# US 7,607,306 B2 · Infrared suppressor apparatus and method > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 7,607,306 B2 - Document ID: US7607306B2 - Status: Granted - Kind: B2 - Application number: 11/196,466 - Filed: 2005-08-03 - Published: 2007-02-08 - Granted: 2009-10-27 - Earliest claimed: 2005-08-03 - Assignees: General Electric Company - Inventors: William Steyer; Christopher Marlow Kieffer; Walter J. Tingle - Web page: https://patentgrep.com/patent/US7607306B2 ## CPC - F02K 1/825: {Infrared radiation suppressors} - F02K 1/386: {mixing devices in the jet pipe, e.g. for mixing primary and secondary flow} - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) ## Abstract A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle 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 ### Claim 1 A method for suppressing infrared radiation from an engine of an aircraft operating in an environment, said method comprising: directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle 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 collapsible, translatable baffle to mix the hot exhaust gas with the cold air. ### Claim 2 (depends on 1) A method in accordance with claim 1 further comprising collapsing and translating the baffle depending upon a threat level of the environment of the aircraft. ### Claim 3 (depends on 2) A method in accordance with claim 2 wherein said collapsing and translating the baffle depending upon a threat level of the environment of the aircraft further comprises selecting between a first mode in which a direct view of an exhaust cavity is blocked, a second mode in which the baffle is opened up to increase pumping and blocking of a line-of-sight into the engine, and a third mode in which the baffle is collapsed to reduce or minimize backpressure. ### Claim 4 (depends on 2) A method in accordance with claim 2 further comprising positioning a hood and a panel of the infrared suppressor in accordance with the threat environment. ### Claim 5 (depends on 4) A method in accordance with claim 4 wherein said collapsing and translating the baffle depending upon a threat level of the environment of the aircraft further comprises selecting between a first mode in which a direct view of an exhaust cavity is blocked, a second mode in which the baffle is opened up to increase pumping and blocking of a line-of-sight into the engine, and a third mode in which the baffle is collapsed to reduce or minimize backpressure. ### Claim 6 (depends on 5) A method in accordance with claim 5 wherein, in said first mode, said hood and said panel are positioned, rotated, or both to turn the exhaust from the engine. ### Claim 7 (depends on 1) A method in accordance with claim 1 further comprising positioning a hood and a panel of the infrared suppressor in accordance with the threat environment. ### Claim 8 (depends on 7) A method in accordance with claim 7 further comprising at least one of positioning or rotating said hood and said panel to turn the exhaust from the engine. ### Claim 9 (depends on 1) A method in accordance with claim 1 further comprising selecting a mode of operation from a set of modes including a first mode in which a direct view of an exhaust cavity is blocked, a second mode that pumps and blocks a line-of-sight into the engine, and a third mode in which backpressure is minimized or reduced. ### Claim 10 An infrared suppressor for suppressing infrared radiation from an engine of an aircraft operating in an environment, said infrared suppressor comprising: a stage I duct configured to direct hot exhaust from the aircraft engine towards a stage II duct; a gap around the stage I duct configured to channel a flow of cold air towards said stage II duct; and a lobed mixer of a single baffle assembly having a collapsible, translatable baffle positioned in said stage II duct, said single baffle assembly configured to generate alternating flows of hot exhaust gas and cold air. ### Claim 11 (depends on 10) An infrared suppressor in accordance with claim 10 further configured to collapse and translate the baffle to accommodate a threat level of the environment of the aircraft. ### Claim 12 (depends on 11) An infrared suppressor in accordance with claim 11 wherein said collapsible and translatable baffle is configurable in a first mode in which a direct view of an exhaust cavity is blocked, a second mode in which the baffle is opened up to increase pumping and blocking of a line-of sight into the engine, and a third mode in which the baffle is collapsed to reduce or minimize backpressure. ### Claim 13 (depends on 11) An infrared suppressor in accordance with claim 11 further comprising a hood and a panel configured to be positioned, rotated, or both. ### Claim 14 (depends on 13) An infrared suppressor in accordance with claim 13 wherein said collapsible and translatable baffle is configurable in a first mode in which a direct view of an exhaust cavity is blocked, a second mode in which the baffle is opened up to increase pumping and blocking of a line-of-sight into the engine, and a third mode in which the baffle is collapsed to reduce or minimize backpressure. ### Claim 15 (depends on 14) An infrared suppressor in accordance with claim 14 wherein, said hood and said panel are configured to be positioned, rotated, or both to turn the exhaust from the engine in said first mode. ### Claim 16 (depends on 10) An infrared suppressor in accordance with claim 10 further comprising a hood and a panel that are each repositionable in accordance with the threat environment. ### Claim 17 (depends on 16) An infrared suppressor in accordance with claim 16 wherein said hood and said panel are at least one of positionable or rotatable to turn the exhaust from the engine. ### Claim 18 (depends on 10) An infrared suppressor in accordance with claim 10 further configured to operate in a set of modes including a first mode in which a direct view of an exhaust cavity is blocked, a second mode that substantially blocks a line-of-sight into the engine, and a third mode in which backpressure is minimized or reduced. ### Claim 19 An infrared suppressor for suppressing infrared radiation from an engine of an aircraft, said infrared suppressor comprising: a stage I duct having an adapter ring configured to slide over a tailpipe of the engine and a lobed mixer; a stage II duct coupled to said stage I duct and having a collapsible and translatable single baffle assembly, said stage II duct configured to receive exhaust from the engine that leaves said stage I duct; and a stage III duct coupled to said stage II duct and configured to receive exhaust from the engine that leaves said stage II duct, said stage III duct comprising a hood and a panel that are at least one of positionable or rotatable to turn exhaust leaving said stage III duct. ### Claim 20 (depends on 19) An infrared suppressor in accordance with claim 19 configured to operate in a set of modes including a first mode in which a direct view of an exhaust cavity is blocked, a second mode that pumps and blocks a line-of-sight into the engine, and a third mode in which backpressure is minimized or reduced.