One-piece baffle infrared suppressor apparatus and method

• US 20070028622A1
• Filed: 08/03/2005
• Published: 02/08/2007
• Est. Priority Date: 08/03/2005
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Steyer, William, Kieffer, Christopher, Jasany, John
• Granted Patent: US 7,607,305 B2
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F02K 1/48 Corrugated nozzles
• CPC Class Codes: F02K 1/825 Infrared radiation suppressors
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A method for suppressing infrared radiation from an aircraft engine includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single baffle assembly to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Claims

1. A method for suppressing infrared radiation from an aircraft engine, said method comprising:

directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single baffle assembly to generate alternating flows of hot exhaust gas and cold air; and

directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to facilitate mixing the hot exhaust gas with the cold air.

2. A method in accordance with claim 1 further comprising providing an additional flow path for cold air so that said hot air flows of said alternating hot and cold air flows are surrounded on three sides by cold air.

3. A method in accordance with claim 2 further comprising shielding a forward or hot baffle of the single baffle assembly in an exit direction using a cold baffle.

4. A method in accordance with claim 3 further comprising shielding the cold baffle in the exit direction.

5. A method in accordance with claim 3 further comprising guiding cold air into a recess inside the cold baffle.

6. A method in accordance with claim 1 further comprising providing a cooling/dilution flow ration of approximately 1.5:

1.

7. A method in accordance with claim 1 additionally comprising further cooling the mixed hot air and cold air in a duct having an extended inlet flowpath.

8. A method in accordance with claim 1 wherein the single baffle infrared suppressor has an axis of at least about 15 degrees relative to an axis of an adaptor ring configured to slide over a tailpipe of the aircraft engine.

9. An infrared suppressor for an aircraft engine, said apparatus comprising a lobed mixer and one single baffle assembly, said apparatus further configured to:

direct hot exhaust from the aircraft engine into said lobed mixer to generate alternating flows of hot exhaust gas and cold air; and

direct the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

10. An infrared suppressor in accordance with claim 9 further configured to provide an additional flow path for cold air so that said hot air flows of said alternating hot and cold air flows are surrounded on three sides by cold air.

11. An infrared suppressor in accordance with claim 10 wherein said single baffle assembly comprises a forward or hot baffle and a cold baffle, and said apparatus is further configured to shield said forward or hot baffle in an exit direction using said cold baffle.

12. An infrared suppressor in accordance with claim 11 further comprising shields configured to shield said cold baffle in an exit direction.

13. An infrared suppressor in accordance with claim 12 further configured to guide cold air into a recess inside the cold baffle.

14. An infrared suppressor in accordance with claim 9 further comprising a stage III duct having an extended inlet flowpath and additionally configured to further cool the mixed hot air and cold air in said stage III duct.

15. An infrared suppressor in accordance with claim 9 further comprising an adapter ring configured to slide over a tailpipe of the aircraft engine and having an axis turned at least about 15 degrees relative to an axis of the adapter ring.

16. An infrared suppressor in accordance with claim 9 wherein lobes of said mixer are hidden from a line-of-sight from an exit of said infrared suppressor.

17. An infrared suppressor in accordance with claim 16 wherein said single baffle assembly comprises a forward baffle and a cold baffle, and said apparatus is further configured to shield at least one of said forward baffle and said cold baffle in an exit direction.

18. An infrared suppressor in accordance with claim 9 further configured to provide an additional flow path for cold air so that said hot air flows of said alternating hot and cold air flows are surrounded on three sides by cold air.

19. A method for suppressing infrared radiation from an aircraft engine, said method comprising:

directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single baffle assembly to generate alternating flows of hot exhaust gas and cold air;

directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air; and

shielding lobes of the lobed mixer from a line of sight from an exit direction for the mixture of hot exhaust gas and cold air.

20. A method in accordance with claim 19 further comprising providing an additional flow path for cold air such that said hot air flows of said alternating hot and cold air flows are surrounded on three sides by cold air.