RESONANCE DRIVEN GLOW PLUG TORCH IGNITER AND IGNITION METHOD

• US 20080299504A1
• Filed: 06/01/2007
• Published: 12/04/2008
• Est. Priority Date: 06/01/2007
• Status: Abandoned Application

• Current Assignee: Aerojet Rocketdyne Of De, Inc. (L3Harris Technologies, Inc.)
• Original Assignee: Aerojet Rocketdyne Of De, Inc. (L3Harris Technologies, Inc.)
• Inventors: Horn, Mark David
• Application Number:
  US11/756,642
• Publication Number:
  US 20080299504A1
• Time in Patent Office: Days
• US Class Current: 431/1
• CPC Class Codes: F02C 7/264 Ignition
• CPC Class Codes: F02K 9/95 characterised by starting or ignition means or arrangements safety devices F02K9/38
• CPC Class Codes: F05D 2260/99 Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity
• CPC Class Codes: F23N 2227/00 Ignition or checking
• CPC Class Codes: F23N 2227/04 Prepurge
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence

Abstract

An ignition system for a combustion device utilizes an oscillating pressure force in a resonance system to generate thermal energy within a resonance driven glow plug. The resonance driven glow plug stores the thermal energy for transfer to ignitable propellant combinations within a torch assembly and thus within the combustion chamber.

Claims

1. An ignition system for a combustor comprising:

a resonance system; and

a resonance driven glow plug heated by said resonance system.

2. The ignition system as recited in claim 1, wherein said resonance driven glow plug includes a generally hollow member in communication with said resonance system.

3. The ignition system as recited in claim 2, further comprising a working fluid inlet to said resonance system, said working fluid inlet generally opposite a gas resonance tube section.

4. The ignition system as recited in claim 1, wherein said resonance driven glow plug includes a stepped inner diameter.

5. The ignition system as recited in claim 4, wherein said resonance driven glow plug includes a stepped outer diameter.

6. The ignition system as recited in claim 4, wherein said resonance driven glow plug includes a constant diameter outer diameter.

7. The ignition system as recited in claim 4, wherein said resonance driven glow plug defines a resonance heated glow plug tip.

8. The ignition system as recited in claim 1, further comprising an insulator separated from said resonance driven glow plug by an annular air gap.

9. A combustor comprising:

an injector system;

a resonance media in fluid communication with said injector system;

a resonance system in communication with said resonance media; and

a resonance driven glow plug heated by said resonance system to ignite an ignitable propellant combination.

10. The combustor as recited in claim 9, wherein said resonance media is a gas.

11. The combustor as recited in claim 9, wherein said resonance media is an inert pressurant.

12. The combustor as recited in claim 9, wherein said resonance media is an oxidizer.

13. The combustor as recited in claim 9, wherein said resonance media is a fuel.

14. A method of igniting a combustion device comprising the steps of:

(A) communicating a resonance media to a resonance system to generate a resonance;

(B) heating a resonance driven glow plug with the resonance generated in said step

(A); and

(C) igniting an ignitable propellant combination with the resonance driven glow plug.

15. A method as recited in claim 14, wherein said step (B) further comprises:

(a) causing an oscillating detached shock to form upstream of an entrance to a gas resonance tube section of the resonance driven glow plug such that successive cycles of shocks cause the formation of a series of oscillating zones of elevated pressure within the resonance driven glow plug which heats the gas within the resonance tube which then heats the walls of the resonance driven glow plug.

16. A method as recited in claim 14, wherein said step (A) further comprises:

(a) communicating an inert pressurant as the resonance media.

17. A method as recited in claim 16, wherein said step (a) further comprises:

(a) exhausting the inert pressurant through an injector section as a purge.

18. A method as recited in claim 14, wherein said step (A) further comprises:

(a) communicating an ignitable propellant as the resonance media.

19. A method as recited in claim 14, wherein said step (C) further comprises:

igniting an ignition torch assembly.

20. A method as recited in claim 14, wherein said step (C) further comprises:

igniting a rocket engine.