초록 ▼

Aircraft exhaust systems and methods are disclosed. In one embodiment, an integrated propulsion assembly includes a wing assembly having an upper surface and a lower surface, and a propulsion unit at least partially disposed within the wing assembly. An exhaust system is configured to conduct an exh

Aircraft exhaust systems and methods are disclosed. In one embodiment, an integrated propulsion assembly includes a wing assembly having an upper surface and a lower surface, and a propulsion unit at least partially disposed within the wing assembly. An exhaust system is configured to conduct an exhaust flow emanating from the propulsion unit to an exhaust aperture. The exhaust aperture is positioned proximate a trailing edge of the wing assembly, and has an aspect ratio of at least five. In further embodiments, the wing assembly includes a flap member moveably coupled along a trailing edge portion of the wing assembly, and the exhaust aperture is configured to direct the exhaust flow over at least a portion of the flap member.

대표청구항 ▼

What is claimed is: 1. An assembly, comprising: a wing assembly extending in a span-wise direction and having an upper surface and a lower surface; at least one propulsion unit at least partially disposed between the upper and lower surfaces, the at least one propulsion unit including at least two

What is claimed is: 1. An assembly, comprising: a wing assembly extending in a span-wise direction and having an upper surface and a lower surface; at least one propulsion unit at least partially disposed between the upper and lower surfaces, the at least one propulsion unit including at least two engines at least partially disposed between the upper and lower surfaces of the wing assembly; and an exhaust system configured to conduct an exhaust flow emanating from the at least two engines into a single exhaust aperture proximate a trailing edge of the wing assembly, the exhaust aperture having an aspect ratio defined as a maximum width over a maximum height, the aspect ratio being at least five. 2. The assembly of claim 1, wherein the wing assembly includes a flap member moveably coupled along a trailing edge portion of the wing assembly, the exhaust aperture being configured to direct approximately all of the exhaust flow over at least a portion of the flap member. 3. The assembly of claim 2, wherein the flap member is moveably coupled to the wing assembly along a hinge line, and wherein the exhaust aperture is integrated within at least one of the upper and lower surfaces and positioned upstream of the hinge line, and configured to direct at least part of the exhaust flow over a portion of the upper surface. 4. The assembly of claim 1, wherein each engine has an engine having an engine diameter, and wherein a ratio of the maximum width of the exhaust aperture divided by the engine diameter is at least approximately three. 5. The assembly of claim 4, wherein the two or more engines comprise at least one of a turbofan engine or a turbojet engine. 6. The assembly of claim 1, wherein each engine has a corresponding exhaust duct that extends to a duct aperture, the plurality of duct apertures collectively forming the exhaust aperture. 7. The assembly of claim 1, wherein the maximum width of the exhaust aperture is at least thirty percent of a semi-span of the wing assembly. 8. The assembly of claim 1, wherein the upper surface includes a fairing portion configured to aerodynamically integrate the exhaust aperture with the wing assembly. 9. The assembly of claim 1, wherein the maximum width of the exhaust aperture is at least eighty percent of a semi-span of the wing assembly. 10. The assembly of claim 6, wherein the exhaust duct transitions from an approximately circular cross-sectional shape proximate each engine to an approximately rectangular cross-sectional shape proximate the exhaust aperture. 11. The assembly of claim 1, wherein the at least one propulsion unit further includes: a plurality of inlets disposed within at least one of the upper and lower surfaces, each inlet configured to receive an incoming airflow; and a plurality of diffusers at least partially disposed between the upper and lower surfaces, each diffuser being coupled to at least one of the inlets and being configured to provide at least a portion of the incoming airflow from the at least one of the inlets to at least one of the engines; and wherein the exhaust system includes a plurality of exhaust ducts at least partially disposed between the upper and lower surfaces, each exhaust duct being coupled to at least one of the engines and extending to a duct aperture, the plurality of duct apertures collectively forming the exhaust aperture. 12. An aircraft, comprising: a fuselage; at least one wing assembly extending outwardly from the fuselage in a span-wise direction, the at least one wing assembly having an upper surface and a lower surface, the at least one wing assembly including a flap member moveably coupled along a trailing edge portion of the at least one wing assembly; at least one propulsion unit at least partially disposed between the upper and lower surfaces, the flap member extending in the span-wise direction along the wing assembly, the flap member having a length greater than the propulsion unit; and an exhaust system configured to conduct an exhaust flow emanating from the at least one propulsion unit to an exhaust aperture proximate a trailing edge of the at least one wing assembly, the exhaust aperture having an aspect ratio defined as a maximum width over a maximum height, the aspect ratio being at least five. 13. The aircraft of claim 12, wherein the exhaust aperture is integrated within at least one of the upper and lower surfaces and configured to direct at least part of the exhaust flow over at least a portion of the flap member. 14. The aircraft of claim 12, wherein the at least one propulsion unit includes an engine having an engine diameter, and wherein a ratio of the maximum width divided by the engine diameter is at least approximately three. 15. The aircraft of claim 12, wherein the maximum width of the exhaust aperture is at least thirty percent of a semi-span of the wing assembly. 16. The aircraft of claim 12, wherein the at least one propulsion unit includes first and second propulsion units and the at least one wing assembly includes first and second wing assemblies, the first and second propulsion units being operatively coupled to a corresponding one of the first and second wing assemblies, each of the first and second propulsion units comprising: a plurality of engines, each engine being at least partially disposed between the upper and lower surfaces of the corresponding one of the first and second wing assemblies; a plurality of inlets disposed within at least one of the upper and lower surfaces, each inlet configured to receive an incoming airflow; a plurality of diffusers at least partially disposed between the upper and lower surfaces, each diffuser being coupled to at least one of the inlets and being configured to provide at least a portion of the incoming airflow from the at least one of the inlets to at least one of the engines; and a plurality of exhaust ducts at least partially disposed between the upper and lower surfaces, each exhaust duct being coupled to at least one of the engines and extending to a duct aperture, the plurality of duct apertures collectively forming the exhaust aperture. 17. A method of propelling an aircraft, comprising: providing a wing assembly extending in a span-wise direction and having an upper surface and a lower surface; providing at least one propulsion unit including at least two engines, the at least one propulsion unit at least partially disposed between the upper and lower surfaces; providing at least one exhaust system coupled between the plurality of engines and an exhaust aperture, the exhaust aperture proximate a trailing edge of the wing assembly, the exhaust aperture having an aspect ratio defined as a maximum width over a maximum height, the aspect ratio being at least five; operating the at least one propulsion unit to provide an exhaust flow; and conducting the exhaust flow through the at least one exhaust system to the exhaust aperture. 18. The method of claim 17, wherein each of the engines have an engine diameter, and wherein providing an exhaust system includes providing an exhaust system having an exhaust aperture integrated within at least one of the upper and lower surfaces and wherein a ratio of the maximum width divided by the engine diameter is at least approximately three. 19. The method of claim 17, wherein providing an exhaust system includes providing a plurality of exhaust ducts, each engine having a corresponding exhaust duct that extends to a duct aperture, the plurality of duct apertures collectively forming the exhaust aperture. 20. The method of claim 17, wherein the maximum width of the exhaust aperture is at least thirty percent of a semi-span of the wing assembly.