초록 ▼

An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either beveled with one or more beveled s

An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either beveled with one or more beveled surfaces, or that contains a curving edge surface or a combination of a beveled edge and a curved edge to help direct noise generated by the jet engine upwardly away from a ground surface during take-off and landing procedures. The primary exhaust nozzle can also be orientated with an elongated lip portion thereof formed by the beveled edge surface such that the lip portion is orientated between a top dead center and a bottom dead center position, to thus help direct noise away from a cabin area of a fuselage of a mobile platform during cruise conditions.

대표청구항 ▼

What is claimed is: 1. A primary exhaust flow exhaust nozzle system for a turbofan jet engine having separate fan flow and primary flow streams, the system comprising: a fan nozzle for directing a fan flow stream; a primary nozzle disposed at least partially within the fan nozzle, the primary nozzl

What is claimed is: 1. A primary exhaust flow exhaust nozzle system for a turbofan jet engine having separate fan flow and primary flow streams, the system comprising: a fan nozzle for directing a fan flow stream; a primary nozzle disposed at least partially within the fan nozzle, the primary nozzle having a longitudinal center line; said primary nozzle further including a downstream edge portion through which said primary exhaust flow stream from said jet engine exits said primary nozzle; and said downstream edge portion of said primary nozzle forming an edge that is non-parallel to a reference line extending orthogonal to said longitudinal center line, and further wherein said downstream edge portion forms a non-flat imaginary plane with a break line that defines a first beveled portion and a second beveled portion. 2. The exhaust nozzle system of claim 1, wherein said first and second beveled portions are formed to extend at different angles relative to said reference line. 3. The exhaust nozzle system of claim 2, wherein at least one of said beveled portions forms an angle of between about 10-50 degrees relative to said reference line. 4. The exhaust nozzle system of claim 2, wherein said beveled portions are arranged to have a dividing line therebetween at a mid-point of said downstream edge. 5. The exhaust nozzle system of claim 1, wherein the downstream edge portion forms a lip that is oriented at a bottom dead center position of the primary nozzle. 6. The exhaust nozzle system of claim 1, wherein the downstream edge portion forms a lip that is oriented at one of a three o'clock and a 9 o'clock position, when looking directly at said downstream edge portion along said longitudinal centerline. 7. The exhaust nozzle system of claim 1, further comprising a center plug disposed at least partially within the primary nozzle. 8. The exhaust nozzle of claim 7, wherein a shape of the center plug is formed for optimum aeroacoustic performance. 9. The exhaust nozzle system of claim 7, wherein the center plug is completely enclosed within the primary nozzle. 10. An exhaust nozzle for a turbofan engine providing separate, non-mixed fan and core flow streams, the exhaust nozzle comprising: a fan nozzle; a primary nozzle disposed at least partially within said fan nozzle and along a longitudinal centerline of said fan nozzle; said primary nozzle having a downstream edge portion through which a core flow stream from said jet engine exits; and said downstream edge portion forming a circle when viewed along said longitudinal centerline, with said circle having a top dead center and a bottom dead center when viewed along a line of sight perpendicular to said longitudinal centerline, and said circle having first and second portions, said first portion beginning at said top dead center and said second portion beginning at a location between said top dead center and said bottom dead center and ending at said bottom dead center; said first portion forming a linear edge extending from said top dead center to a point intermediate said top dead center and said bottom dead center, and the second portion forming a curving edge surface beginning at said point and extending to said bottom dead center. 11. An exhaust nozzle for a turbofan engine providing separate, non-mixed fan and core flow streams, the exhaust nozzle comprising: a fan nozzle; a primary nozzle disposed at least partially within said fan nozzle and along a longitudinal centerline of said fan nozzle; said primary nozzle having a downstream edge portion that forms an imaginary non-flat plane, the downstream edge portion further having a top dead center and a bottom dead center, and a core flow stream from said jet engine passing through said downstream edge portion as said core flow stream exits said exhaust nozzle; and said downstream edge portion including a curving edge that begins at a point between said top dead center and said bottom dead center, and ends at said bottom dead center, when viewing the primary nozzle from a line of sight perpendicular to said longitudinal centerline. 12. The exhaust nozzle of claim 11, wherein said downstream edge portion includes first and second portions, said first portion including a linear edge portion, and said second portion forming said curving edge. 13. The exhaust nozzle of claim 12, wherein said first portion forms a beveled edge portion. 14. The exhaust nozzle of claim 11, wherein said fan nozzle includes a downstream edge portion that is beveled. 15. The exhaust nozzle of claim 11, further comprising a center plug at least partially housed within said primary nozzle. 16. An exhaust nozzle for a turbofan engine having a longitudinal centerline extending through the exhaust nozzle, and providing separate, non-mixed fan and core flow streams, the exhaust nozzle comprising: a fan nozzle; a primary nozzle disposed at least partially within said fan nozzle and along the longitudinal centerline of said fan nozzle; said primary nozzle having a downstream edge portion having a top dead center and a bottom dead center, through which a core flow stream from said jet engine exits; and said downstream edge portion further forming a non-flat imaginary plane laying orthogonal to the longitudinal centerline, the downstream edge portion including a curving portion at least along a portion of the downstream edge portion, the curving portion extending between said top dead center and said bottom dead center of said primary nozzle, when viewing said downstream edge portion along a line of sight perpendicular to said longitudinal centerline. 17. The exhaust nozzle of claim 16, where a first portion of said downstream edge portion forms a linear edge and a second portion of said downstream edge portion forms said curving portion. 18. The exhaust nozzle of claim 17, wherein said first portion forms a beveled edge.