초록 ▼

A method for assembling a gas turbine engine includes mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine, wherein the exhaust nozzle includes a co

A method for assembling a gas turbine engine includes mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine, wherein the exhaust nozzle includes a cowl and a primary nozzle coupled radially inward from the cowl, and coupling an infrared suppression system in flow communication with the engine exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine, wherein the infrared suppression system includes a blocking fin having a substantially U-shaped cross-sectional profile and such that a cooling air flowpath is defined between the cowl and the blocking fin.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: mounting a core engine to a vehicle; coupling a fuselage radially outward and around the core engine; coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine,

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: mounting a core engine to a vehicle; coupling a fuselage radially outward and around the core engine; coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine, wherein the exhaust nozzle includes a cowl and a primary nozzle coupled radially inward from the cowl; and coupling an infrared suppression system in flow communication with the engine exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine, wherein the infrared suppression system includes a blocking fin that has an upstream end face oriented substantially perpendicular to an axis of a rotor of the core engine, said blocking fin having a substantially U-shaped cross-sectional profile and such that a cooling air flowpath is defined between the cowl and the blocking fin. 2. A method in accordance with claim 1 wherein coupling an infrared suppression system in flow communication with the engine exhaust nozzle comprises: coupling an attachment foot to the engine exhaust nozzle; and coupling the blocking fin having a substantially U-shaped cross-sectional profile to the attachment foot. 3. A method in accordance with claim 2 wherein coupling a blocking fin to the attachment foot comprises: coupling a first portion of the blocking fin to the attachment foot; and coupling a second portion the blocking fin to the first portion such that a gap is defined between the first and second portions. 4. A method in accordance with claim 3 further comprising forming a plurality of openings through the upstream first portion blocking fin to enable ambient air to be channeled from the cooling air flowpath into the gap and impinge on second portion to facilitate reducing an operating temperature of the second portion. 5. A method in accordance with claim 1 further comprising a coupling a plurality of cooling fins to the engine exhaust nozzle such that the plurality of cooling fins are axially forward of the blocking fin and substantially hidden from external views by said blocking fin. 6. An exhaust assembly for a gas turbine engine, said exhaust assembly comprising: an engine exhaust nozzle coupled to said gas turbine engine; an exhaust cowl at least partially circumscribing said engine exhaust nozzle such that a cooling passage is defined between said engine exhaust nozzle and said exhaust cowl; and an infrared suppression system coupled to said engine exhaust nozzle, a portion of said infrared suppression system comprising a plurality of blocking fins that have an upstream end face oriented substantially perpendicular to an axis of a rotor of said gas turbine engine with a substantially U-shaped cross-sectional profile that extends at least partially into said cooling passage, said suppression system facilitates suppressing an exhaust infrared signature of the gas turbine engine. 7. An exhaust assembly in accordance with claim 6 wherein said infrared suppression system comprises: an attachment foot coupled to said engine exhaust nozzle; and a blocking fin extending from said attachment foot, said blocking fin having a substantially U-shaped cross-sectional profile. 8. An exhaust assembly in accordance with claim 6 wherein said blocking fin comprises: an upstream first portion; and a second portion extending from said first portion such that a gap is defined between said first and second portions. 9. An exhaust assembly in accordance with claim 8 wherein said upstream first portion comprises a plurality of openings extending therethrough to facilitate channeling ambient cooling air from said cooling passage into said gap and impinging on said second portion. 10. An exhaust assembly in accordance with claim 7 wherein said attachment foot is formed unitarily with said blocking fin. 11. An exhaust assembly in accordance with claim 6 wherein said infrared suppression system is formed unitarily with said engine exhaust nozzle. 12. An exhaust assembly in accordance with claim 6 wherein said infrared suppression system comprises: an attachment foot coupled to said engine exhaust nozzle, said attachment foot having a substantially L-shaped cross-sectional profile; and a blocking fin extending from said attachment foot, said blocking fin having a substantially J-shaped cross-sectional profile. 13. An exhaust assembly in accordance with claim 6 wherein said infrared suppression system comprises: an attachment foot coupled to said engine exhaust nozzle, said attachment foot having a substantially U-shaped cross-sectional profile; and a blocking fin extending from said attachment foot, said blocking fin having a substantially L-shaped cross-sectional profile. 14. An exhaust assembly in accordance with claim 6 further comprising a plurality of cooling fins coupled to said engine exhaust nozzle and axially forward of said infrared suppression system. 15. A gas turbine engine configured to couple to a fuselage, said gas turbine engine comprising: an engine exhaust nozzle coupled to said gas turbine engine; an exhaust cowl at least partially circumscribing said engine exhaust nozzle such that a cooling passage is defined between said engine exhaust nozzle and said exhaust cowl; an infrared suppression system coupled to said engine exhaust nozzle, a portion of said infrared suppression system comprising a blocking fin substantially U-shaped cross-sectional profile that extends at least partially into said cooling passage, said suppression system facilitates suppressing an exhaust infrared signature of the gas turbine engine; and a plurality of cooling fins coupled to said engine exhaust nozzle axially forward of said infrared suppression system. 16. A gas turbine engine in accordance with claim 15 wherein said infrared suppression system comprises: an attachment foot coupled to said engine exhaust nozzle; and a blocking fin extending from said attachment foot, said blocking fin having a substantially U-shaped cross-sectional profile. 17. A gas turbine engine in accordance with claim 15 wherein said attachment foot is formed unitarily with said blocking fin. 18. A gas turbine engine in accordance with claim 15 wherein said infrared suppression system is formed unitarily with said engine exhaust nozzle. 19. A gas turbine engine in accordance with claim 15 wherein said blocking fin comprises: an upstream first portion; and a second portion extending from said first portion such that a gap is defined between said first and second portions. 20. A gas turbine engine in accordance with claim 19 blocking fin wherein said upstream first portion comprises a plurality of openings extending therethrough to facilitate channeling ambient air from said cooling passage into said gap to cool said second portion. 21. A gas turbine engine in accordance with claim 19 blocking fin wherin upstream first portion comprises a plurality of openings extending therethrough to facilitate channeling ambient air from said cooling passage to impinge on and cool said second portion.