Advanced carbon dioxide fuel tank inerting system

• US 7,905,259 B2
• Filed: 11/15/2006
• Issued: 03/15/2011
• Est. Priority Date: 11/15/2006
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Yates, Stephen F., Johnson, Russell W., Zaki, Rehan
• Primary Examiner(s): Maust; Timothy L
• Assistant Examiner(s): NIESZ, JASON KAROL
• Application Number:
  US11/560,290
• Publication Number:
  US 20080128048A1
• Time in Patent Office: 1,581 Days
• Field of Search: 141/4, 141/5, 141/37, 141/44, 141/45, 141/63, 141/64, 141/98, 141/285, 169/5, 169/9, 169/26, 169/62, 220/88.3, 137/209, 252/605
• US Class Current: 141/64
• 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

An onboard inert gas generation system includes an evaporator comprising a vessel that receives a hydrocarbon fuel from a fuel tank, separates vapor fuel components from liquid fuel components, establishes a nearly constant fuel vapor composition, and outputs the fuel vapor to be mixed with air prior to combusting the fuel vapor and air mixture in a catalytic reactor. Water is separated from the inert gas produced and the inert gas is introduced into the ullage space of the fuel tank to prevent or reduce possible hazardous conditions in the fuel tank.

Claims

1. An onboard inert gas generation system comprising:

an evaporator that receives a quantity of liquid hydrocarbon fuel from a source of liquid fuel, separates a first portion of the quantity into vapor fuel components, leaves a second portion of the quantity as liquid fuel components, drains the second portion of the quantity through a fuel return line for return to the source of liquid fuel, establishes a nearly constant fuel vapor composition, and outputs the first portion of the quantity as fuel vapor through a vapor line; and

a catalytic reactor that receives the output of fuel vapor from the vessel and an air input containing oxygen as reactive components.

2. The system of claim 1, wherein the first portion is less than 25% of the quantity of fuel received in the vessel.

3. The system of claim 1, wherein said nearly constant fuel vapor composition varies by no more than plus or minus 20%.

4. The system of claim 1, further comprising:

a fuel heater that adds a controlled amount of heat to said fuel.

5. The system of claim 1, further comprising:

an air heater that adds a controlled amount of heat to air in an air input line; and

a mixing tee that receives the heated air and the fuel vapor and outputs a mixture of the heated air and the fuel vapor to a mixture line.

6. An aircraft fuel system comprising:

a fuel valve that meters fuel;

a fuel heater that heats the metered fuel from the fuel valve;

an evaporator that receives the metered, heated fuel and provides a fuel vapor having a nearly constant fuel vapor composition;

a mixing tee that mixes the fuel vapor with air;

a catalytic reactor that reacts the fuel vapor and air mixture to produce an inert gas;

an air valve that meters air;

an air heater that heats the metered air fed from the air valve; and

a reactor inlet temperature indicator that provides a first control signal to the air heater.

7. The system of claim 6, wherein the catalytic reactor operates at a sufficient temperature and space velocity to oxidize the fuel into carbon dioxide and water vapor at a conversion greater than 90% of the fuel vapor.

8. The system of claim 6, further comprising:

a reactor outlet temperature indicator that provides a control signal to the fuel heater.

9. The system of claim 6, further comprising:

a reactor outlet temperature indicator that provides a second control signal to the fuel heater and the fuel valve; and

a safety temperature indicator that provides a third control signal to the fuel valve.

10. The system of claim 6, further comprising:

a recuperative heat exchanger that heats the metered air fed from the air valve using heat from the catalytic reactor.

11. The system of claim 6, further comprising:

a water separator that receives a reactor output effluent from the catalytic reactor and removes condensed water from the reactor output effluent and delivers the inert gas.

12. A method for fuel tank inerting, comprising the steps of:

introducing a quantity of liquid fuel from a fuel supply into an evaporator;

evaporating a first fraction of the quantity of the fuel into a fuel vapor;

draining a remaining fraction of the quantity of fuel, as a liquid, from the evaporator into the fuel supply;

combusting the fuel vapor with air in a reactor to form an inert gas; and

introducing the inert gas into an ullage space of the fuel tank.

13. The method of claim 12, further comprising:

metering a flow of liquid fuel into the evaporator in response to a control signal to control the fraction of fuel evaporated.

14. The method of claim 12, further comprising:

heating a flow of liquid fuel in response to a control signal to control the fraction of fuel evaporated.

15. The method of claim 12, further comprising:

heating an input air flow in response to a control signal before mixing the input air with the fuel vapor and feeding the fuel vapor with air to the reactor to control reactor operating conditions.

16. The method of claim 12, wherein:

the evaporating step uses only fuel from the fuel tank.

17. The method of claim 12, further comprising:

controlling the temperature of the inert gas using a safety temperature indicator.

18. The method of claim 12, wherein the step of evaporating the first fraction of the quantity of the fuel into a fuel vapor produces the fuel vapor with a first concentration of sulfur compounds smaller than a second concentration of sulfur compounds in the liquid fuel.