Aircraft systems and methods with integrated tank inerting and power generation

Patent metadata

Field	Value
Publication number	US-9604730-B2
Application number	US-201414227689-A
Country	US
Kind code	B2
Filing date	Mar 27, 2014
Priority date	Mar 27, 2014
Publication date	Mar 28, 2017
Grant date	Mar 28, 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 fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity, the fuel cell generating an exhaust product;
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.

2. The system of claim 1 , further comprising
a second compressor configured to receive RAM air, the second compressor fluidly coupled to the fuel cell to provide the RAM air to the fuel cell as cathode air.

3. The system of claim 2 , further comprising a turbine fluidly coupled between the combustor and the first heat exchanger and configured to extract power from the combustion gas to drive the first compressor and the second compressor.

4. The system of claim 3 , wherein the second compressor is coupled to the first heat exchanger such that heat is transferred from the combustion gas to the RAM air.

5. The system of claim 4 , further comprising a second heat exchanger fluidly coupled between the first heat exchanger and the fuel tank to further cool the inerting gas for the fuel tank.

6. The system of claim 5 , wherein the second heat exchanger is additionally fluidly coupled between the first compressor and the fuel processor such that heat is transferred between the air and fuel vapor mixture and the inerting gas.

7. The system of claim 6 , further comprising a RAM air inlet to receive the RAM air and direct the RAM air to the second compressor.

8. The system of claim 7 , further comprising a third heat exchanger fluidly coupled between the second heat exchanger and the fuel tank to further cool the inerting air.

9. The system of claim 8 , wherein the third heat exchanger is additionally fluidly coupled between the second compressor and the RAM air inlet such that heat is transferred between the RAM air and the inerting gas.

10. The system of claim 9 , further comprising a water extractor fluidly coupled between the third heat exchanger and the fuel tank to remove water from the inerting gas.

11. The system of claim 10 , wherein the water extractor is additionally fluidly coupled to the fuel processor and configured to provide the water to the fuel processor.

12. The system of claim 11 , 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.

13. The system of claim 1 , wherein the combustor is an auxiliary power unit (APU) combustor.

14. The system of claim 1 , wherein the first compressor is fluidly coupled between the fuel cell and the combustor.

Assignees

• Honeywell Int Inc

Inventors

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

Classifications

• H01M8/04014

  Heat exchange using gaseous fluids; Heat exchange by combustion of reactants · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• A62C3/08

  in aircraft {(A62C3/0207 takes precedence)} · CPC title

• Y02E60/50

  Fuel cells · CPC title

• B64D2041/005

  Fuel cells · CPC title