IGNITER/THRUSTER WITH CATALYTIC DECOMPOSITION CHAMBER

• US 20090297999A1
• Filed: 06/02/2008
• Published: 12/03/2009
• Est. Priority Date: 06/02/2008
• Status: Active Grant

• Current Assignee: Aerojet Rocketdyne Of De, Inc. (L3Harris Technologies, Inc.)
• Original Assignee: Aerojet Rocketdyne Of De, Inc. (L3Harris Technologies, Inc.)
• Inventors: JENSEN, Jeff, CLAFLIN, Scott
• Granted Patent: US 8,814,562 B2
• Time in Patent Office: Days
• US Class Current: 431/268
• CPC Class Codes: F23Q 11/00 Arrangement of catalytic igniters catalytic igniters per se C06C

Abstract

An ignition system and method of igniting the ignition system includes a main catalyst section in a staged relationship with a pilot-catalyst section to stage a decomposition though the pilot-catalyst section which preheats the main catalyst section.

Claims

1. An ignition system comprising:

a pilot-catalyst section along an axis; and

a main catalyst section in a staged relationship with said pilot-catalyst section along said longitudinal axis.

2. The system as recited in claim 1, further comprising a thermal element in communication with a pilot catalyst bed within said pilot-catalyst section.

3. The system as recited in claim 2, wherein said thermal element is electrically powered.

4. The system as recited in claim 1, further comprising a pilot-catalyst section heater about a pilot catalyst bed within said pilot-catalyst section.

5. The system as recited in claim 4, wherein said thermal element is electrically powered.

6. The system as recited in claim 1, wherein said pilot-catalyst section includes a pilot catalyst bed.

7. The system as recited in claim 6, wherein said pilot catalyst bed includes a material from a platinum metal group.

8. The system as recited in claim 1, wherein said main catalyst section includes a main catalyst bed.

9. The system as recited in claim 8, wherein said main catalyst bed includes a material from a platinum metal group.

10. The system as recited in claim 1, further comprising a pilot inlet in communication with said pilot-catalyst section.

11. The system as recited in claim 10, further comprising a main inlet in communication with said main catalyst section.

12. The system as recited in claim 11, further comprising a propellant in communication with said pilot inlet and said main inlet.

13. The system as recited in claim 12, wherein said propellant is communicated to said pilot inlet and said main inlet such that a percentage of said propellant communicated to said pilot inlet is less than 30%.

14. The system as recited in claim 12, wherein said propellant comprises a Nitrous Oxide (N2O) and a quantity of fuel, said quantity of fuel limited to maintain the propellant below a detonation limit.

15. The system as recited in claim 1, further comprising a nozzle section downstream of said main catalyst section.

16. The system as recited in claim 1, further comprising a nozzle section downstream of said main catalyst section, said nozzle section forms a thruster of a monopropellant thruster.

17. The system as recited in claim 1, further comprising a nozzle section downstream of said main catalyst section, said nozzle section forms an injector of a rocket engine.

18. The system as recited in claim 1, further comprising a nozzle section downstream of said main catalyst section, said nozzle section forms a torch of a cutting torch.

19. A method of igniting an igniter system comprising:

supplying a propellant to an igniter, the propellant having a Nitrous Oxide (N2O).

20. The method as recited in claim 19, further comprising:

supplying a quantity of fuel homogenous with the N2O, the quantity of fuel limited to maintain the propellant below a detonation limit.

21. A method as recited in claim 19, further comprising:

supplying the propellant to an pilot-catalyst section which preheats a main catalyst section adjacent to the pilot-catalyst section.

22. A method of igniting an igniter system comprising:

staging a decomposition though an pilot-catalyst section which preheats a main catalyst section adjacent to the pilot-catalyst section.

23. A method as recited in claim 22, further comprising:

supplying a propellant to the pilot-catalyst section and the main catalyst section.

24. A method as recited in claim 23, further comprising:

supplying the propellant to the pilot-catalyst section and the main catalyst section, the propellant having a Nitrous Oxide (N2O) and a quantity of fuel, the quantity of fuel limited to maintain the propellant below a detonation limit.