Auxiliary power unit with solid oxide fuel cell for an aircraft

Patent metadata

Field	Value
Publication number	US-2018141675-A1
Application number	US-201715814464-A
Country	US
Kind code	A1
Filing date	Nov 16, 2017
Priority date	Nov 16, 2016
Publication date	May 24, 2018
Grant date	—

Abstract

An auxiliary power unit and a method for providing electricity to an aircraft with the auxiliary power unit where the auxiliary power unit includes a turbine with a compressor and an output shaft. A combustor coupled to the turbine and to a fuel source, and a solid oxide fuel cell coupled to the combustor, the compressor and to the fuel source.

First claim

What is claimed is:

1 . An auxiliary power unit for an aircraft comprising:
a turbine including a compressor and an output shaft; a combustor coupled to the turbine and to a fuel source; and a solid oxide fuel cell coupled to the combustor, the compressor, and to the fuel source and having a power output; wherein compressed air from the compressor and fuel from the fuel source undergo a chemical reaction in the solid oxide fuel cell to generate electricity at the power output, and unreacted fuel from the solid oxide fuel cell and fuel from the fuel source combust in the combustor to power the compressor and the output shaft in the turbine.

2 . The auxiliary power unit of claim 1 further comprising a starter generator electrically connected to the power output.

3 . The auxiliary power unit of claim 1 further comprising a pre-reformer between the solid oxide fuel cell and the fuel source to condition the fuel before entering the solid oxide fuel cell.

4 . The auxiliary power unit of claim 1 further comprising a power conditioning unit coupled to the power output.

5 . The auxiliary power unit of claim 4 further comprising a battery supply coupled to the power conditioning unit.

6 . The auxiliary power unit of claim 1 wherein the turbine includes an exhaust and a heat exchanger is connected to the exhaust.

7 . The auxiliary power unit of claim 6 further comprising a thermal electric generator connected between the exhaust and the heat exchanger.

8 . The auxiliary power unit of claim 7 wherein the thermal electric generator is connected to a power conditioning unit coupled to the power output.

9 . The auxiliary power unit of claim 1 where the chemical reaction takes place in a pair of electrodes yielding oxidant ions, electrons, water, and carbon dioxide.

10 . An aircraft comprising:
an auxiliary power unit having a turbine including a compressor and an output shaft; a combustor coupled to the turbine and to a fuel source; and a solid oxide fuel cell coupled to the combustor, the compressor, and to the fuel source and having a power output; wherein compressed air from the compressor and fuel from the fuel source act in the solid oxide fuel cell to generate electricity at the power output, and unreacted fuel from the solid oxide fuel cell and fuel from the fuel source combust in the combustor to power the compressor and the output shaft in the turbine.

11 . The aircraft of claim 10 further comprising a starter generator electrically connected to the power output.

12 . The aircraft of claim 10 further comprising a pre-reformer between the solid oxide fuel cell and the fuel source to condition the fuel before entering the solid oxide fuel cell.

13 . The aircraft of claim 10 further comprising a power conditioning unit coupled to the power output.

14 . The aircraft of claim 13 further comprising a battery supply coupled to the power conditioning unit.

15 . The aircraft of claim 10 wherein the turbine includes an exhaust and a heat exchanger is connected to the exhaust.

16 . The aircraft of claim 15 further comprising a thermal electric generator connected between the exhaust and the heat exchanger.

17 . A method of providing electricity to an aircraft comprising:
supplying compressed air from a turbine compressor in an auxiliary power unit to a solid oxide fuel cell;
supplying fuel to the solid oxide fuel cell;
generating electricity in the solid oxide fuel cell;
directing unreacted fuel from the solid oxide fuel cell to a combustor in the auxiliary power unit;
supplying fuel to the combustor; and
delivering electricity from the solid oxide fuel cell to the aircraft.

18 . The method of claim 17 further comprising conditioning the fuel before supplying the fuel to the solid oxide fuel cell.

19 . The method of claim 18 wherein conditioning includes heating the fuel.

20 . The method of claim 17 further comprising directing exhaust gas from the combustor to a thermal electric generator, and delivering electricity from the thermal electric generator to the aircraft.

Assignees

• Ge Aviat Systems Ltd

Inventors

• Halsey Colin John
• Bailey Michael David

Classifications

• H02J2101/30

  Fuel cells · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title

• F02C6/04

  Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output (F02C6/18 takes precedence {; for a fluidised-bed combustor F02C3/205}) · CPC title

• H01M8/0662

  Treatment of gaseous reactants or gaseous residues, e.g. cleaning · CPC title