Hybrid fuel tank inerting system

• US 8,499,567 B2
• Filed: 06/27/2011
• Issued: 08/06/2013
• Est. Priority Date: 06/27/2011
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Zheng, Daguang, Elsayed, Mahmoud Adel, Hagh, Bijan F, Johnson, Russell W
• Primary Examiner(s): Wongwian, Phutthiwat
• Application Number:
  US13/169,917
• Publication Number:
  US 20120325811A1
• Time in Patent Office: 771 Days
• Field of Search: 60/391.2, 607/79, 607/80, 244/135.R, 220/4.12, 220/4.14, 220/88.3, 137/113, 137/206, 137/209
• US Class Current: 60/779
• CPC Class Codes: B01D 2257/702 Hydrocarbons
• CPC Class Codes: B01D 2259/4516 for fuel vapour recovery systems
• CPC Class Codes: B01D 2259/4575 in aeroplanes or space ships
• CPC Class Codes: B01D 53/002 by condensation
• CPC Class Codes: B01D 53/72 Organic compounds not provided for in groups B01D53/48 - B01D53/70, e.g. hydrocarbons
• CPC Class Codes: B01D 53/75 Multi-step processes
• CPC Class Codes: B64D 37/32 Safety measures not otherwise provided for, e.g. preventing explosive conditions extinguishing or preventing fires in aircraft A62C

Abstract

A self-regulating system for reducing concentration of hydrocarbon vapor in a container may be performed by introducing air into the container and extracting a mixture of air and vapor from the container. The extracted mixture may be compressed with a compressor to produce a flow of compressed mixture of air and vapor. The compressed mixture may be passed through an oxidation reactor that may be either catalytic or thermal to produce a flow air and CO₂. A turbine may be driven with the flow of air and CO₂. The compressor may be driven with the turbine. Extraction from the container may continue until vapor concentration is low enough so that flow of CO₂ and air from the reactor is insufficient to drive the turbine.

Claims

1. An inerting system for an aircraft fuel tank comprising:

a compressor with an inlet connected to the aircraft fuel tank and an outlet connected to a coalescer;

a driving turbine connected to drive the compressor; and

an oxidation reactor,

a vapor outlet of the coalescer being connected to an inlet of the reactor,

an outlet of the reactor being connected to the inlet of the turbine, and

an outlet of the driving turbine being connected to the aircraft fuel tank.

2. The inerting system of claim 1 wherein a liquid outlet of the coalescer is connected to the aircraft fuel tank.

3. The inerting system of claim 1 further comprising a first heat exchanger interposed between the outlet of the compressor and an inlet of the coalescer.

4. The inerting system of claim 3 wherein the first heat exchanger is configured to be cooled with ram air.

5. The inerting system of claim 1 further comprising a second heat exchanger interposed between the vapor outlet of the coalescer and the inlet of the reactor.

6. The inerting system of claim 5 wherein the second heat exchanger is interposed between an outlet of the driving turbine and the aircraft fuel tank.

7. The inerting system of claim 1 further comprising a motor connected to drive the compressor.

8. The inerting system of claim 7 further comprising an oxygen concentration sensor operationally connected to activate the motor.

9. The inerting system of claim 1 further comprising an expansion turbine connected to a shaft driven by the driving turbine, the expansion turbine being interposed between the vapor outlet of the coalescer and the inlet of the reactor.

10. The inerting system of claim 9 further comprising a third heat exchanger interposed between the expansion turbine and the inlet of the reactor.