Inert gas generating system

• US 9,102,416 B1
• Filed: 03/20/2012
• Issued: 08/11/2015
• Est. Priority Date: 03/20/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cutler, Theron Lee
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): MEADE, LORNE EDWARD
• Application Number:
  US13/424,471
• Time in Patent Office: 1,239 Days
• Field of Search: 60/390.91, 607/79
• US Class Current: 1/1
• CPC Class Codes: A62C 3/08 in aircraft A62C3/0207 takes precedence
• CPC Class Codes: A62C 99/0018 using gases or vapours that do not support combustion, e.g. steam, carbon dioxide
• CPC Class Codes: B64D 37/32 Safety measures not otherwise provided for, e.g. preventing explosive conditions extinguishing or preventing fires in aircraft A62C
• CPC Class Codes: F02C 6/00 Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• CPC Class Codes: F02C 7/25 Fire protection or prevention in general A62
• CPC Class Codes: F05D 2260/611 Sequestration of CO2

Abstract

A system for generating an inert gas. An embodiment of the system comprises a turbine engine, a compressor and a blower. Additional elements may be provided to condition the air so that it is satisfactory for use in the fuel tank. Such elements include filters, catalytic converters, air pressure regulators, and heat exchangers, as well as elements to monitor the oxygen content and temperature of the air flow. An embodiment of a method for generating an inert gas is also provided. The method comprises combusting fuel to generate engine exhaust, compressing the engine exhaust to generate compressed exhaust, and directing said compressed exhaust into the fuel tank.

Claims

1. A method of inerting a fuel tank in an aircraft having a main thrust generating engine and an auxiliary power unit, comprising the steps of:

providing a dedicated turbine engine;

combusting hydrocarbon fuel with oxygen in said dedicated turbine engine positioned in the aircraft, said dedicated turbine engine operating independent of the main thrust generating engine and said auxiliary power unit;

operating said dedicated turbine engine at a stoichiometric ratio to generate engine exhaust comprising carbon dioxide and having an oxygen content below a predetermined threshold;

cooling said engine exhaust with a first cooling air flow from a blower powered by said dedicated turbine engine;

compressing said engine exhaust in a compressor powered by said dedicated turbine engine to generate compressed exhaust;

cooling said compressed exhaust with a second cooling air flow from the blower; and

directing said compressed exhaust into the fuel tank.

2. The method of claim 1, further comprising:

detecting the amount of oxygen present in said engine exhaust and providing information to a control system for controlling the amount of fuel being provided to a said dedicated turbine engine and the speed of combustion of said dedicated turbine engine; and

detecting the temperature of said compressed exhaust and providing information to said control system.

3. The method of claim 2, further comprising:

removing particulates from said engine exhaust.

4. The method of claim 2, further comprising:

changing an output of the turbine engine to control the amount of engine exhaust provided to the compressor.

5. The method of claim 2, further comprising:

filtering said compressed exhaust to remove particulates.

6. An aircraft comprising:

an aircraft body;

a fuel tank;

a main thrust generating engine;

an auxiliary power unit;

a dedicated turbine engine operating at a stoichiometric ratio positioned in the aircraft and operable independent of the main thrust generating engine and said auxiliary power unit, the dedicated turbine engine configured to combust hydrocarbon fuel with oxygen to generate engine exhaust comprising carbon dioxide and having an oxygen content below a predetermined threshold;

a compressor powered by said dedicated turbine engine, said compressor operable to compress said engine exhaust to generate compressed exhaust;

a blower powered by said dedicated turbine engine and operable to provide a first cooling air flow to a first heat exchanger and a second cooling air flow to a second heat exchanger, said first heat exchanger configured to receive said compressed exhaust and utilize said first cooling air flow to cool said compressed exhaust, said second heat exchanger configured to utilize said second cooling air flow to cool said engine exhaust before said engine exhaust is compressed; and

a fuel tank feed line configured to direct said compressed exhaust into the fuel tank.

7. The aircraft of claim 6, further comprising:

a bypass valve positioned between said turbine engine and an engine exhaust outlet, said bypass valve operable to control the amount of engine exhaust provided to said compressor; and

an oxygen sensor configured to detect the amount of oxygen present in said engine exhaust and provide information to a control system for controlling the amount of fuel being provided to said turbine engine and the speed of combustion of said turbine engine.

8. The aircraft of claim 7, further comprising:

a catalytic converter interposed between said turbine engine and said compressor; and

a particulate separator interposed between said turbine engine and said compressor, said particulate separator configured to remove particulates from said engine exhaust.

9. The aircraft of claim 7, further comprising:

a filter operable to filter said compressed exhaust; and

a regulator configured to control the pressure of the compressed exhaust provided to said fuel tank.

10. The aircraft of claim 6, further comprising:

an oxygen sensor configured to detect the amount of oxygen present in said engine exhaust and provide information to a control system for controlling the amount of fuel being provided to said dedicated turbine engine and the speed of combustion of said dedicated turbine engine.

11. The aircraft of claim 10, further comprising:

a temperature sensor configured to detect the temperature of said compressed exhaust and provide information to said control system.

12. The aircraft of claim 6, wherein changing an output of the turbine engine changes an amount of compressed exhaust that is generated by said compressor.