-power unit.

5. The power source of claim 1 wherein solid oxide fuel cell multi-power unit comprises a solid oxide fuel cell electrically coupled to an electrically powered compressor and an electrically powered hydraulic pump.

6. The power source of claim 1 wherein solid oxide fuel cell multi-power unit comprises a solid oxide fuel cell fluidly coupled to a gas turbine engine.

7. The power source of claim 1 further comprising supercapacitors electrically coupled the at least one battery to power fast load transients.

8. The power source of claim 1 further comprising an independent fuel source electrically coupled to a second proton exchange membrane fuel cell for supplemental power.

9. The power source of claim 1 further comprising a controller in the aircraft distribution network electrically coupled to each of the solid oxide fuel cell, the proton exchange membrane fuel cell, the solid oxide fuel cell multi-power unit, and the at least one battery to control allocation of electricity from the solid oxide fuel cell, the proton exchange membrane fuel cell, the solid oxide fuel cell multi-power unit, and the at least one battery on the aircraft distribution network.

10. The power source of claim 1 wherein at least one of the first power converter, the second power converter, or the solid oxide fuel cell combined with third power converter is configured to convert DC power to AC power.

11. An aircraft comprising:
a propulsion source;
an aircraft distribution network; and
a separate power source, the separate power source having
a solid oxide fuel cell electrically coupled to a first power converter wherein the first power converter is electrically coupled to the aircraft distribution network to supply electricity to the aircraft;
a proton exchange membrane fuel cell electrically coupled to a second power converter wherein the second power converter is electrically coupled to the aircraft distribution network to supply electricity to the aircraft;
at least one battery electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and the aircraft distribution network to supply electricity to the aircraft and to be recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell; and
a solid oxide fuel cell multi-power unit electrically coupled to a third power converter wherein the solid oxide fuel cell multi-power unit is electrically coupled to the aircraft distribution network to supply electricity to the aircraft, to supply hydraulics to the aircraft, and to supply compressed air to the aircraft.

12. The aircraft of claim 11 wherein the solid oxide fuel cell, the proton exchange membrane fuel cell, and the solid oxide fuel cell multi-power unit are fluidly coupled to a fuel source.

13. The aircraft of claim 12 further comprising at least one reformer between the fuel source and at least one of the solid oxide fuel cell, the proton exchange membrane fuel cell, and the solid oxide fuel cell multi-power unit.

14. The aircraft of claim 11 wherein the solid oxide fuel cell multi-power unit comprises a solid oxide fuel cell electrically coupled to an electrically powered compressor and an electrically powered hydraulic pump.

15. The aircraft of claim 11 wherein the solid oxide fuel cell multi-power unit comprises a solid oxide fuel cell fluidly coupled to a gas turbine engine.

16. The aircraft of claim 11 further comprising supercapacitors electrically coupled the at least one battery to power fast load transients.

17. The aircraft of claim 11 further comprising an independent fuel source fluidly coupled to a second proton exchange membrane fuel cell for supplemental power.

18. The aircraft of claim 11 further comprising a controller in the aircraft distribution network electrically coupled to each of the solid oxide fuel cell, the proton exchange membrane fuel cell, the solid oxide fuel cell multi-power unit, and the at least one battery to control allocation of electricity from the solid oxide fuel cell, the proton exchange membrane fuel cell, the solid oxide fuel cell multi-power unit, and the at least one battery on the aircraft distribution network.

19. The aircraft of claim 11 wherein at least one of the first power converter, the second power converter, or the solid oxide fuel cell combined with third power converter is configured to convert DC power to AC power.

Assignees

• Ge Aviat Systems Ltd

Inventors

• Halsey Colin John
• Bailey Michael David

Classifications

• B64D27/35

  Arrangements for on-board electric energy production, distribution, recovery or storage · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D35/022

  of hybrid-electric type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title