초록 ▼

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 inc

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.

대표청구항 ▼

What is claimed is: 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 g

What is claimed is: 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; 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; and cooling the hot exhaust gas and cold air mixture in a duct having an extended inlet flowpath. 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 exhaust gas 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 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. 8. 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; provide an additional flow path for cold air so that said alternating flows of hot exhaust gas and cold air are surrounded on three sides by 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. 9. An infrared suppressor in accordance with claim 8 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. 10. An infrared suppressor in accordance with claim 9 further comprising shields configured to shield said cold baffle in an exit direction. 11. An infrared suppressor in accordance with claim 10 further configured to guide cold air into a recess inside the cold baffle. 12. An infrared suppressor in accordance with claim 8 further comprising a stage III duct having an extended inlet flowpath and additionally configured to further cool the mixed hot exhaust gas and cold air in said stage III duct. 13. An infrared suppressor in accordance with claim 8 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. 14. An infrared suppressor in accordance with claim 8 wherein lobes of said mixer are hidden from a line-of-sight from an exit of said infrared suppressor. 15. An infrared suppressor in accordance with claim 14 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. 16. An infrared suppressor in accordance with claim 8 further configured to provide an additional flow path for cold air so that alternating flows of hot exhaust gas and cold air are surrounded on three sides by cold air. 17. 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. 18. A method in accordance with claim 17 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.