초록 ▼

A method for exhausting gas from an aircraft engine assembly is provided. The method includes coupling a first exhaust duct in fluid communication only to a first engine. The first exhaust duct includes a primary outlet and a secondary outlet. The method further includes coupling a second exhaust du

A method for exhausting gas from an aircraft engine assembly is provided. The method includes coupling a first exhaust duct in fluid communication only to a first engine. The first exhaust duct includes a primary outlet and a secondary outlet. The method further includes coupling a second exhaust duct in fluid communication only to a second engine. The second exhaust duct includes a primary outlet and a secondary outlet. The method also includes aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet.

대표청구항 ▼

1. A method for exhausting gas from an aircraft engine assembly, said method comprising: coupling a first exhaust duct in fluid communication only to a first engine, the first exhaust duct comprises a primary outlet and a secondary outlet;coupling a second exhaust duct in fluid communication only to

1. A method for exhausting gas from an aircraft engine assembly, said method comprising: coupling a first exhaust duct in fluid communication only to a first engine, the first exhaust duct comprises a primary outlet and a secondary outlet;coupling a second exhaust duct in fluid communication only to a second engine, the second exhaust duct comprises a primary outlet and a secondary outlet;aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet;coupling the first engine secondary outlet to a first passageway defined within a rotor, said rotor including a first airfoil portion and a second opposing airfoil portion, the first passageway extending to a trailing edge of the first airfoil portion and the second airfoil portion; andcoupling the second engine secondary outlet to a second passageway defined within the at least one of a wing and a rotor, the second passageway extending to the trailing edge of the first airfoil portion and the second airfoil portion, wherein the first passageway is adjacent to the second passageway such that gases flowing through the first passageway and the second passageway are channeled in substantially the same direction through the at least one of a wing and a rotor. 2. A method in accordance with claim 1 further comprising: coupling the first exhaust duct to a first cruise nozzle; andcoupling the second exhaust duct to a second cruise nozzle. 3. A method in accordance with claim 1 further comprising: coupling the first exhaust duct to at least one first lift nozzle; andcoupling the second exhaust duct to at least one second lift nozzle, wherein a portion of the at least one first lift nozzle is concentric with a portion of the at least one second lift nozzle. 4. A method in accordance with claim 1 further comprising coupling at least one directional control to at least one of the first exhaust duct and the second exhaust duct. 5. A method in accordance with claim 1 further comprising: coupling a first plenum to the first exhaust duct; andcoupling a second plenum to the second exhaust duct, wherein a portion of the first plenum is concentric with a portion of the second plenum. 6. A method in accordance with claim 5 further comprising: coupling the first plenum to a first rotor outlet; andcoupling the second plenum to a second rotor outlet. 7. A method in accordance with claim 6 further comprising coupling a variable area tip nozzle to the first rotor outlet; andcoupling a variable area tip nozzle to the second rotor outlet. 8. An engine assembly comprising: a first engine comprising a first exhaust duct coupled in fluid communication only to said first engine, said first exhaust duct comprises a primary outlet and a secondary outlet; anda second engine comprising a second exhaust duct coupled in fluid communication only to said second engine, said second exhaust duct comprises a primary outlet and a secondary outlet, a portion of said first engine secondary outlet is aligned substantially concentrically within a portion of said second engine secondary outlet, said first engine secondary outlet is coupled to a first passageway defined within a rotor and said second engine secondary outlet is coupled to a second passageway defined within said rotor, said rotor including a first airfoil portion and a second opposing airfoil portion, the first passageway extending to a trailing edge of the first airfoil portion and the second airfoil portion and the second passageway extending to the trailing edge of the first airfoil portion and the second airfoil portion. 9. An engine assembly in accordance with claim 8 wherein said engine assembly further comprises a first plenum coupled to said first exhaust duct and a second plenum coupled to said second exhaust duct, wherein a portion of said first plenum is aligned substantially concentrically within a portion of said second plenum. 10. An engine assembly in accordance with claim 9 wherein said first plenum is coupled to a first rotor outlet, and said second plenum is coupled to a second rotor outlet, said first rotor outlet comprises at least one first variable area tip nozzle, and wherein said second rotor outlet comprises at least one second variable area tip nozzle. 11. An engine assembly in accordance with claim 8 wherein said first engine primary outlet is coupled to a first cruise nozzle and said second engine primary outlet is coupled to a second cruise nozzle. 12. An engine assembly in accordance with claim 8 wherein said first exhaust duct is coupled to at least one first lift nozzle, and said second exhaust duct is coupled to at least one second lift nozzle, wherein a portion of said at least one first lift nozzle is aligned substantially concentrically within a portion of said at least one second lift nozzle. 13. An engine assembly in accordance with claim 8 further comprising at least one directional control coupled to at least one of said first exhaust duct and said second exhaust duct. 14. A propulsion system for an aircraft, said propulsion system comprising: a first engine comprising a first exhaust duct coupled in flow communication only to said first engine; anda second engine comprising a second exhaust duct coupled in flow communication only to said second engine, wherein said first exhaust duct comprises a primary exhaust and a secondary exhaust, said second exhaust duct comprises a primary exhaust and a secondary exhaust, wherein said first engine secondary exhaust is coupled to a first passageway defined within a rotor and said second engine secondary exhaust is coupled to a second passageway defined within said rotor, said rotor including a first airfoil portion and a second opposing airfoil portion, the first passageway and the second passageway each extending to a trailing edge of the first airfoil portion and the second airfoil portion, and wherein said first passageway is adjacent to said second passageway such that gases flowing through said first passageway and said second passageway are channeled in substantially the same direction through said rotor. 15. A propulsion system in accordance with claim 14 wherein said first engine primary exhaust is coupled to a first cruise nozzle and said second engine primary exhaust is coupled to a second cruise nozzle. 16. A propulsion system in accordance with claim 14 wherein said first exhaust duct is coupled to at least one first lift nozzle, and said second exhaust duct is coupled to at least one second lift nozzle, wherein said at least one first lift nozzle is aligned substantially concentrically within said at least one second lift nozzle. 17. A propulsion system in accordance with claim 14 further comprising at least one directional control coupled to at least one of said first exhaust duct and said second exhaust duct. 18. A propulsion system in accordance with claim 14 wherein said propulsion system further comprises a first plenum coupled to said first exhaust duct and a second plenum coupled to said second exhaust duct, wherein a portion of said first plenum is aligned substantially concentrically within a portion of said second plenum. 19. A propulsion system in accordance with claim 17 wherein said first plenum is coupled to a first rotor outlet, and said second plenum is coupled to second rotor outlet. 20. A propulsion system in accordance with claim 19 wherein said first rotor outlet comprises at least one first variable area tip nozzle, and wherein said second rotor outlet comprises at least one second variable area tip nozzle.