Aircraft systems and methods with integrated tank inerting and power generation

Patent metadata

Field	Value
Publication number	US-9731834-B2
Application number	US-201715434485-A
Country	US
Kind code	B2
Filing date	Feb 16, 2017
Priority date	Mar 27, 2014
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank.

First claim

What is claimed is:

1. A system for inerting a fuel tank of an aircraft, comprising:
a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank;
a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture;
a fuel cell comprising an anode and a cathode, the fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity, the anode generating a first exhaust product; and
an auxiliary power unit (APU) fluidly coupled to the fuel cell and configured to provide cathode air to the fuel cell, wherein the cathode of the fuel cell generates a second exhaust product directed to the fuel tank as inerting gas.

2. The system of claim 1 , wherein the APU comprises a second compressor configured to draw in ambient air to produce compressed air;
a combustor coupled to the second compressor and configured to receive the compressed air and to ignite the compressed air to generate combustion gases;
a turbine coupled to the combustor and configured to be driven by the combustion gases to generate electricity, the turbine generating exhaust gases.

3. The system of claim 2 , further comprising a heat exchanger fluidly coupled between the first compressor and the fuel processor, the heat exchanger further fluidly coupled to the turbine such that heat is transferred from the exhaust gases to the air and fuel vapor mixture.

4. The system of claim 3 , wherein the APU further comprises a third compressor configured to provide the cathode air to the fuel cell.

5. The system of claim 4 , further comprising a water extractor fluidly coupled between the fuel cell and the fuel tank to remove water from the inerting gas.

6. The system of claim 5 , further comprising a desulfurizer coupled to the fuel processor and the fuel tank, the desulfurizer configured to direct liquid fuel from the fuel tank to the fuel processor.

7. The system of claim 1 , wherein the first compressor, the fuel processor, the fuel cell, and the APU form a closed loop inerting system.

8. A system for inerting a fuel tank of an aircraft, comprising:
a fuel processor fluidly coupled and configured to receive an air and fuel vapor mixture from an ullage of the fuel tank and to generate hydrogen from the air and fuel vapor mixture;
a fuel cell comprising an anode and a cathode, the fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity, the anode generating a first exhaust product and the cathode generating a second exhaust product;
a first compressor fluidly coupled to the fuel cell for removing the first exhaust product from the fuel cell; and
an auxiliary power unit (APU) fluidly coupled to the fuel cell and configured to receive the first and second exhaust products, the APU generating exhaust gases that are directed to the fuel tank as inerting gas.

9. The system of claim 8 , wherein the APU comprises a second compressor configured to draw in the second exhaust product from the fuel cell;
a combustor coupled to the second compressor and configured to receive and to ignite the second exhaust product from the second compressor and the first exhaust product from the first compressor, the combustor generating combustion gases; and
a turbine coupled to the combustor and configured to be driven by the combustion gases to generate electricity, the turbine generating the exhaust gases.

10. The system of claim 9 , further comprising a heat exchanger fluidly coupled between the fuel tank and the fuel processor, the heat exchanger further fluidly coupled such that heat is transferred from the exhaust gases to the air and fuel vapor mixture.

11. The system of claim 10 , wherein a second heat exchanger is additionally fluidly coupled between the turbine and a RAM air inlet such that heat is transferred between RAM air and the exhaust gases.

12. The system of claim 11 , further comprising a water extractor fluidly coupled between the second heat exchanger and the fuel tank to remove water from the exhaust gases.

13. The system of claim 12 , wherein the water extractor is additionally fluidly coupled to the fuel processor and configured to provide the water to the fuel processor.

14. The system of claim 13 , further comprising a desulfurizer coupled to the fuel processor and the fuel tank, the desulfurizer configured to direct liquid fuel from the fuel tank to the fuel processor.

Assignees

• Honeywell Int Inc

Inventors

• Hagh Bijan F
• Zheng Daguang
• Johnson Russell W
• Acharya Mukund
• Scaini Mario

Classifications

• B64D37/32 Primary

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• A62C3/065

  for containers filled with inflammable liquids · CPC title

• H01M8/04111

  using a compressor turbine assembly · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title